Universal dynamic navigation, surveillance, emergency location, and collision avoidance system and method
A portion of the disclosure of this patent document contains material to which a claim of copyright protection is made. The copyright owner has no objection to the facsimile reproduction by any one of the patent document or the patent disclosure as it appears in the Patent and Trademark Office patent file or records, but reserves all other rights in the copyrighted work. 
     BACKGROUND 
     1. The Field of the Invention 
     This invention relates to systems and methods for automatically announcing the position of one or more mobile craft to a receiver positioned at a remote location. More particularly, the present invention relates to systems and methods for tracking the positions of a plurality of mobile craft so as to provide assistance in navigation, surveillance, emergency location and collision avoidance. 
     2. The Prior Art 
     Throughout recorded history there has been an ever increasing need for more precise navigational aids. Through the years, the time keeping and position determining devices used for navigation have evolved from sun dials and sextants to sophisticated digital electronic systems capable of providing nearly pinpoint positioning accuracy almost anywhere in the world. 
     In today&#39;s transportation and communications environment, many devices exist that provide specific navigational aid to the operators of air, sea, and land craft. Navigational aids such as the Global Positioning Satellite system (GPS), the Long Range Navigation system (LORAN), and other navigational aids commonly referred to by such various acronyms as: VOR-DME, VOR-TACAN, DECCA, OMEGA, NDB, ILS, MLS, and ADF, are used by craft operators, particularly aircraft pilots, to determine the position of their craft in one, two, or three planes in space. For example, an operator of an aircraft may only desire to know the position of the craft above or below the surface of the earth (altitude or depth) or may desire to know only the position of the craft relative to a fixed terrestrial reference system (latitude and longitude) or the operator may desire to know the craft&#39;s position in all three planes in space. 
     One of the purposes of the various available navigational aids is to allow operators of craft, in particular air and water craft, to avoid collisions between their craft. As is well known, mid-air collisions of aircraft almost always result in disastrous loss of life and property. In an effort to avoid collisions between craft various systems have been implemented in the air and marine transportation industries. 
     In the United States, government agencies dealing with the air transportation industry have recognized a need to prevent mid-air collisions. In an effort to reduce the occurrence of mid-air collisions, U.S. government agencies have mandated that by the end of 1991 all commercial aircraft with thirty or more seats be equipped with collision avoidance equipment. Several types of collision avoidance equipment have been devised and are classified as either &#34;active&#34; or &#34;passive&#34; systems. These systems are commonly designated as Traffic Alert and Collision Avoidance Systems, also referred to as TCAS. 
     TCAS has been designed as a primary collision avoidance system for commercial aircraft and has received the United States Federal Aviation Administration&#39;s approval. An &#34;active&#34; TCAS system (TCAS II or III) provides the capability to interrogate other nearby transponder-equipped aircraft to elicit a responsive reply, while &#34;passive&#34; TCAS systems (TCAS I) simply eavesdrop on nearby interrogation replies from other transponders. In order to detect a &#34;bearing,&#34; a TCAS system requires an expensive directional antenna. 
     The TCAS method is dependant upon either a secondary or beacon surveillance radar system, or other transponder (S) type interrogations in order to elicit a responsive reply. It is also transponder dependant, meaning that any aircraft not equipped with a transponder will not be detected, and any transponder not coupled to an altitude encoder will not deliver altitude information. 
     Recently, serious questions have been raised about how &#34;safe&#34; TCAS is in practice. TCAS operates in a narrow band of Air Traffic Control (ATC) radio frequencies in the microwave region of the spectrum. Thus, because of the number of interrogation requests and replies elicited, and the amount of information needed to be processed both TCAS and the ATC system may be &#34;overwhelmed,&#34; and their operation sufficiently degraded to the point of &#34;saturation,&#34; where the number of aircraft under the control of ATC exceeds the capacity of the system. Already, computer overloads and radar shutdowns have occurred at some busy locations. There is also the danger of a malfunction occurring, such as an item of interrogation equipment becoming stuck in the transmit mode, thereby &#34;locking up&#34; the entire system. 
     The high cost of the on board TCAS equipment makes its installation prohibitively expensive to most aircraft other than commercial aircraft. Moreover, TCAS III has not yet been fully developed. Even further, TCAS II and III are designed with the commercial aviation market in mind, but of the 215,926 active aircraft registered in the United States in 1988, the commercial aviation fleet only amounted to about three percent (3%) of the total. Thus, it is apparent that improved collision avoidance systems need to become more accessible to a much larger portion of the aviation industry, as well as to land and sea-based craft. 
     In view of these drawbacks and difficulties it would be an advance in the art to provide a complete traffic control system not requiring radar, and which provides a system and method for announcing the position of a craft to a remote receiver such that the position of the craft can be continuously monitored and collisions with other craft avoided. It would also be an advance in the art to provide a system and method for collision avoidance which may be used in addition to, and without interference with, preexisting collision avoidance systems and which can be economically implemented in the general aviation and marine industries so that, for example, with a single frequency select switch seagoing vessels could monitor air or land-based traffic and vice versa. 
     It would be a further advance in the art to provide a system and method which allows the operator of a first craft to monitor the position of a plurality of other craft within a predetermined range of the first craft and to alert the operator of a craft of a potential collision between craft as early as possible. It would be yet another advance in the art to provide a system and method for announcing the position of craft to other craft which are within a predetermined range which is reliable, does not distract an operator of a craft from other duties, and provides short and long range navigational assistance to the operator of a craft. 
     It would be a still further advance in the art to provide a system and method of tracking the position of one or more craft within a predetermined range of a location anywhere on the earth such as at a remote airstrip, or beneath the surface of the ocean, or in space. It would be an even further advance in the art to provide a collision avoidance system which does not become saturated in areas of heavy traffic and which is capable of assisting with the landing or mooring of craft operating under poor visibility conditions. Still further, it would be an advance in the art to provide a system and method for tracking the position of a number of craft, for example a fleet of land craft which are carrying out tasks such as delivery of goods or people or other tasks. 
     BRIEF SUMMARY AND OBJECTS OF THE INVENTION 
     In view of the above described state of the art, the present invention seeks to realize the following objects and advantages. 
     It is a primary object of the present invention to announce the position of a craft to a remote receiver such that the position of the craft can be monitored and collisions with other craft avoided. 
     It is also an object of the present invention to provide a system and method for collision avoidance which may be used in addition to, and without interference with, preexisting collision avoidance systems. 
     It is a further object of the present invention to provide an emergency location system for distressed or disabled craft. 
     It is a still further object of the present invention to provide a collision avoidance system which is economically implemented in the general aviation or marine industries. 
     It is another object of the present invention to provide a system and method which allows the operator of a first craft to monitor the position of a plurality of other craft within a predetermined range of the first craft. 
     It is yet another object of the present invention to provide a system and method which will alert the operator of a craft of a potential collision as early as possible. 
     It is another object of the present invention to provide a system and method for announcing the position of any craft to other craft which are within a predetermined range which is reliable and does not distract an operator of a craft from other duties unless operator attention is necessary. 
     It is a further object of the present invention to provide a system and method for providing short and long range navigational assistance to the operator of a craft. 
     It is a still further object of the present invention to provide a system and method which allows the operator of a first craft to continually monitor the positions of a plurality of other craft within a predetermined range. 
     It is another object to the present invention to provide a system and method of tracking the position of one or more craft within a predetermined range of a location anywhere on the earth such as at a remote airstrip as long as one is operating within the constraints of primary navigation inputs. 
     It is another object of the present invention to provide a system and method for tracking the position of each of a plurality of craft which may be operated within an independent fleet of craft. 
     It is a further object of the present invention to provide a collision avoidance system which operates well in areas of heavy traffic. 
     It is still another object of the present invention to provide a system and method for assisting with the landing or mooring of craft under poor visibility conditions. 
     It is yet another object of the present invention to provide a system and method for collision avoidance which presents appropriate information to the operator of the craft in an easily comprehendible manner and which provides traffic alerts and resolution advisories. 
     It is another object of the present invention to allow a permanent record to be made of the movement of any craft within a predetermined range of a monitoring receiver. 
     Another object of the present invention is to provide a direct pilot-based system of traffic control and communication, and to provide a traffic control system and method which does not require radar and that will not interfer with other existing traffic control systems which are based on radar. 
     A further object of the present invention is to provide a comprehensive monitoring, tracking and communication system and method to promote inter-craft operational safety. 
     These and other objects and advantages of the invention will become more fully apparent from the description and claims which follow, or may be learned by the practice of the invention. 
     The present invention allows the position of a first craft to be monitored at a location remote from the craft. The position of the craft can be monitored at a stationary receiver or from on board another craft. Since a craft equipped with the present invention can monitor the position of other properly equipped craft, collisions therebetween can be avoided. 
     In the case where the present invention is fully implemented, i.e., all the craft in a fleet are equipped with embodiments of the present invention, all the craft are able to monitor the position of all other craft within a predetermined range. Moreover, each craft is able to accurately transmit its own position so the present invention is a great aid to navigation. 
     The present invention includes means, on board a first craft, for receiving or determining the position fix of the first craft. Any number of position-determining devices may be used. For example, the position of the first craft may be obtained by using an altimeter or depth finder, the widely accepted LORAN navigation system, or GPS position determining techniques. 
     The position of the first craft is encoded, preferably as a digital signal, so that the position information of the first craft can be carried by a radio frequency signal. Preferably, both the craft position fix, craft identification code, and other relevant information such as radio frequency number, directory advisories, and equipment error flags are encoded so they can be carried by the radio frequency signal. 
     A large number of craft often operate within a limited range and may all transmit position information on the same radio frequency. In order to avoid interference with conflicting radio frequency signals, it is preferred that conflicting signals are listened for prior to transmitting the radio frequency signal. 
     Importantly, the present invention does not require interrogation by a land-based, or other transmitter before position information will be transmitted by a craft. The radio frequency signal carrying the position information, and preferably other messages and identification information, is regularly transmitted on a continuous basis. 
     The radio frequency signal which is transmitted (carrying at least the position information for the craft) is received by another craft or a stationary monitoring receiver at a remote location. The received radio frequency signal is decoded to extract the craft position, identification and other information therefrom. Using the position information, the position of the other craft is displayed. 
     If the radio frequency signal is received on board another craft, the position of the first craft is of great help to the operators of that craft to navigate, communicate and especially to avoid possible collisions. In order to aid the operators of that craft, the relative positions of each craft are also determined and preferably displayed. 
     By displaying the positions of the two craft as the craft move, a heading for each of the craft can be derived and displayed and the possibility of a collision assessed. In accordance with the present invention, if a collision is possible between two craft on their present headings the operators of each craft are alerted so appropriate action can be taken. It will be appreciated that the greatest benefit from the present invention accrues when all craft have an embodiment of the present invention on board. When all the craft are so equipped, all of the craft can monitor the position of all other craft which are within a predetermined range. 
     Importantly, the present invention has applications other than providing collision avoidance advice. The present invention may be used as a navigational aid, for example, by automatically displaying the craft&#39;s position on a terrain map or graphically showing a landing approach. Moreover, with appropriate navigation information, the present invention may be implemented economically and some embodiments of the invention may be used anywhere in the world. Also, the embodiments of the present invention can be used to locate and direct precision emergency location and rescue efforts in the case of disabled craft. 
     Significantly, the present invention does not rely on interrogation by other craft to transmit its position fix. Rather, the radio frequency signal carrying the position information is transmitted regardless of the presence of any other craft or monitoring receiver. The strength of the radio frequency signal is limited so that it is received only within a predetermined range which is of interest. For example, the predetermined range of the radio frequency signal may be five, ten, thirty, or more miles. Moreover, rather than requiring a sophisticated radio direction finding antenna, the radio frequency signal of the present invention is preferably transmitted omnidirectionally so that all craft within the predetermined range will be able to extract the position information therefrom. 
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS 
     In order that the manner in which the herein-recited and other advantages and objects of the invention are obtained can be appreciated, a more particular description of the invention briefly described above will be rendered by reference to a specific embodiment thereof which is illustrated in the appended drawings. Understanding that these drawings depict only a typical embodiment of the invention and are not therefore to be considered limiting of its scope, the invention will be described and explained with additional specificity and detail through the use of the accompanying drawings in which: 
     FIGS. 1A-1B are high level flow charts describing the presently preferred steps carried out by the system described herein. 
     FIG. 2 depicts three aircraft as an example of the operating environment of the described embodiment of the present invention. 
     FIG. 3 is a block diagram showing the major functional components of the described embodiment. 
     FIGS. 4-1 through 4-11 provide a flow chart describing the steps carried out by the preferred embodiment of the apparatus of the present invention. 
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT 
     Reference will now be made to the drawings wherein like structures will be provided with like reference designations. 
     1. General Discussion 
     As discussed above, the widely promoted and available collision avoidance systems, particularly those available to the aviation industry, inherently have several drawbacks. A major drawback is the fact that the cost of installing the necessary on board equipment may exceed the cost of an entire small aircraft. Thus, economic consideration prevents such systems as TCAS, from being adopted by the great majority of the general aviation industry. 
     Moreover, TCAS equipment requires complex on board computers in conjunction with radio direction finding equipment. Since TCAS equipped aircraft are capable of interrogating all other aircraft in close proximity, the result is that a large number of interrogations will occur in high density air space. Eventually, the radio transmission media will become saturated thereby rendering both TCAS and secondary surveillance radar inoperative. 
     Even when working optimally, the TCAS and other collision avoidance systems provide only a transponder code assignment for identification, gives only relative heading information and if properly equipped, altitude information. In addition, the entire system is interrogation dependent. 
     In contrast to the previously available collision avoidance systems, the present invention makes use of existing ground based or satellite based equipment which has already been widely accepted, rather than requiring new dedicated equipment. Moreover, the present invention provides navigational aid and emergency location functions not contemplated in previously available systems. Importantly, the collision avoidance, navigation aid, and emergency location functions are all provided economically and thus the necessary equipment can be installed on board even small privately owned aircraft. Still further, the present invention can be applied in space, air, land, and sea craft and provide collision avoidance, navigation, and emergency location functions in nearly every environment, including IFR conditions. 
     The present invention is able to achieve its great advantages over the previously available systems by utilizing one of the existing position determining systems, or their equivalent, that is now available or currently being implemented. For example, using the LORAN system a craft, or in the case of portable LORAN receivers an individual, can immediately obtain a position fix measured in latitude and longitude, in many areas of the world. Also, the GPS scheme, when fully implemented, will allow a position fix measured in latitude, longitude, and altitude, to be determined anywhere in the world with great precision. These existing position determining systems, and others when available, are used by the present invention to provide advantages not heretofore available in the art. 
     The described presently preferred embodiment of the invention utilizes the LORAN position determining system. While one form or another of the LORAN system has been known for many years, especially in the marine environment, it has recently gained world-wide acceptance among other types of craft operators, and particularly among aircraft operators. The LORAN system provides more useful navigational information than many other navigational instruments now in popular use, especially in the aviation environment. It has proven to be a highly reliable and safe system and has even been conditionally approved by the FAA for non-precision approaches to approved landing strips. 
     The precision of the LORAN system generally ranges from 60 to 600 feet depending on the location of the craft in relation to the geometry of several widely spaced low frequency radio transmitters which provide the necessary position fixing signals. Because of the precision and versatility of the LORAN system, LORAN receivers are available which include computers, databases and displays providing mapping and navigational aids to the operator of a craft as the craft travels. For example, LORAN equipment intended for aviation use is often provided with databases that are updated monthly to provide all current airport frequencies, runway orientation and length, airport elevations, VOR, restricted and prohibited flight areas, and other useful information. 
     Furthermore, some aviation LORAN receivers are able to immediately locate several of the nearest airports in times of emergency. LORAN equipment installed on aircraft is able to compute ground speed, wind direction and speed, tracking error, offer tracking and vertical navigation advisories, and report minimum safe altitudes and degrees of magnetic variation. 
     Excellent LORAN coverage is now available throughout most of North America. LORAN coverage is partially available in most other areas of the world including the North Atlantic, the United Kingdom, Europe, the Mediterranean Sea, North Africa, the Persian Gulf, Saudi Arabia, and Japan. The relatively low cost and high benefits of installing LORAN transmitters make the LORAN system attractive to governments of both industrialized and developing nations. Furthermore, upon its full implementation, the GPS scheme will provide even greater benefits. Since an existing position determining system is not available everywhere, the term &#34;operational range&#34; will be used to denote when a craft is in an area in which an existing position determining system can be effectively used. 
     Complete information concerning the LORAN system can be obtained from the publications Melton, L., The Complete Loran-C Handbook (Marine Publishing Co. 1986) and Sweeny, D. J., &#34;Learning About Loran,&#34; Radio-Electronics Magazine 50-58, 69 (May 1987) which are incorporated herein by reference. Likewise, the GPS scheme may also be used in accordance with the present invention. Further information concerning GPS can be obtained from the publications entitled &#34;Introduction to Global Positioning,&#34; Civil Engineering 16-20 (January/February 1987), Ashjaee, J., &#34;Global Positioning System: Refined Processing for Better Accuracy,&#34; Sea Technology 20, 22-25 (March 1986) and Enge, P. K. et al, &#34;Differential Operation of the Global Positioning System,&#34; 26 IEEE Communications Magazine 48-60 (July 1988) which are incorporated herein by reference. 
     It will be appreciated that the present invention has application in many different circumstances. Thus, as used herein the term &#34;craft&#34; is intended to include any stationary object, any mobile animal or person, or any mobile apparatus or vehicle. For example, land, sea and air craft are specifically intended to fall within the meaning of the term &#34;craft.&#34; 
     Also, as used herein, the term &#34;monitoring receiver&#34; means any device or apparatus invention which can monitor the position of a craft which is transmitting position information in accordance with the present invention. 
     The present invention comprises an apparatus and method for announcing the position of a craft to a monitoring receiver, either stationary or mobile, remotely located from the craft. In one application, the present invention can be used to track the position of one or more craft at a stationary receiver. In another application, the present invention can be used by one craft to track one or more other craft. With the present invention in place, as a first craft tracks all the other craft positioned within a predetermined range of the first craft, and the operator of the first craft is apprised of the position of all the other craft, collisions between the craft can be avoided. 
     The presently preferred embodiment of the invention which is described herein is intended to be used primarily in the aviation industry. Those familiar with the aviation industry will appreciate that the problems of collision avoidance are particularly troublesome in today&#39;s crowded airspace. Adding to the problem of collision avoidance in the aviation industry are: the limited operator&#39;s field of vision in an aircraft cockpit; the speeds of the craft on a collision course provide very little time for a pilot to react and take corrective action; and an aircraft on a collision course may come from any direction in space. 
     Also a universally useable or mandated collision avoidance system must be economically feasible for both small, modestly priced aircraft carrying just one or two persons and large multi-million dollar aircraft carrying hundreds of passengers and/or freight. Thus, at the current time, a most urgent need for the present invention lies within the aviation industry. 
     Nevertheless, the present invention can be used as a position announcing and/or collision avoidance system in other demanding situations such as with water craft. Also, the present invention can be applied where a dispatcher needs to track the movement of a plurality of vehicles in a fleet, for example, motor trucks as their movements are coordinated for making deliveries and/or pickups, buses, trains, construction and other land based equipment. 
     2. Detailed Description in Reference to FIGS. 1-4 
     In order to describe the presently understood best mode for making and using the present invention, the presently preferred embodiment of the present invention, as intended to be used in an aircraft environment will be described. As will be appreciated, the application of the present invention to air traffic monitoring and collision avoidance is one of, if not the most, demanding of the contemplated applications of the present invention because of, among other things, the speeds of the craft involved and the desirability to monitor three dimensional space as opposed to two dimensional space in the case of water and land craft. 
     Referring now to FIGS. 1A-1B, the preferred general method used by the system of the present invention will be explained. 
     As shown at 10 in FIG. 1A, the initial step of the transmit loop 9 is to obtain a position fix for one&#39;s own craft, also sometimes referred to herein as a first craft. The position fix is obtained using apparatus on board the craft. It is preferred that the position fix be obtained using an existing automated navigational system which will provide the position of the craft relative to a fixed reference, for example, latitude and longitude. This arrangement is in contrast to other collision avoidance systems which merely determine the distance between two craft and not their position relative to a fixed reference system. The LORAN system and the GPS system are among the preferred existing external automated navigational systems. 
     While navigational systems which are capable of providing a position fix in two dimensions (e.g., LORAN) or three dimensions (e.g., LORAN in combination with an altitude encoder or GPS) are preferred, in some applications of the present invention it may only be necessary to obtain a position fix in one dimension or plane of space. For example, in one application of the present invention, an operator of an aircraft may only need to know if another craft is operating at the same altitude. While such information is only a portion of that which the described embodiment of the present invention can provide, it is of use to alert the operator of an aircraft. If another aircraft is operating within a close range at the same altitude, an operator of the aircraft should be warned that a collision with a another aircraft is possible if precautions are not taken. 
     Thus, the position fix can be obtained from an altimeter only (for a one dimensional position fix), from a LORAN receiver (for a two dimensional position fix), from both a LORAN receiver and an altimeter or a GPS device (for a three dimensional position fix). Other devices can also be used to obtain a position fix. 
     As indicated at step 12 in FIG. 1, the position fix which was obtained in step 10 is encoded so that it can be carried by a radio frequency signal. In addition to the position fix, an identification code (such as an aircraft registration number) and/or other messages are also encoded. It is preferred that the position fix and the identification code and other messages be digitally encoded so that they can be transmitted at a relatively high baud rate as will be described in detail below. 
     In the United States, the radio frequency allocation of 1.6 Gigahertz has been reserved for aviation use. Thus, it is presently preferred, but not required, to utilize the 1.6 Gigahertz frequency allocation. Since all aircraft utilizing the present invention preferably utilize the same frequency, step 14 provides that any conflicting radio frequency signals are listened for. 
     One of the significant advantages of the present invention is that, as opposed to previously available collision avoidance systems, a craft transmits its own position fix and identification code information without being interrogated. 
     Since many craft may be using the described embodiment of the present invention, all using just one or a few radio frequency allocations, avoidance of conflicting radio frequency signals is necessary. In use, some conflicts may occur in the described embodiment in areas where craft are highly concentrated. In the described embodiment, the position fix and identification code information is regularly and repeatedly transmitted. Thus, if an attempt at transmitting the position fix and identification code is postponed or &#34;walked on&#34; by another transmission, the information will be repeated in a short period of time. 
     One preferred arrangement for preventing interference between conflicting radio frequency signals is to first listen for conflicting signals, as at step 14, and if a conflicting signal has existed, then wait a random period of time after the detection of a conflicting radio frequency signal, as at step 15. The length of the random period of time can be, for example, derived from the registration number of the aircraft, a random generation, or some other means. Alternatively, after the detection of a conflicting radio frequency signal, a predetermined period of time may be waited before transmission. 
     Additional details concerning the settlement of a conflict between radio frequency signals can be devised by those skilled in the art and further information concerning the preferred example is provided later in this disclosure. It will be understood that various schemes, including the use of scanned multiple frequencies (speed spectrum technology), higher transmission rates, and other non-interrogation schemes, can be devised and used with the present invention. 
     At step 16 in FIG. 1, the radio frequency signal carrying the position fix and identification code information is transmitted and the pilot&#39;s own craft and relative bearing are displayed at step 17. The system then waits at step 19 for the transmit timer to expire, before re-entering the loop for another transmission. 
     Whether it is desired to avoid collisions between multiple craft or to track a single craft, it is nearly always desirable to have the radio frequency signal received only within a limited range. Thus, the radio frequency signal is of limited strength. For example, when functioning to avoid collisions between aircraft, the area of interest is generally a radius of between from about 1 to about 30 miles around one&#39;s own aircraft or around the airport. Nevertheless, in some cases, such as in the case of land or sea craft, the range of interest may be greater or lesser than that which is desirable for aircraft. 
     The radio frequency signal carrying the position fix, identification code information, and other messages, is of limited power so that only the radio frequency signal transmitted from craft within a predetermined range will be received. This reduces the number of radio frequency signals which conflict with one another, allowing a large number of aircraft to be simultaneously operating within a predetermined range. Other embodiments of the present invention can be fabricated which allow a greater number of craft to be simultaneously operating within the predetermined range. 
     Preferably, the radio frequency signal from each of the aircraft is transmitted, and received, omnidirectionally. Since position information is encoded within the radio frequency signal, and not derived from the signal strength or direction, complicated antenna arrangements are not necessary with the present invention. As will be appreciated, in the case of aircraft the term &#34;omnidirectionally&#34; is intended to include three planes of space while in the case of land or water craft, the term &#34;omnidirectionally&#34; generally need only include horizontal two dimensional planes surrounding the craft. 
     As indicated at step 18 of receive loop 13 in FIG. 1B, the radio frequency signals for other craft are transmitted and are received at a craft or another location which is equipped with a monitoring receiver in accordance with the present invention. The receiving location may be a ground location which is tracking one or more craft. The radio frequency signals are decoded, as indicated at step 20, and the position fix and identification code information is displayed at step 21. 
     Once the position information has been extracted from the radio frequency signals, the position of all the other craft within the predetermined range can be displayed as represented at step 21 in FIG. 1B. As each craft regularly transmits its own position, it is possible to calculate all relative essential elements of heading, speed and distance of each craft which can then be displaced. In the case of craft on a collision course, the projected point of impact and time of impact can be calculated and displayed while the operators of the craft are alerted to the danger and given appropriate advisories. While it is not always necessary, it is preferred that an identification code for each craft be transmitted. The transmission of a craft identification code and its current operating communication radio frequency simplifies the organization of incoming data and enhances safety by providing a craft identification for two-way radio communication. 
     Included in step 21 of displaying the position of all craft transmitting a radio frequency signal within the predetermined range is preferably the step of displaying the position of one&#39;s own craft. Also, it is preferable to issue a collision alert if a collision is possible between two craft on their present headings. Also, since, one&#39;s own position fix has already been determined, it is possible to display the position of one&#39;s own craft against a map superimposed on the display. Data to create such maps can be provided by databases as are available in the art. 
     Preferably, each of the craft may be provided with a recording device which will provide a non-volatile record of all position and identification information which is received, and if desired the position information of one&#39;s own craft. Thus, if an aircraft were to become disabled and go down, the radio frequency transmissions would continue to transmit the position and identification of the craft to be obvserved by other craft. If the apparatus did not survive a crash, any properly equipped craft within range recording all received position and identification information and the last transmitted radio frequency signal from the downed aircraft would provide precise information of the location information of the crash site. With either alternative, the present invention can be used as an emergency location system that will supply more precise information than that commonly available on the ELT (Emergency Location Transmitter) system in current use. 
     Referring next to FIG. 2, a primary aircraft 30 is represented at the center of a sphere 36. The sphere (which is not to scale) represents the predetermined range in which the radio frequency signal broadcast from the primary aircraft 30 can be received by other aircraft also carrying the system of the present invention. Thus, the operator of a secondary aircraft 32, being within the predetermined range, will receive a collision alert if the two craft are on a collision course. Alternatively, another secondary craft 34 will not be made aware of the position of the other two aircraft until it comes within the predetermined range represented by sphere 36. A ground based monitoring receiver 38 is also represented in FIG. 2. The ground based monitoring receiver can function as an air traffic control station as the craft come within range. 
     Referring next to FIG. 3, a block diagram of the presently preferred embodiment of the present invention is provided. The high level functional blocks include: a position determining block 100; an interface controller block 102; a radio frequency block 104; an antenna 106; and a control block 108. In most of the functional blocks, additional components are represented. The components represented in FIG. 3 are generally included on board a craft or can be located at a stationary location. 
     Represented within the position determining block 100 are a latitude/longitude position determining device 100A and an altitude determining device 100B. It will be appreciated that many aircraft already include appropriate latitude/longitude position determining devices and an altitude determining device and thus the components represented within the position determining block 100 may not be included in all embodiments of the present invention. It is one of the advantages of the present invention that the existing equipment already provided on many aircraft can be used in conjunction with embodiments of the present invention. In the case of a water or land craft, the inclusion of only a latitude/longitude device is generally all that is necessary. 
     The presently preferred latitude/longitude position determining device is a LORAN-C receiver available from ARNAV, a subsidiary of Flight Dynamics, Inc., of Portland, Oreg. and referred to as Model R-50. The described LORAN receiver provides many desirable features as well as the ability to communicate with other devices via the industry standard RS-232 communication protocol. 
     The presently preferred altitude determining device is an altimeter available from ACK Technologies, Inc. of San Jose, Calif., Model A-30. Information concerning interfacing the indicated altimeter to other components is available from the manufacturer. 
     The devices included in the position determining block 100 are a preferred example of a means for determining, on board a craft, the craft&#39;s position using an existing external navigation system. The means for determining the craft&#39;s position can include, depending upon the particular application of the invention, devices for determining the craft&#39;s position in one, two, or three dimensions (or planes) of space. 
     The present invention includes means for encoding the position of the craft, which can also preferably encode an identification code for the craft, so such information can be carried by a radio frequency signal. The presently preferred example of a means for encoding the position and identification of the craft is the interface controller 102 represented in FIG. 3. 
     The identification code may be an aircraft registration number or any other number unique to the craft. While it is not essential to encode and transmit the craft identification code with the radio frequency signal, it is desirable to do so. 
     Still referring to FIG. 3, the interface controller 102 communicates with the devices of the position determining block 100 by way of communication ports included in the devices. The presently preferred example of the interface controller 102 is a system available from Enduratek Corporation of Salt Lake City, Utah and referred to as the Data-V-Com system. Complete information concerning the Data-V-Com system can be obtained from the publication &#34;Mobile Data Terminal System Operations Manual&#34; available from Enduratek Corporation and which is incorporated herein by reference. 
     The interface controller 102 system performs data encoding and preparation functions needed to transmit the digital information via a radio frequency signal and functions as the presently preferred example of a means for encoding the position of the craft into information which can be carried by a first radio frequency signal and a means for decoding the other craft&#39;s position from a radio frequency signal. Other devices performing similar or equivalent functions are intended to be included within the scope of the means for encoding included within the present invention. The designated interface controller 102 also functions as the presently preferred example of a means for decoding the position and identification information received from other craft. The radio frequency block 104 includes a modulator 104A, a radio transmitter 104B, an antenna duplexer 104C, a radio receiver 104D, and a demodulator 104E. The components of the radio frequency block are preferably included in a radio frequency transceiver capable of operating in the microwave band containing 1.6 Gigahertz. One presently preferred transceiver which operates in the VHF band is available from Icom, Model No. IC-A20. It will be appreciated that devices other than the designated transceiver, and frequencies other than 1.6 Gigahertz, for example any appropriate radio frequency may be used within the scope of the present invention. 
     Also represented in FIG. 3 is an antenna 106, which may comprise one or more individual antennas or antenna elements, and which is preferably one that will provide an omnidirectional radiation pattern. It is desirable that the radiation pattern and the reception pattern both be omnidirectional. The antenna duplexer 104C serves to isolate the radio transmitter 104B from the radio receiver 104D while allowing both to use the same antenna. 
     Still referring to FIG. 3, a modulator 104A functions to modulate the carrier radio frequency wave with the craft position and identification information encoded by the interface controller 102. A demodulator 104E similarly functions to extract the position and identification information from any radio frequency signal which is received and to pass the same onto the interface controller 102. The modulator 104A and demodulator 104E may be embodied in a device commonly referred to as a modem, which is available in the art. 
     The components represented within the radio block 104 and the antenna 106 are the presently preferred example of a means for transmitting the first radio frequency signal and a means for receiving a radio frequency signal. The interface controller 102 communicates with, and operates, the components of the radio frequency block 104 by way of connectors and cables customarily included on radio frequency transceivers as will be understood by those skilled in the pertinent art. 
     The interface controller 102 represented in FIG. 3 also communicates with a computer 108A which is included in the components of the control block 108. The computer 108 is preferably one which is equivalent to an IBM model PC AT. One of the many commercially available portable models (generally referred to as &#34;Lap Tops&#34;) of the specified equivalent computer can also be used. The computer 108A and the interface controller 102 communicate with each other by way of the customary connectors and protocols (such as the RS-232 protocol) which are well known to those skilled in the art. 
     The programming code which is presently preferred for use with the interface controller 102 is attached hereto as Appendix A. The programming code which is presently preferred for use with the computer 108A is attached hereto as Appendix B. 
     Included in the control block 108 is a display 108B. The display 108B may be integral with the computer 108A or may be separate therefrom. The display is preferably used to provide a graphical representation of the position of the craft which are within the predetermined range of the monitoring craft or receiver. Thus, the operator of the craft can observe on the display the position of both his own craft (desirably in the center of the display) and the position of all other craft surrounding his craft within the predetermined range. 
     One preferred embodiment of the display would incorporate the use of a head-up display to display not only collision avoidance information, but to also aid in proximity reporting, navigation under IFR conditions, coordinated descent into controlled and uncontrolled airports and landing strips, and other relevant information, and to project these pertinent images in a forward view mode into the wind screen and line of the actual and preferred flight path. 
     It will be appreciated that some embodiments of the present invention may provide additional benefits if the display is one which not only provides high resolution in two dimensions, but one which is also suitable for displaying three dimensions, i.e., a display wherein depth can be represented by either using a three dimensional graphics mode or by decreasing intensity as a position recedes from the viewer and greater intensity as the position moves toward the viewer. Altitude information as well as indicators showing whether or not aircraft are climbing or descending can also be depicted on the display. 
     In the case of the present invention as applied to the aviation industry, it is desirable that the position of aircraft other than those in the same horizontal plane be displayed. Namely, the display 108B should provide position information of a plurality aircraft vertically displaced from the monitoring craft (i.e., differing altitude) as well as in the same horizontal plane (latitude and longitude). Depending upon the particular embodiment of the invention, the display 108B , or all of the components represented in radio block 108, function as a means for displaying a craft&#39;s position as defined by the present invention. Other devices and arrangements performing similar or identical functions are intended to be considered equivalent to the described structures. 
     Also represented in the control block 108 are input devices 108C. Input devices 108C can include a keyboard (which may be integral with the computer 108A) or other general purpose or dedicated input devices. An audio/visual alarm 108D is also represented in control block 108. The audio/visual alarm can be integral with the computer 108A or can be one of several dedicated alarm devices intended to apprise the operator of a craft of a potential collision or other situation requiring attention. 
     A recorder 108E is also provided in the control block 108 to make a non-volatile recording of selected data received by the computer 108A. Preferably, the recorder 108E is used to periodically log the position of all craft within the predetermined range. Thus, if a monitored craft becomes disabled and stops transmitting its radio frequency signal carrying position information, the last recorded position fix logged in the recorder 108E of any craft or observation station within the predetermined range can aid in the location of a disabled craft. 
     Furthermore, if a craft continues to transmit its radio frequency signal with its own position fix after becoming disabled, it will function as an emergency location device and will assist search and rescue crews in the rapid location of the disabled craft. In some embodiments of the invention, the radio frequency signal can carry, in addition to position and identification information, a distress signal as well as other messages to indicate a need for emergency assistance and even describe what type of emergency assistance is required at the disabled craft. 
     If desired, the components of the control block 108, the interface block 102, and the reception components of the radio frequency block 104 can be used as a monitoring receiver. For example, a monitoring receiver can be used as a ground control station to monitor the airspace surrounding an airport. In the case of small airstrips or airports in developing areas, the present invention can be adapted to provide both airborne craft and ground control personnel the information necessary to coordinate air traffic. This application of the embodiment of the invention would allow for the system&#39;s use as a standard ATC system exclusive of expensive radar installations, and at extremely low cost. 
     It will be appreciated that while the described embodiment is the presently best known mode for carrying out the invention, those skilled in the pertinent art will understand that other components may be used to carry out the invention. For example, the functional blocks illustrated in FIG. 3 may be combined into a few, or just one, devices housed in a single enclosure. Moreover, as the art progresses, the inventive concepts of the present invention may be embodied in devices not yet available but carrying out functions equivalent to those described in connection with the preferred embodiment. All such alternative embodiments of the invention are intended to fall within the scope of the present invention. 
     Provided in FIGS. 4-1 through 4-11 is a more detailed flow chart describing the steps carried out by the above-described embodiment. In these figures, the boxed letter designations indicate the interconnections between the portions of the flow chart which are divided between figures. 
     The flow chart provides a description of the high-level functions carried out principally by the interface controller 102 represented in FIG. 3. In the presently preferred embodiment of the present invention, the interface controller 102 is implemented by the above described Data-V-Com system. Also, as indicated earlier, the presently preferred programming code for the Data-V-Com system is included in Appendix A attached hereto. 
     It will be appreciated that the flow chart represented in FIGS. 4-1 through 4-11 represents just one preferred example of the programming steps that can be used to carry out the present invention and those skilled in the art will be able to devise other embodiments of the present invention using the teaching contained herein. Also, as will be appreciated after an examination of FIGS. 4-1 through 4-11, the Lap Top (a portable computer which functions as the computer 108A represented in FIG. 3) functions principally to display the data presented to it by other components and to provide input and output functions with a human user. The text contained in the dashed boxes are included to improve the clarity of the flow chart and do not represent steps in the method. 
     Also, as indicated earlier, the presently preferred programming code for the Lap Top is included in Appendix B attached hereto. Those skilled in the art will be able to provide embodiments of the present invention which perform functions similar or equivalent to those performed by the described embodiment, using the teachings contained herein. 
     The flow chart contained in FIGS. 4-1 through 4-11 is divided into several principal routines as indicated below. 
     
         ______________________________________                                    
Flow Chart Routine                                                        
                  FIG. NOS.                                               
______________________________________                                    
Initialization    FIGS. 4-1 through 4-4                                   
Radio             FIGS. 4-5 through 4-6                                   
Loran             FIG. 4-7                                                
Altimeter         FIG. 4-8                                                
Lap Top           FIGS. 4-9 through 4-11                                  
______________________________________                                    
 
    
     Further information concerning each of the routines indicated above is provided in the Glossaries set forth below. 
     
         ______________________________________                                    
Ref.                                                                      
No.  Label       Description                                              
______________________________________                                    
A. Initialization Routine Glossary                                        
200  START       This is the beginning of the program.                    
                 When the micro-processor is reset via                    
                 hardware or software it is vectored to                   
                 this point. At START, the Stack                          
                 Pointers, Interrupt disabling and                        
                 various other Housekeeping chores are                    
                 performed.                                               
202  SELFTEST    This is the beginning of the Selftest                    
                 Module. At this point the Diagnostic                     
                 Terminal will display that Selftest has                  
                 started. Also at this point Selftest                     
                 Interrupts will be set up and enabled.                   
206  RAM TEST    The RAM (Random Access Memory) test                      
     PASS        is run. The RAM test writes data found in                
                 a ROM table to each RAM address. If                      
                 the same data that was written is read                   
                 back, the program continues through the                  
                 table until the data 00H is written.                     
                 This signifies the end of the test and                   
                 leaves all RAM cleared and ready for                     
                 use. If the test fails at any point                      
                 the data read, data written and the                      
                 address are saved and reported back to                   
                 the Diagnostic Terminal. The RAM                         
                 should be replaced at the address                        
                 reported if failure occurs.                              
208  SET RAM     The Selftest Status is sent to the Lap                   
     TEST FAIL   Top and to other Aircraft via the                        
     BIT         Radio. If this bit is set it means                       
                 that the RAM Test Failed and all data                    
                 is unreliable.                                           
210  ROM TEST    All Used ROM (Read Only Memory) is                       
     PASS        added and the sum must equal zero. The                   
                 Check Sum Adjust Byte at 3FFFH                           
                 ensures that the sum (without carry) is                  
                 zero. If the sum is not zero the test fails              
                 and ROM should be replaced. The test                     
                 failure status and the erroneous check                   
                 sum are reported to the Diagnostic                       
                 Terminal.                                                
212  SET ROM     The Selftest Status is sent to the Lap                   
     TEST FAIL   Top and to other Aircraft via the                        
     BIT         Radio. If this bit is set it means                       
                 that the ROM Test Failed and all data                    
                 is unreliable.                                           
214  LAP TOP     The USART (Universal Synchronous                         
     INTER.      Asynchronous Receive Transmit) 8051 is                   
     PASS        Software reset and the MIF (Mode                         
                 Instruction Format) set up. Status is                    
                 then checked and verified.                               
216  SET LAP     The Selftest Status is sent to the Lap                   
     TOP         Top and to other Aircraft via the                        
     INTERFACE   Radio. If this bit is set it means                       
     FAIL BIT    that the Lap Top Communication could be                  
                 unreliable.                                              
218  I/O TEST    The PIA (Peripheral Interface Adapter)                   
     PASS        8155 is initialized for the proper                       
                 mode, which ports are Inputs and which                   
                 are outputs and the Baud rate Clock set                  
                 up. Outputs are initialized. Status                      
                 is then checked and verified.                            
220  SET         The Selftest Status is sent to the Lap                   
     INPUT/      Top and to other Aircraft via the                        
     OUTPUT      Radio. If this bit is set it means                       
     FAIL BIT    that the PIA is unreliable. The PIA                      
                 interfaces mainly with the Altimeter.                    
222  RADIO       The USART (Universal Synchronous                         
     INTER       Asynchronous Receive Transmit) 8051 is                   
     PASS        Software reset and the MIF (Mode                         
                 Instruction Format) set up. Status is                    
                 then checked and verified.                               
224  SET RADIO   The Selftest Status is sent to the Lap                   
     INTERFACE   Top and to other Aircraft via the                        
     FAIL BIT    Radio. If this bit is set it means                       
                 that the Radio Communication could be                    
                 unreliable.                                              
226  ADD         Each System has its own Aircraft                         
     AIRCRAFT    Identification Via the Diagnostic                        
     ID          Terminal the Aircraft Identification is put              
                 in NonVolatile Memory or EEPROM.                         
                 (Electrically Erasable Read Only                         
                 Memory). This Identification number                      
                 will not be lost if the system is reset                  
                 or powered down. When Selftest is run                    
                 the system can sense that the Terminal                   
                 is attached and allaow the user the                      
                 option of changing the Aircraft                          
                 Identification This block asks the                       
                 question, Do You Want to Enter Aircraft                  
                 Identification?                                          
228  GET         This block Prompts the Terminal, for                     
     AIRCRAFT    the Identification, Error Checks it and                  
     ID          buffers it.                                              
230  ENTER       This block enters the buffered aircraft                  
     AIRCRAFT    Identification into EEPROM.                              
     ID                                                                   
232  PUT IN      Because the preferred embodiment of the                  
     RANDOM      present invention is polite (will not                    
     XMIT        transmit when another signal is already                  
     TIMER       present on the frequency). To eliminate                  
                 various systems transmitting                             
                 simultaneously, each system will have                    
                 different wait times before transmit-                    
                 ting after a frequency has cleared.                      
                 This random wait time is determined by                   
                 the system Aircraft Identification in                    
                 the preferred embodiment.                                
234  TOGGLE      Changes the printer status.                              
     PRINTER                                                              
     STAT.                                                                
236  CHG         To enable someone to monitor the entire                  
     PRINTER     system there is a port for a printer or                  
     STAT        some other type of monitor. At this                      
                 time the Diagnostic Terminal can be                      
                 used for changing the Status of the                      
                 Printer or Monitor. The Status is kept in                
                 NonVolatile ROM or EEPROM so that                        
                 if the System is powered down or reset                   
                 that status will not change.                             
240  INITIA-     Pointers such as the Input and Output                    
     LIZE        Pointers for the Rotating buffers used                   
     POINTERS    for the Lap Top Interface are set up at                  
     TIMERS      this time.                                               
     ETC.                                                                 
242  SET         At this point in the Program it is not                   
     ALTIMETER   known if the Altimeter is functional or                  
     DATA TO     not, especially since the Altimeter                      
     9&#39;s         does not function for several minutes                    
                 after it is powered up. So that any                      
                 data present is not mistaken for good                    
                 Altimeter Data all 9&#39;s are inserted in                   
                 the Altimeter use area.                                  
244  SET LORAN   At this point in the Program it is not                   
     DATA TO     known if the Loran Receiver is                           
     9&#39;s         functional or not, especially since the                  
                 Loran Receiver must be initialized                       
                 manually to send the proper information                  
                 at the proper baud rate, transmit rate,                  
                 and so forth. To ensure that any                         
                 random data already present is not                       
                 mistaken for good data, all 9&#39;s are                      
                 inserted in the Loran Longitude and                      
                 Latitude buffers.                                        
246  SET #       The # message Flag is set so that when                   
     MESSAGE     the system is fully initialized and                      
     FLAG        functional, the # message will be sent                   
                 to the Lap Top Computer.                                 
250  EXECLP      This is the exit point for                               
                 initialization that has been performed                   
                 heretofore and the loop point for the                    
                 rest of the program. When the rest of                    
                 the program has completed it will come                   
                 back to this point and begin again at                    
                 this point.                                              
252  CALL        The Radio Module (See step 276, FIG.                     
     RADIO       4-5) is interfaced at this point.                        
256  CALL        The Loran Module (See step 312, FIG.                     
     LORAN       4-7) is interfaced at this point.                        
260  CALL LAP    The Lap Top Computer Module (See step                    
     TOP         348, FIG. 4-9) is interfaced at this                     
                 point.                                                   
264  RESET       See step 266.                                            
     WATCH DOG                                                            
266  TRANSMIT-   If the system is transmitting the watch                  
     TING        dog timer is not reset. This helps to                    
                 ensure that the system does not                          
                 transmit for too long a period. If the                   
                 watch dog is not reset every 1.1                         
                 seconds the system is reset, the                         
                 Program Counter goes to 0000H or the                     
                 Start.                                                   
268  CALL        The Altimeter Module is interfaced at                    
     ALTIMETER   this point.                                              
B. Radio Routine Glossary.                                                
272  RANDOM      After the frequency has been busy this                   
     TIMER EXP   timer must expire before transmitting.                   
                 (See step 232 (FIG. 4-2) and 278 (FIG.                   
                 4-5).                                                    
274  `T`                                                                  
     RELOAD                                                               
     VALUE NON                                                            
     0?                                                                   
276  RADIO       This is the entrance to the RADIO                        
                 module. This module handles all the                      
                 communication to/from the Radio. All                     
                 communication to other aircraft is via                   
                 the Radio.                                               
278  RESET       The value used to reset the XMIT timer                   
     XMIT        is the value obtained from the `T` message               
     TIMER       from the Lap Top Computer. (See                          
                 steps 274 (FIG. 4-5), 350 (FIG. 4-                       
                 9) &amp; 376 (FIG. 4-10).                                    
280  CHANNEL     Because the system is polite (See step                   
     CLEAR       232 (FIG. 4-2)). It will not                             
                 transmit unless the channel is clear.                    
                 The Carrier Active Sense (CAS) is                        
                 checked at this point to see if the                      
                 frequency is clear or not.                               
282  XMIT        The location message for this aircraft                   
     TIMER EXP   must be transmitted to the other                         
                 aircraft at a rate determined via a `T`                  
                 message from the Lap Top Computer. If                    
                 the `T` message time is 0 then (which                    
                 is what is is upon initialization) then                  
                 the message is not transmitted at all.                   
286  GET THIS    The Aircraft Identification is read                      
     AIRCRAFT    from EEPROM and stored in the Radio                      
     ID          Transmit buffer. (See steps 230, 228                     
                 (FIG. 4-2), &amp; 226).                                      
290  RESET       The Random timer must be reset with the                  
     RANDOM      value determined from the Aircraft                       
     TIMER       Identification (See steps 232 (FIG.                      
                 4-2), 280 &amp; 372 (FIG. 4-5).                              
292  GET LORAN   The most recent data from the Loran                      
     LAT. LON.   Receiver is placed in the Transmit                       
     DATA        buffer. (See steps 292 (FIG. 4-6),                       
                 314 &amp; 320 (FIG. 4-7)).                                   
296  MESSAGE     By examining the input buffer it can be                  
     RECEIVED?   determined if a message has been                         
                 received.                                                
298  CHECK SUM   Each byte of the message is added                        
     CORRECT     w/carry and it is determined if the                      
                 message is error free or not.                            
300  PUT         The message received above is                            
     MESSAGE     rebuffered into the large rotating Lap                   
     IN LAP      Top Computer Buffer for transmittal to                   
     TOP         the Lap Top Computer.                                    
     BUFFER                                                               
302  GET LORAN   This byte indicates the Loran Status.                    
     STATUS      (See step 330 (FIG. 4-7)). The Loran                     
                 Receiver transmits in addition to the                    
                 Latitude and Longitude the Status of                     
                 the Receiver.                                            
304  SET         This flag tells the Lap Top Module that                  
     LAPTOP      a message is ready to go to the Lap Top                  
     MESSAGE     Computer.                                                
     READY                                                                
     FLAG                                                                 
306  GET DATA    The Data-V-Com Status includes not only                  
     V - COM     the Selftest status, (See steps 208,                     
     STATUS      212, 216, 220 &amp; 224 (FIGS. 4-1 &amp; 4-                      
                 2)) but also status as to how current                    
                 the Loran Information is.                                
308  GET         After concluding with step 306 (FIG.                     
     MESSAGE     4-6) the message is formatted and the                    
     CHECKSUM    Check sum is calculated by adding up                     
                 each byte (w/carry).                                     
310  OUTPUT      The message formatted above is output                    
     MESSAGE     (AFSK) via the USART.                                    
                 An attack delay (a period of no data to                  
                 enable the transmitter to stabilize) as                  
                 well as a time delay at the end is                       
                 necessary.                                               
C. Loran Routine Glossary.                                                
312  LORAN       This is the Entrance Point for the                       
                 Loran Module. This module handles the                    
                 interface with the Loran receiver.                       
                 Besides receiving the Latitude and                       
                 Longitude it also saves the Loran                        
                 Status and keeps track of if an update                   
                 occurs between Message transmissions to                  
                 other aircraft and to the Lap Top.                       
314  SAVE        The Latitude less the spaces is saved.                   
     LATITUDE    (See step 318 (FIG. 4-7)). A flag is                     
                 set so that it can be determined that                    
                 data was received for Lat. and Lon. so                   
                 that when processed will be data that                    
                 is compatible.                                           
316  LATITUDE    Checks for LAT (See step 318 (FIG. 4-                    
                 7)) in message coming in from Loran                      
                 Receiver.                                                
318  MESSAGE     The entire message from the Loran                        
     COMING      Receiver is not saved. If a message is                   
     IN?         coming in the program looks for LAT for                  
                 Latitude and LON for longitude and SD                    
                 for Loran Status. If these labels are                    
                 found the data less the spaces is                        
                 saved.                                                   
320  SAVE        The Loran Status is saved for                            
     STATUS      transmission to other Aircraft, as well                  
                 as the Lap Top Computer. This makes it                   
                 possible to know the accuracy of the                     
                 Loran as well as other pertinent                         
                 information. (See steps 388 (FIG. 4-                     
                 11) &amp; 302 (FIG. 4-6)).                                   
322  LONGITUDE   Checks for LON (See step 318 (FIG. 4-                    
     ?           7)) in message coming in from Loran                      
                 Receiver.                                                
324  ALL DATA    See step 318.                                            
     RECEIVED?                                                            
326  PUT LAT.    The message received above is                            
     IN LAPTOP   rebuffered into the large rotating Lap                   
     BUFFER      Top Computer Buffer for transmittal to                   
                 the Lap Top Computer.                                    
330  SAVE        See step 320.                                            
     STATUS                                                               
332  LORAN       A flag is set for each of the 11                         
     STATUS?     different types of status if that                        
                 particular status is read from the                       
                 Loran Receiver.                                          
334  PUT LON.    See step 326.                                            
     IN LAPTOP                                                            
     BUFFER                                                               
336  PUT LORAN   See step 332.                                            
     STATUS IN                                                            
     LAPTOP                                                               
     BUFFER                                                               
D. Altimeter Routine Glossary.                                            
338  ALTIMETER   This is the Entrance point to the                        
                 Altimeter handler. It reads the 11                       
                 Discrete inputs and decodes the data to                  
                 an ASCII altitude. If the altitude is                    
                 bad a 998 is output.                                     
340  GET         Reads the 11 Discrete inputs from the                    
     DISCRETE    Altimeter. If some are not used the                      
     INPUTS      program is modified so that they are                     
     (11)        assumed to be most significant and low.                  
342  GET ALT.    The data is deemed good and saved for                    
     FROM        messages to the Lap Top and to other                     
     TABLE       Aircraft.                                                
344  INPUT       A look up table is used to decode the                    
     DATA IN     11 inputs to a three digit altitude                      
     TABLE       reflecting 100&#39;s of feet. If the table                   
                 reflects 998 then the data is deemed to                  
                 be bad and is rejected.                                  
346  GET `998`   The data in the table was bad, so                        
                 instead of unreadable data a `998` is                    
                 used to reflect the error.                               
E. Laptop Routine Glossary.                                               
348  LAPTOP      This is the input to the module. This                    
                 module handles all communication                         
                 to/from the Lap Top Computer.                            
350  PUT `#`     Put the `#` in the output buffer for                     
     IN          this particular message to the Laptop.                   
     MESSAGE                                                              
352  CLEAR `#`   See step 354 (FIG. 4-9).                                 
     FLAG                                                                 
354  `#` FLAG    This flag indicates that a # Message                     
     SET?        must be sent to the Lap Top Computer.                    
                 This flag is set only during                             
                 Initialization. (See step 246 (FIG.                      
                 4-3)).                                                   
358  GET THIS    The Aircraft Identification in                           
     AIRCRAFT    Nonvolatile memory (EEPROM), is put                      
     ID          in the transmit buffer to go to the Lap                  
                 Top Computer. (See step 228 (FIG. 4-                     
                 2)).                                                     
360  GET         The message that was received from                       
     MESSAGE     another aircraft via. the RADIO module                   
     FROM        is rebuffered and sent to the Lap Top                    
     OTHER       Computer.                                                
     AIRCRAFT                                                             
362  `0` FLAG    The `O` determines if messages from                      
     SET?        other Aircraft are accepted or not. If                   
                 the Flag is set, which must occur when                   
                 a `O` message is received from the Lap                   
                 Top Computer, (See step 378 (FIG. 4-                     
                 10)) then other aircraft messages are                    
                 accepted.                                                
364  GET         The Selftest Status (See steps 208,                      
     SELFTEST    212, 216, 220 (FIG. 4-1) &amp; 224                           
     STATUS      (FIG. 4-2)) is put in the buffer to                      
                 be transmitted to the Lap Top Computer.                  
366  RESET `L`   The time value received from the Lap                     
     TIMER       Top Computer, (See step 390 (FIG. 4-                     
                 11)) is used to reset this timer.                        
368  `L` TIMER   The `L` timer determines how often the                   
     EXP         Location message for this aircraft is                    
                 sent to the Lap Top Computer. If the                     
                 value is set at 0, which occurs on                       
                 initialization, it is not sent at all.                   
                 The value that the `L` timer is set to                   
                 is determined by the `L` message                         
                 received from the Lap Top Computer.                      
                 (See step 390 (FIG. 4-11).                               
372  GET THIS    The Aircraft Identification in                           
     AIRCRAFT    Nonvolatile memory (EEPROM), is put                      
     ID          in the transmit buffer to go to the Lap                  
                 Top Computer. (See step 228 (FIG. 4-                     
                 2)).                                                     
376  GET THIS    This information is obtained from the                    
     LONGITUDE   Loran module. (See steps 314 &amp; 320                       
     LATITUDE    (FIG. 4-7)) and is put in the                            
                 transmit buffer to go to the Lap Top                     
                 Computer.                                                
378  &#34;0&#34;         Is the incoming message from the Lap                     
     MESSAGE?    Top Computer an `O`                                      
                 message? If so the `O` flag is set.                      
                 (See step 362 (FIG. 4-10)).                              
380  SET &#34;0&#34;     See step 378 (FIG. 4-10).                                
     FLAG                                                                 
382  GET THIS    This information is obtained from the                    
     ALTITUDE    Altitude module. (See step 342 (FIG.                     
                 4-8)) and is put in the transmit buffer                  
                 to go to the Lap Top Computer.                           
384  &#34;T&#34;         Is the incoming message from the Lap                     
     MESSAGE?    Top Computer a `T` message? (See steps                   
                 274 &amp; 282 (FIG. 4-5)). If so the `T`                     
                 Reload value is saved. This value                        
                 determines how often the Radio                           
                 Transmits the Location of the Aircraft                   
                 to other Aircraft.                                       
386  GET &#34;T&#34;     See step 384 (FIG. 4-11). This value                     
     RELOAD      is used at step 372 (FIG. 4-5).                          
     VALUE                                                                
388  GET THIS    This information is obtained from the                    
     LORAN       Loran module. (See step 330 (FIG. 4-                     
     STATUS      7)) and is put in the transmit buffer                    
                 to go to the Lap Top Computer.                           
390  &#34;L&#34;         Is the incoming message from the Lap                     
     MESSAGE?    Top Computer and `L` message? (See                       
                 steps 368 (FIG. 4-10) &amp; 392 (FIG.                        
                 4-11)). If so the `L` Reload value is                    
                 saved for use at step 366 (FIG. 4-                       
                 10).                                                     
392  GET &#34;L&#34;     See step 390 (FIG. 4-11). This value                     
     RELOAD      is used at step 366 (FIG. 4-10).                         
     VALUE                                                                
394  GET         After concluding with step 388 (FIG.                     
     CHECKSUM    4-11) the message is formatted and the                   
                 Check sum is calculated by adding up                     
                 each byte (w/carry).                                     
396  &#34;R&#34;         Is the incoming message from the Lap                     
     MESSAGE?    Top Computer an `R` message? If so the                   
                 program is vectored through software to                  
                 the start address. (See step 276                         
                 (FIG. 4-5)).                                             
398  OUTPUT      The message formatted above is output                    
     MESSAGE     via the USART to the Lap Top                             
                 Computer.                                                
______________________________________                                    
 
    
     3. Summary 
     In view of the foregoing, it will be appreciated that the present invention provides a system and method for announcing the position of a craft to a remote receiver such that the position of the craft can be continuously monitored and collisions with other craft avoided. The present invention also provides a system and method for collision avoidance which may be used in addition to, and without interference with, preexisting collision avoidance systems. 
     It will be further appreciated that the present invention also provides an emergency location system for distressed or disabled craft and a collision avoidance system which can be economically implemented in the general aviation industry. Still further, the present invention provides a system and method which allows the operator of a first craft to monitor the position of a plurality of other craft within a predetermined range of the first craft and to be alerted of a potential collision as early as possible. 
     The present invention also provides a system and method of monitoring craft proximity spacing, a critical function, while operating within the flight sector system in high density areas and while transitting or making approaches in VFR and IFR controlled airspace. Further, the system and method provide a similar function in the marine environment, particularly under adverse weather conditions and high density mooring or docking maneuvers. 
     Even further, after consideration of the foregoing, it will be understood that the present invention provides a system and method for announcing the position of any craft to other craft which are within a predetermined range which is reliable and which does not distract an operator of a craft from other duties unless operator attention is necessary. Moreover, the operator of a first craft is allowed to continually monitor the positions of a plurality of other craft within a predetermined range. Even further, the present invention provides a system and method of tracking the position of one or more craft within a predetermined range of a location anywhere on the earth such as at a remote airstrip or allows the position of each of a plurality of craft belonging to a fleet to be tracked. Still further, the present invention provides a collision avoidance system which does not become saturated in areas of dense traffic and which readily makes a permanent record of the movement of any craft within a predetermined range of a monitoring receiver. 
     The present invention may be embodied in other specific forms without departing from its spirit or essential characteristics. The described embodiment is to be considered in all respects only as illustrative and not restrictive. The scope of the invention is, therefore, indicated by the appended claims rather than by the foregoing description. All changes which come within the meaning and range of equivalency of the claims are to be embraced within their scope. ##SPC1##