Ground-controlled guided-missile system
The need for an air defense system which is capable of substantially simultaneously engaging a multiplicity of air born targets has existed for some time. However, before the invention of phased array radar, such a defence system was not feasible. With the old types of conventional radar, it was possible to track and engage a multiplicity of targets with a multiplicity of radar units. With this old type radar, a defence system could be easily over ridden with a multiplicity of air born targets due to the time required for each engagement. However, with a system that includes phased array radar as disclosed herein it is possible to selectively engage a multiplicity of targets, which may even be arranged in cloud formations with decoy targets, with a multiplicity of interceptors and thereby defeat the threat of a multiplicity of targets. 
     In a defense system of this type, there is also a need for self protection against moving ground targets that may be a threat to the defense system. 
     Therefore, it is a primary object of this invention to provide a defense system for protection against a plurality of air born targets as well as moving ground targets. 
     Another object of this invention is to provide a defense system that utilizes a phased array radar that performs the functions of search, target track and interceptor track all on a time sharing basis, and is capable of performing these functions substantially simultaneously on a multiplicity of targets, advancing from different directions and in cloud formation. 
     A further object of this invention is to provide a missile system that is completely mobile. A still further object of this invention is to provide a missile system that has wireless communication means. 
     Still another object of this invention is to provide a missile system that requires a minimum amount of time to set up and put into operation. 
     A still further object of this invention is to provide a missile system that utilizes command control guidance. 
     In accordance with this invention, the missile system is composed of: 
     (A) A plurality of solid propellant missiles each containing guidance mechanism suitable for surface-to-air and surface-to-ground mission, 
     (B) EACH MISSILE CONTAINING A BISTATIC RADAR AND SUITABLE ELECTRONICS FOR MAINTAINING COHERENT RELATIONSHIPS AMONGST THE REFERENCE AND ERROR SIGNALS WHILE TIME-SHARING THE ELECTRONICS USED TO COMMUNICATE WITH THE GROUND SYSTEM, 
     (C) A MEANS OF LAUNCHING THESE MISSILES, 
     (D) A MULTI-FUNCTION GROUND RADAR INSTALLATION CAPABLE OF (1) PROPAGATING TO AND RECEIVING FROM A PLURALITY OF TARGETS USABLE SIGNALS AND WAVEFORMS SUITABLE FOR SURVEILLANCE AND TRACKING, AND (2) SELECTIVELY TRANSMITTING COMMAND SIGNALS DERIVED FROM SAID SURVEILLANCE AND TRACKING SIGBALS TO THE GUIDED MISSILES ALL ON A TIME-SHARING BASIS, AND 
     (E) A DATA-PROCESSING INSTALLATION OPERATIVELY ASSOCIATED WITH SAID RADAR AND LAUNCHING INSTALLATIONS AND CAPABLE OF TRANSLATING SAID TIME-SHARED SURVEILLANCE AND TRACKING SIGNALS FROM THE GROUND RADAR AND BISTATIC RADAR SIGNALS INTO TIME-SHARED COMMAND SIGNALS SUITABLE FOR TRANSMISSION TO, AND USED FOR, CONTROL OF THE MISSILE AND ITS WARHEAD. 
     The system has full tactical mobility in that the launching means, the radar installation, and the data-processing installation are contained in separate self-sufficient mobile units. For special missions, the data-processing equipment and the radar may be contained in the same self-sufficient mobile unit and deployed separately with associated launcher units. 
    
    
     In the accompanying drawing forming a part of this specification, and in which like numerals are employed to designate corresponding parts throughout the same: 
     FIG. 1 is a diagramatic illustration of a missile system according to this invention; and 
     FIG. 2 is a perspective view illustrating the overall components and mobility of the system. 
    
    
     The invention may be better understood by referring to the drawing in which FIG. 2 illustrates a missile system with the components thereof set up for defending an area. The components include a plurality of launchers 1 (only two of which are illustrated) mounted on track vehicles 3, four fire control units 7 with each mounted on a track vehicle 9, and a command and control center 11 mounted on track vehicle 12 and centrally located relative to the fire control units. The particular elements in each of the components are more completely set forth below. 
     The Launcher 
     Each launcher 1 is normally carried on a carrier vehicle 3 but may be demounted to release the carrier vehicle for other purposes. In firing position, the launcher is trainable in azimuth over a full 360° and has an elevation control system which maintains the elevation angle fixed (at substantially 60°). The launcher is lowered to a horizontal position for travel and reloading. 
     Each launcher 1 has a plurality of missiles 4 (nominally five to a launcher) supported in their containers which also serve as launching rails. The launcher carries its own handling gear for reloading and charging warheads. Each container is sealed and maintained at slight positive pressure to provide protection for the missile during long-term storage. The end covers for each container are removed upon installation on the launcher, and environmental protection is maintained by frangible diaphragms until firing. 
     The Missile 
     Each missile 4 is a solid-propellant high performance interceptor. Tail control surfaces 5 on the missile (see FIG. 1) provide yaw, pitch, and roll control. Each of the four control surfaces is independently positioned by individual servo-actuators to provide pitch and yaw maneuvering. The missile is roll stabilized. 
     Two radar antenna systems are provided on the missile: a forward antenna 13 designed to pick up bistatic reflections from the target 15; and a rear antenna 17 to provide a link 8 between ground sensor fire control unit 7 and interceptor 4. 
     The major electronic subsystems of the missile are the airborne sensor, the missile electrical power supply, gyro servo amplifier and missile electroexplosive devices. All sub-units are hermetically sealed to provide isolation from vibration and temperature. Solid state components are employed wherever feasible. 
     The missile electronics has three basic functions: to coherently amplify and transpond tracking signals to the ground, to receive, decode, and process commands, and to receive and process in a bistatic link, skin reflections from the target and coherently transmit the reference and error signals to the ground, and to receive and re-transmit jamming signals originating from the target for cross-correlation with these jamming signals as seen by the ground sensor. The error signals of bistatic receiver 13 are delayed with respect to the reference signals by appropriate and carefully controlled delay lines so that time multiplexing may be used in transmission. 
     The Fire Control Unit 
     The Fire Control Units 7 (FCU) house the multi-function radar and its related signal processor. Each FCU 7 nominally is assigned to a quarter hemisphere region of space in which it performs: 
     (1) Surveillance and detection 
     (2) Target tracking 
     (3) Missile (interceptor) tracking 
     (4) Missile (interceptor) command, safety destruct, and fuzing 
     (5) Reception of bistatic target reflections, target jamming signals, and coded data all relayed from the interceptor. 
     This multi-function radar derives its high degree of flexibility by utilizing inertialess scanning of the phase steering and/or frequency steering techniques or a combination of both. This technique has a capability of changing the direction of radiation (and reception) of energy in, essentially, zero time (a few microseconds). This ability to change direction coupled with a capability of changing waveform and repetition frequency to optimally match the desired mode (track, configuration, surveillance, etc.) provides a highly versatile multi-function sensor. A large number of targets requiring a variety of radar modes for proper handling, may be automatically maintained on a time-shared basis. This same antenna may be used for all up-link and down-link communications with the missiles. 
     A signal processor contained in the FCU 7 is used to control the radar and to process the direct and bistatic target returns and also the missile tracking returns. Coherent signal processing is used where appropriate and the results of all processing is transmitted to a computer (nominally located in the BCC 11). 
     As a means of improving performance in a jamming environment, auxiliary antennas are used to provide side-lobe inputs to a signal processor correlator for purposes of cancelling jamming signals appearing in the main beam. These auxiliary antenna utilize horns in the main steerable array and, thus, are not separate equipments. The signal processor, as mentioned before, will also cross-correlate target originated jamming signals seen by both the ground sensor 7 and the airborne sensor to facilitate the location of these jamming sources. 
     Solid state microelectronics are used where feasible and packaging and mounting techniques are used to provide maximum protection against shock, vibration, and other environmental factors. The FCU 7 may be utilized while on its carrier vehicle 9 thus minimizing emplacement time. 
     The Battery Control Center 
     Overall coordination, control, and command of a battery is accomplished by a combination of data-processing equipments and operators located in the Battery Control Center 11 (BCC). The BCC 11 is a self-contained data-processing, display, and communications center. The central computer is a digital stored program device combining data received from the ground sensor, the air borne sensor, the communication system (especially IFF), and operators with stored a prior knowledge to determine the proper radar modes to evaluate the threat situation, to determine the proper engagement reaction for a threat, to properly guide the missile to a sucessful destructionn of the target which may be air-supported or a Tactical Ballistic Missile (TBM) and may be seen in a benign or in a jamming environment, to correctly aim and fire the warhead at the proper time, to provide for inter and intra battery and surface-to-surface mission control, and to perform system and self checkout, monitoring, and diagnosis. Data must be prepared in proper form and format for display to an operator; and operator inputs which may be commands, instructions, or pertinent data must be recognized and utilized properly. 
     The equipments in the BCC employ solid state microelectronics where feasible and are packaged and mounted for maximum protection against shock, vibration, and other environmental factors. The BCC shelter may be utilized while emplaced on its own carrier vehicle thus providing maximum flexibility with minimal setup time. 
     Communications between the BCC 11 and FCU 7 are via a microwave link 19. The BCC communications with Launchers 1 are by very high frequency (VHF) link 21 with security and jamming protection circuits. Similar VHF links 23 provide extra-battery communications with off-site fire coordination net and adjacent batteries. 
     It is to be understood that the form of our invention, herewith shown and described, is to be taken as a preferred example of the same, and that various changes in the arrangement of parts may be resorted to, without departing from the spirit of our invention, or the scope of the subjoined claims.