the commercial service platform in space of the present invention offers an affordable solution to the access to the attributes of space by combining five new technologies with innovation . reusable launch vehicles ( rlvs ) offer some additional affordability in the transportation to orbit . these rlvs offer initial transportation , deployment services , check out of orbital hardware , reboost and platform upgrades / degrades plus later disposal . an emerging space transportation trend is a reusable launch vehicle used to deploy payloads in a predetermined orbit . these vehicles have evolved over the last few years and are capable of multiple hardware reuse at a cost - effective commercial rate . these evolutionary rlvs are further enhanced by innovation to provide affordable space platforms . recent reusable vehicle advances , technological improvements and commercial market forces have moved the payload industry toward smaller , more commercial networks of communications payloads requiring multiple payloads in various orbital planes around earth . the system of the present invention , i . e ., reusable launch vehicle , communications network , inflatable / deployable structures , advanced robotics , solar arrays and unmanned evolution , are applied to space platforms . the increased demand for communication payload networks has given rise to active , more capable customer sensitive payload phone networks offering the customer the ability to operate its orbital hardware from a decentralized computer via a phone link . the new commercial networks require new innovative payloads of different size , weight and transportation requirements . existing government space facilities have always been thought to require large centralized facilities , but the trend can go the other way in the commercial world . inflatable and deployable structures both offer options for affordable structures in orbit by being compressed during launch and expanding in orbit to deploy the two flat end cap disks . inflatable structures offer the options of expanding in orbit , forcing the two flat end cap structures apart with a temporary inflatable envelope , rigidizing the created volume with inflation gas and foam , deploying solar arrays and remaining useful with internal structural foam . deployable truss structures also offer the options of expanding in orbit , forcing the flat end cap structures apart , deploying solar arrays and contracting as required for solar array reel replacement , reboost and other purposes the platform uses inflatable and deployable structures for solar cell support , platform structure and expandable robotic arms . stowable robotic technology offers more unmanned robotics options in orbit by applying unmanned aero vehicle ( uav ), expandable robotic arms , enhanced tv viewing and control , end effector change - out tooling and communication technologies to orbital robotic operation . manufacturing advances in the thin film solar cell manufacturing and the resulting solar arrays offer a substrate and array that is ¼ th the cost and 1 / 10 th the weight of previous space solar arrays . these more affordable arrays are flexible , space resistant and potentially refurbished in orbit . the commercial service platform in space of the present invention places payloads into a location where the attributes of space are accessed by the customer &# 39 ; s payloads , because the platform combines the advantages of a reusable launch vehicle with the flexibility , common communications , structures , robotics , power and subsystems , multiple payload placement and various service systems of the orbital service platform . the commercial service platform in space of the present invention relates to enhancing existing reusable launch vehicle ( rlv ) technology and its use in the payload transportation industry . the present invention provides a more cost - effective transportation cycle capable of placing cargo into orbits beyond the capability of original rlv or expendable launch vehicle ( elv ). reference is now made to fig1 , which illustrates a preferred embodiment of the invention . fig1 is an early orbital service platform using inflatable platform 18 and reusable launch vehicles to produce an affordable alternative to existing sources for microgravity researchers . flat end caps 26 on each end of rigidized platform envelope structure 19 containing payload module interface 22 where one flat end cap 26 on inflatable platform 18 meshes and rotates with second flat end cap 26 on future payload module 23 ( shown in fig5 ) to produce an interface plane where various attributes are transferred either physically and / or electronically from one flat end cap 26 to another flat end cap 26 . using robotic arm 50 with end effector 51 to grapple or grab flat end cap 26 of payload module 23 ( shown in fig5 ) and attach modules or other devices to the vicinity of another flat end cap 26 , where payload module interface 22 uses center spindle or male device to mate with and join with female side of another payload module interface 22 to pull the disks together and align with rotation each disk with the other disk . robotic arm 50 has elbow 76 , inflated or rigidized arms 74 , and end effector 51 , which rotates 360 degrees using circular disk with track 78 on flat end cap 26 . the orbital service platform also has solar panel 52 to provide power , re - entry capsule 68 for customer return of hardware and commercial advertising 70 for the generation of revenue . solar cell panel connection with robot arm 106 is positioned on each solar panel 52 to permit the changeout , as required , of solar panel 52 with end effector 51 on robotic arm 50 . fig2 a – 2c ( side views ), and fig2 d – 2f ( section views ), show flat end cap 26 , which is preferably disposed at each end of inflatable platform 18 . payload module interface 22 is preferably created by the joining of two flat end caps 26 as depicted in fig2 a and 2b . robotic arm 50 of a first end cap preferably uses end effector 51 to attach to a second flat end cap 26 and pull it near the first end cap for the purpose of drawing the first and second end caps together at payload module interface 22 . payload module interface 22 is considered the entire area within the full thickness of material connecting a first flat end cap 26 with a second flat end cap 26 , except the volume used to stow the robotic arm 50 and components of the robotic arm system . robotic arm 50 preferably has elbow 76 . robotic arm 50 is preferably transported into space as deflated arm 72 , which is subsequently inflated and becomes rigidized arm 74 , with end effector 51 , which preferably rotates 360 degrees on flat end cap 26 . rigidized arm 74 preferably uses track - mounted robotic traveler 94 on circular disk with track 78 to rotate 360 degrees around flat end cap 26 and grapple items with the aid of tv camera 92 . robotic arm 50 has end effector change out device 90 , which is preferably stowed within flat end cap 26 , to permit the change - out of end effector tools to fit specific tasks . while a myriad of end effector designs can be used by robotic arm 50 of the present invention , an end effector is preferably provided which enables to arm 26 to easily grasp and manipulate flat end cap 26 . although robotic arm 50 can be controlled from space , it is preferable that telecommunication systems known to those skilled in the art be used to enable earth - based control of arm 50 . a first flat end cap 26 is placed by robotic arm 50 near second flat end cap 26 so as to put male center spindle connection 85 near enough to female center spindle connection 87 with both controlled by the surface to further join or mate the first and second flat end caps 26 with the help of tv camera 92 . first end cap 26 and second flat end cap 26 are preferably joined at the center and rotated around the center with respect to each other and adjusted with respect to the distance between the two . inside , tv camera 92 is preferably used to view the precise adjustments from the ground of stowed connection interface 80 , battery container 88 and other items to permit alignment , connections and dis - connections of various items . flat end cap 26 is preferably used to stow and transport various parts for the orbital service platform in both the open volume between the two disks outside of payload module interface 22 and the volume inside payload module interface 22 . minor adjustments in alignment and distance are accomplished by viewing tv camera 92 and communication from the surface to various telerobotic devices on stowed connection interface 80 , battery container 88 and other devices . inflatable platform 18 is preferably stowed for launch in a compact cylindrical shape with one flat end cap 26 on each end . inside flat end cap 26 is platform subsystem package 86 and battery container 88 , which are transferred from one flat end cap 26 to another flat end cap 26 when joined by payload module interface 22 . stowed connection interface 80 becomes extended connection interface 82 with remote command from the surface after the two flat end caps 26 are mated . extended connection interface 82 is aligned , guided and mated to connection receptacle 84 providing a flow of attributes including power , communications , and other utilities from one platform subsystem package 86 to another similar platform subsystem package 86 . flat end cap 26 also has the ability to leave platform subsystem package 86 , battery container 88 and other boxes in the mated and plugged in condition for purposes of testing the new combination of old and new box and leaving the combination in orbit for purposes of upgrading the platform . battery container 88 and other boxes are sized to accept second battery container 88 or other boxes and operate together to enhance the platform , because of redundancy and backup subsystems . while exterior portions of flat end cap 26 can be made from a number of materials known to those skilled in the art , composite materials are preferably used , and these exterior portions are preferably spaced apart with a short tube structure . with the ability of arm 50 to manipulate and mate flat end caps 26 , modules can be joined without the need for an impact velocity . fig3 a – c show the deployment system of the present invention , which uses a reusable launch vehicle space such as the k - 1 orbital vehicle ( ov ) 20 , inflatable technology such as stowed inflatable platform 16 and low earth orbit communications such as communications bus from one or more of the low earth orbit networks , but is also unique for what it does not use . rigidized inflatable platform envelope structure 19 is long enough to use the gravity gradient stabilization rather than attitude control systems requiring propellant , thruster systems and other platform subsystems . a stowed inflatable platform 16 enclosed within two flat end caps 26 and a series of stowed solar panels 53 is simple enough to launch on a single launch with some revenue producing services intact . inflating platform 17 remains attached to the reusable launch vehicle as the inflation and deployment progresses , so as to insure a successful working orbital service platform conclusion prior to separation using payload module k - 1 attachment remotely operated 49 . a similar deployment process is depicted in fig5 for deployable platform 30 with deployable truss structure 32 and stowed solar panel 53 in solar panel reel 34 that becomes deployed solar panel 52 . step one of the deployment of stowed inflatable platform 16 is transport in k - 1 orbital vehicle ( ov ) 20 and payload module dome 24 is opened . k - 1 orbital vehicle ( ov ) 20 uses extended payload module 47 to carry two flat end caps 26 with rigidized platform envelope structure 19 in between with stowed solar panel 53 used as the outer packing container with a cable cutter pyrotechnic device as the deployment sequence starter at each end . robotic arm 50 is stowed as deflated arm 72 and is stiffened into rigidized arm 74 in two ways . first , the pressuring gas unfurls and rigidizes the tube structure . second , the pressuring gas also activates foaming powder 112 inside the tube and converting it to rigidized arm 74 . step two of the deployment of stowed inflatable platform 16 is the stabilization at the proper orbital altitude and orbital inclination with long axis toward the center of the earth and payload module dome 24 open . stowed solar panel 53 is used as the outer packing container with a cable cutter pyrotechnic device as the deployment sequence starter at each end . redundant inflation systems packed on the interior of the extended payload module 47 activate the deployment and inflation of stowed inflatable platform 16 . robotic arm 50 is stiffened and used to spread apart inflating platform 17 panels and membranes . first , the pressuring gas unfurls and rigidizes stowed inflatable platform 16 , which becomes inflating platform 17 . second , the pressuring gas also activates foaming powder 112 cavities of inside inflating platform 17 and converting it to rigidized platform envelope structure 19 . foaming powder 112 starts a slow process that inflates , expands and become rigid in layers , tubes and other volumes with inflation gas activation to permit the inflated volumes to be penetrated by high speed orbital objects without deflating these rigid volumes . inflating platform 17 also changes stowed solar panel 53 into solar panel 52 by unfolding and doubling their stowed length with the help of robotic arm 50 . re - entry module 68 contains customer payloads , gets power , communications and structural attachment from the inflatable platform 18 and is controlled from the surface via built in low earth orbit communications network bus acting as one of the series of network satellites . step three continues the inflation process with the help of four robotic arms 50 with elbows 76 and end effectors 51 . inflating platform 17 is stiffened into inflatable platform 18 in two ways . first , the pressuring gas expands and provides activated foaming powder 112 filled interior layer inside the inflatable layer to rigidized platform envelope structure 19 . second , the pressuring gas also activates torus ring inflatable volume 110 at each end of the inflated cylinder inside the tube and converting the structure to inflatable platform 18 . the orbital service platform is checked out with the launch vehicle in place including the power system , communications systems and robotic systems . k - 1 orbital vehicle ( ov ) 20 detaches and with the help of robotic arm 50 drifts away after the completion of detach of payload module k - 1 attachment remotely operated 49 and k - 1 orbital vehicle ( ov ) 20 returns to the surface as part of normal operations after securing payload module dome 24 . fig4 a – c show the orbital service platform power system and the second of several different alternative methods of stowed solar panel 53 . panels depicted are thin wide curved substrate for manufactured thin film light weight solar cells on stowed solar panel 53 with the panels relatively thin and attached loosely to inflatable surfaces volume with solar cell panel connection with robot arm 106 . the second , stowed solar panel 53 shown here in fig4 c as stowed inflatable platform 16 , is a more rigid stowed solar panel 53 . it is molded with a curvature consistent with the stowed diameter and length of extended payload module 47 or similar module and the final use diameter in orbit of inflatable in fig4 a platform 18 ( also see fig1 and 3 ). stowed solar panel 53 becomes solar panel 52 with different deployed curvature in rigidized platform envelope structure 19 in orbit . with one flat end cap 26 at each end , stowed solar panels 53 integrated with stowed inflatable platform 16 in extended payload module 47 as shown in fig4 c . solar panels 52 are stowed in a circular manner and already attached to stowed inflatable platform 16 and rigidized platform envelope structure 19 via connection receptacle 84 . the solar panels 52 act as a part of the transportation envelope packing exterior of stowed inflatable platform 16 . k - 1 orbital vehicle ( ov ) 20 transports stowed inflatable platform 16 also contains commercial advertising 70 in extended payload module 47 . fig5 shows the orbital service platform transferring customer payloads to and from expendable launch vehicles ( elvs ), reusable launch vehicle ( rlv ) or k - 1 orbital vehicle ( ov ) 20 . deployable platform 30 is operated with re - entry capsules 68 , until such time that flat end cap 26 payload module 23 is transported to deployable truss structure 32 for transfer to deployable platform 30 by robotic arm 50 using end effector and grapple . robotic arm 50 is used to assist k - 1 orbital vehicle ( ov ) 20 during station keeping maneuvers and later exchanges of cargo by the second robotic arm 50 . k - 1 orbital vehicle ( ov ) 20 is launched with flat end cap payload module 23 and positions itself near the orbital service platform . rigidized arm 74 with elbows 76 of robotic arm 50 grabs k - 1 orbital vehicle ( ov ) 20 and removes new module and replaces it with similar payload module 23 using second robotic arm 50 . stowed solar panel 53 in solar panel reel 34 becomes solar panel 52 pulled into use on four sides when deployable truss separates the two flat end caps 26 using controls from the surface . end effector 51 is performs solar cell panel connection with robot arm 106 to the deployable truss 32 . end effector 51 is capable of assisting small re - entry payload from the small re - entry payload envelope 96 toward re - entry in the atmosphere and is capable of moving payload module 23 with flat end cap 26 capable of accepting end effector 51 to a position payload module 23 with deployed platform 30 . fig6 shows the orbital service platform reboost propulsion system . inflatable platform 18 is reboosted using logistics delivery k - 1 orbital vehicle ( ov ) 20 . similar reboost is possible with other versions of the platform . several methods are used to do the module change out , but one method can use payload module interface 22 to attach the one module on k - 1 orbital vehicle ( ov ) 20 to the module on the platform . this means k - 1 orbital vehicle ( ov ) 20 with two payload modules 23 in line is connected at the flat end caps 26 via payload interface 22 with the rest of inflatable platform 18 . reaction control system k - 1 orbital maneuvering system propulsion 21 is used to propel rigidized platform envelope structure 19 to some different location in orbit . robotic arm 50 is positioned in solar cell panel connection 84 with robot arm end effector 51 of solar panel 52 using end effector 51 to stabilize the platform during reboost . the solar cell panel connection with robotic arm 106 fastens the solar panel 52 to rigidized platform envelope structure 19 and solar cell panel connection 84 allows robot arm 50 with end effector 51 to release solar panel 52 from rigidized platform envelope structure 19 so it can be replaced . the design rigidity of inflatable platform 18 may be driven by the reboost operation , which could collapse the platform , if the propulsion system imparts too much acceleration in the reboost of the module . fig7 a side view and 7 b section view shows the double configuration for the orbital service platform and growth version of inflatable platform 18 using several rigidized platform envelope structures 19 . module support structure 25 between two platform envelope structures 19 is a space truss deployment created within payload module 23 . each flat end cap 26 has payload module interface 22 with some capability to specifically modify each payload module interface 22 . self deploying module support structure 25 is a space structure with built in payload module interface 22 and flexible connection cables 27 permitting k - 1 orbital vehicle ( ov ) 20 to plug into payload module interface 22 . this expands the number of payload modules 23 supported and power available . k - 1 orbital vehicle ( ov ) 20 reboosts inflatable platform 18 in the same manner once inflatable platform 18 is upgraded with module support structure 25 , second inflatable platform 18 increases the ability of the platform to accommodate more customers is added . module support structure 25 accommodates up to 48 each payload modules 23 on payload module interfaces 22 at the end of flexible connection cables 27 . with the platform balanced each of 48 modules is close to the center of gravity of the platform and the best quality of microgravity is available on the platform . robotic arm 50 is used to grab payload module interface 22 at one end of flexible connection cables 27 and second robotic arm 50 grabs payload module 23 to perform the transfer . a future production configuration mates payload module 23 containing the heavy production facilities with product module 46 to segment the product manufacturing hardware from the raw materials and finished product carrier in product module 46 , which travels back and forth to the surface . this quantity of payload modules 23 may require additional inflatable platforms 18 to accommodate the power requirements . payload modules 23 remain in the same quality microgravity location , if additional inflatable platforms 18 are added evenly to each end . fig8 a side view shows a side view of extended payload module 47 configurations for k - 1 orbital vehicle ( ov ) 20 of the orbital service platform . extended payload module 47 is fabricated from three flat end caps 26 in between cylinders capable of being separated into two payloads for return to the earth &# 39 ; s surface as one unpressurized module with payload module k - 1 attachment remotely operated 49 . the second return payload module 23 can be pressurized and either can contain sounding rocket diameter payload envelope 14 , space station rack payload envelope 15 and small brick payload envelope 95 . fig8 b section view shows a section view of an extended payload module ( not visible in section view ) configurations for k - 1 orbital vehicle ( ov ) of the orbital service platform . the payload module is fabricated from two flat end caps 26 in a cylinder with payload module k - 1 attachment remotely operated on one end . payload module 23 contains mid - deck locker payload envelopes 12 and expanded locker payload envelope 13 in ring shapes patterns in both the side and upright position with last minute slip in small brick payload envelopes 95 in the center . fig8 c shows a side view of extended payload module 47 configurations for k - 1 orbital vehicle ( ov ) 20 of the orbital service platform . payload module 23 is fabricated from two flat end caps 26 in a cylinder with payload module k - 1 attachment remotely operated 49 on one end . payload module 23 contains mid - deck locker payload envelopes 12 in ring shapes patterns in both the side and upright position with last minute slip in small brick payload envelopes 95 in the center . expanded locker payload envelope 13 is larger than mid - deck locker payload envelope 12 due to the curved nature extended payload module 47 . separation plane remotely operated 100 is used to divide those payloads returning to earth and those payloads consumed , discarded in orbit or in re - entry operations . fig8 d shows a side view of extended payload module 47 configuration for k - 1 orbital vehicle ( ov ) 20 of the orbital service platform . expanded payload carrier configuration for large re - entry payload envelope 98 is sized to fit within the maximum payload envelope available within k - 1 orbital vehicle ( ov ) 20 of the orbital service platform . the normal utilization for large re - entry payload envelope 98 without the platform is to launch the re - entry capsule 68 with sufficient power , communications and other support hardware to remain in orbit for a specific period of time and return to the surface by re - entry methods discarding the support hardware . the normal utilization for large re - entry payload envelope 98 with the platform is to launch the re - entry capsule 68 , plug into the platform and use platform power , communications and other support hardware to remain in orbit for a specific period of time and eject for return to the surface using de - orbit propulsion re - entry methods without discarding the support hardware . sufficient volume exists for within extended payload module 47 configurations to launch two flat end cap 26 with a cylinder section carrying mid - deck locker payload envelopes 12 and payload module k - 1 attachment remotely operated 49 . some interface hardware may be discarded above the top flat end cap 26 and two flat end caps 26 that returned to earth . this modular logistics system uses flat end cap 26 to act as a pressure bulkhead on one side and load carrying for unpressurized re - entry module 68 large re - entry payload envelope 98 on the other side . the re - entry mass capable of being re - entered by k - 1 orbital vehicle ov is accommodated by adjusting the mass above and below a separation plane remotely operated 100 within the extended payload module 47 and some mass is ejected as large re - entry payload envelope 98 and some support mass is re - entered by other means . fig8 e is a side view of smaller payload module 23 configurations for k - 1 orbital vehicle ( ov ) 20 servicing the orbital service platform . the smaller payload carrier configuration for medium re - entry payload envelope 97 is sized to fit a specific and / or existing customer re - entry payload hardware within k - 1 orbital vehicle ( ov ) 20 . the normal utilization for medium re - entry payload envelope 97 with the platform is to plug into the platform re - entry capsule 68 in the form medium re - entry payload envelope 97 and draw sufficient power , communications from the platform . the entire package is to remain in orbit on the platform for a specific period of time and eject or a portion is returned to the surface by re - entry methods . the support hardware base or payload module k - 1 attachment remotely operated 49 is recovered and returned to the surface by reattaching flat end cap 26 with support hardware into k - 1 orbital vehicle 20 or discarding the support hardware later from the platform . this modular logistics carrier uses flat end cap 26 to act as payload module interface ( not shown ) to platform and interface and attach to k - 1 orbital vehicle ( ov ) 20 for the launch and transfer . fig8 f shows a side view of an inflated platform 18 compressed inside extended payload module 47 configuration for k - 1 orbital vehicle ( ov ) 20 of the orbital service platform . the length of k - 1 orbital vehicle ( ov ) 20 allows a gravity gradient stable platform with the long axis of the vehicle pointing toward the center of the earth . the k - 1 orbital maneuvering system 21 is used to attain the proper orbit for the deployment and used to reboost the platform as required . expanded payload carrier configuration launches the initial orbital platform consisting of two flat end caps 26 , one with payload module k - 1 attachment remotely operated 49 in each flat end cap 26 and stowed solar panels 53 with stowed inflatable platform 16 inside and not visible . payload module k - 1 attachment remotely operated 49 requires more innovation , is a part of the flat end cap 26 and is assumed to be both male and female coupling capabilities . k - 1 orbital vehicle ( ov ) 20 is unique partly because it is a blunt nose vehicle capable of removing payload module dome 24 and elevating the payload to a position for unobstructed deployment . fig8 g shows a side view of smaller payload module 23 configurations for k - 1 orbital vehicle ( ov ) 20 of the orbital service platform . payload module 23 is fabricated from two flat end caps 26 with a cylinder capable of containing various sized payloads including unpressurized or pressurized module volumes such as sounding rocket diameter payload envelopes 14 , expanded locker payload envelope 13 , space station rack payload envelopes 15 and payload module k - 1 attachment remotely operated 49 . fig8 h shows a section view of smaller payload module 23 configurations for k - 1 orbital vehicle ( ov ) 20 ( not shown in this fig .) of the orbital service platform . payload module 23 is fabricated from two flat end caps 26 ( not shown in this fig .) with a cylinder capable of containing various sized payloads including pressurized module volumes such as mid - deck locker payload envelopes 12 , brick shaped experiment envelope 95 and expanded locker payload envelopes 13 with payload module k - 1 attachment remotely operated 49 ( not shown in this fig .) fig8 i shows a side view of smaller payload module 23 configurations for k - 1 orbital vehicle ( ov ) 20 of the orbital service platform . payload module 23 is fabricated from two flat end caps 26 in a cylinder with payload module k - 1 attachment remotely operated 49 on one end . payload module 23 contains mid - deck locker payload envelopes 12 in ring shapes patterns in both the side and upright position with last minute slip in small brick payload envelopes 95 in the center and expanded locker payload envelopes 13 . fig9 shows a side view of smaller payload module 23 configuration for k - 1 orbital vehicle ( ov ) 20 showing the outside payload container cylindrical walls and payload module dome 24 . payload module 23 is fabricated from two flat end caps 26 in a cylinder with payload module k - 1 attachment remotely operated 49 on one end . payload module k - 1 attachment remotely operated 49 is used for both the k - 1 connection and the connection to platform . payload module 23 contains sounding rocket diameter payload envelope 14 , mid - deck locker payload envelopes 12 in ring shapes patterns in both the side and upright position with last minute slip in small brick payload envelopes 95 in the center . small brick payload envelopes 95 , and small re - entry payload envelope 96 are contained in re - entry capsules 68 and spring jettisoned as commanded from the surface . re - entry capsules 68 draw services from the platform such as power , communications and quality microgravity . re - entry capsule 68 framework portion is discarded at separation plane remotely operated 100 or returned with a different mission . the reduced weight of the remaining two flat end caps 26 and the cylinder with mid - deck locker payload envelopes 12 , expanded mid - deck lockers 13 , brick shaped experiment envelopes 95 and other payload envelopes are sized and accommodate below separation plane remotely operated 100 to accommodate k - 1 orbital vehicle ( ov ) 20 return cargo mass capability . fig1 shows an expanded configuration of the orbital service platform on an external tank . salvaged external tank in orbit 102 is the subject of another patent and result of an enabling agreement with nasa , which includes a cash deposit . salvaged external tank in orbit 102 is retained on a space transportation system ( sts ) mission and the external tank separation and jettison maneuver is delayed with nasa cooperation until orbit . ( the salvage of the external tank is the subject of u . s . pat . no . 5 , 813 , 632 .) this space shuttle change in the mission profile saves some propulsion energy and provides an opportunity to salvage the external tank by placing a commercial package including propulsion package 104 and module support structure 25 on the external tank prior to separation from the space shuttle orbiter in orbit . the package provides attitude control and a reboost capability to the salvaged external tank prior to separation from the nasa orbiter . the salvage operation using a salvage package placed on the external tank by placing an orbiter payload from the shuttle orbiter payload bay on the external tank is the subject of u . s . pat . no . 5 , 813 , 632 or a k - 1 orbital vehicle transports the salvage package to orbit . fig1 shows an expanded configuration of the commercial service platform in space using salvaged external tank in orbit 102 . the external tank is a propellant tank used by the space shuttle for 8 . 3 minutes on the ascent to orbit . this 154 - foot long tank is then jettisoned into a re - entry trajectory and 80 % burns up in the atmosphere re - entering above the pacific ocean . a new external tank is used each time and is taken to within 1 or 2 percent of full orbital velocity before being discarded . this means the cost for transporting the 58 . 000 pound external tank mass to orbit is already invested in the salvaged external tank in orbit 102 . salvaged external tank in orbit 102 starts with a normal space shuttle launch with other customers using most of the shuttle payload weight and volume capability . the space shuttle retains salvaged external tank in orbit 102 as an attached space transportation system component , until the shuttle reaches orbit . the space shuttle with attached salvaged external tank in orbit 102 meets k - 1 orbital vehicle ( ov ) 20 using its k - 1 orbital maneuvering system propulsion 21 to accomplish a station keeping location below the shuttle orbiter near the aft end of to be salvaged external tank in orbit 102 . one or more k - 1 orbital vehicles deliver payloads of various types to the salvaged hardware in orbit and after one or more payloads are delivered and attached , sufficient orbital propulsion and control of the salvaged external tank in orbit 102 or other salvaged items is achieved to a level to permit the space shuttle to disconnect and proceed on other missions . ( ov ) 20 k - 1 orbital vehicle ( ov ) 20 with payload module dome 24 opened and extended payload module 47 containing modified k - 1 orbital maneuvering system ( oms ) propulsion 21 , large k - 1 oms propellant tanks , deployable module support structure 25 , stowed solar panel 53 , flexible connection cable 27 , flat end cap 26 and payload module k - 1 attachment remotely operated 49 . flat end cap 26 contains two robotic arms 50 with end effector 51 able to operate with commands from the surface . flat end cap 26 contains stowed connection interface 80 with a liquid transfer capability permitting the transfer of liquids from future logistics propellant tanks into propulsion module 104 . k - 1 orbital vehicle ( ov ) 20 and flat end cap 26 module with two robotic arms 50 moves within the visiting vehicle envelope of the orbital space shuttle with salvaged external tank 102 and maneuvers to a point near the aft end of salvaged external tank 102 . the space shuttle uses its shuttle remote manipulator system ( rms ) to monitor and control k - 1 orbital vehicle ( ov ) 20 . the space shuttle remote manipulator system ( rms ) arm does not have the reach to remove flat end cap 26 module or salvage system package on the external tank near the aft end of the to be salvaged external tank 102 . k - 1 orbital vehicle ( ov ) 20 with flat end cap 26 module deploys two robotic arms 50 and grabs the solid rocket booster aft attachment points on salvaged external tank in orbit 102 . flat end cap 26 module contains platform subsystem package 86 and end effector 51 . flat end cap 26 module transfers platform subsystem package 86 using end effector 51 to aft end of the salvaged external tank 102 . platform subsystem package 86 is activated from the ground and takes control of salvaged external tank 102 including attitude control , communications and reboost as required . then k - 1 orbital vehicle ( ov ) 20 remains attached via the structural attachment of platform subsystem package 86 and the space shuttle performs a minimum explosive bolt separation from salvaged external tank 102 . the minimum explosive bolt separation operation duplicates the normal launch plus t + 488 second et separation maneuver with some exceptions per nasa approval . the et is structurally separated from the orbiter by means of pyrotechnic devices that fracture attachment links . the separation occurs in a manner that assumes no recontact between the orbiter and salvaged external tank in orbit 102 . much of the range safety system ordnance and tumbling subsystem have been removed , which makes the salvage more technically feasible . the external tank separation normally occurs approximately 488 seconds into the flight at an altitude of 59 nautical miles . in the space shuttle operations normally the 17 inch propellant lines are closed in the separation , but efforts to discard the propellant rather than contain it may be in the best interests of safety on early operations to salvage external tank in orbit 102 . k - 1 orbital vehicle ( ov ) remains attached to salvaged external tank in orbit 102 and capable of maneuvering and reboosting salvaged external tank in orbit 102 to a higher orbit . the long axis of k - 1 orbital vehicle ( ov ) 20 is aligned to pass through the center of gravity of salvage external tank in orbit 102 . salvaged external tank in orbit 102 is accomplished with a minimum of space shuttle participation and / or expense in hopes of accelerating the salvage operation into the shuttle operations participating in the assembly of the international space station ( iss ). k - 1 orbital vehicle ( ov ) 20 and other logistics vehicles add later items to the commercial service platform including inflatable platform 18 components , solar panels 52 , robotic arms 50 , payload modules 23 , flexible connection cables 27 to enhance the microgravity quality , product module 46 , extended payload module 47 and module support structures 25 . propulsion module 104 is re - supplied with propellant by k - 1 orbital vehicle ( ov ) 20 and other logistics vehicles . circular disk with track 78 is placed near the center of gravity of the salvaged external tank 102 where the microgravity is the best and used to robotic arms 50 with end effectors s 51 are used to place payload modules 23 and additional module support structures 25 as required by the market . at some point the platform complex of development will become too large to deliver quality microgravity and other services at which time another distributed platform can be created . fig1 shows a corner configuration of inflatable orbital service platform 18 shown in the inflating platform 17 configuration . stowed solar panels 53 are the exterior of stowed inflatable platform 16 launch to orbit as extended payload module 47 on k - 1 orbital vehicle ( ov ) 20 . solar panel 52 shown in stowed solar panel 53 configuration contains stowed inflatable platform 16 between two flat end caps 26 . at least one flat end cap 26 has payload module k - 1 attachment remotely operated 49 to permit remote release of stowed inflatable platform 16 in orbit . solar cell panel connection with robot arm 106 using robotic arm 50 and end effector change out device 90 permit correct end effector 51 for the removal and replacement of stowed solar panels 53 using tv camera 92 . stowed solar panels 53 become solar panel 52 deployed and plugged into solar cell panel connection with robot arm 106 . as stowed inflatable platform 16 becomes inflating platform 17 and later inflatable platform 18 torus ring inflatable volume 110 the inflation process by inflating first and rigidizing with foaming powder 112 activated by the inflation gas to become a rigid torus with structural foam inside . other interior volumes similar to torus ring inflatable volume 110 are used to maintain inflatable platform 18 in useful shape . internal wiring 108 is compressed inside stowed inflatable platform 16 and decompresses as inflating platform 17 is inflated to become useful in connecting stowed solar panels 53 to platform subsystem package 86 in final inflatable platform 18 . although the invention has been described in detail with particular reference to these preferred embodiments , other embodiments can achieve the same results . variations and modifications of the present invention will be obvious to those skilled in the art and it is intended to cover all such modifications and equivalents .