Abstract:
Affordable commercial service platforms in space focusing on customer affordability, quality microgravity services, innovation and combining five emerging space technologies. The invention provides an integrated approach to microgravity services in orbit. First, the reusable launch vehicle (RLV) offers affordable transportation services, platform reboost, and eliminates platform subsystems of propulsion, RCS, liquid storage/resupply, and the like. Second, deployable structures are not heavy for the launch, but expand in orbit. Third, orbital phone networks offer customers control of unmanned experiments. Fourth, an enhanced robotic system transfers payloads. Fifth, manufactured thin film solar cells in orbit offer advantages including weight/cost reductions. The orbital service platform has a low initial cost, expands as the market demands, is repairable, offers quality unmanned microgravity, leads to production facilities using similar hardware and offers numerous affordable commercial services.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
   This application is a continuation-in-part application of U.S. patent application Ser. No. 10/366,905, entitled “Commercial Service Platform in Space”, to Thomas Carl Taylor, filed on Feb. 14, 2003 now abandoned, and the specification thereof is incorporated herein by reference. 

   NO GOVERNMENT RIGHTS 
   No government funding, no government support or government contract or clause is related to this invention. 
   COPYRIGHTED MATERIAL 
   A portion of the disclosure of this patent document contains material that is subject to copyright protection. The owner has no objection to the facsimile reproduction by anyone of the patent document or the patent disclosure, as it appears in the Patent and Trademark Office patent file or records, but otherwise reserves all copyrights whatsoever. 
   BACKGROUND OF THE INVENTION 
   1. Field of the Invention (Technical Field) 
   The present invention relates to unmanned orbital hardware for the delivery of customer services in space using innovation and the combination of emerging technologies to provide affordable commercial services on the orbital node on the transportation cycle to space. 
   2. Background Art 
   The transportation of cargo to space and maintaining a platform in orbit is expensive. Cost is the problem. The cost creates a barrier to commercial development of space and the investment of private capital in technically viable ventures. Governments rely on large aerospace organizations for future studies and these private “for profit” organizations make their money by delivering aerospace hardware to government agencies as it rolls out the door. The aerospace industry uses cost estimating techniques based primarily on weight and previous cost experience, so part of the problem is the “built-in” incentive to deliver larger heavier hardware of increasing cost, so the fees based on a percentage are increased. The current result is an $85 billion International Space Station that the potential commercial customers and most member nations are finding too expensive to maintain an adequate crew and use as a research facility. Current government attempts to address the cost of space transportation, for example, have resulted in over $5 billion in failed government programs dating back to the National Aerospace Plane that have spent money with little progress toward solutions to the problem of cost. 
   The problem is the cost of the individual operations required to transport cargo to orbit, do business and return some productive result. After over 50 years of aerospace development experience, the orbital commercial environment is still expensive. Transportation is approximately half the cost of commercial space ventures. The European Space Agency (ESA) has taken over half of the world launch market with newer technology and a better-positioned launch site near the earth&#39;s equator. Expendable launch vehicles (ELVs) are currently used for most payload transportation to space, but ELVs are revisions to the World War II technology based on disposing of the hardware safely into oceans or unpopulated areas. 
   U.S. Pat. No. 6,439,508 to Taylor, entitled “INFLATABLE HABITATION VOLUMES IN SPACE,” discloses a habitation volume inflatable in space and which can be connected to other volumes in space to provide orbital habitation facilities. 
   Previous attempts to satisfy commercial users of microgravity, the view from space, high vacuum, large temperature change and the other attributes of space have been expensive. Some believe two orders of magnitude in cost reduction must be found to stimulate the increased commercial use of space. Cost reductions must include the transportation to and from orbit plus the hardware and unmanned services in orbit. 
   U.S. Pat. No. 4,867,395, to Taylor, et al., entitled “FLAT END CAP MODULE FOR SPACE TRANSPORTATION SYSTEMS,” discloses a flat end cap on each end of a truncated manned pressure cylinder module on an expensive transportation vehicle. The &#39;395 patent discloses a pressurized module in the space shuttle payload bay that has reduced the cost of manned tended research in the space by a factor of ten. This was not enough to stimulate significant commercial experiment flow to establish follow-on industries. The device reduces the transportation costs by being shorter and using heavy pressure disc flat end caps, which must withstand a full interior pressure. The present invention flat end cap is similar in name only and is not a manned module at any time. The SPACEHAB system replaced a nearly identical European supplied Module system ($920 million) called “Spacelab” with a commercial start-up venture with $105 million in a private funds, an innovative hardware solution and the same “Spacelab” structure subcontractor. It did reduce the cost of “Mid-Deck Locker” research in microgravity and the hardware used by an order of magnitude. A reduction of two more orders of magnitude in cost reduction is required. 
   U.S. Pat. No. 5,431,328 to M. E. Dobbs, et al., entitled “SPACECRAFT PAYLOAD EXCHANGE SYSTEM” discloses a passive docking system dependent on a forward velocity and collision to complete the docking and transfer of canisters to accomplish microgravity manufacturing. Individual canisters are transferred, after their stay in orbit, back to a carrier vehicle for return to earth. The transfer of mass across a separation plane is far more complicated and expensive than it needs to be. The transfer of power, communication and structural connection is transferred, which appears to sell hardware rather than eliminate it and its cost. 
   U.S. Pat. No. 3,910,533 to D. C. Cheatham, et al., entitled “SPACECRAFT DOCKING AND ALIGNMENT SYSTEM,” discloses a space docking system that requires duplicate targets and monitor means on both vehicles. The system again requires some impact velocity to force the mechanical systems to work and again sells hardware. This invention is expensive, manned and uses an impact docking system. It does not have active aspect or rotation. 
   U.S. Pat. No. 5,816,539 to Chan; entitled “INTEGRATED STORAGE AND TRANSFER SYSTEM AND METHOD FOR SPACECRAFT PROPULSION SYSTEMS,” discloses an orbital assist module (OAM) built into the stack of an expendable launch vehicle (ELV). The orbital assist module propellant comprises liquids such as hydrazine and it is difficult to handle liquid rather than eliminate liquid in all forms. 
   U.S. Pat. No. 4,730,797, to Minovitch, et. al., entitled “INFLATABLE CORE ORBITAL CONSTRUCTION METHOD AND SPACE STATION,” discloses a construction form inflated in orbit and used to hold wraps of other materials to form large space volumes. The &#39;797 patent device is complicated and expensive. Although suggested as automatic, much of what is suggested is hand labor. Labor in orbit is 1,000 to 1 times more expensive than on the surface for the portions of this device that cannot be automatic and must be performed in a microgravity vacuum. Without gravity, typical construction techniques in one gravity do not work in microgravity and vacuum. There is no mention of solutions for the above or launch loads and pressure used for habitation in orbit, plus any high-speed particle impact protection in orbit. The &#39;797 patent device is manned and the inflatable envelope is useful only as a form in orbit. The &#39;797 patent device offers only a large up-front cost, transportation on an expensive vehicle and no phased build up to soften the financial impact of the project or allow the revenue flow to be used in later financial support of the project. 
   U.S. Pat. No. 4,562,979, to Taylor, et. al., entitled “EXPANDABLE SPACECRAFT” discloses a telescoping metal module innovation in an attempt to double the interior volume using a shorter module and less metal. The &#39;979 patent to Taylor in Jan. 7, 1986 also discloses difficult-to-use seals in the extended configuration. The extra metal required to react to the launch loads encountered and provide a maximum pressurized volume in a 3 gravity launch load vehicle adds significant weight. The &#39;979 patent is an attempt to start a habitation volume in orbit, but uses metal and it is heavy. The manned metal module pressure boundary in the Spacelab Module is limited to fifty days on orbit by design and has limited impact protection. The removal of the module from the space shuttle is complicated in orbit, not a part of &#39;979 patent device and the Spacelab Module requires the Environmental Control Life Support (ECLS) Systems from the orbiter. The solution is expensive partly, because it is designed to be manned. Spacelab modules have been given to museums and replaced by less expensive SPACHAB and other more expensive International Space Station hardware. 
   U.S. Pat. No. 5,184,789, to Aldrin, entitled “SPACE STATION FACILITY,” discloses a standard space station with metal pressurized modules and lots of struts. Manned activities are generally thought to be an order of magnitude more expensive and more complicated than the unmanned present invention. The &#39;789 patent pressurized modules are standard metal and the struts fold in the center to fit within the 60′ long space shuttle. This means the struts are approximately 120′ long and the modules larger than any known launch vehicle could carry. It is not clear what value the struts provide; e.g., do they make the modules lighter and how do they address the primary commercial issues of transportation weight and cost? One gravity thinking common to the earth&#39;s surface and typical of humans evolved in a one gravity environment is easy to transfer to low or microgravity of space in the form of scaffolding, but this type of thinking seems to have limited value in space. The absence of gravity actually requires less structural strength than the earth&#39;s surface one gravity environment. Space or microgravity design just requires keeping the modules spaced from each other in a manner so as not to damage the commercial quality microgravity. The quality microgravity is a function of the distance of a specific location from the center of gravity of a series of modules in orbit. In orbit certain gravity gradient forces exist within long structures in microgravity space and these small forces degrade the pure quality of the microgravity by adding extra gravity gradient force, which induce forces in a commercial quality microgravity that are not wanted. The &#39;789 patent device is manned, maximizes the logistics required with struts and uses rigid strut structures to hold distant or space the microgravity modules with some provisions for the forces during reboost. Rigidity is counterproductive in a 3-gravity launch environment. The launch design loads are generally three times the loads experienced in a one gravity earth environment and usually drive the design rather than the loads experienced in orbit. Building bigger, more centralized facilities is expensive and distributed de-centralized facilities are the norm in surface based commercial operations. 
   U.S. Pat. No. 4,834,325, M. A. Faget, et al., entitled “MODULAR SPACECRAFT SYSTEM,” discloses a modular metal module dependent on the space shuttle and traditional solar arrays that require expensive pointing hardware. This manned structure was estimated to cost $3 billion in the mid 1980&#39;s, but was thought by NASA to potentially compete with ISS and failed to get built. While the &#39;325 patent device had metal to resist the launch loads in the launch configuration, it was one or two orders of magnitude more expensive than required. Max Faget&#39;s $3 billion manned concept would have eliminated the present space station and the next NASA step, which means it had little chance politically and the initial cost was difficult to raise from private sources, partly because it was not phased to take advantage of the customer revenue flow. The system was pressurized, manned and had rotating solar arrays pointing toward the sun. 
   U.S. Pat. No. 5,511,748, to Scott, entitled “METHOD OF EXTENDING THE USEFUL LIFE OF A SPACE SATELLITE,” continues the dream of satellite servicing for most of traditional aerospace and NASA, but it fails to address the major stumbling block with the satellite manufacturers. The major stumbling block is no satellite manufacturer or financier will build a space serviceable satellite, until a satellite servicing industry exists. 
   U.S. Pat. No. 5,451,975, to Miller, et al., entitled “FURLABLE SOLID SURFACE REFLECTOR,” discloses a metal expanding structure with interlocking metal panels expanded to create a reflector. While this solution may address launch loads in the compressed configuration and provide a reduced volume; little else applies to the useful life of an inflatable or executable service platform. 
   U.S. Pat. No. 3,836,417, to Yaeger, et al., entitled “LAMINATE FOR HUMAN HABITATION,” discloses earth based air supportable structures with rigidized beams on the surface of the earth, but in a microgravity/vacuum environment the pressure alone provides the beam strength until the membrane suffers a puncture. The composite materials in the &#39;417 patent device do not appear appropriate for microgravity, vacuum and impact uses. The composite layers contain metal flakes, which may result in significant weight. Again unmanned is the next step rather than the manned solutions, which failed to get any private or government funding as TransHab. 
   U.S. Pat. No. 4,024,679, assigned to Irvin Industries, Inc., to Rain, et. al., entitled “AIR SUPPORTED STRUCTURE MEMBRANE CONFIGURATION,” discloses surface based air supported volumes with multiple layers and structural beams rigidized by air on the surface of the earth. In orbit in a microgravity environment, the inflation pressure is sufficient for strength. These composite materials do not appear appropriate for microgravity, vacuum and impact uses; however the material does have limited radiation protection. Reasonable inflatable designs exist for the orbital environment, but this is probably not one of them. 
   U.S. Pat. No. 5,813,632, to Taylor, et al., entitled “SALVAGE HARDWARE APPARATUS AND METHOD FOR ORBITING OBJECTS,” discloses salvaging hardware transported to orbit for other reasons and potentially available in orbit. The &#39;632 patent device salvages the external tank using a subsystem package transferred from the space shuttle by the remote manipulator system (RMS). 
   The &#39;632 patent device uses a space shuttle transported systems package to accomplish salvage of the discarded tank hardware in orbit and proceeds to use the pressurized tank volume for new uses including a habitation configuration. No extra metal is required and no transportation costs are incurred, except for the salvage systems package, and the material and labor used to develop the interior of the ET in orbit. This solution is in the range of $150 m to $300 m per salvaged item and could offer two orders of magnitude of cost reduction for manned volumes in orbit, but the concept is too large of a change from normal practice to permit private financing and too economical to attract government contractor or government interest. TransHab was a NASA attempt to change the government/industry mindset, for example, and not successful. The unmanned platform is a big enough leap. 
   The transportation loads encountered by the tank are not changed on ascent and later the tank is reused to provide a maximum of pressurized manned volume in orbit, (The external tank of the space shuttle is, for example, pre-tested to +40 psia before launch.) with added interior and Environmental Control Life Support Systems (ECLSS) placed inside the tank in orbit. The &#39;632 patent device is an attempt to develop the habitation volume in orbit from existing materials, but the ET is metal, labor intensive and it is heavy. The on orbit labor rate is currently 10,000+ times higher than on earth. 
   U.S. Pat. No. 5,350,138 to Cubbertson, et al., entitled “LOW COST SHUTTLE-DERIVED SPACE STATION,” discloses a combination of an external tank and the space shuttle using pre-positioned inflatable inserts instead of inserts placed in orbit as suggested in the present invention. Altering the external tank before launch in any way requires a re-certification of the external tank, which is very expensive. 
   In contrast, the present invention uses a reusable launch vehicle with special capabilities and a simple replicable platform in orbit with only the platform subsystem capabilities required. This platform hardware is gravity gradient stabilized, which requires no propellant, is self powered by solar cells without any pointing capability, simple robotics capable of transferring customer cargo to and from the platform and self communicating using the emerging low earth orbit phone networks. The present invention includes an unmanned use of the salvaged external tank device and uses a non space shuttle transported subsystem package. 
   SUMMARY OF THE INVENTION 
   The present invention relates to an apparatus or platform in outer space. The preferred platform comprises a module with at least two end caps. The module is transportable to outer space in a compressed form and inflatable in outer space between the end caps. At least one of the end caps comprises at least one robotic device for inflating the module in space. 
   The platform may connect with another space vehicle. Preferably, the platform connects with a module of the other space vehicle, then the other module is movable to the platform. One end cap preferably rotates and meshes with an end cap on the other space vehicle module via the robotic device. 
   The platform preferably comprises extendable and retractable connection hardware. This connection hardware is adjustable and rotatable to one or more positions. The end caps are preferably flat. The flat end caps preferably comprise a disc shape. 
   The platform preferably comprises a robotic device track. The robotic device is preferably capable of switching out, stowing and loading modules. The robotic device is preferably stowed in the end cap for transport into outer space in a deflated position and inflated in outer space. The robotic device preferably comprises an end effector and at least one elbow. All of the end caps comprise robotic devices. Likewise, at least one end cap preferably comprises communications electronics and/or transportation electronics. 
   The end caps are disposed apart by an inflatable or deployable structure. They are preferably disposed far enough apart to establish a gravity gradient stability for the platform. 
   The invention may further comprise a support structure between the end caps for supporting the inflated platform. This support structure may comprise a truss system. 
   The invention is also directed to an orbital unmanned platform combined with a reusable launch vehicle comprising: a payload transported to space in a payload bay of the reusable launch vehicle; and a different payload transported upon return from space in the payload bay of the reusable launch vehicle. This combination creates a complete transportation cycle and a functioning node in space. Part of the payload may remain in space and at least part of the payload may return from space. The payloads may be accumulated, assembled, tested and transferred to other transportation vehicles at the node platform. The present invention also relates to a method of transporting a module in a space vehicle to outer space comprising the steps of: stowing a module in a compressed form between at least two end caps, the end caps comprising at least one robotic device; transporting the module in the compressed form into outer space; and inflating the module between the two end caps via the robotic device in outer space. The present invention may further comprise the step of exchanging the module with another space vehicle module in outer space via the robotic device. The present invention may further comprise the step of adding an additional module from another space vehicle in outer space via the robotic device. The robotic device is capable of switching out modules, stowing modules, and loading modules. 
   In accordance with the commercial service platform in space method of the invention of delivering services in low earth in a cost effective manner, the hardware of the invention uses the combination of capabilities of a reusable launch vehicle in support, a simple platform system with common integrated ground handling, upgrading and payload processing. 
   The present invention also relates to a space platform having a first module which is transportable to outer space in a compressed form and inflatable in outer space. The first module preferably has end caps disposed at its ends. At least one of the end caps can have one or more tracks circumferentially disposed within or around it. The first module preferably expands along an axis defined by the end caps during inflation. Further, one or more carriers are preferably disposed on the one or more tracks. The first module also preferably has one or more inflatable robotic arm devices disposed within each of the end caps, and the arm devices are can be attached to one of the carriers. 
   The space platform of the present invention can also include a second module transportable to outer space in a compressed form and inflatable in outer space. This second module preferably has end caps disposed at its terminal portions. At least one of these end caps can have one or more tracks circumferentially disposed within or around it. Like the first module, the Second module also preferably expands along an axis defined by the end caps during inflation. The second module also can have one or more carriers disposed on the one or more tracks, and one or more inflatable robotic arm devices disposed within each of the end caps and attached to one of the carriers. Each of the carriers of the first and second modules are preferably movable about its corresponding track. 
   The first and second modules are preferably connectable at the end caps. One of the end caps on the first module preferably rotates with an end cap on the second module from force provided by one or more of the robotic arm devices. The end caps are preferably capable of transferring connectable box items between the end caps. 
   The space platform of the present invention can also have extendable and retractable connection hardware, and the connection hardware can be adjustable and rotatable connection hardware. 
   At least some of the robotic arm devices are preferably capable of switching out, stowing and loading additional modules. Each of the end caps can comprise a disc-shape, and the space platform can also have communications electronics, as well as transportation electronics. The robotic arm devices of the present invention can have at least one elbow, and/or an end effector. The first module is preferably expandable to a length sufficient to establish gravity gradient stability for the platform of the present invention. Further, a support structure can be disposed between the end caps of the first module, and this support structure can comprise a truss system. 
   The present invention also relates to an orbital unmanned platform combined with a reusable launch vehicle comprising an unmanned payload transported to space, the payload having an inflatable structure with end caps disposed at terminal portions thereof. The structure preferably expands along an axis defined by the end caps during inflation. At least one of the end caps can have one or more tracks circumferentially disposed within or around the end cap, and one or more carriers can be disposed on the one or more tracks. The orbital unmanned platform combined with a reusable launch vehicle also preferably includes one or more inflatable arm sections disposed within the end caps and attached to one of the carriers. Further, a different payload can be transported upon return from space, thus creating a complete transportation cycle and a functioning node in space. 
   At least part of the payload can remain in space and at least part of the payload can return from space. The payloads can be accumulated, assembled, tested and transferred at a node platform. 
   Accordingly, several objects and advantages of the present invention are the cost effectiveness, reliability, efficiency, and an orbital service platform with minimum platform subsystems required. The platform permits re-configuration to specific customer systems and increased customer sensitivity. 
   Another primary object of the commercial service platform in space is to transport the customer&#39;s cargo to and from the platform in orbit, plug the cargo into the commercial service platform in space location, derive the services available in a cost effective manner and later return the cargo to the customer. 
   A primary advantage of the present invention is the cost effective combination of a reusable launch vehicle subsystem, orbital hardware including efficient affordable structures, power and communications subsystems, pre-engineered common computer interfaces, payload and shipping envelopes, communications, power, command and control tasks and attitude control subsystems. 
   The advantage of the commercial service platform on a reusable launch vehicle is an opportunity for the elimination of platform subsystems by using subsystems already on the launch vehicle including reboost and/or platform hardware providing cost effective common subsystems through commonality in design, procurement, testing and payload loading. 
   Another advantage of the invention is the common ground handling techniques, technical maintenance, financing and ownership of the platform, launch vehicle, and payloads. 
   Another advantage of the invention is an integrated commercial payload delivery operation that all works together in a cohesive manner to accomplish the ground processing, launch, transfer to the proper orbit, plug-in of the payload, services in orbit, potential follow-on support, and safe return of some of the delivery payload hardware. 
   Another advantage of the commercial service platform is an integrated design, flexible flow process to be capable of accommodating, on a general customer base, a number of different payloads from numerous organizations with varying requirements, different weights, various final orbits, different ground processing requirements, and varying financial needs. 
   Another advantage of the commercial service platform is an integrated design, combined with the reusable launch vehicle capable of the future coupling of the platform and the reusable launch vehicle for the changing of orbital altitude, location and gravity gradient orientation for purposes of accommodating orbital decay of the platform, decreasing the normal systems required on either object, enhancing either object with items from the other object and disposing of the platform at end of life. 
   Another advantage of the invention is the increased energy efficiency in the use of solar cells, including the different sources and technologies, the decreased cost in simplifying the ground handling by using the same payload envelopes as transported in the reusable launch vehicle, increased flexibility from the simple orbital platform, and the increased reliability and simplified handling from the common pre-tested hardware systems. 
   Another advantage of the invention is a single, affordable, robotic interface located at the base of the orbital service platform and each payload. 
   Another advantage of the orbital service platform is an inflatable or deployable payload structure that holds the customer payloads from the K-1 orbital vehicle (OV) or other vehicles using robotic systems. 
   Another advantage of the invention includes the various payloads with different shapes that can be attached to the support structure using adaptable structural interfaces. 
   Manufacturing advances in the thin film solar cell manufacturing and the resulting solar arrays offer a substrate and array that is ¼ the cost and 1/10 the weight of previous space solar arrays. These more affordable arrays may be flexible, space resistant and refurbished in orbit. 
   Another advantage of the invention is the lack of a propulsion system or propulsion subsystems. 
   Another advantage of the invention is the lack of propellant tanks pressurized by gas storage bottles filled with pressurants. 
   Another advantage of the invention is the lack of an orbital service platform avionics system. 
   Another advantage of the invention is the lack of an orbital service platform reboost system. 
   Another advantage of the invention is the lack of an orbital service platform attitude control system. 
   Another advantage of the invention is the lack of an orbital service platform manned support system. 
   Another advantage of the orbital service platform, in a nominal mission mated with one or more customer payloads, is the reboost using the K-1 and/or other vehicle to perform the platform reboost and repositioning. 
   Another advantage of the invention is the robotics capability to capture and deploy the orbital service platform and delivery vehicle to sufficient distance to allow for further separation by the vehicle&#39;s thrusters. 
   The orbital service platform 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 subsystems, multiple payload placement and various service systems of the Orbital Service Platform. 
   Other objects, advantages and novel features, and further scope of applicability will be set forth in part in the detailed description to follow, orbital service platform drawings taken in conjunction with the accompanying drawings, and in part will become apparent to those skilled in the art upon examination of the following, or may be learned by practice of the invention. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
     The accompanying drawings, which are incorporated into and form a part of the specification, illustrate several embodiments of the present invention and, together with the description, serve to explain the principles of the invention. The drawings are only for the purpose of illustrating a preferred embodiment of the invention and are not to be construed as limiting the invention. In the drawings: 
       FIG. 1  is an orbital service platform of the present invention; 
       FIGS. 2A–2C  are drawings showing side views of end caps of the present invention having inflatable arms disposed therein; 
       FIGS. 2D–2F  are drawings showing cutaway views of end caps of the present invention wherein inflatable arms are disposed; 
       FIGS. 3A–C  show the deployment system of the present invention; 
       FIGS. 4A–C  show the orbital service platform power system of the present invention; 
       FIG. 5  shows the expanded truss orbital service platform of the present invention transferring customer payloads to and from a reusable launch vehicle (RLV); 
       FIG. 6  shows the orbital service platform reboost propulsion system of the present invention; 
       FIGS. 7A and 7B  show the double configuration for the orbital service platform of the present invention; 
       FIGS. 8A–I  show an expanded payload carrier configuration of the orbital service platform of the present invention; 
       FIG. 9  shows an example payload carrier configuration of the orbital service platform of the present invention; 
       FIG. 10  shows an expanded configuration of the orbital service platform of the present invention on an external tank; and 
       FIG. 11  shows a corner configuration of the inflatable orbital service platform of the present invention. 
   

   DESCRIPTION OF THE PREFERRED EMBODIMENTS 
   BEST MODES FOR CARRYING OUT THE INVENTION 
   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  FIG. 1 , which illustrates a preferred embodiment of the invention.  FIG. 1  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  FIG. 5 ) 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  FIG. 5 ) 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 . 
     FIGS. 2A–2C  (side views), and  FIGS. 2D–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  FIGS. 2A 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. 
     FIGS. 3A–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  FIG. 5  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 . 
     FIGS. 4A–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  FIG. 4C  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  FIG. 4A  platform  18  (also see  FIGS. 1 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  FIG. 4C . 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 . 
     FIG. 5  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 . 
     FIG. 6  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. 
     FIGS. 7  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. 
     FIG. 8A  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 . 
     FIG. 8B  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. 
     FIG. 8C  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. 
     FIG. 8D  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. 
     FIG. 8E  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. 
     FIG. 8F  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. 
     FIG. 8G  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 . 
     FIG. 8H  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.) 
     FIG. 8I  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 . 
     FIG. 9  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. 
     FIG. 10  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. 
     FIG. 10  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. 
     FIG. 11  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.