Abstract: A transportation node that orbits a celestial body includes a truss having two ends with least at one end of the truss having at least one coupling tether cable with a tether tip at individual ends. The truss, while orbiting the celestial body, rotates around its center of mass in a direction to control the tether tip in relation to a surface of the celestial body and to cancel a relative velocity between the tether tip and the surface for transferring a payload attached to the tether tip to and from the surface. A method of transferring payload to and from a celestial body includes reeling in/out from an orbiting transportation node a coupling tether cable with a tether tip configured to attach to the payload.

Abstract: A thin diaphragm valve includes a base plate attached to a valve attach plate. A diaphragm is positioned between the plates to move between open and closed positions. A spring can be provided between the diaphragm and a sealing flange of a pipe. Because no sliding friction occurs between sealing surfaces, wear is reduced and leakage is also reduced. A pierceable membrane can also be added to provide additional security.

Abstract: An aerospace frame accommodates propellant tanks for facilitating propellant operations in space. The frame includes at least two plates for supporting the propellant tanks; at least one brace supporting the plates; and a cavity between two plates that accommodates a removable propellant tank.

Abstract: A space transportation propellant depot has multiple locations, sources and capabilities. Maximizing known mature technologies coupled with realistic industrial techniques results in the incremental development of a propellant source on the moon. Propellant depots are economically driven locations with defined services, sources of propellant and innovation in the pursuit of transportation related commerce as mankind explores for resources beyond Earth.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

Abstract: A transportation node system orbits a celestial body. The node system includes a truss having two ends, the truss rotating around its center of mass while orbiting the celestial body. The truss stores payloads. The node system also includes tether tips, each attached to one end of the truss via a tether so that each tether tip can extend from the truss and retract to the truss for transfer of payloads. The tether runs through the length of the truss and connects to each tether tip, each tether tip being capable of engaging payloads. The node further includes at least one tether cable reel that reels in and reels out the tether so the tether tips can extend from and retract to the truss.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Previously expensive arc jet wind tunnels attempted to simulate the re-entry temperatures and ever changing re-entry flow environment for researchers. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes.

Abstract: A platform for storage and transfer of payloads in space includes a plate for supporting a payload, and a transfer mechanism for transferring the payload to and from the plate. A groove extends diametrically between two edges of the plate for receiving a rail provided on the payload. The rail includes a plurality of teeth, and the transfer mechanism includes a gear which interacts with the teeth for moving the rail. Two platforms may be positioned adjacent to each other for transferring a payload. Docking of the two platforms includes engagement of tapered pins and tapered holes on the platforms. In this manner, the grooves of the platforms are aligned. The rail is passed between the grooves of the platforms for transferring the payload between the platforms.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

Abstract: A method for measuring a target constituent of an electroplating solution using an electroanalytical technique is set forth in which the electroplating solution includes one or more constituents whose by-products skew an initial electrical response to an energy input of the electroanalytical technique. The method comprises a first step in which an electroanalytical measurement cycle of the target constituent is initiated by providing an energy input to a pair of electrodes disposed in the electroplating solution. The energy input to the pair of electrodes is provided for at least a predetermined time period corresponding to a time period in which the electroanalytical measurement cycle reaches a steady-state condition. In a subsequent step, an electroanalytical measurement of the energy output of the electroanalytical technique is taken after the electroanalytical measurement cycle has reached the steady-state condition.

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.

Abstract: A platform for storage and transfer of propellant tanks in space includes frames configured to releasably support plural propellant tanks in storage positions, and transfer mechanisms configured to transfer propellant tanks to and from the storage positions. The platform includes a central structure to which the plural frames are connected at predetermined spaced intervals. The transfer mechanisms include extendable telescoping arms mounted to the central structure. The arms have end effectors configured to grip bands on propellant tanks. Two platforms may be positioned adjacent each other for the transfer of propellant tanks therebetween.

Abstract: A platform for storage and transfer of payloads in space includes a plate for supporting a payload, and a transfer mechanism for transferring the payload to and from the plate. A groove extends diametrically between two edges of the plate for receiving a rail provided on the payload. The rail includes a plurality of teeth, and the transfer mechanism includes a gear which interacts with the teeth for moving the rail. Two platforms may be positioned adjacent to each other for transferring a payload. Docking of the two platforms includes engagement of tapered pins and tapered holes on the platforms. In this manner, the grooves of the platforms are aligned. The rail is passed between the grooves of the platforms for transferring the payload between the platforms.

Abstract: A system for transportation and storage of cargo in space includes one or more platforms. The platforms are operable to hold multiple removable propellant tanks and rendezvous with one or more other platforms in space. The platforms also include one or more thruster systems and positioners. Each positioner has an effector operable to grip a band disposed around each propellant tank. Each positioner is operable to facilitate the transfer of the multiple removable propellant tanks between platforms during the rendezvous.

Abstract: An orbital experiment system with different internal experiment locations within a reusable launch vehicle making daylong delivery trips to space. The experiments get access to the attributes of low earth orbit, the reusable launch vehicle's power and other subsystems. The experimenter utilizes uniform experiment trays having a uniform connector for connection to an experiment management unit mounted on the orbital vehicle. The experiment management unit provides power and data from the orbital vehicle related to the operation of the orbital vehicle and permits an experiment check simulation prior to integration into the launch vehicle. The uniform size and connectivity requirements provide low cost options for the delivery of an experiment into space and the return of the experiment from space.

Abstract: An orbital experiment system with different internal experiment locations within a reusable launch vehicle making daylong delivery trips to space. The experiments get access to the attributes of low earth orbit, the reusable launch vehicle's power and other subsystems. The experimenter utilizes uniform experiment trays having a uniform connector for connection to an experiment management unit mounted on the orbital vehicle. The experiment management unit provides power and data from the orbital vehicle related to the operation of the orbital vehicle and permits an experiment check simulation prior to integration into the launch vehicle. The uniform size and connectivity requirements provide low cost options for the delivery of an experiment into space and the return of the experiment from space.

Abstract: An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

Abstract: A method for measuring a target constituent of an electroplating solution using an electroanalytical technique is set forth in which the electroplating solution includes one or more constituents whose by-products skew an initial electrical response to an energy input of the electroanalytical technique. The method comprises a first step in which an electroanalytical measurement cycle of the target constituent is initiated by providing an energy input to a pair of electrodes disposed in the electroplating solution. The energy input to the pair of electrodes is provided for at least a predetermined time period corresponding to a time period in which the electroanalytical measurement cycle reaches a steady-state condition. In a subsequent step, an electroanalytical measurement of the energy output of the electroanalytical technique is taken after the electroanalytical measurement cycle has reached the steady-state condition.

Abstract: A method for measuring a target constituent of an electroplating solution using an electroanalytical technique is set forth in which the electroplating solution includes one or more constituents whose by-products skew an initial electrical response to an energy input of the electroanalytical technique. The method comprises a first step in which an electroanalytical measurement cycle of the target constituent is initiated by providing an energy input to a pair of electrodes disposed in the electroplating solution. The energy input to the pair of electrodes is provided for at least a predetermined time period corresponding to a time period in which the electroanalytical measurement cycle reaches a steady-state condition. In a subsequent step, an electroanalytical measurement of the energy output of the electroanalytical technique is taken after the electroanalytical measurement cycle has reached the steady-state condition.

Abstract: A method for measuring a target constituent of an electroplating solution using an electroanalytical technique is set forth in which the electroplating solution includes one or more constituents whose by-products skew an initial electrical response to an energy input of the electroanalytical technique. The method comprises a first step in which an electroanalytical measurement cycle of the target constituent is initiated by providing an energy input to a pair of electrodes disposed in the electroplating solution. The energy input to the pair of electrodes is provided for at least a predetermined time period corresponding to a time period in which the electroanalytical measurement cycle reaches a steady-state condition. In a subsequent step, an electroanalytical measurement of the energy output of the electroanalytical technique is taken after the electroanalytical measurement cycle has reached the steady-state condition.