Abstract: A reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. A variety of cargo modules of different configurations allow cargo to be uplifted into orbit. In one embodiment, the cargo module is an unpressurized cargo module in which the cargo is exposed to the environment of space during the unloading process. The cargo module may also be a pressurized cargo module. In an alternative embodiment, the cargo module may include both a pressurized cargo module and unpressurized cargo module.

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: 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: 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 reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. A variety of cargo modules of different configurations allow cargo to be uplifted into orbit. In one embodiment, the cargo module is an unpressurized cargo module in which the cargo is exposed to the environment of space during the unloading process. The cargo module may also be a pressurized cargo module. In an alternative embodiment, the cargo module may include both a pressurized cargo module and unpressurized cargo module.

Abstract: A reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. A variety of cargo modules of different configurations allow cargo to be uplifted into orbit. In one embodiment, the cargo module is an unpressurized cargo module in which the cargo is exposed to the environment of space during the unloading process. The cargo module may also be a pressurized cargo module. In an alternative embodiment, the cargo module may include both a pressurized cargo module and unpressurized cargo module.

Abstract: An improved method for loading propellants into separate tanks on a reusable launch vehicle (RLV) uses three innovative methods. The liquid loading provides three liquid transfer methods, integrated and coordinated to provide less complicated loading and unloading operations, transfers, and cools and controls the liquids to provide a safe, cost effective solution to reusable vehicle tanking and de-tanking under commercial conditions. To insure the density of the propellant is maximized by cooling in a quick liquid loading environment, pre-cooling may be used.

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: 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 active satellite dispenser is preferably attachable to a reusable launch vehicle for deployment of one or more satellites into one or more desired orbits. The active satellite dispenser includes a center mast that releasably receives the satellite(s), a liquid propellant rocket, and an orbital control system on an avionics pallet. In the preferred embodiment, a pressurized gas selectively pressurizes the propellant tanks (which may include fuel and oxidizer tanks), to provide propellant to the rocket. In operation, the launch vehicle releases the satellite dispenser in a first deployment orbit. The active dispenser rocket and orbital control system then transport the active dispenser and satellite(s) into the final deployment orbit. In the preferred embodiment the active dispenser can operate multiple times to place individual satellites in different orbits.

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: An orbital vehicle (34) having a propulsion module (33) and a logistics module (36). The logistics module includes a generally cylindrical outer shell (56, 541, 542) with first and second ends. An openable cover (58) is coupled with the outer shell at the first end, thereby providing access to the interior of the logistics module. The second end is adapted to couple to the propulsion module. A cargo container (54) is disposed generally within the outer shell, the cargo container including a berthing mechanism (70) disposed to be accessible when the cover is opened. A retractable grapple fixture (176) is provided on the logistics module, selectively positionable between an extended position and a retracted position. When the grapple fixture is in the extended position a grapple shaft (78) can be accessed to secure the orbital vehicle. When the grapple fixture is retracted, it is enclosed within the orbital vehicle.

Abstract: An active satellite dispenser is preferably attachable to a reusable launch vehicle for deployment of one or more satellites into one or more desired orbits. The active satellite dispenser includes a center mast that releasably receives the satellite(s), a liquid propellant rocket, and an orbital control system on an avionics pallet. In the preferred embodiment, a pressurized gas selectively pressurizes the propellant tanks (which may include fuel and oxidizer tanks), to provide propellant to the rocket. In operation, the launch vehicle releases the satellite dispenser in a first deployment orbit. The active dispenser rocket and orbital control system then transport the active dispenser and satellite(s) into the final deployment orbit. In the preferred embodiment the active dispenser can operate multiple times to place individual satellites in different orbits.

Abstract: An aerospace vehicle for delivering a payload into space includes a first stage and a second stage with a plurality of separation assemblies coupling the first stage to the second stage. At least one container charged with pressurized gas in fluid communication with the separation assemblies provides pressurized gas to the separation assemblies to cause separation of the first stage and the second stage.

Abstract: A feedline for transporting propellant from a tank of a launch vehicle to an engine includes a first conduit coupled to the tank, a second conduit coupled to the engine, and a flexible joint connecting the first conduit to the second conduit. The flexible joint provides fluid communication between the first conduit and the second conduit.

Abstract: A spacecraft launch system includes a support assembly and a seat coupled to a hinge having a hinge axis. In operation, the support assembly and the seat rotate about the hinge axis to move the spacecraft from a horizontal position to a vertical position for launching. The launch system may incorporate an alignment technique that includes alignment members and actuators.

Abstract: A recoverable/reusable booster stage has a restartable center liquid-fueled rocket engine mounted in the aft portion of a vehicle body in alignment with the center axis of the body. The booster stage may also include two side liquid-fueled rocket engines mounted in the aft portion of the body in symmetrical relation to the center rocket engine. After booster stage separation, the center engine is restarted to direct the booster stage towards a recovery site.

Abstract: A system is provided for delivering liquid propellant in a booster stage of a launch vehicle. The system includes an arrangement of tanks and valves to direct a first supply of liquid propellant during ascent of the booster stage and a second supply during descent of the booster stage. In disclosed embodiments, tanks may be arranged in series or parallel.

Abstract: An aluminum cryogenic tank for launch vehicles has aluminum skirts that extend from each end of a peripheral wall of a tank body. The skirts provide a temperature differential between the tank body and the ends of the skirts so that composite panels can be used in locations longitudinally proximate to the tank body without over stressing either the skirts or the composite panels in regions near their junctures and without sacrificing structural integrity of the composite panels due to an excessively low temperature. The peripheral wall of the tank and the skirts provide a portion of a structural/aerodynamic wall or shell of the launch vehicle.