Abstract: A reusable container which provides flame and thermal protection for shipping hazardous materials such as cylinders containing compressed gas has a flame resistant reinforced outer shell having a bottom section hingedly coupled to a top section. A first inner layer of thermal insulating material is fitted into the top and bottom sections of the outer shell. An optional second inner layer of shock absorbing material with thermal insulating properties is fitted next to the first inner layer and configured to contact and conform to surface sections of the compressed gas cylinder. An interior liner comprised of a durable liner constructed of fabric or molded heat-resistant plastic.

Abstract: A radio frequency (RF) drive system and method for driving the ion trap or mass filter of a mass spectrometer has a programmable RF frequency source coupled to a RF gain stage. The RF gain stage is transformer coupled to a tank circuit formed with the ion trap or mass filter. The power of the RF gain stage driving the ion trap or mass filter is measured using a sensing circuit and a power circuit. A feedback value is generated by the power circuit that is used to adjust the RF frequency source. The frequency of the RF frequency source is adjusted until the power of the RF gain stage is at a minimum level. The frequency value setting the minimum power is used to operate the RF drive system at the resonance frequency of the tank circuit formed with the transformer secondary inductance and the ion trap or mass filter capacitance.

Abstract: Enhanced translational thrusting is provided by reaction engines configured to permit translational thrusting off or through the center of gravity of a spacecraft or other vehicle. Among other applications, this approach is useful for a Satellite Life Extension System (SLES) that provides maintenance services to orbiting satellites. By attaching to the satellite and conducting maneuvers to maintain its operational orbit and attitude, the SLES increases the working lifetime of the satellite. Since the engines of the SLES are redundant, the failure of a single engine will not jeopardize the overall success of the mission.

Abstract: An ion trap for a mass spectrometer has a conductive central electrode with an aperture extending from a first open end to a second open end. A conductive first electrode end cap is disposed proximate to the first open end thereby forming a first intrinsic capacitance between the first end cap and the central electrode. A conductive second electrode end cap is disposed proximate to the second open end thereby forming a second intrinsic capacitance between the second end cap and the central electrode. A first circuit couples the second end cap to a reference potential. A signal source generating an AC trap signal is coupled to the central electrode. An excitation signal is impressed on the second end cap in response to a voltage division of the trap signal by the first intrinsic capacitance and the first circuit.

Abstract: An underway replenishment system is used to deliver payloads and supplies to an orbiting receiving space vehicle. This system combines the advantages of the maneuverability of a delivering space vehicle with the large payload capacity of expendable launch vehicles to minimize payload delivery cost. Large payloads are launched into low orbit with expendable launch vehicles. A delivering space vehicle rendezvous with the independently launched payloads and assembles them into a payload stack. The receiving space vehicle located at a higher orbit deploys a tether towards the orbital path of the delivering space vehicle located at a lower orbit, and the tether is used to capture and retrieve the payload from the delivering space vehicle to the receiving space vehicle.

Abstract: A deployable crew quarters incorporates folding panels and acoustic panels to provide a lightweight on-orbit crew quarter. The deployable crew quarters preferably includes a frame and a plurality of panels mounted to the frame. At least one of the panels is hinged to the frame to allow movement between a stowed position and a deployed position. More specifically, the panels include a front panel coupled to the frame and two side panels moveable coupled to the frame. The two side panels are moveable between a stowed position and a deployed position. Still further, a top panel is also preferably moveable coupled to the frame, wherein the top panel is moveable between a stowed position and a pop-up deployed position. The front panel includes a sliding door panel to allow crew access to the deployable crew quarters. The front panel also preferably extends outward from the frame, which provides space in which a ventilation mechanism can be mounted.

Abstract: A logistics rack has a common core with a top end and a bottom end, an interchangeable upper interface adapter releaseably coupled to the top end, and an interchangeable lower interface adapter releaseably coupled to the bottom end. The upper and lower interface adapters may be readily changed to allow the logistics rack to be utilized on a variety of space vehicles or modules. The common core includes a plurality of stowage bays in which logistics bags are secured.

Abstract: A secondary universal communication system enables dedicated and independent communications capability between space vehicle payload elements and ground based communications networks. The system may either utilize existing communications satellites as an intermediate network to provide continuous communications with payload elements, regardless of orientation or configuration of the space vehicle, or may communicate directly with ground stations via down link capability. The system has a navigation system and an inertial measurement system to provide antenna pointing and tracking capability to actively track satellites. The secondary universal communications system can provide supplemental and independent communications capacity to the space vehicle's primary communication system.

Abstract: A universal communication system enables dedicated and independent communications capability to NSTS payload elements and ground based communications networks. The system may either utilize existing communications satellites as an intermediate network to provide continuous communications with payload elements, regardless of orientation or configuration of the NSTS Orbiter, or may communicate directly with ground stations via down link capability. In addition, the universal communications system can provide supplemental and independent communications capacity to the NSTS Orbiter's primary communication system.

Abstract: The present invention provides an integrated cargo carrier assembly that is compatible with the NSTS Orbiter and space stations located, in Earth orbit. The integrated cargo carrier assembly is capable of carrying various cargo panels on a pallet assembly and includes a pressurized tunnel that provides a translation path for crew members between the crew compartment of the NSTS Orbiter and a pressurized module located in the cargo bay. In addition, the pressurized tunnel can be utilized to carry payloads required to be maintained in a pressurized environment. The combination of the cargo carrying and connectivity features of the integrated cargo carrier assembly eases manifesting and on-orbit operations and greatly reduces the effort required to ground process various cargo. Further, the integrated cargo carrier assembly also eliminates difficulties in mating and de-mating payload to the NSTS Orbiter by providing integral latching means that permits payloads to be easily removed from the carrier on-orbit.

Abstract: A universal communication system enables dedicated and independent communications capability to NSTS payload elements and ground based communications networks. The system may either utilize existing communications satellites as an intermediate network to provide continuous communications with payload elements, regardless of orientation or configuration of the NSTS Orbiter, or may communicate directly with ground stations via down link capability. In addition, the universal communications system can provide supplemental and independent communications capacity to the NSTS Orbiter's primary communication system.

Abstract: The invention provides a variable length mission configurable module that can be readily reconfigured to meet the specific pressurized space and payload requirements for a wide variety of Earth orbit missions. The module system includes a plurality of truncated body portions, a substantially flat forward bulkhead, and a substantially flat aft bulkhead. The plurality of truncated body portions and bulkheads are coupled together, wherein the forward bulkhead is located at a front end of a line of coupled truncated body portions and the aft bulkhead is located at an aft end of the coupled truncated body portions. The number of truncated body portions employed can be readily varied to adjust the overall length, pressurized volume and payload capabilities of the module system to specific mission requirements.

Abstract: The invention provides a modular system including one or more interchangeable pressurizable body sections, a front end cap and a rear end cap. A tendon array assembly is coupled between the front endcap and the rear endcap. The body sections are preferably coupled together by a flexible seal. The interchangeable pressurizable body sections may be preloaded prior to launch or left vacant for cargo retrieval from an orbiting facility. Once loaded, the various elements of the modular system may be easily assembled with other elements into a plurality of configurations. The modular system can be attached to an orbiting space structure or utilized within the cargo bay of the NSTS Orbiter to provide a wide range of mission objectives.

Abstract: A module incorporating at least one flat end cap is positioned within the payload of the Space Shuttle or other space vehicle to enhance the capabilities of the payload area. The flat end cap reduces the required volume in the launch vehicle to be occupied by the module and provides for efficient use of the interior space of the Space Shuttle by providing more flat surfaces to which necessary equipment can be fastened. The module is truncated, thus adding another flat surface, i.e., a ceiling, to the interior of the vehicle. The truncated top of the module is capable of separate integration and carries additional experiments within racks which can be attached to its interior surface. The module can be fabricated from aluminum members in an aircraft type fashion of construction, or can be assembled from existing or modified Space Lab hardware.