An exemplary method protects a delicate device from potential damage from shock or vibration. A material in a liquid state is placed in contact with the delicate device. The liquid material is cooled causing it to transition to a solid state which stabilizes the delicate device in contact with the solid material against shock and vibration. The solid state material is heated causing it to sublimate into a gas thus releasing the delicate device for operation.

A space vehicle includes one or more magnetorquers operable to change an attitude of the space vehicle in an external magnetic field, each magnetorquer comprising a coil, and a switching circuit for short-circuiting the coil of at least one of the magnetorquers so that a closed electric circuit comprising said coil is formed, for damping tumbling motion of the space vehicle in the external magnetic field. The switching circuit is configured to short-circuit the coil of the at least one magnetorquer upon occurrence of a condition indicative of end-of-life or failure of the space vehicle. The application further relates to a corresponding method of operating a space vehicle.

An active composite variable damping rotational control device includes a variable damping module and a power module. The variable damping module includes a magnetorheological fluid tank and a rotational inertia wheel. The rotational inertia wheel is arranged in the magnetorheological fluid tank fully filled with magneorheological fluid. The power module includes a device tubular cavity, a driver, an encoder and a speed changer. The driver is fixed on the inner wall of the device tubular cavity. The driver, the encoder and the speed changer are coaxial. A driving shaft of the driver passes through the speed changer and extends into the magnetorheological fluid tank to be fixed perpendicularly at the center of the rotational inertia wheel. The control effect of the present invention may not be greatly affected by the change of a structural form and the change of an external load.

The disclosed apparatus may include (1) a subassembly including (a) a first conductive coil, where at least a portion of the first coil defines a portion of a spherical surface and is oriented along a first direction along the portion of the spherical surface, (b) a second conductive coil proximate the first coil, where at least a portion of the second coil is oriented along a second direction orthogonal to the first direction along the portion of the spherical surface, and (c) a body that holds the coils, (2) a structure that generates a magnetic field through the portion of the first and second coils along a third direction orthogonal to the first and second directions, and (3) a coil driver circuit that supplies current to the coils to move the structure relative to the subassembly, or vice-versa, along the first and second directions. Various other embodiments are also disclosed.

A low pressure duct configured to channel a gas within a structure includes a tubular body formed from a polymer foam material, and a first plurality of strands adhered to a surface of the tubular body along a plurality of paths. The plurality of paths includes a first set of paths oriented longitudinally along the tubular body. The first set of paths are spaced apart from each other around a circumference of the tubular body. The plurality of paths also includes a second set of paths oriented circumferentially around the tubular body. The second set of paths are spaced apart longitudinally along the tubular body.

An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.

A vibration isolation/damping satellite mount of a chopped carbon fiber reinforced thermoplastic composite material mainly includes two parts, and the two parts are connected through bolts. Considering the limitation of the molding process, the mount configuration is further optimized, and the mount structure is prepared by using the injection molding process. Furthermore, the vibration isolation/damping satellite mount of the chopped carbon fiber reinforced thermoplastic composite material prepared in the present invention can be used for large loads and complex working conditions, and the connectivity, overall strength stability, vibration isolation performance and service life of the mount all meet the design requirements. The present invention provides an efficient optimization design and manufacturing method for engineering manufacturing of thermoplastic composite materials, and vibration isolation/damping satellite mount manufactured by the method is low in cost, high in practicability and easy to produce on a large scale.

A compartment for a space vehicle includes a pressurized structure having a structural wall, the structural wall having interior surfaces facing an interior of the compartment and exterior surfaces exposed to an external environment. An internal mounting structure for mounting a component is provided within the compartment, and mounting features support the internal mounting structure from the pressurized structure. The internal mounting structure is spaced away from the interior surfaces of the pressurized structure, and a thermal fluid is provided in the pressurized structure. The thermal fluid enables convective heat transfer between the component mounted on the internal mounting structure and the interior surfaces of the pressurized structure.

Embodiments of the present invention generally relate to a novel system, device, and methods for providing an isolator for components and instrumentation to isolate vibrations, shock, static or quasi-static loads, thermal loads, and electrical currents. The novel isolator has an asymmetrical shape, experiences uniform motion under quasi-static loading, and reduces the effective modal mass across a range of frequencies. The novel isolator outperforms conventional vibration isolators in terms of cost, schedule (manufacturing time and lead time), heat dissipation, and performance.

A pogo effect corrector system for a feed system for feeding a rocket engine with liquid propellant, the corrector system comprising: a feed pipe part for feeding liquid propellant that is configured to be connected both upstream and downstream to a liquid propellant feed pipe of the feed system; and a hydraulic accumulator comprising a tank connected to the feed pipe part via at least one communication orifice; the corrector system being characterized in that: at least a portion of the feed pipe part is at least partly surrounded by the inner volume of the tank; with each cross-section of said portion relative to its central axis being at least partly surrounded by the corresponding cross-section of the inner volume of the tank, in such a manner that the corresponding cross-section of the inner volume of the tank is off-center relative to said cross-section of said portion.