A pushing-out apparatus for an extendible mast includes a mast storing unit, a mast pushing-out unit and a mast pushing-out driving unit. The storing unit stores an extendible mast including stages of foldable trusses in a state that the stages are folded. The pushing-out unit is stored in the storing unit around the stage-folded mast stored in the storing unit. The driving unit moves the pushing-out unit to a projecting position in an outside of the storing unit while the stages of the mast are folded, sequentially extend out the folded stages of the mast stored in the storing unit by the pushing-out unit from the storing unit and push out the extended stages from the pushing-out unit of the projecting position in a side of the pushing-out unit opposing to the storing unit.

A large area, deployable flexible blanket photovoltaic solar array architecture for high power applications is disclosed. The structure is a modularized and scalable solar array system that provides high power level scalability. The structure is comprised of repeating, similar modular deployable roll-out solar array wings mounted in an opposing manner and along the length of a rigid, strong and efficiently packaged deployable backbone structure. The deployable roll-out solar array building block modular winglet elements can be comprised of either a rolled or z-folded flexible photovoltaic blanket configuration, and their structural deployment is motivated by the elastic strain energy of longitudinal roll-out booms. The backbone structure is comprised of a stiff deployable beam structure articulated that is deployed perpendicular with respect to the spacecraft sidewall and latched out. Deployment of the winglets can be conducted once the articulated backbone structure has been deployed, is latched, and forms a rigid beam.

A fuel depot in space is provided. The fuel depot has a collapsible housing with a guidance, navigation, and control (GNC) system, a power management system, and a reaction control system (RNC). Connected to the housing are a plurality of fuel tanks that are connected via collapsible rods. The fuel tanks have pipe systems that are in communication with a plurality of pumps to transfer fuel from the tanks through a refueling arm and into a spacecraft during refueling.

The present invention relates to a light baffle assembly including a base baffle member comprising a base wall portion positioned substantially parallel to a longitudinal axis, an upper baffle member comprising an upper wall portion coupled to an upper blade portion, the upper wall portion positioned substantially parallel to the longitudinal axis, and the upper blade portion positioned to extend inwards from the upper wall portion towards the longitudinal axis, and a resilient member configured to extend the upper baffle member away from the base baffle member.

A method of deploying a space based occulter is provided. The occulter comprises a base portion and a blanket section extending radially from the base portion. A plurality of starlight blocking petals are attached to the base portion and attached to the blanket section, the petals extending radially from the base portion, each of the petals being hingedly connected to an adjacent petal.

The present invention relates to an assembly apparatus for assembling components of spacecraft in space. The assembly apparatus includes: a core platform; and a mobile platform including an end effector configured to perform an assembly or manufacturing task. The mobile platform is connected to the core platform by a tether. The core platform includes a body and a coupling element connected to and extendable from the body such that the coupling element may be spaced from the body of the core platform. The tether connects the mobile platform to the body via the coupling element. The assembly apparatus further includes an actuator configured to vary the length of the tether extending between the coupling element and the mobile platform to control the position of the mobile platform relative to the body of the core platform.

A telescopic boom system provides an extensible boom that may be used in spacecraft applications including supporting photovoltaic panels, communication antennas, instrumentation, and so forth. A stowed configuration is volumetrically compact, including the boom and actuators such as a motor. During deployment, threaded nuts for each nested section of the boom are self-aligning with respect to a leadscrew driven by the motor. Sections are staged for extension in staged sequence by a flexure arm engaging a ramp feature on a portion of the nested section. Extension failure mitigation is enhanced by allowing partial retraction of some sections during extension. Once fully extended, tension of the boom may be later adjusted, modifying the structural fundamental frequency. A ratchet may be engaged with extension of a final nested section to prevent retraction of the extended boom.

A cable-driven telescopic boom with several boom segments repositionable between stowed positions and deployed positions. The boom includes multiple spaced apart and separate cables that engage pulleys connected to each boom segment. A drive system can be used to apply tension to the cables to reconfigure the boom from a stowed configuration to a deployed configuration.

A cable-driven telescopic boom with several boom segments repositionable between stowed positions and deployed positions. The boom includes multiple spaced apart and separate cables that engage pulleys connected to each boom segment. A drive system can be used to apply tension to the cables to reconfigure the boom from a stowed configuration to a deployed configuration.

A cable-driven telescopic boom with several boom segments repositionable between stowed positions and deployed positions. The boom includes multiple spaced apart and separate cables that engage pulleys connected to each boom segment. A drive system can be used to apply tension to the cables to reconfigure the boom from a stowed configuration to a deployed configuration.