A rigidizing latch assembly comprises a robotically compatible aerospace attachment mechanism which comprises a male latch and a receptacle configured to cooperatively couple. The male latch comprises a male latch housing and a latch assembly movably disposed within the male latch housing; a driver operatively in communication with a latch support; a male latch core; a driver interface access port; and one or more extraction feet operatively in communication with the driver. The receptacle comprises a receptacle housing sized to receive a lower portion of the male latch housing; a positioning target adapted to provide a visual positioning targeting cue; and one or more latch interfaces dimensioned to releasably mate with a corresponding lead-in guide of the plurality of lead-in guides.

A reprovisionable spacecraft and reprovisioning subassemblies for mating with a reprovisionable spacecraft are both described. The reprovisionable spacecraft has one or more mechanical, thermal, data, and or electrical mating interfaces for attaching, powering, and communicating with a reprovisioning subassembly, which for one embodiment is a self-contained thruster unit. The self-contained thruster unit preferably comprises a fuel tank, control electronics, and a thruster assembly. Alternately, a reprovisioning subassembly can comprise a fuel tank and control electronics, a fuel tank, or a thruster. Also, a reprovisionable spacecraft may be carried into orbit without reprovisioning subassemblies attached, and then deployed after reprovisioning subassemblies have been attached to their respective mating interfaces. Reprovisioning utilizing a self-contained thruster unit or tank eliminates the large risk associated with refueling satellites in space. Reprovisioning also eliminates the need for a dedicated attached life extension vehicle.

A method for the deployment of reconnaissance devices including buoy cameras and robotic devices in a target mission area of a remote location in space utilizing a maneuverable descent de-booster capsule and a buoyant vessel for the deployment is disclosed, including identifying the target area from an orbiting spacecraft; deploying the de-booster into orbit over the target area; initiating gradual descent of the de-booster in the atmosphere of the remote location in space; ejecting the buoyant vessel and its payload from the de-booster; filling the buoyant portion of the buoyant vessel with a lifting gas to cause the buoyant portion to become a large balloon; activating reconnaissance devices on the bay portion of the buoyant vessel, including video and other devices for monitoring and surveiling the target mission area; maneuvering the buoyant vessel to refine mission site selection; opening cargo bay doors at a predetermined altitude to deliver payloads including buoy cameras to the target mission area; causing the at least one buoyant vessel to rise in the atmosphere over the target mission area after payload delivery; and activating communication relay functions in the buoyant vessel while maintaining ongoing reconnaissance activities.

A deployable multi-section boom comprising a first hinge assembly including a base section adapted to be attached to a structure, a movable section that is pivotably attached to the base section and a first boom attached to the movable section. The first hinge assembly is configured to allow the first boom to pivot in a first direction to a first predetermined maximum angle with respect to the base section. A first constant torque assembly constantly urges the first boom to pivot in the first direction and includes a component attached to the base section of the first hinge assembly. The multi-section boom includes a second hinge assembly that includes a first section attached to the first boom and a second section that is pivotably attached to the first section. A second boom is attached to the second section of the second hinge assembly wherein the second hinge assembly allows the second boom to pivot in a second direction to a second predetermined maximum angle with respect to the first boom. A second constant torque assembly constantly urges the second boom to pivot in the second direction and includes a component that is attached to the first section of the second hinge assembly. The first constant torque assembly and second constant torque assembly cooperate to configure the multi-section boom in a fully deployed state wherein the constant torque applied to the first boom causes the entire multi-section boom to pivot in the first direction while the constant torque applied to the second boom causes the second boom to simultaneously pivot in the second direction with respect to the first boom while the entire multi-section boom continues to pivot in the first direction. The multi-section boom is fully deployed when the first boom pivots to the first predetermined maximum angle and the second boom pivots to the second predetermined angle.

To facilitate on-orbit servicing, such as for a refueling operation, techniques are presented for a servicing satellite to cut through the multi-layer insulation blanket of a client satellite to provide access to the client satellite without releasing unacceptable quantities of foreign object debris from the multi-layer insulation. The serving satellite includes a sealing tool, such as a pair of heater rollers, that apply pressure and heat to the insulating blanket to melt the inner layers and seal the outer layers together. The servicing satellite can then use a cutting tool to cut the sealed region and access the client satellite.

A space transportation system for providing high volume, high mass access to space that includes tethers that extend between the earth and one or more space stations or platforms. One or more counterweights may be utilized at the terminal end of the tethers in space. The tethers utilize may be made of carbon nanotubes or other advanced materials and woven into cables with electromagnets embedding therein. The tethers include tapering profiles along their lengths to facilitate operation of the system. Transport vehicles for passengers and cargo travel up the tethers using electromagnetic levitation and impulsion. Energy from solar panels or movement of the vehicles along the tethers may be generated for use in the system or for supplemental uses.

A spacecraft, reconfigurable from a launch configuration to an on-orbit configuration, includes a main body structure, a manipulator, a first deployable rigid reflector and an attachment arrangement, including at least one hold-down assembly (HDA). In the launch configuration, the HDA is in a fully engaged configuration such that the attachment arrangement mechanically attaches the first reflector with the spacecraft main body structure and prevents relative motion between the first reflector and the spacecraft main body. Reconfiguring the spacecraft from the launch configuration to the on-orbit configuration includes (i) actuating the HDA from the fully engaged configuration to a partially engaged configuration; (ii) grasping and moving the first reflector, with the manipulator, a distance in the first direction; and (iii) moving the first reflector from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration.

A tension stiffened and tendon actuated manipulator is provided performing robotic-like movements when acquiring a payload. The manipulator design can be adapted for use in-space, lunar or other planetary installations as it is readily configurable for acquiring and precisely manipulating a payload in both a zero-g environment and in an environment with a gravity field. The manipulator includes a plurality of link arms, a hinge connecting adjacent link arms together to allow the adjacent link arms to rotate relative to each other and a cable actuation and tensioning system provided between adjacent link arms. The cable actuation and tensioning system includes a spreader arm and a plurality of driven and non-driven elements attached to the link arms and the spreader arm. At least one cable is routed around the driven and non-driven elements for actuating the hinge.

The present disclosure relates to a robotically controlled satellite refueling tool and associated robotically controlled support and site preparation tools which facilitates on-orbit refueling by teleoperation of fill/drain valves of various designs and dimensions on satellites not originally prepared for on-orbit servicing, through the installation of quick connect safety valves, using vision-based feedback as well as feedback from sensors embedded in the refueling tool to operate a suite of adaptable and adjustable mechanisms. The refueling tool has an open architecture to allow a refueling tool vision system to see the fill/drain valve and the section of the refueling tool that is engaged with the fill/drain valve. The support tools include a blanket cutter tool, a blanket handler tool, a wire cutter tool, a gripper tool, and the site preparation tools include a B-nut removal tool and a crush seal removal tool. Each of these tools includes a common base structure which is interfaced to the end effector of the robotic arm for transmitting rotation and torque to the various tools.

A spacecraft bus system described herein includes a propulsion assembly, a top plate assembly, and a bottom plate assembly. Each one of the propulsion assembly, the top plate assembly, and the bottom plate assembly is configured to be separately assembled and tested for spaceworthiness. Also described herein is a propulsion assembly for use with a spacecraft. The propulsion assembly includes a propellant tank containing propellant therein, at least one thruster, and a frame configured for supporting the propellant tank and the at least one thruster thereon. The propulsion assembly, as an individual module, is configured to be assembled and subjected to testing related to spaceworthiness. Additionally, the frame may be further configured for attachment to other components of the spacecraft, after being assembled and subjected to testing, without modification to the propulsion assembly or the other components of the spacecraft.