Abstract: A battery charging system includes a charging rack comprising multiple receptacle, multiple battery assemblies. Each of the battery assemblies includes a housing having a handle, rechargeable battery cells disposed within the housing, and a mating feature protruding away from the housing, wherein the mating feature is configured to selectively connect the battery assembly with the receptacle of the charging rack and includes multiple ports electrically connected to the battery cells and configured receive power from the charging rack to charge the battery cells, and wherein the handle comprises a release button configured to selectively disengage the battery assembly from the receptacle of the charging rack.

Abstract: Telescoping boom systems, devices, and methods are provided in accordance with various embodiments. For example, some embodiments include zero dead band telescoping boom systems, devices, and methods. Embodiments in general include hard stop preloading mechanisms for telescoping booms with multiple tube segments. Some embodiments provide components that facilitate the deployment sequencing of the multiple tube segments along with facilitating preloading of the multiple tube segments of a telescoping boom. The tools and techniques provided may be integrated into the multiple tube segments rather than being provided as a separate system. Some embodiments allow for precise deployment of the multiple tube segments of the telescoping boom systems, devices, and methods.

Abstract: An explosive detonating system comprises connectable components to connect/disconnect a pathway that ignites an explosion. A firing actuator activates primers. An adapter connects the firing actuator to shock tube and channels the ignition force from the primers into the shock tube. A cap box houses blasting caps coupled to the end of the shock tube. A priming well is coupled to the cap box/blasting caps and detonating cord. When the firing actuator is initiated, the percussion caps ignite, sending an explosive jet of gas into the shock tube, which ignites an explosive liner. An explosive wave travels through the shock tube and activates the blasting caps, which activate the detonating cord in the priming well. The explosive is placed in a location to provide a desired explosive effect. For example, the system may be employed as a system to breach into structures, remove obstacles and/or barriers, or other applications.

Abstract: An explosive detonating system comprises connectable components to connect/disconnect a pathway that ignites an explosion. A firing actuator activates primers. An adapter connects the firing actuator to shock tube and channels the ignition force from the primers into the shock tube. A cap box houses blasting caps coupled to the end of the shock tube. A priming well is coupled to the cap box/blasting caps and detonating cord. When the firing actuator is initiated, the percussion caps ignite, sending an explosive jet of gas into the shock tube, which ignites an explosive liner. An explosive wave travels through the shock tube and activates the blasting caps, which activate the detonating cord in the priming well. The explosive is placed in a location to provide a desired explosive effect. For example, the system may be employed as a system to breach into structures, remove obstacles and/or barriers, or other applications.

Abstract: Deployable devices, systems, and methods are provided. Some embodiments include a system that may include: multiple frames configured to support multiple elements; multiple longerons; multiple diagonals coupled with the multiple longerons; and multiple battens. One or more battens may be coupled with at least one or more longerons and one or more frames such that the respective batten is offset at least along a length of the respective longeron with respect to at least a hinge point between the respective longeron and another longeron from the multiple longerons or along a length of the respective frame with respect to a hinge point between the respective frame and another frame from the multiple frames. Some embodiments include a method for ensuring synchronous deployment of a system that may include orienting a hinge axis coupled with at least one longeron substantially perpendicular to a hinge axis coupled with two or more frames.

Abstract: A tape drive comprises a roll of a tape that can be extended from a rolled state to an extended state. The tape includes a rigid material that supports the tape and a pliable material disposed at least partially on one side of the tape. A compression roller is disposed on a side of the tape and is biased toward the tape. A drive roller is disposed on the other side of the tape. The drive roller comprises an uneven surface that mechanically engages the pliable material of the tape, without protruding through the tape, as a result of the bias of the compression roller forcing the tape toward the drive roller. A motor turns the drive roller to extend the tape from the roll as the protrusions of the uneven surface of the drive roller mechanically engage the pliable material of the tape as the drive roller turns.

Abstract: Distributed flexible membrane backing systems, devices, and methods are provided in accordance with various embodiments. Some embodiments utilize distributed backing structures in lieu of a central boom technology or rigid panel structure. Disaggregating the structural component generally allows the structure mass and volume to be distributed more efficiently across the backside of the flexible membrane, such as a photovoltaic membrane. This distribution generally enables an increased number of structural support points (within the deployed flexible membrane), which may increase the performance of the flexible membrane. Some embodiments interface the structure and the membranes throughout the entire surface of the deployed membrane. The distribution of structure may allow more efficient stowage of the deployable structure.

Abstract: An explosive detonating system comprises connectable components to connect/disconnect a pathway that ignites an explosion. A firing actuator activates primers (percussion caps). An adapter connects the firing actuator to shock tube and channels the ignition force into the shock tube. A cap box houses blasting caps coupled to the end of the shock tube. A priming well is coupled to the cap box/blasting caps and the detonating cord. When the firing actuator is initiated, the percussion caps ignite, sending an explosive wave into the adapter, which channels the wave into the shock tube and ignites the shock tube. The explosive wave travels through the shock tube and activates the blasting caps, which activate the detonating cord in the priming well. The explosive is placed in a location to provide a desired explosive effect. For example, the system may be employed as a system to breach structures or other applications.

Abstract: Telescoping boom systems, devices, and methods are provided in accordance with various embodiments. For example, some embodiments include zero dead band telescoping boom systems, devices, and methods. Embodiments in general include hard stop preloading mechanisms for telescoping booms with multiple tube segments. Some embodiments provide components that facilitate the deployment sequencing of the multiple tube segments along with facilitating preloading of the multiple tube segments of a telescoping boom. The tools and techniques provided may be integrated into the multiple tube segments rather than being provided as a separate system. Some embodiments allow for precise deployment of the multiple tube segments of the telescoping boom systems, devices, and methods.

Abstract: A panel structure for use in a deployable and cantilevered solar array structure is provided. A panel includes first and second planar panel sections and an intermediate panel section connecting the first and second sections. The planar panel sections are capable of being situated with respect to one another so as to have a V-tent-like shape when the panel is in a deployed state and to be coplanar when the panel is in a stowed state. When in the V-tent-like shape, the intermediate section of the panel extends in a straight line that is collinear or parallel to the longitudinal axis of the cantilevered solar array structure when deployed. The V-tent-like shape produces A panel structure that has a relatively high moment of inertia, is stiff, and can provide a large area for supporting solar cells.

Abstract: An explosive detonating system comprises connectable components to connect/disconnect a pathway that ignites an explosion. A firing actuator activates primers. An adapter connects the firing actuator to shock tube and channels the ignition force from the primers into the shock tube. A cap box houses blasting caps coupled to the end of the shock tube. A priming well is coupled to the cap box/blasting caps and detonating cord. When the firing actuator is initiated, the percussion caps ignite, sending an explosive jet of gas into the shock tube, which ignites an explosive liner. An explosive wave travels through the shock tube and activates the blasting caps, which activate the detonating cord in the priming well. The explosive is placed in a location to provide a desired explosive effect. For example, the system may be employed as a system to breach into structures, remove obstacles and/or barriers, or other applications.

Abstract: A solar panel array assembly is provided that is adapted to transition between a stowed condition in which at least two solar panels are stacked and a deployed condition in which the solar panels are unstacked relative to the stowed condition and that exhibits a low-profile when in the stowed condition. In one embodiment, the assembly includes at least two solar panels, a flexible hinge connecting and extending between the panels that allows relative rotation of the panels to one another, a torsion bar for providing the force for causing the rotation of the panels for the transition between the stowed and deployed conditions, and a truss structure that transitions from a relatively flat, inoperative state when the panels are stowed to an operative state for use with deployed panels.

Abstract: An explosive detonating system comprises connectable components to connect/disconnect a pathway that ignites an explosion. A firing actuator activates primers (percussion caps). An adapter connects the firing actuator to shock tube and channels the ignition force into the shock tube. A cap box houses blasting caps coupled to the end of the shock tube. A priming well is coupled to the cap box/blasting caps and the detonating cord. When the firing actuator is initiated, the percussion caps ignite, sending an explosive wave into the adapter, which channels the wave into the shock tube and ignites the shock tube. The explosive wave travels through the shock tube and activates the blasting caps, which activate the detonating cord in the priming well. The explosive is placed in a location to provide a desired explosive effect. For example, the system may be employed as a system to breach structures or other applications.

Abstract: This description relates to an extensible space-based infrastructure platform having modules that can be launched in a stowed configuration, placed in orbit, and then deployed to extend the modules away from each other for an integrated infrastructure platform configuration. This infrastructure platform provides power, timing, communications, data management, attitude control, and other vital and non-vital services to docked payloads. Multiple payloads can be launched into orbit, maneuvered into position, and docked with the space-based services platform. Each docked payload utilizes the infrastructure of the space-based services platform and its interconnected network of docked payloads. Multiple space-based platforms can be docked together to provide a larger space-based infrastructure platform with a broader array of services available to all docked payloads and users.

Abstract: A tape drive comprises a roll of a tape that can be extended from a rolled state to an extended state. The tape includes a rigid material that supports the tape and a pliable material disposed at least partially on one side of the tape. A compression roller is disposed on a side of the tape and is biased toward the tape. A drive roller is disposed on the other side of the tape. The drive roller comprises an uneven surface that mechanically engages the pliable material of the tape, without protruding through the tape, as a result of the bias of the compression roller forcing the tape toward the drive roller. A motor turns the drive roller to extend the tape from the roll as the protrusions of the uneven surface of the drive roller mechanically engage the pliable material of the tape as the drive roller turns.

Abstract: A deployable thin membrane apparatus for use with a spacecraft is provided. The apparatus includes a flexible membrane structure and a deployment mechanism for transitioning the membrane structure from an undeployed state towards a deployed state in which the membrane can perform a function needed by a spacecraft. In one embodiment, the deployment mechanism includes a plurality of pantographs that each engage the membrane structure, a rotatable disk structure that engages and coordinates the transition of the pantographs from an undeployed state towards a deployed state, and a spring system for providing energy that is used to rotate the disk structure.

Abstract: One embodiment of the invention is directed to an array of articulable masts for use with an array of directional elements. In a particular embodiment, each of the masts employs: (a) a linked structure with a plurality of pivotally connected links that includes a fixed link which is attached to a base and a free link which is adapted to support a directional antenna and (b) a wire structure that engages the linked structure. The array also includes a rotor structure that engages the corresponding wire structure associated with each of the linked structures. In operation, rotation of the rotor structure causes the free ends of the linked structures to move such that the boresights of any attached directional elements are moved at the substantially the same time and in the same way and so that each boresight is collinear or parallel to a radius of a spherical section.

Abstract: A solar array including a solar array assembly, hub assembly, and wing assembly.

Abstract: A thin membrane structure for stabilizing a spacecraft is provided. The spacecraft has a first end and a second end. The spacecraft has a center of pressure and a center of gravity. The thin membrane structure comprises a module secured to the spacecraft and a structure having a polygonal base and a plurality of triangular side panels meeting in a point opposite the base with the point secured to the module. Prior to deployment, the structure is entirely contained within the module. Subsequent to deployment, the structure expands to a pyramidal shape with the distance between the center of pressure and the center of gravity increasing to a length greater than approximately one-half the length of the spacecraft.

Abstract: A Deployable Morphing Modular Solar Array (DMMSA) for deploying Deployable Morphing Modular Solar Power Assemblies (DMMSPAs) from a spacecraft is provided. The DMMSA comprises a Root Staging and Deployment Mechanism (RSDM) mounted to a spacecraft. A plurality of petal assemblies are rotatably secured to the RSDM with each petal assembly having at least DMMSPA secured thereon and each DMMSPA having a slight V-configuration. A launch restraint assembly stacks and sandwiches the petal assemblies prior to deployment with the launch restraint assembly pre-loading each petal assembly's one or more DMMSPA into a substantially flat configuration. Upon release of the launch restraint assembly, the stacked and sandwiched petal assemblies rotate relative to the spacecraft and each petal assemblies DMMSPA elastically morphs from the substantially flat configuration into the slight V-configuration.