Abstract: 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.

Abstract: A system includes at least two spacecraft disposed together for launch by a launch vehicle. In a launch configuration, a second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement (ISCA). The system is configured to be deployed following injection into a first orbit by the launch vehicle, while the second spacecraft is mechanically coupled with the first spacecraft. The first spacecraft includes a thruster configured to execute an orbit transfer maneuver from the first orbit to a second orbit, the thruster delivering thrust along a thrust vector. In an on-orbit configuration, the ISCA is switchable between a first mode that permits rotation of the first spacecraft with respect to the second spacecraft about a first axis of rotation that is approximately parallel with the thrust vector and a second mode that prevents rotation of the first spacecraft with respect to the second spacecraft.

Abstract: Techniques for two-axis articulation of a deployed spacecraft solar array are disclosed. In one aspect, an arrangement mechanically coupling a solar array with a sidewall of a body of a spacecraft includes a proximal appendage, a distal appendage rotatably coupled with the proximal appendage by way of a hinge, and a closed cable loop (CCL) system coupled with the proximal appendage and the distal appendage. In an on-orbit configuration, a long axis of the proximal appendage defines an ? axis that is substantially orthogonal to the sidewall. The hinge includes CCL disengagement mechanism configured to de-couple the CCL system from the proximal appendage and the distal appendage and a rotation driving mechanism configured to cause the distal appendage to rotate about a ? axis when the proximal appendage is in the on-orbit configuration, the ? axis being not aligned with the ? axis.

Abstract: An incremental deployment device is provided. The incremental deployment device may include a first member with a slotted track having alternating deployment and braking segments, as well as a second member that is movably coupled with the first member and that includes a cam follower that is configured to travel within the slotted track. The deployment segments may be configured to allow relative movement between the first member and the second member with little resistance, whereas the braking segments may be configured to permit relative movement between the first member and the second member with much greater resistance or to not permit any relative movement between the first member and the second member at all. Thus, the first member and the second member may be allowed to accelerate relative to one another within the deployment segments, and are decelerated within the braking segments.

Abstract: 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.

Abstract: A release device having a multi-segment split spool with a central bore adapted to axially restrain a tensioned member. A tensioned tape is overlappingly wound around the spool segments thereby preventing radial movement of the spool segments. The overlapping winding allows for a low profile housing for the-release device. The multiple segments require less radial motion for release of the tensioned member.

Abstract: Single or multi-axis positioning mechanisms are provided that include a caging mechanism that may be actuated without requiring axial displacement of rotational components of the positioning mechanisms. In some multi-axis positioning mechanism implementations, each rotational axis may have an associated caging mechanism that is transitioned between a caged and uncaged state using a common release device. In some implementations, the release device may be a single-use device. In other implementations, the release device may be capable of re-caging the positioning mechanism after uncaging the positioning mechanism.

Abstract: Latching or locking deployment hinges are provided that include a latch mechanism, a spring-loaded tensioning device, and a trigger mechanism. The trigger mechanism and the spring-loaded tensioning device are configured to transfer the compressed spring load in the spring-loaded tensioning device to the latch mechanism once the hinge has closed sufficiently far enough to latch together, thus inducing a pre-load through the latch mechanism that eliminates gapping in the hinge interface. The hinges may be sprung or actuated using a powered drive mechanism.

Abstract: Latching or locking deployment hinges are provided that include a latch mechanism, a spring-loaded tensioning device, and a trigger mechanism. The trigger mechanism and the spring-loaded tensioning device are configured to transfer the compressed spring load in the spring-loaded tensioning device to the latch mechanism once the hinge has closed sufficiently far enough to latch together, thus inducing a pre-load through the latch mechanism that eliminates gapping in the hinge interface. The hinges may be sprung or actuated using a powered drive mechanism.

Abstract: An incremental deployment device is provided. The incremental deployment device may include a first member with a slotted track having alternating deployment and braking segments, as well as a second member that is movably coupled with the first member and that includes a cam follower that is configured to travel within the slotted track. The deployment segments may be configured to allow relative movement between the first member and the second member with little resistance, whereas the braking segments may be configured to permit relative movement between the first member and the second member with much greater resistance or to not permit any relative movement between the first member and the second member at all. Thus, the first member and the second member may be allowed to accelerate relative to one another within the deployment segments, and are decelerated within the braking segments.

Abstract: A high capacity satellite having a launch configuration in which one or more antenna reflectors may be stored forward of a forward surface of the spacecraft and an on-orbit configuration in which a reflector boom may be rotated to displace the one or more antenna reflectors a substantial distance from the main body in the yaw axis direction and in a direction orthogonal to the yaw axis direction.

Abstract: A preload reducing fastener adapted to be fastened into a system in which includes a release system. The fastener may have an integral collar which is adapted to change shape, as in the case of a shape memory alloy. The application of heat to fastener may deform the collar such that the fastener may move axially in the load direction, thus reducing the preload previously held by the fastener. A preload reducing device including a preload reducing fastener may include an outer case adapted to center and capture a preload reducing fastener. The case may center the fastener in a desired location in a preloaded system, and may also capture the fastener after release of the system.

Abstract: A high capacity satellite having a launch configuration in which one or more antenna reflectors may be stored forward of a forward surface of the spacecraft and an on-orbit configuration in which a reflector boom may be extended forward and rotated to place the one or more antenna reflectors outboard of the spacecraft main body and further forward of the forward surface of the spacecraft.

Abstract: Various roll-up contamination covers for shielding sensors and other sensitive equipment from particulate contamination are provided. Such covers may be provided by using a sheet of flexible material that has an elastically stable state of a spiral torsion spring, e.g., a clock spring shape. The spiral torsion spring may be anchored to a frame along one end that is substantially parallel to the center axis of the spiral torsion spring, and may be unrolled into a substantially unrolled state so as to cover an aperture in the frame. A movable release mechanism may be engaged with the unrolled end of the spiral torsion spring to prevent the spiral torsion spring from returning to the elastically stable state. When the release mechanism is moved to release the unrolled end of the spiral torsion spring, the spiral torsion spring may roll back into the elastically stable state and uncover the aperture.

Abstract: A deployable solar panel array featuring in-line solar panels and side solar panels, where the side solar panels are configured to deploy in a staggered fashion after deployment of the in-line panels. A passive deployment mechanism governs the deployment sequence.

Abstract: A hold-down mechanism for a steerable spacecraft appendage, the appendage being coupled to a spacecraft structure with a positioning mechanism, is configured (1) to support, when in a hold-down mode, the appendage at a first position substantially fixed with respect to the spacecraft; (ii) release, upon receipt of a signal, the appendage, thereby enabling the positioning mechanism to steer the spacecraft appendage; and (iii) retract from the appendage without regard to whether the appendage remains substantially in the first position. The first position may result in the spacecraft appendage being aligned in a nominal operating location and orientation, so that the antenna positioning mechanism is not required to initially deploy or otherwise reorient the appendage.

Abstract: Extensible solar arrays configured to support one or more rollable solar panel units and that feature yoke segments and array segments that are configured to be stowed with their long axes substantially parallel to a spacecraft's roll axis. The yoke segments and array segments may be transitioned to a deployed configuration where the yoke segments are substantially perpendicular to the position the yoke segments were in in the stowed configuration, and the array segments are substantially perpendicular to the yoke segments. Some implementations of the extensible solar arrays may also include a rigid solar panel supported by one of the yoke segments.

Abstract: Latching or locking deployment hinges are provided that include a shape-memory alloy (SMA) pre-load device configured to induce a pre-load across a contact interface of the latching hinge in a direction substantially perpendicular to the hinge pivot axis when the latching hinge is in a closed condition. The hinges may be sprung or actuated using a powered drive mechanism. Some implementations may feature a sprung latch/hook that is tensioned using the SMA pre-load device. Some other implementations may feature a multi-bar linkage that is tensioned using the SMA pre-load device.

Abstract: A release device having a multi-segment split spool with a central bore adapted to axially restrain a tensioned member. A tensioned tape is overlappingly wound around the spool segments thereby preventing radial movement of the spool segments. The overlapping winding allows for a low profile housing for the-release device. The multiple segments require less radial motion for release of the tensioned member.

Abstract: A release device having a multi-segment split spool with a central bore adapted to axially restrain a tensioned member. A tensioned tape is overlappingly wound around the spool segments thereby preventing radial movement of the spool segments. The overlapping winding allows for a low profile housing for the release device. The multiple segments require less radial motion for release of the tensioned member.