Abstract: Provided herein are systems and methods for minimizing jitter. A method for minimizing jitter for at least one sensitive component on a spacecraft includes receiving a rotary actuator speed command indicating a rotary actuator speed for a stepper motor on the spacecraft, setting a stepping mode of the stepper motor to one of a first stepping mode and second stepping mode based on a preconfigured data structure which encodes a corresponding stepping mode for the rotary actuator speed based on a pre-determined jitter-sensitive frequency band, wherein the first stepping mode and the second stepping mode each maintain harmonics of the spacecraft outside of the jitter-sensitive frequency band. A system includes a stepper motor, an onboard processing unit to generate rotary actuator speed commands, and a mechanism control electronics (MCE) subsystem, wherein the MCE subsystem controls a stepping mode of the stepper motor based on a rotary actuator speed command.

Abstract: A system for an open-back spacecraft platform structure, a method of assembling a primary platform structure of an open-back spacecraft platform, and a method of assembling a system including an open-back spacecraft platform structure are provided. The system includes the spacecraft platform structure including a circular or polygonal primary support structure including one or more individual modules, each individual module including sub-modules disposed within or on the individual module, each individual module being all or part of a side of the circular or polygonal primary support structure and defining an open back of the spacecraft platform structure, a secondary support structure including a first frame including at least four first frame members, each first frame member connected to the primary support structure via a first fitting and connected to the other frame members, and one or more module connectors for bearing and/or transmitting loads of the open-back spacecraft platform structure.

Abstract: Provided is a bracket for use in a hold and release mechanism (“HRM”) system for releasably holding a deployable payload in a stowed configuration. The bracket includes a conical portion for nesting with a conical portion of a second bracket for forming a first separation interface therebetween. The conical portion of the bracket is configured as a cone and the conical portion of the second bracket is configured as a cup. The bracket includes one or more bracket connectors for connecting the bracket to the deployable payload or a platform on which the deployable payload is stowed. The second bracket connects to whichever of the deployable payload or the platform the first bracket is not connected.

Abstract: A system and method for robotic interfacing is provided herein. The robotic system includes a payload interface comprising a platform side and a receptacle side. The platform side is robotically maneuverable, and adaptable to carry a payload. The receptacle side is affixed to a host structure. The payload interface is autonomously removed and replaced by a robotic manipulator. The robotic manipulator includes an end effector having a grapple mechanism that connects with a grapple fixture of the platform side.

Abstract: A system and method for holding and releasing a deployable component is provided. The system includes a plurality of latching mechanisms each including a first component attached to the deployable component and a second component attached to a spacecraft. In a hold position, each of the first components is held by a respective second component. A pivoting mechanism is disposed on the bottom surface of the deployable component that rotates to move the first component into the hold position. A release mechanism holds the pivoting mechanism in a stowed configuration wherein the pivoting mechanism is rotated in a first direction and the first components are held by the respective second components. Releasing the release mechanism rotates the pivoting mechanism in a second direction and releases the first components from the hold position.

Abstract: An antenna system is provided. The antenna system includes a base structure, a transmission line, a ground plane, and a backfire antenna element. The transmission line extends from the base structure and is coupled to the base structure at a first end of the transmission line. The ground plane is coupled to the transmission line at a second end of the transmission line. The backfire antenna element extends between the ground plane and the base structure. The backfire antenna element is coupled to the second end of the TEM line.

Abstract: Provided are systems and methods for a radiating element assembly, for an antenna. The radiating element assembly includes a radiating element for emitting and/or receiving electromagnetic waves and a radiating element support system for physically supporting the radiating element when in operation. The radiating element support system includes a plurality of dielectric support threads, where the plurality of dielectric support threads act as non-linear structural links which interconnect the radiating element to constrain the radiating element in one or more of an axial direction, radial direction, and torsional direction, and the plurality of dielectric support threads are taut with near zero tension, and at least one support wherein the plurality of threads interconnect the radiating element with the at least one support to constrain the radiating element in the axial and/or radial and/or torsional directions. The radiating element support system may be used to constrain other satellite payloads.

Abstract: Provided herein is a deployable antenna assembly, a method of deploying an antenna, and systems and methods for sequentially deploying an extendable structure. The deployable antenna assembly includes an extendable pillar configured to extend in an axial direction along a deployment axis of the deployable antenna assembly to deploy an antenna. The extendable pillar includes at least one extendable element configured to convert between a stowed configuration and a deployed configuration where the deployed configuration is longer in the axial direction than the stowed configuration. The extendable pillar also includes a launcher configured to initiate conversion of the plurality of extendable elements from the stowed configuration to the deployed configuration, thereby extending the extendable pillar and deploying the antenna.

Abstract: Provided herein is a deployable antenna assembly, a method of deploying an antenna, and systems and methods for sequentially deploying an extendable structure. The deployable antenna assembly includes an extendable pillar configured to extend in an axial direction along a deployment axis of the deployable antenna assembly to deploy an antenna. The extendable pillar includes at least one extendable element configured to convert between a stowed configuration and a deployed configuration where the deployed configuration is longer in the axial direction than the stowed configuration. The extendable pillar also includes a launcher configured to initiate conversion of the plurality of extendable elements from the stowed configuration to the deployed configuration, thereby extending the extendable pillar and deploying the antenna.

Abstract: Provided herein is a deployable antenna assembly, a method of deploying an antenna, and systems and methods for sequentially deploying an extendable structure. The deployable antenna assembly includes an extendable pillar configured to extend in an axial direction along a deployment axis of the deployable antenna assembly to deploy an antenna. The extendable pillar includes at least one extendable element configured to convert between a stowed configuration and a deployed configuration where the deployed configuration is longer in the axial direction than the stowed configuration. The extendable pillar also includes a launcher configured to initiate conversion of the plurality of extendable elements from the stowed configuration to the deployed configuration, thereby extending the extendable pillar and deploying the antenna.

Abstract: A deployable aperture reflector for use in antennas to reflect an RF electromagnetic signal of a predetermined signal frequency band includes a deployable aperture structure deployable between a stowed aperture configuration and a deployed aperture configuration. The aperture structure includes a plurality of rigid members connecting to one another to support an RF reflective assembly when in the deployed aperture configuration. The RF reflective assembly includes a plurality of faceted cells adjacent one another that form an assembly mechanical shape approximating an optimal desired electrical surface shape. Each faceted cell includes at least one layer carrying RF resonant elements thereon that electrically compensate a difference between the assembly mechanical shape and the optimal desired electrical surface shape.

Abstract: A node and a strut connect to one another to form a spaceframe structure, in which the strut has a strut bending stiffness and defines a strut axis. The node has a main body and an arm connecting to and extending from the main body along the strut axis and toward the strut. The arm has a node end attaching to the main body, a strut end connecting to the strut and a midsection extending there between. The midsection includes a neck portion having a neck bending stiffness being less than 20% of the strut bending stiffness. The strut includes primary and secondary sections that axially slidably connect to one another to position them between adjacent respective end-fittings of adjacent nodes, and partially axially overlap and secure to one another and to the end-fittings respectively. At least one of the end-fittings connects to the strut end of the arm.

Abstract: A heat exchanger includes a core portion and at least one substantially straight header plate. The core portion includes a plurality of heat exchanger tubes and fins disposed alternatively.

Abstract: A parasitic element for a helical antenna having at least one helix conductor extending from a secured first longitudinal end of the antenna to an opposite free second longitudinal end thereof around an antenna major-axis. The parasitic element includes an electrically conductive ring located adjacent and spaced apart from the second end in a direction leading away from the first end with the ring axis being parallel to and substantially collinear with the antenna major-axis. The ring has an outer diameter substantially equal to the diameter of the helix conductor at the second end.

Abstract: A parasitic element for a helical antenna having at least one helix conductor extending from a secured first longitudinal end of the antenna to an opposite free second longitudinal end thereof around an antenna major-axis. The parasitic element includes an electrically conductive ring located adjacent and spaced apart from the second end in a direction leading away from the first end with the ring axis being parallel to and substantially collinear with the antenna major-axis. The ring has an outer diameter substantially equal to the diameter of the helix conductor at the second end.

Abstract: A helical antenna has a helix supported by a helix support. The helix support includes at least one piece of flexible sheet having its two surfaces covered with a layer antistatic material. The flexible sheet is curlable into a revolution surface configuration to form a revolution surface-shaped support section for at least partially supporting a portion of the helix component there around. A grounding mechanism electrically grounds the external sheet surface to the helix and the two sheet surfaces to one another when in the revolution surface configuration while a locking mechanism locks the flexible sheet in the revolution surface configuration. The combination of the helix and the flexible support renders the antenna structurally relatively rigid in all directions.

Abstract: A helical antenna has a helix supported by a helix support. The helix support includes at least one piece of flexible sheet having its two surfaces covered with a layer antistatic material. The flexible sheet is curlable into a revolution surface configuration to form a revolution surface-shaped support section for at least partially supporting a portion of the helix component there around. A grounding mechanism electrically grounds the external sheet surface to the helix and the two sheet surfaces to one another when in the revolution surface configuration while a locking mechanism locks the flexible sheet in the revolution surface configuration. The combination of the helix and the flexible support renders the antenna structurally relatively rigid in all directions.