A deployable structure for use in establishing a reflectarray antenna is provided that includes a flexible reflectarray and a deployment structure that includes an endless pantograph for deploying the flexible reflectarray from a folded, undeployed state towards a deployed state in which the flexible reflectarray is substantially planar. In a particular embodiment, the deployment structure includes a plurality of tapes that engage the endless pantograph and are used to establish a positional relationship between the deployed reflectarray and another component of the reflectarray antenna.

An attitude control module is described for providing propellant-free attitude control and momentum desaturation to a spacecraft. The attitude control module includes at least one solar sail comprising a reflective surface for reflecting solar photons; and at least one robotic arm coupled to the at least one solar sail, said at least one robotic arm comprising at least 4 degrees of freedom for positioning and orienting the at least one solar sail relative to the spacecraft. A corresponding method for operating the attitude control module to unload excess momentum from a spacecraft is also described.

The present invention provides a system configured to move a solar wing in three dimensions to increase downforce and solar panel efficiency. This is accomplished through a solar wing, a drive mechanism, a rail mechanism, and a support mechanism. These components work in conjunction to provide a lightweight and compact system configured to move and rotate a solar wing to maximize downforce and increase solar panel efficiency.

A method of space travel using a high acceleration thrust vehicle in combination with a plurality of low acceleration thrust vehicles. A primary spacecraft has a kinetic launcher that is utilized to discharge a plurality of subsidiary spacecraft in order to navigate the primary spacecraft along a flight path. Each of the plurality of subsidiary spacecraft has a propulsion system, allowing each of the plurality of subsidiary spacecraft to navigate to a refueling point. The refueling point for each of the plurality of subsidiary spacecraft may be a central location or a unique position along a subsequent flight path. Each of the plurality of subsequent spacecraft is then reloaded onto the primary spacecraft or loaded onto a subsequent spacecraft for another voyage. The kinetic launcher can be repositioned in order to control the direction of the acceleration experienced by the primary spacecraft.

A method and apparatus for the control of the attitude of earth orbiting satellites and the orbit and attitude control of a novel gravitational wave detection satellite configuration located near the sun-earth Lagrangian points L3, L4 and L5, utilizing the control of solar radiation pressure by the use of electrically controllable variable reflection glass panels to provide the torques and forces needed.

Described herein are systems and methods for attitude determination using infrared Earth horizon sensors (EHSs) with Gaussian response characteristics. Attitude information is acquired by detecting Earth's infrared electromagnetic radiation and, subsequently, determining the region obscured by Earth in the sensors' fields of view to compute a nadir vector estimation in the spacecraft's body frame. The method can be applied when two sensors, each with known and distinct pointing directions, detect the horizon, which is defined as having their fields of view partially obscured by Earth. The method can be implemented compactly to provide high-accuracy attitude within small spacecraft, such as CubeSat-based satellites.

The present invention generally is a system and method for ground, atmospheric and space based solar powered electrical energy generation and transmission of beamed microwave power. Specifically it is a system and method for generating electrical energy from a plurality of photovoltaic cells dispersed on a flexible surface each in close proximity to and functionally connected to microwave generating and transmitting means for controllably forming one or more stronger microwave beams by combining a plurality of much weaker individual microwave beams. The invention can be a microwave beam weapon for detecting and transferring microwave energy to non-cooperative targets or it clear orbital debris by momentum transfer to space object through microwave radiation pressure. Most practically it can provide electric power and microwave beam weapon defense to remote military and civilian facilities, including forward operating bases.

A hold-down release apparatus includes a housing, a reciprocating retention member, a release member, bias member(s), and a fuse wire. The retention member moves between retention and release positions and is biased toward the release position. With the retention member in the release position, the release member can move out of the housing; with the retention member in the retention position, the retention member obstructs the release member from moving out of the housing. The fuse wire obstructs movement of the retention member to the release position and holds the retention member in the retention position against the bias force. With an actuation current flowing through the fuse wire, the bias force breaks the fuse wire, allowing the retention member to move to the release position in response to the bias force, and the release member to move out of the housing.

A spacecraft is provided, which includes one or more of a centrally-oriented core, which includes a computing device. The computing device includes a processor and a memory, coupled to the processor, including computer instructions to control the spacecraft. The spacecraft may also include a power source, coupled to the core, a plurality of struts, each including a root end coupled the core and a distal end, the plurality of struts extending radially from the core. The spacecraft may also include a plurality of blade deployers, coupled to distal ends of the plurality of struts and a plurality of blades, coupled to the plurality of blade deployers and extending radially away from the core and in a common plane with the plurality of struts. The plurality of blades includes material configured to be deflected by solar pressure. Each of the struts is configured to provide damping to a corresponding blade.

Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, a rocket propulsion system is configured to produce thrust for a spacecraft and includes: one or more optical elements configured to receive solar energy. The optical elements include: a first window configured to allow energy to enter the rocket propulsion system and form a concentrated energy beam, and a second window positioned to allow the concentrated energy beam to pass to the heat exchanger. The second window is spaced away from the first window to form a pressurized plenum chamber therebetween. The system further includes: a heat exchanger configured to receive the energy and use it to heat and pressurize a propulsion gas, and a rocket nozzle configured to expel the pressurized propulsion gas.