Northrop Grumman Systems Corporation

Astro Aerospace Corporation

Trw-astro Aerospace Corporation

Geoffrey William Marks

David Rohweller

Mark W Thomson

John M Hedgepeth

Mehran Mobrem

David J Rohweller

Daniel J Ochoa

Christian J Pedersen

James Trevor Renshall

James T Renshall

A telescopic boom and reflector assembly for a spacecraft that includes a telescopic boom having a plurality of boom sections that are nested together within a prime batten or where the prime batten is attached to an outermost section of the boom when the boom is in a stowed position, where an innermost and smallest diameter section of the boom is secured to the spacecraft to facilitate testing and integration of the boom and reflector as a unitized assembly. The assembly also includes a reflector having a truss structure configured to allow the reflector to be collapsed into a stowed configuration, where the reflector is mounted to the prime batten. The assembly is configured to be deployed from the spacecraft by releasing the boom in a telescopic manner where the boom sections increase in diameter from the spacecraft outward when the boom is deployed.

Integrated telescopic boom and large deployable reflector

A solar panel assembly for a spacecraft includes a bracket and first and second booms each having a first end secured to the bracket and a second end extending away from the bracket. Each boom is formed from a plurality of tubes that telescope between a stowed condition nested within one another and a deployed condition aligned end-to-end with one another. A solar panel is secured to the first and second booms for receiving solar energy and converting the solar energy to electrical power. The solar panel has a stowed condition collapsed between the first and second booms and a deployed condition extending in a plane between the first and second booms.

Deployable solar panel array for spacecraft

A reflector assembly includes a frame centered about a longitudinal axis and having a first height along the axis. A curved body extends from the frame and has a second height along the longitudinal axis could be greater than the first height. A stretchable membrane has an electromagnetically reflective surface and is secured to the curved body.

Mesh reflector with truss structure

A helical antenna operable to be stowed on and deployed from a cubesat. The antenna includes two helical elements wound in opposite directions and defining an antenna column, where one of the helical elements is a conductive antenna element. The antenna also includes a plurality of circumferentially disposed vertical stiffeners extending along a length of the column and being coupled to the helical elements at each location where the vertical stiffeners and the helical elements cross. The helical elements and the vertical stiffeners are formed of a flexible material, such as a fiber glass, so that the antenna can be collapsed and stowed into a relatively small space. To position the antenna in the stowed configuration, the vertical stiffeners are folded on each other in a radial direction, and then the folded antenna is rolled in an axial direction from one end of the column to the other end.

Deployable helical antenna for nano-satellites

An embodiment of the present method may comprise: heating up at least one structural element beyond a change state temperature thereof; changing the configuration of the structural element from an extended configuration to a reduced size configuration; cooling the structural element to below the change state temperature thereof; covering the structural element with a thermal protection device; removing the thermal protection device to expose the structural element to heat radiation; and heating, via the heat radiation, at least a portion of the structural element to thereby cause the structural element to change from the reduced size configuration to the extended configuration. In one embodiment each of the structural elements is formed from a thin elastic memory composite material.

Solar heat powered deployable structure

A spacecraft, such as a satellite, includes a panel array comprised of a plurality of panels that are stacked together and secured to the side of the satellite during launch. At least one shear tie device is configured to couple the panels together in shear to increase the resistance to deformation of the stack of panels. The shear tie device preferably comprises a male member that mates with a female member. A plurality of fingers secure the male member within the female member during launch. Upon reaching orbit, a bladder is inflated which deforms the fingers and releases the male member from engagement with the female member.

Shear tie device

A reflector assembly for use in antennas or solar collectors in which light weight and high reflector surface shape accuracy are essential for maintaining desired RF or light reflection requirements. The assembly is provided with a rigid, deployable outer support rim and at least one curved frame net supported by the outer rim. The frame net may be formed of a network of intersecting bands extending across the surface. A reflective material is placed against the frame net. A load is applied to the frame net to form a concave surface. The assembly is collapsible for convenient delivery into space prior to deployment.

Light-weight reflector for concentrating radiation

A low concentration solar array for spacecraft and other uses which has a series of solar panels which can be deployed from a folded stowed configuration to a planar configuration. When the solar panels are stowed, the padding of reflector panels cushions and protects the solar panels from the stresses and vibrations of launch and space flight. Once the solar panels are extended into a deployed planar configuration, the reflector panels are raised to concentrate sunlight upon the solar panels. These reflector panels are constructed from rigid honeycomb substrates and therefore are the active structural members of the solar array, providing the structural rigidity for the solar array.

Growing community of inventors

Santa Barbara, CA, United States of America

Geoffrey William Marks