Alliedsignal Inc.

Trw Limited

Astro Aerospace Corporation

Teledesic LLC

Trw-astro Aerospace Corporation

Mark W Thomson

Dan S Matulich

Douglas Gene Lockie

L Dwight Gilger

Terence P Emerson

Geoffrey William Marks

John M Hedgepeth

Steve Davis

John C Gereau

David J Rohweller

Peter B Laraway

Daniel S Chae

A hinge system for deploying panels or other structures from a satellite or spacecraft has at least two configurations. The panels are held in a substantially stacked disposition in the stowed configuration by the hinge system which connects to each panel and includes an intermediate arm sized to span any necessary space between the two panels in the stowed configuration. A deployment cable is attached to one of the panels and threaded over a series of pulleys disposed on the hinge system and onto a spool in the other panel. When the spool is driven to wind the deployment cable onto it, the tension in the cable pulls on the pulleys, causing the hinge to unfold and then slide into a housing located on one of the panels. This deployed configuration allows the panels to be held aligned and directly adjacent to one another by the tension of the deployment cable.

Pulley actuated translational hinge system

A spacecraft, such as a satellite, comprises a panel array including a plurality of panels that are rotatably coupled to one another. The panel array is movable between a folded state and an extended state. In the folded state, the panels are stacked atop one another. In the extended state, the panels are positioned such that active surfaces of the panels are aligned within a common plane. A plurality of hinge mechanisms preferably rotatably couple the panels to one another. The hinge mechanisms are configured to move the panel array from the folded state to the extended state without interfering with the active surfaces of the panels when the panel array is extended.

Spacecraft with deployable panel array

A perimeter truss structure (,) that may be used, for example, to support an RF reflector may include multiple deployed bays (,) arranged in a ring. Each deployed bay (,) includes a first upper horizontal support member (,) attached to a first vertical support member (,) and collapsible on a first joint (,) translating on a second vertical support member (,), as well as a first lower horizontal support member (,) attached to the second vertical support member (,) and collapsible on a second joint (,) translating on the first vertical support member (,). The first and second vertical support members (,) define a ring inside (,) and a ring outside (,). The first upper horizontal support member (,) is disposed on one ring side (e.g., the outside), while the first lower horizontal support member (,) is disposed on the opposite ring side. The horizontal support members (,) (which are oriented vertically in the stowed position) are thus non-interfering in the stowed position.

Micro fold reflector

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

An advanced active element phased array satellite antenna is disclosed. Incorporating these novel antenna systems on a constellation of low Earth orbit spacecraft, allows phone customers worldwide to communicate through a system whose switching intelligence resides on orbit, bypassing traditional land-based networks, and offering a revolutionary expansion of communications potential. The present invention utilizes electronic beam steering is utilized to provide extremely high gain signals. In one preferred embodiment, a satellite (S) includes an Earth-facing array (10) of hexagonal antenna facets (12), mated together along their sides to form a slightly flattened, hemispherical shell. The antenna array (10) is connected to two rectilinear, unfurled, solar panels (P). The antennas (10) transmit and receive signals from terrestrial units located within the footprints (14) of the beams (11). Another embodiment (34) uses deployable, folding panels (41) which maximize panel surface area for a given weight and launch vehicle container volume. The panels (41) are stacked upon a central plate (39) along the depth axis of the container in accordion fold layers and are separately deployed radially from the center (C) of the central plate (39). The contour of the deployed panels permit the antenna beam footprints (14) to cover the desired area.

Spacecraft antennas and beam steering methods for satellite

An apparatus and method of providing an Environmental Control System (ECS) for use in conjunction with a turbine engine power plant, to deliver a flow of purified, conditioned air to an enclosed space, such as an aircraft cabin. The ECS includes contaminate neutralization means to neutralize airborne chemical and biological agents.

Contaminate neutralization system for use with an advanced environmental

A deployable and retractable, telescoping style mast assembly and method employs a plurality of tubular sections of differing diameters. The tubular sections are nested one-in-another and are slidable with respect to each other, in a telescoping manner, to provide a deployable/retractable telescoping mast assembly. Retractable pins are provided to retractably extend from a collar coupled to at least one of the tube sections. In their extended state, the retractable pins are adapted to extend through apertures provided in an adjacent tube section. The retractable pins are provided with a head at one end thereof. The head of each pin is adapted to be engaged by a guide coupled to a third tube section upon the third tube section being in a collapsed state. Upon engagement with the pin head, the guide operates to pull the pin into a retracted state so as to retract the pin out of the pin receiving aperture.

Deployable/retractable telescoping mast assembly and method

An air cycle machine for use within an Environmental Control System (ECS) operating in conjunction with a turbine engine. The air cycle machine includes two turbines commonly mounted on a shaft with a compressor. The air cycle machine is designed to directly receive high temperature, high pressure bleed air from the turbine engine and maximize energy extraction and utilization of the bleed air.

ECS with advanced air cycle machine

An advanced Environmental Control System (ECS) for use in conjunction with a turbine engine to provide conditioned, pressurized air to an enclosed space such as an aircraft cabin, as well as cooling capacity for the aircraft avionics. The ECS features a dual turbine air cycle machine to minimize the amount of bleed air or power required from the turbine engine.

Growing community of inventors

Ventura, CA, United States of America

Mark W Thomson