The Aerospace Corporation

Siegfried W Janson

Henry Helvajian

Jon Victor Osborn

Donald C Mayer

Peter D Fuqua

Chia-Chun Chao

Richard P Welle

Margaret H Abraham

Victor Shiaw-Jong Lin

Edward J Simburger

Jerome Keith Fuller

John Sheldon Serafini

Roger Yang

James E Pollard

Brian E Kirkpatrick

A thermal display module configured to create a thermal pattern discerned by a visually impaired user to determine his or her surroundings. The thermal display module includes a plurality of thermoelectric modules, each of which are configured to cool or heat a pixel plate in close proximity to a user's skin. The cooling or heating of each of the thermoelectric modules create the thermal pattern discernable by the user.

Wearable thermoelectric array as a graphical user interface

A control algorithm that determines one or more deviations in an orbit of a companion satellite, and control the companion satellite to minimize effects of perturbing forces.

Deployment and control algorithms for wheel cluster formations of satellites

A plurality of spacecraft may be dispersed into a ring constellation or structure. Data may be wirelessly relayed between spacecraft similar to data flowing in a ring network. The ring structure minimizes inter-spacecraft velocities and tracking angle motion to allow use of fixed high-gain radio frequency (RF) antennas or medium-divergence lasers for crosslinks. Data may flow between spacecraft to be downloaded by the next spacecraft that will be passing over a ground station. This reduces data latency when a single ground station is used, and significantly reduces data latency when more than one ground station is used.

Ring constellations for decreased data latency and increased download rates

A system for reducing the cost and increasing the rate and reliability of data transmission from space to ground includes a network of relay satellites in low Earth orbit (LEO). Each relay satellite is configured to receive data from one or more client satellites, and configured to transmit data from LEO to ground using optical communications. The system may also include multiple optical ground stations configured to receive the data and transmit the received data using terrestrial networks to client locations. The network may provide an alternative to downlinking large amounts of data for new satellite operators without an existing ground network and for established satellite operators seeking higher data rates, lower latency, or reduced ground system operating costs.

Satellite laser communications relay network

A deployment algorithm that populate a group of companion satellites around a center satellite, and a control algorithm for maintaining the companion satellites in close formation around the center satellite.

Under one aspect of the present invention, a monolithic sun sensor includes a photosensor; a spacer material disposed over the photosensor; and a patterned mask disposed over the spacer material and defining an aperture over the photosensor. The spacer material has a thickness selected such that the patterned mask casts a shadow onto the photosensor that varies as a function of the monolithic sun sensor's angle relative to the sun. The sun sensor may further include a substrate in which the photosensor is embedded or on which the photosensor is disposed. The spacer material may be transparent, and may include a layer of inorganic oxide, or a plurality of layers of inorganic oxide. The patterned mask may include a conductive material, such as a metal. The aperture may be lithographically defined, and may be square. The sun sensor may further include a transparent overlayer disposed over the patterned mask.

Monolithic sun sensors assemblies thereof

A thermo-photovoltaic power generator for efficiently converting thermal energy into electric energy including a selective thermal emitter for receiving thermal energy and emitting thermal radiation with black body emissivity over a range of wavelengths, low-bandgap photovoltaic cells responsive to thermal radiation at wavelengths within a particular band of said range of wavelengths and operative to convert such thermal radiation to electric energy, and a band pass filter disposed between the thermal emitter and the photovoltaic cells for transmitting thermal radiation from the emitter at wavelengths within the particular band to the photovoltaic cells, and for reflecting thermal radiation from the emitter at wavelengths outside the particular band back to the emitter.

Thermo-photovoltaic power generator for efficiently converting thermal energy into electric energy

Certain embodiments of the invention may include systems, methods, and apparatus for sensing flight direction of a spacecraft. According to an example embodiment of the invention, a method is provided for determining flight direction of a spacecraft. The method includes providing at least one imaging detector associated with a spacecraft; imaging at least a portion of a celestial body onto the at least one imaging detector; acquiring, by the at least one imaging detector, sequential images of at least a portion of the celestial body; and determining the spacecraft flight direction relative to the celestial body based at least in part on processing the sequential images, wherein the processing is performed by one or more computer processors.

Systems, methods, and apparatus for sensing flight direction of a spacecraft

Propulsion systems and methods utilize one or more propellant masses in the form of smart propellant devices to move a spacecraft or other object through outer space and/or substantially airless environments. A spacecraft maneuver, for example, is facilitated by forces imparted on the spacecraft resulting from the ejection of one or more smart propellant devices from the spacecraft and/or the recapture of one or more of the propellant masses at the spacecraft. The smart propellant devices are each programmed to return to the spacecraft along a particular trajectory and to impact the spacecraft at a particular time and place. The spacecraft is provided with ejection devices and recovery devices that eject and recover, respectively, the one or more smart propellant devices. The recovery devices can also be configured to capture kinetic energy from incoming smart propellant devices.

Propulsion systems and methods utilizing smart propellant

Photostructurable glass and ceramic materials in slabs are processed into pixelized screens having opaque baffles therein for defining therebetween light pipes in the material through which pixel light is passed and directed with limited fields of view and for stereoscopic viewing, the screens being made using various manufacturing processes included focused UV light exposure and baking of the photostructurable material.

Photostructured imaging display panels

A refrigerator apparatus includes a housing with an interior chamber, thermoelectric devices that are thermally coupled to the interior chamber, and dual redundant electronics configured to generate and apply input power to the thermoelectric devices.

Thermoelectric-based refrigerator apparatuses

A method using an etchant and a laser for localized precise heating enables precise etching and release of MEMS devices with improved process control while expanding the number of materials used to make MEMS, including silicon-dioxide patterned films buried in and subsequently released from bulk silicon, as a direct write method of release of patterned structures that enables removal of only that material needed to allow the device to perform to be precisely released, after which, the bulk material can be further processed for additional electrical or packaging functions.

Laser assisted chemical etching method for release microscale and nanoscale devices

Integrated glass ceramic spacecraft include a plurality of glass ceramic components including molded, tempered, annealed, and patterned glass ceramic components coupled together for forming a support structure or frame or housing through which is communicated optical signals through an optical communications grid and electrical signals through an electrical communications grid, with the optical communications grid and electrical communication grid forming a composite electrooptical communications grid for spacecraft wide intercommunications. The support structure multifunctions as a frame, a housing, a support, a thermal control system, and as part of an electrooptical communications grid while encapsulating a plurality of optical, electronic, electrical, and MEMS devices between which is communicated the electrical and optical signals over the electrooptical communication grid.

Integrated glass ceramic systems

Integrated glass ceramic spacecraft

An inflatable structure includes a plurality of inflation cells each have a respective internal gas generator connected to an external control processor for sequential inflation of the inflatable structure. Power and control lines feed through the inflation cells for powering the internal gas generator and for communicating control signals between the gas generators and the external control processor. A method of sequence inflation can use various types of exemplar gas generators, such as cellular containment evaporation gas generators and laser ablation gas generators.

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Redondo Beach, CA, United States of America

Siegfried W Janson