The Aerospace Corporation

Other

John H Schilling

Eric Joseph Nemanick

Andrea G Hsu

Brian Blaise Brady

Andrew C Cortopassi

Henry Helvajian

John D DeSain

John Desain

An isotope power source configured to act as a vehicle includes a plurality of radioisotope power sources encased around one or more elements therein to form a tile-shaped spacecraft.

Independent non-solar powered exploratory craft for orbital rendezvous and positioning framework

Solid rocket motors are provided herein. In certain embodiments, a solid rocket motor includes a housing containing thin layers of fuel and thin layers of an inert oxidizer, separated by a thin nonconductive layer. The housing has a nozzle at the end for gas release and channeling. Prior to use, the inert oxidizer is activated by electrochemical oxidation which can generate an active oxidizer and additional fuel. Ignition of the oxidizer and fuel can be triggered whereby the contents of the housing can ignite, generating hot gasses to be channeled out through the nozzle to generate thrust. Replacing current state solid rocket motors with embodiments described herein can improve cost, safety and increase capability. The disclosed embodiments can be safe to transport, store, and handle. Additionally, there can be no moving parts unlike hybrid or liquid rocket motors.

Electrochemical rocket motor

A de-orbiting system for a space vehicle may include one or more lithium ion (Li-ion) batteries configured to release hot gases to be used for thrusting during de-orbiting of the apparatus. The system may also include one or more heaters surrounding each of the one or more Li-ion batteries, which are configured to send each of the one or more Li-ion batteries into a thermal runaway. The thermal runaway causes the one or more Li-ion batteries to release stored electrochemical energy within each of the one or more Li-ion batteries.

Lithium ion battery de-orbiter

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Lancaster, CA, United States of America

John H Schilling