James T Small

US Patent:

51466163, Sep 8, 1992

Filed:

Jun 27, 1991

Appl. No.:

7/722621

Inventors:

Raymond Tang - Fullerton CA
James G. Small - Westlake Village CA

Assignee:

Hughes Aircraft Company - Los Angeles CA

International Classification:

H04B 700
G01S 7282

US Classification:

455103

Abstract:

A predetermined radar pulse train is formed in space by transmitting individual spectral components thereof. Thus, a train of extremely short pulses is obtained without switching a radio frequency signal on and off at a high rate. A crystal oscillator is coupled to a harmonic generator such as a comb generator. A power divider distributes the output of the harmonic generator to a multiplicity of final filter amplifiers. Each final filter amplifier has a phase-locked VCO circuit that provides frequency accuracy, spectral purity, low noise and frequency stability. Thus, each final filter amplifier provides one of the spectral components of the predetermined radar pulse train. The final filter amplifiers are coupled by duplexers to a broadband multiplexing feed such as a nested cup dipole feed that illuminates a reflector. On receive, the broadband multiplexing feed separates all the spectral components of the incoming pulse train. Each spectral component is coupled to its own narrow band receiver by the duplexers.

US Patent:

52393097, Aug 24, 1993

Filed:

Jun 27, 1991

Appl. No.:

7/722769

Inventors:

Raymond Tang - Fullerton CA
James G. Small - Westlake Village CA

Assignee:

Hughes Aircraft Company - Los Angeles CA

International Classification:

G01S 728

US Classification:

342 13

Abstract:

An impulse radar that forms a predetermined radar pulse train in space by transmitting individual spectral components thereof. Thus, a train of extremely short pulses is obtained without switching a radio frequency signal on and off at a high rate. An oscillator is coupled to a harmonic generator, and a power divider distributes the output of the harmonic generator to a multiplicity of amplifiers. Each amplifier has a phase-locked VCO circuit that provides frequency accuracy, spectral purity, low noise and frequency stability. Thus, each amplifier provides one of the spectral components of the predetermined radar pulse train. The amplifiers are coupled to a multiplexing feed that illuminates a reflector. On receive, the multiplexing feed separates the spectral components of the incoming pulse train. Each spectral component is coupled to its own narrow band receiver, and one receiver is used to amplify and detect each spectral component.

US Patent:

20220290635, Sep 15, 2022

Filed:

May 27, 2022

Appl. No.:

17/827429

Inventors:

- Lake View Terrace CA, US
Philip J. Wahl - Alta Dena CA, US
James G. Small - Sonoita AZ, US

International Classification:

F02K 9/50
E21C 51/00
F02K 9/68
F02K 9/64

Abstract:

Solar thermal and chemical hybrid rocket configurations for mining and other space applications are disclosed. One aspect is a rocket propulsion system configured to provide rocket thrust, including a solar absorber, a rocket nozzle, and a solar power collection system configured to collect solar energy from the sun, generate an energy beam from the collected sunlight, heat the solar absorber to transfer heat to one or more pressurized propulsive gases, and expel the heated pressurized propulsive gases through a rocket nozzle. A solar absorber can be formed from a granular collection or agglomeration of solids (e.g., of beads), which can be layered with more transparent layer(s) above and more absorbing layer(s) below to create a temperature profile in propellant(s) flowing through the absorber. A hybrid motor can provide an energy (e.g., solar) absorber for absorbing and transferring radiative energy as well as a combustion area. Multiple propellants can be present in a single chamber and be forced from a nozzle to produce thrust. Pressure in a rocket can be achieved from heating inert gasses, and alternatively or simultaneously, from mixing and igniting non-inert gasses.

US Patent:

20220258885, Aug 18, 2022

Filed:

May 3, 2022

Appl. No.:

17/735357

Inventors:

- San Jose CA, US
Joel Sercel - Lake View Terrace CA, US
Mikhail Kokorich - Los Altos Hills CA, US
James Small - Sonoita AZ, US
Nicholas Simon - San Jose CA, US
Nathan Orr - San Jose CA, US
Samuel Avery - San Jose CA, US
Scott Stanley - Northridge CA, US

International Classification:

B64G 1/40
B64G 1/54

Abstract:

In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

US Patent:

20220177166, Jun 9, 2022

Filed:

Mar 5, 2020

Appl. No.:

17/437044

Inventors:

- Santa Clara CA, US
Joel Sercel - Lake View Terrace CA, US
Aaron Mitchell - Santa Clara CA, US
Gedi Minster - Santa Clara CA, US
Yuqi Wang - San Jose CA, US
Lee Wilson - Santa Clara CA, US
James Small - Sonoita AZ, US

International Classification:

B64G 1/40
F02K 9/56
F17C 7/04

Abstract:

To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.

US Patent:

20230130545, Apr 27, 2023

Filed:

Jul 18, 2022

Appl. No.:

17/813312

Inventors:

- Lake View Terrace CA, US
Philip J. Wahl - Altadena CA, US
Conrad T. Jensen - Altadena CA, US
James G. Small - Sonoita AZ, US
Benjamin G. Workinger - Chattanooga TN, US

International Classification:

F02K 9/64
F02K 9/60
B64G 1/40
F24S 20/20
F02K 9/42
F02K 9/44
F24S 23/30
F24S 23/70
F03H 99/00
B64G 1/44
F24S 70/16

Abstract:

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

US Patent:

20230068871, Mar 2, 2023

Filed:

Nov 4, 2022

Appl. No.:

17/981270

Inventors:

- San Jose CA, US
Joel Sercel - Lake View Terrace CA, US
Philip Mainwaring - San Jose CA, US
James Small - Sonoita AZ, US
Matthew Parman - Mountain View CA, US

International Classification:

H01J 37/32
F03H 1/00
B64G 1/40

Abstract:

In a spacecraft for operating a thruster that includes a microwave source, a resonant cavity, and a source of propellant which the thruster converts to hot gas and directs via a nozzle to generate thrust, a method includes operating the thruster in an ignition mode in which the microwave source outputs power at a first rate, and operating the thruster in a propulsion mode in which the microwave source outputs power at a second rate higher than the first rate.

US Patent:

20210404419, Dec 30, 2021

Filed:

Apr 26, 2021

Appl. No.:

17/240750

Inventors:

- Lake View Terrace CA, US
Philip J. Wahl - Altadena CA, US
Conrad T. Jensen - Altadena CA, US
James G. Small - Sonoita AZ, US
Benjamin G. Workinger - Chattanooga TN, US

International Classification:

F02K 9/64
F02K 9/44
F24S 20/20
F24S 23/30
F24S 23/70

Abstract:

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.