Andrew J Mactavish

7922124, Apr 12, 2011

Dec 7, 2006

11/608229

James D. Soldi - Redondo Beach CA, US
Andrew I. Mactavish - Hermosa Beach CA, US

The Boeing Company - Chicago IL

B64G 1/10
B64G 1/26
B64G 1/44

2441588, 244169, 2441727

Systems and methods are disclosed employing electric propulsion stationkeeping in a cyclical manner to better match the cyclical pattern of power generated by the solar array system. For a typical orbit design, e. g. a geostationary orbit, North-South stationkeeping can be intermittently suspended, tolerating some additional drift but yielding in a very significant reduction in the required solar power system. If necessary, stationkeeping can be supplemented with a chemical thrusters during off periods for the electric propulsion. Because of this, the overall electrical power margin for the solar array system design can be reduced without compromising the mission performance.

60534540, Apr 25, 2000

Sep 4, 1998

9/148581

John V. Smolik - Granada Hills CA
Spencer C. Ku - Rancho Palos Verdes CA
Andrew I. Mactavish - Hermosa Beach CA
Mark A. Spiwak - Redondo Beach CA

Hughes Electronics Corporation - El Segundo CA

B64G 110

244158R

A modular payload support for placement in an enclosure defined by the sidewalls of a launch vehicle includes a central hub, a plurality of trusses, and a plurality of modular outer panels. Each of the trusses includes an inner edge secured to the hub and extends radially outward from the hub. Each of the trusses further includes an outer edge, and a modular outer panel is secured to each of the truss outer edges. Each modular outer panel is adapted for attachment to the vehicle sidewall, with each modular outer panel being sized to span the available distance between the truss outer edge and the vehicle sidewall. Each of the trusses is constructed of a number of layers or plies, so that the trusses may be tailored to meet strength and stiffness requirements of a contemplated application.

20210237910, Aug 5, 2021

Apr 16, 2021

17/232988

- Chicago IL, US
Craig Alan Christy - Seal Beach CA, US
Andrew Ian Mactavish - Palos Verdes Estates CA, US
Kevin Nemeth - Redondo Beach CA, US

B64G 1/10
B67D 7/36
B67D 7/02

A transfer system for supplying a receiving tank of a receiving spacecraft with a supply gas from a supply spacecraft. A transfer tank is disposed on the supply spacecraft and configured to retain a supply gas. A transfer line is coupled to the transfer tank, and one end thereof maybe coupled to the receiving tank. A transfer valve is operatively coupled to the transfer line. A heating system is thermally coupled to the transfer tank. A control system is operatively coupled to the transfer valve and the heating system. The control system is operable to cause a transfer quantity of the supply gas to be heated, and to open the transfer valve, such that a difference between the increased pressure of the supply gas in the transfer tank and a pressure in the receiving tank causes the transfer quantity of the supply gas to flow to the receiving tank.

20200102098, Apr 2, 2020

Oct 1, 2018

16/148870

- Chicago IL, US
Craig Alan Christy - Seal Beach CA, US
Andrew Ian Mactavish - Palos Verdes Estates CA, US
Kevin Nemeth - Redondo Beach CA, US

B64G 1/10
B67D 7/02
B67D 7/36

A method of supplying a receiving tank of a receiving spacecraft with a supply gas. The method includes coupling a second end of a transfer line in flow communication with the receiving tank. The transfer line extends from a first end to the second end. The first end is coupled to a transfer tank disposed on a supply spacecraft. The transfer tank holds a transfer quantity of the supply gas. The supply spacecraft includes a heating system coupled in thermal communication with the transfer tank and a transfer valve operatively coupled to the transfer line. The method also includes activating the heating system while the transfer valve is closed such that a pressure of the transfer quantity of the supply gas is increased. The method further includes opening the transfer valve, wherein a difference between the increased pressure of the supply gas in the transfer tank and a pressure in the receiving tank causes a portion of the transfer quantity of the supply gas to flow through the transfer line to the receiving tank.

20160046395, Feb 18, 2016

Aug 17, 2014

14/461415

- Chicago IL, US
John D. Haskell - Chino Hills CA, US
Andrew I. Mactavish - Hermosa Beach CA, US

B64G 1/26
B64G 1/28

A system for managing momentum accumulation of a spacecraft in orbit may include a reaction wheel assembly for controlling an attitude of a body of a spacecraft, the body defining at least one face, and absorbing momentum, a plurality of arcjet thrusters coupled to the face to generate thrust, and a control processor coupled to the plurality of arcjet thrusters for controlling the thrust, wherein actuation of each arcjet thruster of the plurality of arcjet thrusters is configured to produce a net momentum accumulation in the reaction wheel assembly that is below a momentum saturation point of the reaction wheel assembly.