Dana Ray Andrews

US Patent:

8292232, Oct 23, 2012

Filed:

Aug 11, 2010

Appl. No.:

12/854827

Inventors:

Dana G. Andrews - Seattle WA, US
Michael Beerman - Seattle WA, US
Kevin A. Brown - Seattle WA, US
Jeffrey H. Cannon - Maple Valley WA, US
Krissa E. Watry - Puyallup WA, US
Jason Andrews - Seattle WA, US

Assignee:

Andrews Space, Inc. - Tukwila WA

International Classification:

B64G 1/00

US Classification:

2441591, 244158 R, 244160

Abstract:

A satellite recovery apparatus having a base configured to be attached to a satellite and having a pressurized gas chamber and a valve assembly. A plurality of walls are hingedly attached to the base and movable between a closed position, wherein the walls define a volume above the base, and an open position, wherein the walls are disposed spaced away from the base. A heat shield is attached to the base. A deployable decelerator is attached to the heat shield and has an outer perimeter with an expandable torus that is operably connected to the valve assembly such that the expandable torus can be pressurized from the chamber. Pressurization of the expandable torus deploys the decelerator assembly from a non-deployed position within the volume to a deployed high-drag position.

US Patent:

44443684, Apr 24, 1984

Filed:

Oct 30, 1981

Appl. No.:

6/315588

Inventors:

Dana G. Andrews - Seattle WA

Assignee:

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

International Classification:

B64C 920

US Classification:

244216

Abstract:

Variable camber actuator assemblies 50 broaden the range of speeds at which lift to drag performance is maximized for slotted flap wings. Lift is improved over a broader range of cruising speeds by varying wing camber with rotational flap movements that do not introduce wing slots and induced drag. Forward flaps 40 are secured to forward flange links 26 which extend from, and are a part of, forward flap linkage assemblies 20. The forward flaps 40 rotate about flap pivots 39 with their rotational displacement controlled by variable camber actuator assemblies 50 located between the forward flaps and the forward flange links. Rear flaps 45 are held relative to the forward flaps 40 by rear flap linkage assemblies 70 which may act independently from the forward flap linkage assemblies and the variable camber actuator assemblies. Wing camber is varied by rotating the flaps with the variable camber actuator assemblies while the flaps are in a deployed or tucked position. Rotating flaps in a tucked position does not introduce significant wing surface discontinuities, and reduces aircraft fuel consumption on most flight profiles.

US Patent:

45181373, May 21, 1985

Filed:

Nov 1, 1979

Appl. No.:

6/090296

Inventors:

Dana G. Andrews - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64G 158

US Classification:

244113

Abstract:

Liquid hydrogen stored aboard a space vehicle, and constituting a fuel for use in the vehicle's main rocket motor, is introduced, in a gaseous state, into an inflatable aerodynamic braking member, for moving it from a collapsed stored position outwardly into an inflated operational position. Such member provides a large area braking surface which extends generally laterally outwardly from the space vehicle. During reentry the space vehicle is oriented to reenter nozzle end first. Fuel is consumed within the rocket motor to produce gases which are discharged out through the rocket nozzle to provide a cooling layer of gases forwardly of the large area braking surface. A space vehicle equipped with such an aerodynamic braking system is operated to reenter into the atmosphere. The drag produced by the braking member slows the space vehicle down and then the space vehicle is set into a low earth orbit.

US Patent:

45040311, Mar 12, 1985

Filed:

Mar 2, 1982

Appl. No.:

6/353828

Inventors:

Dana G. Andrews - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64G 158

US Classification:

244113

Abstract:

A space vehicle 10 is steered from outer space toward the earth's atmosphere main rocket nozzle end first. An inflatable braking member 28 is deployed around the vehicle 10 by introducing gas into it. The main rocket motor 16 is ignited to produce a substantially throttled stream of gases. This stream provides a cooling layer forwardly of the braking member 28 to protect the member 28 from heating by friction with the atmosphere. The reduction of the velocity of the vehicle 10 is controlled by directly varying the drag of the vehicle 10 to compensate for variations in the density of the atmosphere. The drag is varied by varying the thrust of the motor 16 and/or varying the shape of the member 28. A backup method is to deflate the member 28 in the atmosphere. The member 28 may be jettisoned after the vehicle 10 leaves the atmosphere to enter a low earth orbit.