Spacecraft with aerodynamic control

Patent metadata

Field	Value
Publication number	US-9889950-B2
Application number	US-201514627936-A
Country	US
Kind code	B2
Filing date	Feb 20, 2015
Priority date	Feb 20, 2015
Publication date	Feb 13, 2018
Grant date	Feb 13, 2018

Abstract

A spacecraft operating in a low earth orbit having an altitude in the range of 160 to 800 km has a main body that includes heat dissipating electrical equipment and an earth-facing payload. Control surfaces on the spacecraft are articulated so as to: provide three-axis attitude control to the spacecraft main body using aerodynamic drag effects, such that the earth-facing payload is maintained in a selected orientation with respect to the earth; and control one or both of orbit altitude and period by articulating the control surfaces so as to regulate an amount of aerodynamic drag. The control surfaces include a first control surface disposed, in an on-orbit configuration, on a boom, the boom being mechanically coupled with the main body, and with one or both of a solar array electrically coupled with the electrical equipment and a thermal radiating array thermally coupled with the electrical equipment.

First claim

What is claimed is:

1. A method comprising:
operating a spacecraft in a low earth orbit having an altitude in the range of 160 to 800 km, the spacecraft having a main body that includes heat dissipating electrical equipment and an earth-facing payload;
articulating control surfaces so as to:
provide three-axis attitude control to the spacecraft main body using aerodynamic drag effects, such that the earth-facing payload is maintained in a selected orientation with respect to the earth; and
control one or both of orbit altitude and period by articulating the control surfaces so as to regulate an amount of aerodynamic drag; wherein:
the control surfaces include a first control surface disposed, in an on-orbit configuration, on a boom, a first portion of the boom being mechanically coupled with the main body, and a second portion of the boom being mechanically coupled with one or both of a solar array that is electrically coupled with the electrical equipment and a thermal radiating array that is thermally coupled with the electrical equipment; and
a longitudinal axis of the boom approximately coincides with a roll axis of the spacecraft.

2. The method of claim 1 , wherein the thermal radiating array is configured to radiate waste heat to space.

3. The method of claim 1 , wherein the spacecraft is an unmanned communications or observation satellite.

4. The method of claim 3 , wherein the spacecraft has a power to mass ratio of at least 10 W/kg.

5. The method of claim 1 , wherein the first control surface is configured to provide a variable amount of pitch torque and the control surfaces include a second control surface and a third control surface, each of the second control surface and the third control surface being disposed in an on orbit configuration so as to provide a variable amount of one or both of roll and yaw torque.

6. The method of claim 5 , wherein controlling one or both of orbit altitude and period by articulating the control surfaces includes articulating the second control surface and the third control surface so as to adjust orbital velocity.

7. The method of claim 5 , wherein articulating the control surfaces includes regulating the amount of aerodynamic drag to be substantially constant.

8. The method of claim 1 , further comprising controlling one or both of orbit altitude and period by deploying a drag chute.

9. The method of claim 8 , further comprising jettisoning or restowing the drag chute.

10. The method of claim 1 , wherein the spacecraft is configured to exclude propulsion subsystem equipment, momentum storage equipment, and magnetic torquers.

11. The method of claim 1 , wherein the selected orientation is nadir pointed, a selected angular offset with respect to nadir pointed, or toward a fixed location on the earth.

12. The method of claim 1 , wherein the control surfaces are configured to regulate aerodynamic drag so as to maintain the spacecraft in a desired position with respect to one or more other spacecraft in a constellation.

13. The method of claim 12 , further comprising:
maintaining the spacecraft in a desired position with respect to one or more other spacecraft in a constellation by adjusting an angle of attack of the control surfaces such that an amount of aerodynamic drag is incremented upward or decremented downward from an intermediate amount.

14. The method of claim 1 , further comprising configuring the control surfaces to increase drag so as to achieve a deorbiting objective.

15. The method of claim 14 , wherein the deorbiting objective is to ensure that the spacecraft is deorbited within a selected timeframe.

16. The method of claim 1 , wherein the control surfaces are configurable to vary the ratio of effective surface area to spacecraft mass within a range from about 0.001 square meters per kilogram to about 0.003 square meters per kilogram.

Assignees

• Space Systems/Loral LLC

Inventors

• Turner Andrew E

Classifications

• B64G1/503

  Radiator panels · CPC title

• B64G1/1007

  Communications satellites · CPC title

• B64G1/44

  using radiation, e.g. deployable solar arrays · CPC title

• B64G1/1021

  Earth observation satellites · CPC title

• B64G1/222

  for deploying structures between a stowed and deployed state · CPC title