Solar torque control using thin film directionally reflective, emissive, absorptive and transmissive surfaces
View Patent ↗Controlling the solar torque imposed on a spacecraft ( 10 ) in flight by providing a film ( 52 ) with variable absorptive, reflective, emissive and/or transmissive properties on the sun side of a thermal shield ( 50 ) of the spacecraft ( 10 ). As the orientation of the thermal shield ( 50 ) changes relative to the sun line, the absorptive, reflective, emissive and/or transmissive properties of the shield ( 50 ) change to cause the shield's ( 50 ) center of solar pressure to change, thus aligning it with the spacecraft ( 10 ) center of mass ( 24 ) as viewed from the direction of the sun line. In accordance with another embodiment of the invention, the spacecraft ( 100 ) is provided with a plurality of control vanes ( 110-116 ) that have a variable absorptive, transmissive, reflective and emissive property to maintain the spacecraft ( 100 ) stably pointed towards the sun.
1. A spacecraft comprising:
a spacecraft bus; and
at least one thermal control surface positioned relative to the spacecraft bus, said surface including an outer layer having at least one of variable absorptive, transmissive, reflective and emissive characteristics so that the center of solar pressure on the spacecraft changes as the sun incidence angle on the thermal control surface changes.
2. The spacecraft according to claim 1 wherein the outer layer is an external layer of a thermal control surface.
3. The spacecraft according to claim 1 wherein the surface is a thermal shield.
4. The spacecraft according to claim 3 wherein the thermal shield is circular and results in an axi-symmetric balancing of solar generated torques.
5. The spacecraft according to claim 3 wherein the thermal shield is circular and the outer layer is formed by a plurality of pie-shaped sections, wherein each pie-shaped section includes the same variable absorptive, reflective and emissive property from an outer perimeter of the shield to the center of the shield.
6. The spacecraft according to claim 1 wherein the thermal control surface includes an embossed film including ridges with an elongated triangular shaped cross-section, and wherein the orientation of the thermal control surface relative to the incident solar radiation determines the effective absorptive, reflective and emissive, and transmissive properties of the surface.
7. The spacecraft according to claim 6 wherein the embossed film is symmetrical about a center line of the thermal control surface so that the reflective surfaces on opposite sides of the center line face each other.
8. The spacecraft according to claim 6 wherein the embossed film is an outer layer of a multi-layer insulation blanket.
9. The spacecraft according to claim 1 wherein the absorptive, reflective, emissive and transmissive properties of the surface are designed to shift the center-of-pressure as a function of sun incidence angle so as to align the center of pressure with the spacecraft center of mass as viewed from the direction of the sun line.
10. The spacecraft according to claim 1 wherein the outer layer is a holographic thin film material.
11. The spacecraft according to claim 1 wherein the outer layer is a diffraction grating.
12. The spacecraft according to claim 1 wherein the outer layer includes stacked multi-layer materials to form a directional interference pattern.
13. A control panel including an outer layer formed on a substrate, said outer layer having a variable absorptive, reflective, emissive and/or transmissive characteristics so that the center of solar pressure on the panel changes as the sun incidence angle on the panel changes.
14. The control panel according to claim 13 wherein the panel is circular and the outer layer is formed by a plurality of pie-shaped sections, wherein each pie-shaped section includes the same variable absorptive, reflective, emissive and transmissive properties.
15. The control panel according to claim 13 wherein the outer layer includes an embossed film formed of ridges with an elongated triangular-shaped cross-section, and wherein one surface of each triangular cross-section is absorptive and another surface of each triangular cross-section is reflective so that the orientation of the panel relative to the incident solar radiation determines the “effective” absorptive, reflective, emissive and/or transmissive properties of the panel.
16. The control panel according to claim 15 wherein the embossed film is symmetrical about a center line of the panel so that the reflective surfaces on opposite sides of the center line face each other.
17. A spacecraft comprising:
a bus;
spacecraft optics; and
a thermal shield positioned between the spacecraft bus and the spacecraft optics, said thermal shield including an outer layer having a variable absorptive, reflective and emissive characteristic so that the center of solar pressure on the spacecraft changes as the angle of incident solar radiation on the thermal shield changes.
18. The spacecraft according to claim 17 wherein the thermal shield is circular and the outer layer is formed by a plurality of pie-shaped sections, wherein each pie-shaped section includes the same variable absorptive, reflective and emissive properties.
19. The spacecraft according to claim 17 wherein the outer layer is an embossed thin film.
20. The spacecraft according to claim 17 wherein the outer layer includes an embossed film consisting of ridges with an elongated triangular-shaped A cross-section, and wherein one side of each triangular cross-section is absorptive and another side of each triangular cross-section is reflective so that the orientation of the surface relative to the incident solar radiation determines the “effective” absorptive, reflective and emissive properties of the surface.
21. The spacecraft according to claim 20 wherein the embossed film is symmetrical about the center line of the surface so that the reflective surfaces on opposite sides of the center line face each other.