MICROSATELLITE COMPRISING A PROPULSION MODULE AND AN IMAGING DEVICE

• US 20110240801A1
• Filed: 12/10/2008
• Published: 10/06/2011
• Est. Priority Date: 12/10/2008
• Status: Active Grant

• Current Assignee: Giulio Manzoni
• Original Assignee: Giulio Manzoni
• Inventors: Manzoni, Giulio
• Granted Patent: US 8,967,545 B2
• Time in Patent Office: Days
• US Class Current: 244/171.1
• CPC Class Codes: B64G 1/1021 Earth observation satellites
• CPC Class Codes: B64G 1/1028 using optical means for mapping, surveying or detection, e.g. of intelligence
• CPC Class Codes: B64G 1/26 using jets
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: F02K 9/605 Reservoirs
• CPC Class Codes: F02K 99/00 Subject matter not provided for in other groups of this subclass

Abstract

A microsatellite comprising a propulsion module for moving and/or pointing said microsatellite and an imaging device (100) mounted to said propulsion module. Furthermore there is a fuel supply (210) located within said imaging device (100).

Claims

1. A spacecraft comprising:

a propulsion module for moving and/or pointing said micro satellite; and

a chamber comprising;

an optical system for transmission of light from an image target to an optical sensor, the optical system comprising at least a window disposed at an end of the chamber, the window being for transmission therethrough of light from the image target; and

wherein the chamber is arranged to contain fuel.

3. The spacecraft according to claim 1 arranged for the chamber to contain liquid fuel, the chamber further comprising a bellow for containing the liquid fuel, the bellow being arranged to contract as the liquid fuel is consumed, wherein the bellow is terminated by a flat transparent window.

4. The spacecraft according to claim 1 wherein the chamber is of selectively variable volume such that on depletion of said fuel, the chamber is correspondingly reduced in volume.

5. The spacecraft according to claim 4 wherein the chamber comprises a piston for reducing the volume within the chamber.

6. The spacecraft according to claim 1 wherein the chamber comprises an extendable structure to move a first group of lenses forward so as to increase an optical length of the optical system.

7. The spacecraft according to claim 6 wherein the chamber includes at least two concentric portions in sliding engagement and an actuator to cause relative movement between said at least two portions between a retracted position and an extended position.

15. The spacecraft according to claim 1, wherein said chamber includes a deformable supporting structure such that variation of propellant refractive index due to changes in pressure and temperature are compensated for by deforming to a shape to cancel optical effects due to the fuel supply.

2. (canceled)

8. A spacecraft comprising

a propulsion module comprising a housing having an internal chamber;

said housing having formed in walls of said housing a fuel inlet port, a thrust port and conduits providing a fuel path there between;

said propulsion module further including a thrust assembly mounted to said thrust port.

9. The spacecraft according to claim 8 wherein said thrust assembly comprises a thrust module having a plurality of nozzles and a plurality of thrust control valves each corresponding to said nozzles;

such that said thrust control valves are located intermediate the thrust port and the thrust module.

10. The spacecraft according to claim 9 wherein said propulsion module includes a plurality of thrust ports having a thrust assembly associated with each thrust port.

11. The spacecraft according to claim 8 wherein said housing includes an engagement surface and an adaptor assembly mountable to said engagement surface such that the adaptor assembly permits engagement of peripheral equipment to said propulsion module.

12. The spacecraft according to claim 11 wherein said peripheral equipment comprises one of a telescope, photographic equipment, pressure sensors, fuel loading valves, control electronics and test instrumentation.

13. The spacecraft according to claim 9 wherein said thrust module includes a heating or vaporization assembly for vaporizing fuel at or near the nozzle.

14. The spacecraft according to claim 13 wherein said vaporization assembly includes a resistor mounted within a duct adjacent to the nozzle;

said resistor in electrical communication with a power supply in order to heat said fuel to a vaporization temperature.

16. An electromagnetic valve comprising

a substrate having an inlet port;

a planar valve assembly said valve assembly comprising a valve frame and a selectively movable seat member co-planar with said valve frame;

said movable seat member forming a layer on the valve frame;

an electromagnetic coil having an axis perpendicular to a plane of said valve assembly;

said electromagnetic coil being adjacent to said valve assembly;

said seat member having a ferromagnetic material placed on a portion of said seat member adjacent to said electromagnetic coil;

wherein on energizing the electromagnetic coil the seat member is arranged to move within the plane of the valve frame towards said coil from a closed position sealing the inlet port to an open position opening the inlet port.

17. The electromagnetic valve according to claim 16 further including a resilient member such that on de-energizing of said electromagnetic coil, the resilient member is arranged to bias the seat member from the open position to the closed position.

18. The electromagnetic valve according to claim 17 wherein said resilient member includes a spring member.

19. The electromagnetic valve according to claim 18 wherein said spring member includes an etched zone of the seat member providing a compressible portion of the seat member within the plane of said seat member and further including a compressible seal such that insertion of the seal between the frame and seat members biases the spring member so as to form a resilient return mechanism on de-energizing of the electromagnetic coil.

20. The electromagnetic valve according to claim 16 wherein the substrate further includes an outlet port such that a fluid path from the inlet port to the outlet port passes through the seat member so as to create a valve effect controlling fluid flow from the inlet to the outlet.

21. The electromagnetic valve according to claim 20 further including a second valve sealing layer placed on the valve assembly

said valve sealing layer having a seal member corresponding to the seal member of the valve assembly

said ferromagnetic material arranged to couple the two seat and seat seal members so as to operate together on energizing and de-energizing of the electromagnetic coil such that the valve sealing layer acts to seal the seat member of the valve assembly.

22-38. -38. (canceled)