MEMS microthruster array

• US 6,378,292 B1
• Filed: 11/10/2000
• Issued: 04/30/2002
• Est. Priority Date: 11/10/2000
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Youngner, Daniel W.
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US09/709,107
• Time in Patent Office: 536 Days
• Field of Search: 602/24, 602/25, 602/50, 602/57, 60/398.23, 244/169, 244/172
• US Class Current: 60/224
• CPC Class Codes: B64G 1/26 using jets
• CPC Class Codes: B64G 1/403 Solid propellant rocket engines
• CPC Class Codes: C06B 45/00 Compositions or products which are defined by structure or arrangement of component of product explosive charges of particular form or shape F42B1/00, F42B3/00
• CPC Class Codes: F02K 9/763 with solid propellant
• CPC Class Codes: F02K 9/94 Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants
• CPC Class Codes: F42B 10/661 using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge

Abstract

A microelectrical mechanical system (MEMS) microthruster array is disclosed. The MEMS microthruster array of the present invention can be used for maintaining inter satellite distance in small satellites. One microthruster array includes numerous microthruster propulsion cells, each having a vacuum enclosed explosive igniter disposed on one side by a breakable diaphragm and having a propellant-filled chamber on the opposite side of the diaphragm. Upon explosion of the explosive igniter, the first diaphragm breaks, which, together with the explosion of the explosive igniter, causes the propellant to expand rapidly, thereby providing exhaust gases which are ejected from an exterior face of the microthruster propulsion array, thereby providing a small unit of thrust.

Claims

1. A microthruster having a plurality of propulsion cells, wherein each of the propulsion cells comprise:

a first cavity;

an explosive igniter disposed within said first cavity;

a second cavity separated from said first cavity by a first diaphragm,

wherein said first diaphragm is cooperatively dimensioned with said igniter to break upon the explosion of said explosive igniter; and

a propellant disposed in said second cavity, said propellant selected to expand rapidly in response to said igniter exploding through said broken first diaphragm.

2. A microthruster as in claim 1, wherein said explosive igniter disposed within said first cavity is disposed within a thermal insulator.

3. A microthruster as in claim 2, wherein said thermal insulator is a vacuum.

4. A microthruster as in claim 1, wherein said explosive igniters are individually selectable and ignitable.

5. A microthruster as in claim 1, wherein said first cavity is defined at least in part by materials selected from the group consisting of silicon, silicon dioxide, and silicon nitride.

6. A microthruster as in claim 1, wherein said first cavity is defined at least in part by silicon dioxide walls and said first diaphragm is formed of silicon nitride.

7. A microthruster as in claim 1, wherein said explosive igniter includes a resistive heater coupled to an explosive material.

8. A microthruster as in claim 1, wherein said first cavity has a floor and said explosive igniter is suspended between said first cavity floor and said first diaphragm.

9. A microthruster as in claim 1, wherein said propellant is selected from the group consisting of plastic explosives, nitrocellulose, and nitrocellulose acetate.

10. A microtliruster as in claim 1, wherein said second cavity includes a second diaphragm dividing said second cavity into a first portion and a second portion, wherein said first portion is disposed between said first and second diaphragm, and said second portion is disposed on an opposing side of said second diaphragm from said first portion.

11. A microthruster as in claim 10, wherein one of said second cavity first and second portions contains a propellant fuel, and wherein the other of said second cavity first and second portions contains a propellant oxidizer, wherein said second diaphragm is breakable upon the explosive ignition of said explosive igniter.

12. A rocket motor as in claim 1, wherein said cells are disposed in an array, wherein said first cavities are separated by first cavity walls, and wherein said explosive igniters are sufficiently thermally insulated from adjacent cells such that igniting a first cell does not ignite propellant in an adjacent cell.

13. A microthruster cell having an interior surface, an exterior exhaust surface and an exhaust axis substantially orthogonal to said exterior exhaust surface, said microthruster cell comprising:

an explosive ignition chamber having chamber walls and a floor, said floor being disposed toward said interior surface, said chamber walls being oriented substantially parallel to said exhaust axis;

an explosive igniter disposed within said explosive ignition chamber, said explosive igniter being ignitable by an externally supplied signal;

a propellant chamber oriented coaxially with said explosive ignition chamber, said propellant chamber having propellant chamber walls oriented substantially parallel to said exhaust axis, said propellant chamber containing a propellant material and having an exhaust orifice disposed toward said exterior exhaust surface; and

a first diaphragm disposed between said explosive ignition chamber and said propellant chamber, said first diaphragm being cooperatively dimensioned with said explosive igniter to break upon the explosion of said explosive igniter.

14. A microthruster cell as in claim 13, wherein said propellant exhaust orifice is capped by an exhaust diaphragm adapted to break upon ignition of said propellant in said propellant chamber.

15. A microthruster cell as in claim 13, wherein said propellant chamber has a single, undivided interior.

16. A microthruster cell as in claim 13, wherein said propellant chamber has at least a first portion and a second portion, wherein said first portion is separated from said second portion by an internal propellant diaphragm adapted to break upon the explosion of said explosive igniter.

17. A microthruster cell as in claim 13, wherein said explosive igniter is disposed within a thermal insulator within said explosive ignition chamber.

18. A microthruster cell as in claim 17, wherein said thermal insulator is a vacuum.

19. A microthruster cell as in claim 13, wherein said explosive ignition chamber is sufficiently insulated to preclude unwanted ignition of adjacent explosive ignition chambers.

20. A microthruster cell comprising:

a first cavity;

an explosive igniter at least partially suspended within said first cavity;

a second cavity separated from said first cavity by a first diaphragm,

wherein said first diaphragm is cooperatively dimensioned with said igniter to break upon the explosion of said explosive igniter; and

a propellant disposed in said second cavity, said propellant selected to expand rapidly in response to said igniter exploding through said broken first diaphragm.