Ram air combustion steering system for a guided missile

• US 4,573,648 A
• Filed: 01/20/1983
• Issued: 03/04/1986
• Est. Priority Date: 01/20/1983
• Status: Expired due to Fees

• Current Assignee: Loral Aerospace Corp. (MHR Holdings LLC (New York))
• Original Assignee: Ford Aerospace & Communications Corporation (Galileo Parent, Inc.)
• Inventors: Frazer, Alson C., Morenus, Richard C.
• Primary Examiner(s): Jordan, Charles T.
• Application Number:
  US06/491,953
• Time in Patent Office: 1,139 Days
• Field of Search: 102/229, 102/374, 102/380, 102/381, 102/503, 244/3.21, 244/3.22, 244/52, 60/270.1, 137/625.42, 137/625.46, 137/625.47, 137/862, 137/887, 137/15.1, 137/15.2, 137/874, 137/875, 137/876, 137/625.16
• US Class Current: 244/3.22
• CPC Class Codes: F42B 10/663 using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves

Abstract

An open-ended diffusion chamber and an adjacent combustion chamber located in the nose of a projectile to receive ram air that ignites a solid fuel material within the combustion chamber. A pair of oppositely disposed lateral steering ports are provided aft of the combustion chamber and are interconnected therewith via a diverting valve that is controllable to selectively divert the escaping combustion gases from the combustion chamber to one or both of the steering ports to thereby change or maintain the trajectory course of the projectile after firing.

Claims

1. A directional steering system for a guided missile comprising:

means defining the nose end of said missile;

means within said nose means for receiving ram air therein;

means within said nose means adjacent said ram air receiving means for providing combustible fuel;

means within said nose means defining a combustion chamber wherein ram air ignites said fuel;

means within said nose means and aft of said combustion chamber defining lateral thrust steering ports to provide escape paths for combustion gases from said combustion chambers means to the external environment;

means within said nose means for selectively diverting combustion gases generated within said combustion chamber means to one or more of said lateral thrust steering ports.

2. A steering system as in claim 1, wherein said combustible fuel means comprises a quantity of solid fuel formed to have a surface exposed to said ram air in said combustion chamber means.

3. A steering system as in claim 1, wherein said diverting means includes an electrically controllable vane mechanism that is rotatable to completely block no more than one of sad lateral thrust steering ports at a time.

4. A system for directionally controlling a fired projectile over its flight path comprising:

means at the nose end of said projectile for defining a compression chamber having one end open for receiving ram air;

a pair of oppositely disposed jet ports extending from said compression chamber means to opposite sides of said projectile;

means defining a solid combustible fuel within said compression chamber means and being ignited by said ram air to produce combustion gases;

valve means between said compression chamber means and said jet ports for responsively diverting the flow of combustion gases to each of said jet ports to control the steering direction of said projectile.

5. A system as in claim 4, wherein said compression chamber means includes an internal wall surface which is formed by a solid fuel material, and further wherein, said solid fuel material is ignited by said ram air within said compression chamber means and generates combustion gases that are forced towards said pair of jet ports to escape therefrom and thereby provide steering thrust to said projectile.

6. A system as in claim 5, wherein said compression chamber means is generally cylindrically shaped and lies longitudinally concentric with the major axis of said projectile and further wherein said jet ports extend radially with respect to said compression chamber means.

7. A system as in claim 6, wherein said valve means comprises a partially cylindrical vane element on a rotatable base that is electrically controlled and wherein said element is mounted for axial rotation along the axis of said projectile.

8. A system as in claim 6, wherein said vane element is at least large enough to block one of said jet ports when located between it and said combustion chamber means and sufficiently small enough to leave both said jet ports open when equal thrust is desired at each jet port.

9. A system as in claim 4, wherein said compression chamber means is generally cylindrical shaped and lies longitudinally concentric with the major axis of said projectile and further wherein said jet ports extend radially with respect to said compression chamber means.

10. A system as in claim 8, wherein said valve means comprises a partially cylindrical vane element on a rotatable base that is electrically controlled and wherein said element is mounted for axial rotation along the axis of said projectile.