Method and apparatus for initating stable operation of a ram accelerator

• US 4,982,647 A
• Filed: 06/16/1988
• Issued: 01/08/1991
• Est. Priority Date: 06/16/1988
• Status: Expired due to Fees

• Current Assignee: Board of Regents of The University of Washington (University of Washington)
• Original Assignee: Washington Research Foundation (University of Washington)
• Inventors: Bogdanoff, David W., Bruckner, Adam P., Hertzberg, Abraham, Knowlen, Carl
• Primary Examiner(s): BENTLEY, STEPHEN
• Application Number:
  US07/207,706
• Time in Patent Office: 936 Days
• Field of Search: 89/8, 102/520, 102/523
• US Class Current: 89/8
• CPC Class Codes: F41A 1/04 Missile propulsion using the combustion of a liquid, loose powder or gaseous fuel, e.g. hypergolic fuel
• CPC Class Codes: F42B 35/00 Testing or checking of ammunition apparatus for measuring the energy of projectiles G01L5/14

Abstract

A method and apparatus for supersonically accelerating a projectile in a thermally choked subsonic combustion mode. A projectile (50) is initially preaccelerated using either a tank (24) of compressed helium or a chemical propellant charge preaccelerator (152). The projectile enters a portion of a tube (22) filled with a combustible mixture (54) of a gaseous fuel and an oxidizer and is propelled by a ram acceleration process as the mixture burns. In several different embodiments, various devices are used to control the velocity of a shock wave generated as the projectile enters the combustible mixture and the dynamic impulse pressure immediately behind the projectile, so that the shock wave attaches to the projectile along an aft portion, thereby establishing a stable subsonic combustion zone along the aft end (64) of the projectile, in which combustion of the gaseous fuel accelerates the projectile down the bore of the tube. In one embodiment, a perforated sabot (52) is used to propel the projectile during preacceleration. The sabot has a plurality of passages (114) extending longitudinally between its front and rear surfaces, which are initially closed with a thin plate (110) during the preacceleration of the projectile. However, the plate is dislodged as the projectile enters the combustible mixture, allowing the dynamic pressure of the shock wave caused by the sabot to dissipate through the open passages.

Claims

1. In a ram accelerator, including a projectile having an aft portion and a linearly extending tube having a bore, at least a portion of which is filled with a combustible mixture of a gaseous fuel and an oxidizer, apparatus for preaccelerating the projectile, and for initiating a stable combustion zone behind the projectile, comprising:

force generating means for providing a force acting on the aft portion of the projectile so as to accelerate it to supersonic velocity, propelling it into the portion of the tube filled with the combustible mixture; and

throttling means that are independent of the projectile and its profile, for controlling the velocity of a shock wave generated at the aft portion of the projectile as the projectile enters the combustible mixture by controlling the dynamic impulse pressure immediately behind the projectile so that the shock wave does not propagate ahead of it, said throttling means causing the shock wave to instead attach to the projectile, thereby establishing a stable subsonic combustion zone along the aft portion of the projectile in which combustion of the gaseous fuel continues to accelerate the projectile down the bore of the tube.

2. The apparatus of claim 1, wherein the force generating means comprise a sabot sized to slide in a close fit down the bore of the tube, said sabot having two opposed surfaces, and a source of compressed fluid applied to one of the two opposed surfaces of the sabot to initially accelerate the sabot, the other of the two opposed surfaces of the sabot engaging the aft portion of the projectile, propelling it down the bore ahead of the sabot.

3. The apparatus of claim 2, wherein the sabot is perforated to provide fluid communication between said opposed surfaces of the sabot, said throttling means including flow control means for closing said perforation while the compressed fluid is accelerating the sabot, and opening said perforation upon entry of the projectile and sabot into the portion of the tube filled with the combustible mixture, so that the dynamic impulse pressure is reduced as the mixture flows through said perforation in the sabot, reducing the velocity of the shock wave generated by the sabot so that it is less than or equal that of the projectile.

4. The apparatus of claim 3, wherein the flow control means comprise a thin plate loosely fitted on the surface of the sabot exposed to the compressed fluid, closing said perforation as the sabot is accelerated by the compressed fluid, said thin plate being detached from the sabot as the sabot enters the portion of the tube filled with the combustible mixture, thereby opening said at least one passage.

5. The apparatus of claim 2, wherein the throttling means comprise a low mass sabot having a kinetic energy that is a function of the velocity and mass of the sabot, the mass of the sabot being predetermined so that its kinetic energy is rapidly dissipated after it enters the portion of the tube filled with the combustible mixture, said sabot rapidly slowing as it enters said portion so that the shock wave generated by the sabot falls behind the projectile, and so that a new shock wave generated by the combustion of the mixture attaches to the projectile in place of the sabot generated shock wave.

6. The apparatus of claim 1, wherein the throttling means comprise an explosive pellet disposed proximate a point where the projectile enters the portion of the tube filled with the combustible mixture, said pellet being exploded to generate a shock wave of predefined velocity as the projectile enters said portion of the tube, thereby causing the shock wave to attach to the projectile at a point along its length.

7. The apparatus of claim 1, wherein the throttling means comprise a plasma jet injector disposed in a wall of the tube proximate where the projectile enters the portion of the tube filled with the combustible mixture, said plasma jet injector generating a shock wave of predetermined velocity as the projectile enters said portion of the tube, thereby causing the shock wave to attach to the projectile.

8. The apparatus of claim 1, wherein the throttling means comprise a port disposed in the tube, upstream of the portion filled with the combustible mixture, said port providing fluid communication between the interior of the tube and an external ambient pressure and thus comprising a passage through which the dynamic impulse pressure of the shock wave is at least partly dissipated.

9. The apparatus of claim 8, wherein the force generating means comprise an explosive powder mixture, which is ignited to accelerate the projectile into the portion of the tube filled with the combustible mixture.

10. The apparatus of claim 8, wherein the force generating means comprise a source of compressed gas.

11. The apparatus of claim 1, wherein the throttling means comprise a relatively lightweight disk loosely attached to the rear of the projectile and having a diameter only slightly less than the bore of the tube, said disk detaching from the projectile as it enters the combustible mixture, falling behind the projectile and throttling a shock wave that results from the ignition of the combustible mixture so that the shock wave attaches to the projectile as the disk enters the portion of the tube filled with the combustible mixture.

12. The apparatus of claim 1, wherein upon entry of the projectile into the portion of the tube filled with the combustible mixture, the throttling means are further operative to cause ignition of the combustible mixture.

13. The apparatus of claim 12, wherein the force generating means include a perforated sabot and means for closing the perforations until the sabot enters the portion of the tube filled with the combustible mixture, said throttling means comprising the perforations in the sabot, compressive heating of the combustible mixture within the perforations causing its ignition.

14. A method for initializing stable ram propulsion of a projectile along a bore of a tube having at least a portion thereof filled with a combustible mixture of a gaseous fuel and an oxidizer, comprising the steps of:

(a) preaccelerating the projectile upstream of said portion of the tube, so that it enters said portion at a supersonic velocity relative to the combustible mixture;

(b) independently of the projectile and its profile, throttling the shock wave caused as the projectile enters said portion of the tube, so that on an aft portion of the projectile, the velocity of the shock wave is approximately equal that of the projectile; and

(c) initiating a stable combustion zone immediately behind the projectile, combustion of the mixture in said zone accelerating the projectile along the bore of the tube.

15. The method of claim 14, wherein the projectile is preaccelerated to a supersonic velocity relative to the combustible mixture, before entering said portion of the tube filled with the combustible mixture, using a compressed gas.

16. The method of claim 14, wherein the step of preaccelerating comprises the step of igniting a propellant charge behind the projectile, and wherein a port through a wall of the tube in fluid communication with ambient pressure is provided proximate to where the projectile enters said portion of the tube filled with the combustible mixture, at least a portion of a dynamic impulse pressure associated with the shock wave at the time the projectile enters the combustible mixture dissipating through said port to reduce the velocity of the shock wave to substantially the velocity of the projectile.

17. The method of claim 14, wherein a perforated sabot is used to propel the projectile into said portion of the tube filled with the combustible mixture, further comprising the steps of blocking fluid flow through the perforation during preacceleration of the projectile, and opening the perforation to fluid flow after the projectile has entered said portion of the tube, at least a portion of a dynamic impulse pressure associated with the shock wave being dissipated through said perforation to reduce the velocity of the shock wave.

18. The method of claim 17, wherein compressive heating of the combustible mixture with the perforation ignites the combustible mixture.

19. The method of claim 14, wherein the steps of throttling and initiating the stable combustion zone comprise the step of detonating an explosive pellet disposed in a cavity along the bore of the tube proximate where the projectile enters said portion of the tube filled with the combustible mixture, the explosion of said pellet generating a shock wave of predetermined velocity that attaches to the projectile.

20. The method of claim 14, wherein the steps of throttling and initiating the stable combustion zone comprise the step of activating a plasma jet injector disposed in a wall of the tube proximate where the projectile enters the portion of the tube filled with the combustible mixture, the plasma jet injector generating a shock wave of predetermined velocity that attaches to the projectile.

21. The method of claim 14, wherein a relatively lightweight sabot is used to accelerate the projectile upstream of said portion of the tube, the mass of the sabot being predetermined so that it decelerates upon entry of the projectile and sabot into said portion of the tube filled with the combustible mixture, enabling a peak dynamic pressure associated with the shock wave to dissipate, so that it attaches to the projectile, reducing the velocity of the shock wave to substantially that of the projectile.

22. The method of claim 14, wherein the step of throttling the shock wave includes the step of igniting the combustible mixture.

23. For use in a ram jet accelerator in which a projectile is accelerated to a supersonic velocity prior to entry into a bore filled with a combustible mixture of a gaseous fuel and an oxidizer, a method of establishing a thermally choked mode for propelling the projectile through the bore, comprising the steps of:

(a) independently of the projectile and its profile, controlling the velocity of a shock wave generated as the projectile enters the combustible mixture so that it does not propagate down the bore at a velocity greater than that of the projectile;

(b) creating a subsonic flow over an aft portion of the projectile as it passes down the bore; and

(c) initiating a stable combustion zone along the aft portion of the projectile, in which the combustible mixture burns to propel the projectile down the bore.

24. The method of claim 23, wherein the step of controlling the velocity of the shock wave comprises the step of choking flow of the combustible mixture through a perforated sabot initially used to accelerate the projectile.

25. The method of claim 24, wherein compressive heating of the combustible mixture within perforations of the perforated sabot ignites the combustible mixture.

26. The method of claim 23, wherein the steps of controlling the velocity and creating a subsonic flow comprise the step of generating a shock wave of predetermined velocity as the projectile enters the combustile mixture.

27. The method of claim 23, wherein the step of creating a subsonic flow comprises initially accelerating the projectile to a supersonic velocity using a compressed fluid that acts on a lightweight disk to propel the projectile into the bore, further comprising the step of selecting the mass of said disk so that its kinetic energy is sufficiently low to ensure said disk falling behind as the projectile enters the combustible mixture, so that the shock wave attaches to the projectile.

28. The method of claim 27, wherein the disk is loosely attached to the rear of the projectile.

29. The method of claim 23, wherein a propellant charge initially accelerates the projectile to a supersonic velocity relative to the combustible mixture prior to its entry into the combustible mixture.

30. The method of claim 29, wherein a port communicating with ambient pressure dissipates the shock wave as the projectile enters the combustible mixture.