Regenerative piston liquid propellant rocket motor

• US 5,768,885 A
• Filed: 12/03/1996
• Issued: 06/23/1998
• Est. Priority Date: 12/03/1996
• Status: Expired due to Term

• Current Assignee: Autoliv ASP Incorporated (Autoliv Incorporated)
• Original Assignee: Autoliv ASP Incorporated (Autoliv Incorporated)
• Inventors: Johnson, Darrin L., Lauritzen, Donald R.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US08/760,011
• Time in Patent Office: 567 Days
• Field of Search: 60/39.76, 60/39.81, 60/204, 60/247, 60/259
• US Class Current: 60/204
• CPC Class Codes: F02K 9/50 using pressurised fluid to pressurise the propellants

Abstract

A regenerative liquid propellant rocket motor including a body having an integrally formed central tube. A primary combustion chamber is disposed in the body. A secondary combustion chamber is formed by the central tube of the body. A reservoir of liquid propellant is disposed in the body. A regenerative piston is slidably disposed in the body for delivering the liquid propellant to the primary and secondary combustion chambers. The piston includes a plurality of injection ports for injecting the liquid propellant. An ignitor is disposed in the body for initiating combustion of the liquid propellant. A nozzle is formed at a free end of the central tube for producing thrust, wherein upon ignition of the ignitor combustion occurs in the primary combustion chamber driving the piston into the liquid propellant reservoir and the liquid propellant is injected into the primary combustion chamber to produce combustion products which are channeled into the secondary combustion chamber and expanded through the nozzle.

Claims

1. A regenerative liquid propellant rocket motor comprising:

a body including an integrally formed central tube;

a primary combustion chamber disposed in the body;

a secondary combustion chamber formed by the central tube of the body;

a reservoir of liquid propellant disposed in the body;

regenerative piston means slidably disposed in the body for delivering the liquid propellant to the primary and secondary combustion chambers, the piston means including a plurality of injection means for injecting the liquid propellant;

ignitor means disposed in the body for initiating combustion of the liquid propellant; and

nozzle means formed at a free end of the central tube for producing thrust, wherein upon ignition of the ignitor means combustion occurs in the primary combustion chamber driving the piston means into the liquid propellant reservoir and the liquid propellant is injected into the primary combustion chamber to produce combustion products which are channeled into the secondary combustion chamber and expanded through the nozzle means.

2. The regenerative rocket motor of claim 1, wherein the primary and secondary combustion chambers communicate via a plurality of apertures.

3. The regenerative rocket motor of claim 1, wherein the piston means comprises a skirted piston slidably disposed on the central tube of the body.

4. The regenerative piston of claim 3, wherein the liquid propellant reservoir is enclosed by the piston and the central tube.

5. The regenerative piston of claim 1, wherein the nozzle means comprises a converging diverging nozzle.

6. The regenerative piston of claim 1, wherein injection means comprises a plurality of injection ports disposed in a face of the piston, the liquid propellant being injected into the primary combustion chamber through the injection ports.

7. A method of regeneratively injecting liquid propellant into a plurality of combustion chambers of a liquid propellant rocket motor comprising the steps of:

movably positioning a piston within a body of the rocket motor, the body including an integrally formed central tube, a primary combustion chamber disposed in the body, a secondary combustion chamber formed in the central tube, and a reservoir of liquid propellant;

driving the piston into the liquid propellant reservoir;

injecting the liquid propellant into the primary and secondary combustion chambers; and

combusting the liquid propellant in the primary and secondary combustion chambers, the central tube including a nozzle formed on an end thereof, wherein combustion occurs in the primary combustion chamber driving the piston into the liquid propellant reservoir and the liquid propellant is injected into the primary combustion chamber to produce combustion products which are channeled into the secondary combustion chamber and expanded through the nozzle.