TANDEM SOLID-HYBRID ROCKET MOTOR

• US 3,789,610 A
• Filed: 06/21/1967
• Issued: 02/05/1974
• Est. Priority Date: 06/21/1967
• Status: Expired due to Term

• Current Assignee: William C. Stone
• Original Assignee: William C. Stone
• Inventors: Stone, William C.
• Primary Examiner(s): Feinberg, Samuel
• Application Number:
  US04/649,420
• Time in Patent Office: 2,421 Days
• Field of Search: 60/207,220,224,225,250,251,245
• US Class Current: 60/245
• CPC Class Codes: F02K 9/72 using liquid and solid propellants, i.e. hybrid rocket-engine plants

Abstract

A single-chamber rocket motor containing both a hybrid fuel charge (with associated oxidizer) and a solid propellant charge. Termination of the hybrid motor at the time desired provides accurate missile range zoning. The hybrid fuel charge is in tandem with and forward of the solid propellant charge which provides the minimum impulse of the rocket motor and the minimum missile range. The volume vacated by the solid propellant charge serves as a mixing chamber for more efficient hybrid fuel charge combustion. A gas mixer baffle plate separates the two charges and provides additional mixing.

Claims

1. A rocket motor comprising:

a motor case defining a combustion chamber therein;

a solid propellant charge at the aft end of said combustion chamber;

a solid hybrid fuel charge at the forward end of said combustion chamber, said solid propellant charge and said solid hybrid fuel charge being juxtaposed in tandem;

an oxidizer in fluid communication with said solid hybrid fuel charge;

means for controlling the flow of said oxidizer to said solid hybrid fuel charge;

a perforated gas mixer baffle plate located intermediate adjacent ends of said solid propellant charge and said solid hybrid fuel charge to separate said solid propellant charge from said solid hybrid fuel charge and provide additional mixing of exhaust gases from combustion of said solid hybrid fuel charge as the exhaust gases pasS through said perforated baffle plate to thereby further increase the combustion efficiency of said solid hybrid fuel charge with said oxidizer; and

means for igniting said solid propellant charge.

2. The rocket motor as set forth in claim 1 wherein said gas mixer baffle plate comprises annular carbon inserts located in holes therein, said carbon inserts defining orifices therein.

3. The rocket motor as set forth in claim 1 wherein said means for controlling the flow of said oxidizer to said hybrid fuel charge comprise pressure-time integral means for timing said flow of said oxidizer to said hybrid fuel charge.

4. The rocket motor as set forth in claim 1 wherein said hybrid fuel charge is in the form of a wagonwheel configuration defining hybrid grain spokes, and wherein injector means for injecting said oxidizer are positioned for injecting said oxidizer down the center of said wagonwheel and intermediate said grain spokes.

5. The rocket motor as set forth in claim 4 wherein said orifices in said gas mixer baffle plate are in alignment with said hybrid grain spokes.

6. The rocket motor as set forth in claim 5 wherein said orifices are positioned in said gas mixer baffle plate with even-numbered ones of said spokes having one orifice in alignment therewith, and odd-numbered ones of said spokes having two orifices in alignment therewith.

7. The rocket motor as set forth in claim 6 wherein said spokes number twelve.

8. The rocket motor as set forth in claim 4 wherein said means for controlling the flow of said oxidizer to said hybrid fuel further includes an explosively actuated oxidizer inlet valve located in fluid communication intermediate said oxidizer and said injector means.

9. The rocket motor as set forth in claim 8 wherein a cavitating venturi is located in fluid communication intermediate said inlet valve and said injector means, said cavitating venturi being located near said injector head.