Supersonic ramjet missile

• US 4,291,533 A
• Filed: 12/30/1965
• Issued: 09/29/1981
• Est. Priority Date: 12/30/1965
• Status: Expired due to Term

• Current Assignee: the united states of america as represented by the secretary of the navy
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Billig, Frederick S., Dugger, Gordon L.
• Primary Examiner(s): Tudor, Harold J.
• Application Number:
  US04/517,801
• Time in Patent Office: 5,752 Days
• Field of Search: 60/235, 60/243, 60/270, 60/240, 60/270 R, 137/15.1, 137/15.2, 138/44-46, 102/49 J, 102/49 S
• US Class Current: 60/240
• CPC Class Codes: F02C 7/042 having variable geometry
• CPC Class Codes: F02K 7/10 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 137/0645 With condition responsive control means

Abstract

1. In a supersonic combustion ramjet missile,

a body,

an innerbody having a portion within the body and a portion projecting fordly therefrom,

said innerbody being spaced from said body to define an inlet for compressing an air flow from a hypersonic flight Mach number to a supersonic flight Mach number,

said body having therein a combustion chamber, an exhaust nozzle and a fuel tank,

nozzles in the wall of the combustion chamber for discharging fuel from the tank into said chamber,

means in the body and providing fuel flow rate adjustment as a function of Mach number and altitude to control fuel-air equivalents ratio to effect desired missile operation,

said means including sensors communicating with the combustion chamber, a distribution valve, a fuel pump and a turbine meter connected between the tank and the valve, a turbine driving the fuel pump, a sensor control unit connected to the valve, one of said sensors being connected to said unit and another to said valve, a computer for controlling said turbine, said turbine meter and said sensor control unit, and means for supplying control signals to the computer representative of pitot and static pressures impinging on the forward end of the innerbody,

said innerbody being shiftable axially within said body in response to Mach number changes, whereby shock waves will be maintained at optimum positions between the body and the innerbody.

Claims

1. In a supersonic combustion ramjet missile,

a body,

an innerbody having a portion within the body and a portion projecting forwardly therefrom,

said innerbody being spaced from said body to define an inlet for compressing an air flow from a hypersonic flight Mach number to a supersonic flight Mach number,

said body having therein a combustion chamber, an exhaust nozzle and a fuel tank,

nozzles in the wall of the combustion chamber for discharging fuel from the tank into said chamber,

means in the body and providing fuel flow rate adjustment as a function of Mach number and altitude to control the fuel-air equivalents ratio to effect desired missile operation,

said means including sensors communicating with the combustion chamber, a distribution valve, a fuel pump and a turbine meter connected between the tank and the valve, a turbine driving the fuel pump, a sensor control unit connected to the valve, one of said sensors being connected to said unit and another to said valve, a computer for controlling said turbine, said turbine meter and said sensor control unit, and means for supplying control signals to the computer representative of pitot and static pressures impinging on the forward end of the innerbody,

said innerbody being shiftable axially within said body in response to Mach number changes, whereby shock waves will be maintained at optimum positions between the body and the innerbody.

2. A supersonic missile as recited in claim 1, wherein

the body comprises a forward section, an aft section, and a cowl, and

said innerbody comprises forward and aft sections that are relatively movable with respect to each other and to said body.

3. A supersonic missile as recited in claim 2,

including means mounted within the innerbody for shifting said innerbody sections axially of the body,

said means shifting the forward innerbody section a relatively long distance and the aft innerbody section a relatively short distance,

the shifting of the innerbody sections providing optimum positioning of the shock waves on and within the missile during flight thereof at different Mach numbers.

4. A supersonic missile as recited in claim 3, wherein said means comprises:

a motor having a shaft with a relatively coarse threaded portion and a relatively fine threaded portion,

a nut on the innerbody forward section and receiving said coarse threaded shaft portion,

a nut on the innerbody aft section and receiving said fine threaded shaft portion,

means for controlling operation of the motor, and

pressure operated means for actuating said last mentioned means.

5. A supersonic missile as recited in claim 2, wherein

said innerbody sections include telescoping connected sleeves,

struts mounted in the cowl, and

an annular member secured to the struts,

said annular member engaging one of the sleeves for mounting the innerbody in the body.

6. A supersonic missile as recited in claim 1, including additionally

a booster coupling ring mounted in the open end portion of the exhaust nozzle, and

a booster detachably connected to the missile and having a nose engaging said ring.

7. A supersonic missile as recited in claim 5, wherein

said sleeves are formed with registering slots and said motor is mounted on said annular member and extends through said slots, and

including a housing secured to the motor within the innerbody.

8. A supersonic missile including a body open at its forward end and having a combustion chamber and a fuel tank,

a plurality of outwardly swept wings on the body and arranged in cruciform configuration,

a plurality of steering fins on the body aft of the wings and in symmetry therewith,

nozzles in the body and communicating with the combustion chamber,

means for pumping fuel from the tank to the nozzles,

means in the body for sensing pressures in the combustion chamber,

means connected with said sensing means and operable for controlling said fuel pumping means to provide fuel flow rate adjustment as a function of Mach number and altitude whereby supersonic flow through the combustion chamber will be maintained,

an innerbody having relatively movable conical forward and aft sections,

means mounting the innerbody in the open forward end of the body to project inwardly and outwardly thereof, and

means on said first-mentioned means for moving the sections relative to each other as a function of flight Mach number for positioning shock waves impinging on the missile during flight thereof for optimum missile performance.

9. A supersonic missile as recited in claim 8,

including a booster having a nose engagable in the aft end of the missile for providing a starting impulse therefor.

10. A supersonic missile as recited in claim 8,

wherein said last-mentioned means comprises a motor,

an annular member mounting the motor,

and a plurality of struts mounting the annular member in the missile body.