×

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
First Claim
Patent Images

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.

View all claims
  • 0 Assignments
Timeline View
Assignment View
    ×
    ×