IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0517801
(1965-12-30)
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발명자
/ 주소 |
- Dugger Gordon L. (Silver Spring MD) Billig Frederick S. (Silver Spring MD)
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출원인 / 주소 |
- The United States of America as represented by the Secretary of the Navy (Washington DC 06)
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인용정보 |
피인용 횟수 :
15 인용 특허 :
0 |
초록
▼
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
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 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.
대표청구항
▼
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 nu
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.
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