Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1987-12-17
1989-08-15
Jordan, Charles T.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
F42B 15033
Patent
active
048567345
DESCRIPTION:
BRIEF SUMMARY
This invention relates to a reaction jet control system. It relates particularly to a system for use in a vehicle capable of flight outside the earth's atmosphere where reaction jets are used to control attitude and flight direction.
In providing a jet control system it is necessary for the system to be able to effect the necessary changes in vehicle attitude and flight direction whilst maintaining economy of the fuel gas supply. It is quite likely that the gas for the jet reaction nozzles would be derived from a solid propellant charge which, once ignited, would burn continuously at a steady rate until all the fuel is consumed. Since the gas pressure within a combustion chamber burning a solid propellant charge needs to be maintained within predetermined limits to avoid too slow or too fast burning of the charge, it is not in general possible to modify the gas flow through one nozzle without making a corresponding change to the flow through a different nozzle.
The present invention was devised in order to provide a simple and reliable way of controlling the jet flows which would give economy in the number of mechanical parts needed.
According to the invention, there is provided a reaction jet control system for a flying vehicle, the system comprising pairs of jet reaction nozzles with associated gas flow supply ducts, the duct between two nozzles of any one pair including a first gas diverter valve, and the duct between two pairs of nozzles including a second gas diverter valve.
Preferably, the said first gas diverter valve is a fluidic valve capable of controlling output gas flows without mechanical moving parts. The said fluidic valve may be a momentum interaction amplifier valve. The said fluidic amplifier valve may have two control ports responsive to fluid pressure inputs, the said control ports being connected to a gas pressure balance valve.
Conveniently, the said gas pressure balance valve is a gas flapper valve.
The first diverter valve and the second diverter valve may each be connected to respective gas pressure balance valves.
By way of example, some particular embodiments of the invention will now be described with reference to the accompanying drawings, in which:
FIG. 1 is a side view of a jet vehicle showing one arrangement of jet nozzles,
FIG. 2 is a cross-sectional view taken on the line II--II of FIG. 1,
FIG. 3 is an enlargement of FIG. 2 showing details of the nozzle alignment,
FIG. 4 is a block diagram showing a diverter valve arrangement,
FIG. 5 shows a diverter arrangement using spool valves,
FIG. 6 is a rotary diverter valve,
FIG. 7 is a fluidic diverter valve,
FIG. 8 shows a schematic diagram symbol for a fluidic diverter valve,
FIG. 9 is a flapper valve,
FIG. 10 is a schematic diagram of a fluidic diverter and flapper valve circuit, and,
FIG. 11 is a schematic control system for four nozzles.
FIG. 1 shows a jet vehicle 1 suitable for flying at extremely high altitude or in space, and which utilises a system of reaction jets from nozzles 2 to control attitude and flight direction. The main thrust nozzles of the vehicle have not been shown.
The cross-sectional view of FIG. 2 shows that two jet nozzles on each side at the front part of the vehicle are capable of controlling Rolling Moment L, Lateral Thrust Y and Vertical Thrust Z. A similar set of four nozzles at the vehicle rear can be used in conjunction with the front nozzles to give additional control of the vehicle attitude.
As shown in FIG. 3, the front nozzles, 3, 4, 5 and 6 can be operated in various arrangements by a control system 7 which has valves to divert a gas supply to different pairs of the nozzles in turn. Thus the jet nozzle 5 can have a jet efflux 8 and this will produce a thrust acting along the line 9 on the vehicle body.
In such a vehicle, it is quite likely that the gas for the jet reaction nozzles will be derived from a solid propellant charge, which once ignited would burn continuously at a steady rate until all the fuel is consumed. In these circumstances it is evident that when any maneuver is demanded, ea
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Jordan Charles T.
Plessey Overseas Limited
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