| 摘要 |
1,217,280. 280. Rocket propulsion plant. NORD AVIATION SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES. Dec. 19, 1968 [Dec. 22, 1967], No.60521/68. Heading F1J. [Also in Division F4] In a hypergolic reaction system, a device 1, Fig. 1, for regulating the flow of a liquid propellant into a rocket combustion chamber 5 containing the other propellant for the reaction comprises an axially slidable piston 8 controlling the flow of propellant through an orifice 7 from an inlet 6 to a distribution duct 2 having injectors 3. The piston 8 slides in a chamber 1a and has acting on its upper surface the pressure of the propellant immediately upstream of orifice 7 and on its lower surface the pressure of propellant tapped off from inlet 6 through passage 11 and restriction 12. The latter pressure is assisted by a spring 13 which holds a ball 16 against the push rod 18 of a bellows 19. The position of the ball 16 and hence the leakoff therepast to a discharge passage 17 is controlled by the pressure of an inert gas within the bellows 19. The gas is supplied to the bellows 19 through a passage 20 having a setting needle 21 and an electrically controlled leak-off 22, 22a. Thus adjustment of the leak-off 22, 22a controls the position of piston 8 and its tapered extension 8a and hence the flow of propellant through orifice 7 to distribution duct 2. A by-pass passage 9 around orifice 7 maintains a pilot flow of propellant to duct 2 when orifice 7 is fully closed. Each injector 3 comprises, Fig. 3, a frusto-conical cup 37 sliding on a central body 38 and held against a seat 40 by a spring 30. The seat 40 is open to the distribution duct 2 at 41 and is fixed thereto by a threaded sleeve 42. The cup 37 is urged off its seat when the propellant overcomes the force of spring 39. To provide a pilot flow of propellant into the combustion chamber 5, the injector 3 includes a central bore 44 in the body 38 to which propellant flows through drillings 47. A rod 43 with a frustoconical head 46 fits into the bore 44 to provide a pilot injection orifice 45 between the head 46 and the body 38. The size of the orifice 45 can be pre-set by nut 49 on the threaded end 48 of rod 43. The other propellant for the hypergolic reaction may be block surrounding the duct 2 and separated therefrom by a space 35, or a further liquid. Several rocket units (F1 to F8), Fig. 2 (not shown), each having the hypergolic reaction system described may be used to control the attitude of a space vehicle, the liquid propellant being a mixture of NO 3 H and N 2 O 4 . |
