Abstract: An explosively driven latch-and-seal device for latching and sealing the ends of two telescoping members, such as a fixed nozzle section 14 and an extendible nozzle section 16 of a rocket engine. The forward end of the extendible nozzle 16 is formed with an axially extending flange 24. The rear end of the fixed nozzle 14 is formed with a radially extending projection 18 which has a recess 20 in its outer surface adjacent to the extendible nozzle flange 24. An explosively expandable tube (EET) 30 containing a mild detonating fuse (MDF) 32 is placed in contact with the flange 24 in such position with relation to the recess 20 that, when the MDF 32 is detonated, it expands to force the flange section in contact with it into the recess 20. A seal is formed between the deformed section of the flange 24 and the wall of the recess 20.

Abstract: An apparatus and method for deploying and forming a rocket engine nozzle extension 10. A pneumatic bag 18 within the fixed nozzle 14 of a rocket engine is inflated to push and unfold the nozzle extension 10. The nozzle extension 10 is of the type which attaches to the end of the fixed nozzle 14 and is turned inwardly toward the central axis of said fixed nozzle 14 and folded along creases so that prior to it being extended the nozzle extension 10 is in a stowed configuration inside the fixed nozzle 14. After the nozzle extension 10 is completely formed, pneumatic bag 18 may be jettisoned by firing the rocket engine or by a mechanical releasing mechanism.

Abstract: A method for forming small-diameter, angled ducts and manifolds in a face plate for a rocket-engine injector or the like. A surface of a circular base plate 16 is formed with an annular flange 18 thereon having two inwardly sloping sides 11 and 13. Grooves 20, 22 are machined along the intersections of the sides 11 and 13 with the surface of the base plate 16 for propellant-containing manifolds 36 and 38. Grooves 10 are etched in spaced sets of two down the sloping sides of the flange from the flange top 24 to the manifold grooves 20,22. The grooves 10, 20, 22 are filled with wax 23 and a layer 26 of metal is electrodeposited over the grooved surface of the base plate 16 to cover the top 24 of the flange 18, the deposited layer forming orifice ducts and propellant manifolds from the grooves. This layer 26 is machined down to a depth at which the orifice ducts 34 are exposed so that orifices 12 appear at the surface 30 of the machined layer. The wax 23 is now removed by heat or a solvent.

Abstract: An ultrasonic diesel fuel injector comprises an injector body including a means for flowing fuel through the injector body, a check valve located within the means for flowing fuel, and a means for ultrasonically vibrating the check valve.

Abstract: A propellant injector for a liquid rocket engine has an injection cylinder and moving piston in the cylinder. The cylinder on one side of the piston opens into the combustion chamber of the engine. The other side of the piston has a coaxial tubular portion projecting therefrom. A pair of valve members have concentric sleeves slidably mounted respectively on the inside and outside surfaces of the tubular portion of the piston. The outer ends of the concentric sleeves and tubular portion extend through an end wall of the injection cylinder. The valves open and close passages extending through the piston by relative axial movement of the sleeves and the piston. Pneumatic actuator means, connected to the outer ends of the sleeves and tubular portion, moves the sleeves axially relative to the piston to open the valves and move the piston toward the end wall of the injection cylinder to force propellant through the passages into the combustion chamber.

Abstract: The injection piston of a regenerative liquid propellant gun is attached to a second piston that has a programmed hydraulic resistance which controls its motion, thus the propellant injection rate from the injection piston and the burning rate of the injected propellants is controlled to provide better propellant pressure-time burning characteristics.