Abstract: In an integral rocket-ramjet having a combustor which initially serves as a rocket combustion chamber for booster propellant, and after the booster propellant is expended, serves as a ramjet combustor where fuel and air are burned, a fuel control system is described for the ramjet stage by which ram burner light-off is automatically initiated upon transition from rocket to ramjet propulsion. The fuel control regulates fuel flow to the combustor over the entire flight regime and responds to operating conditions to provide a light-off schedule, to stabilize the shock wave in the air inlet, to provide a maximum fuel-to-air ratio limit, to limit the maximum vehicle Mach number, and to prevent lean burner blowout by providing a minimum fuel-to-air ratio limit. Mach number limiting is performed in closed loop fashion, while the other functions are scheduled or open loop controls.

Abstract: A device for joining the two stages 2 and 3 of a self-propelled engine comprises means for achieving the separation of the two stages 2 and 3 after the combustion of the pyrotechnic charge 12 of the rear stage 2 is completed, means for carrying out the ignition of the pyrotechnic charge 19 of the front stage 3.A rear part of the front stage 3 and a front part of the rear stage 2 are assembled together for sliding axial movement therebetween. A temporary connection breakable under the effect of the ignition of the rear stage 2 maintains a predetermined spacing e between the two stages. The front stage 3 includes means 22 and 23 for igniting, after a predetermined delay, a pyrotechnic charge 19 of the front stage 3 and the rear stage 2 includes means 29 for triggering the igniting means after said temporary connection is eliminated.

Abstract: The invention relates to a combustion chamber of a ramjet and booster rocket, which comprises an inner envelope provided with upstream lateral ports for the inlet of air and a downstream nozzle for ejecting the combustion gases, to allow functioning of the rocket at cruising speed; an outer envelope, concentric to the inner envelope and closed, with the exclusion of a single rear port for the ejection of the gases, to allow functioning of the rocket at launching speed; and separating means for separating from the combustion chamber at least a part of the outer envelope, at the end of the launching phase, in order to ensure the clearance of the upstream lateral ports of the inner envelope.

Abstract: Protectors for certain elements such as fuel injectors and flameholders used in conjunction with the ramjet phase of an integral rocket ramjet.In the preferred embodiment slip-on caps of a high temperature material such as graphite are used to protect the fuel injectors and flameholders. The caps are installed and the solid boost propellant packaged about them. Following boost burnout the initial fuel pressurization for transition to ramjet operation would remove the caps allowing operation in a ramjet mode.

Abstract: A sensor for rocket engines having at least one combustion chamber including a pressure-sensitive sensing device responsive to pressure in the combustion chamber for providing an output signal to a control device in response to the pressure in the combustion dropping below and/or rising above at least one predetermined pressure. The pressure-sensitive sensing device includes a piston arranged for displacement between first and second positions. The piston is displaceable from at least the first position to the second position in response to a first predetermined pressure value in the combustion chamber. A restoring force is effective for displacing the piston from the second position toward the first position in accordance with a second predetermined pressure value in the combustion chamber. The piston is arranged for triggering a signal in at least one of the first and second positions thereof.

Abstract: A rocket motor grain consisting of a one-piece solid base propellant divided into an aft end section having a central cavity extending throughout its length, a forward end section having a central longitudinal cavity filled with a propellant having a substantially higher burning rate than the base propellant and a central web section being defined between the forward and aft end sections. This radial end burning rocket motor grain provides a means for utilizing high energy and high density propellants which have high burning rates in a manner such that the burning rate effects can be offset to provide enhanced motor performance without the sacrifice of high energy. After initiation of the rocket motor grain, the aft end section and central web section begin burning together to provide the desired mass flow rate, followed by initiation of a higher burning rate propellant in the forward section.

Abstract: A missile is initially propelled through space by the burning of solid fuel in a combustor. The heat produced by the combustion of such fuel is used to vaporize a liquid, the pressurized vapor being used to pump liquid fuel to the combustor after the solid fuel has been depleted.

Abstract: A plug for closing an opening in a partition between rocket motor chambers is made in segments and will resist a relatively high pressure differential between the chambers in one direction but will unblock the opening in response to a relatively low pressure differential between the chambers in the other direction.

Abstract: A barrier system for use in preventing the pre-ignition of second pulse rocket grains in a dual pulse rocket motor. The system includes two double layers of rubber material positioned between the first and second pulse grains with an igniter assembly adjacent to the second grain.

Abstract: A partition arrangement for rocket motors with at least two mutually independent thrust stages and nozzle and nose sides. The partition arrangement includes a partition member separating a combustion chamber on the nozzle side from another chamber on the nose side with the partition member being provided with at least one flow aperture therein. A sealing element is disposed on the nozzle side for sealing the at least one flow aperture of the partition member with the sealing element being displaceable for freeing the at least one flow aperture of the partition member and being maintained within the another chamber on the nozzle side upon displacement. At least the partition member and/or the sealing element is provided with only one flow aperture for permitting propellant gases from the nose side combustion chamber to enter the another chamber on the nozzle side only in a central direction.

Abstract: Four embodiments of high-thrust rocket engines, each having separate propellant delivery apparatus for each propellant to be delivered to the engine thrust chamber, are illustrated herein. One engine is designed to provide a high thrust using only one fuel and one oxidizer. The other three engine embodiments are all designed to use different propellants having different densities during different portions of a rocket flight. Each of these additional engines includes the basic structure of the first. The first engine is thus not only an effective engine, but also a building block that can be easily modified to provide an engine capable of operating effectively with different propellants.

Abstract: A combination injector/port cover for a solid fuel ramjet (SFRJ) having a be-in-hole injector which uses two seals to lock the tube into the air inlet and injector port during the boost phase, and which moves the tube into the combustion chamber during transition to the sustain phase.

Abstract: An emergency hydraulic power system for aircraft which becomes operable upon aircraft engine failure includes a hot gas turbine for driving a hydraulic pump, a decomposition chamber to provide hot gas for driving the turbine, a normally unpressurized fuel storage tank, and a fuel pump for delivering fuel from the tank to the decomposition chamber. A start system includes a start fuel bottle having a cell filled with fuel and provided with a movable wall, and a cylinder of gas under high pressure which is regulated to put intermediate pressure on the movable wall and expel fuel from the cell, and also to put low pressure on the fuel tank, after a start valve is opened. Both the fuel tank and the start fuel cell communicate with an inlet conduit which goes to the fuel pump inlet, and a valve is provided to prevent start fuel from going into the fuel tank; and there is also means normally blocking communication from the start bottle and the tank to the pump inlet.

Abstract: A passive chamber wall fragmenter adapted to be mounted on or in connection with a portion of a chamber wall which is mounted to be dislodged by a pressure differential across the wall portion, wherein the fragmenter is adapted to become active upon displacement of the wall portion to cause the displaced wall portion to fragment or break up into small pieces so as to minimize damage that might result from larger pieces striking sensitive structure making up the chamber.