Abstract: The present invention describes a hybrid rocket motor that includes a first solid reactant and at least one thrust nozzle and at least one moveable combustion control member within the hybrid rocket motor that restricts the contact of a first fluid reactant in the combustion chamber. In this way, it is then possible to regulate the exposure of the solid reactant to the fluid reactant and thus control thrust.

Abstract: This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomised and then ignited. The atomisation step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidisers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion whilst doing so.

Abstract: In order to make a drive device available on the basis of a gel-type propellant, in particular, for a flying object, comprising at least one tank for gel-type propellant, a combustion chamber and a device for supplying propellant to the combustion chamber, which is of a simple construction it is suggested that at least one radiation impinging device be provided for acting on gel-type propellant with electromagnetic radiation and/or at least one heating device for heating gel-type propellant in order to improve the flow behavior.

Abstract: A gas delivery system includes a gas booster module for delivering natural gas from a utility gas service to power generation equipment installed in or around a building in a manner that meets the minimum volume and pressure requirements of the power generation equipment. The gas delivery system advantageously uses pipe of a relatively small size for delivering gas to the power generation equipment, thereby substantially reducing installation costs and eliminating the need for a welded gas line. The gas delivery system also provides a control system that facilitates close control over the gas flow and ensures compliance with local building codes and safety regulations and requirements.

Abstract: In order to make a drive device available on the basis of a gel-type propellant, in particular, for a flying object, comprising at least one tank for gel-type propellant, a combustion chamber and a device for supplying propellant to the combustion chamber, which is of a simple construction it is suggested that at least one radiation impinging device be provided for acting on gel-type propellant with electromagnetic radiation and/or at least one heating device for heating gel-type propellant in order to improve the flow behavior

Abstract: Device in a burner for gas turbines, comprising a cylindrical housing (10) and a fuel inlet tube (16) arranged centrally within said housing, said housing (10) and fuel inlet tube (16) mutually defining an annular chamber (28). The annular chamber (28) extending into an extended diameter combustion chamber (18), having means (25) for supplying combustion air to said annular chamber (28). Radial flow swirlers (14) are provided for creating a rotational movement of the combustion air in said annular chamber. The housing (10) has a downstream restriction (20) in front of the free end of the centrally located fuel inlet tube (16), at the entrance of the combustion chamber (18), for creating a rich combustion spinning tubular swirl dominated flow of a mixture of air and fuel, with a recirculation central core, said tubular spinning flow extending into the combustion chamber (18).

Abstract: A high density inhibited red fuming nitric acid oxidizer gel is disclosed ich results in an improvement from 0.5% to about 1.0.% in the impulse over a baseline formulation containing 14% nitrogen tetroxide. An improvement from about 3.0% to about 6.0% is achieved in the density impulse baseline formulation. The higher density inhibited red fuming nitric acid is derived by adding from about 15 percent by weight to about 45 percent by weight percent of nitrogen tetroxide to nitric acid in an amount from about 80 percent by weight to about 40 percent by weight. The other ingredient of the oxidizer gel comprise a gellant of about 0-10 percent by weight, water from about 0-4 percent by weight, and an inhibitor agent of about 0-1 percent by weight. IRFNA is inhibited with phosphoric acid, iodine compounds, or hydrogen fluoride which is present in the oxidizer gel as an additive.

Abstract: Elemental silicon is a solid high energy material which provides an advane when added to gel, hybrid, and ducted rocket fuels by increasing both specific impulse, lsp, and density specific impulse, .rho.*lsp. The quantity added depends on the specific applications for which the formulation will be used. The usual concentration ranges from about 0.5% to about 70% by weight. The important parameters to consider during formulation are particle size, concentration, combustion efficiency, physical properties, and plume signature. Comparisons for 50% solid fuel loading in a gel bipropulsion system predicts a maximum lsp of 286 lbf.s/lbm as compared to 267 lbf.s/lbm for carbon--a 7% increase. The .rho.*lsp produced by silicon is 14.5 lbf.s/cubic inch as compared to 13.7 lbf.s/cubic inch produced by carbon--a 7% increase. A 25% solid loading in solid fuel-gas generators for the hybrid rocket produced a maximum lsp of 278 lbf.s/lbm as compared to 267 lbf.s/lbm produced by carbon--a 4% increase. The .rho.

Abstract: A pressure controlled pintle is employed in combination with a throttling quid, gel, or hybrid engine to provide a constant pressure and variable thrust from a single operating engine. As the propellants are throttled back and the chamber pressure drops, the pintle moves and closes the gap between the pintle and nozzle throat, thereby lowering the throat area and re-establishing the design chamber pressure related to pintle spring tension. By retaining the design pressure over a wide thrust range, the engine efficiency remains at the design value. This eliminates the drop of Isp due to pressure and keeps the cost of the system reasonable because only one engine is required. When a higher thrust is desired, a throttling valve in an injector increases the propellant flow rate, which causes a higher pressure in the combustion chamber. The constant pressure actuator moves the pintle to open the nozzle throat, which reduces the pressure to the design value. The design value may not be optimum.

Abstract: A propulsion system is disclosed comprising a glycidyl azide polymer (GAP) olid fuel generator (SFGG) that produces fuel-rich hot gases which are combusted in a combustion zone of a combustion chamber of a solid fuel ducted rocket. A basic embodiment comprises an airbreathing engine wherein a ducted member scoops air in from the atmosphere for hypergolic reaction with the fuel-rich hot gases for propulsion during a sustain stage of a flight. An augmentation of the basic embodiment is achieved by combusting the fuel-rich GAP SFGG effluent with inhibited red fuming nitric acid (IRFNA) gel oxidizer to produce higher thrust during the boost and dash stages of a flight. During the high thrust stages, the air ducts of the ducted member are closed and IRFNA gel is injected into the combustion chamber to react with the fuel-rich hot gases from the GAP SFGG.

Abstract: A gel/solid bipropellant propulsion system employs fuel-rich combustion gs from a solid gas generator and an oxidizer gel in a highly efficient combustion chamber wherein the fuel-rich combustion gases and the oxidizer gel are each metered through a vortex injector into a combustion chamber to produce a hypergolic reaction. The solid gas generator (SSG) has a preferred composition of glycidly azide polymer (GAP). The GAP SSG is composed of GAP diol and/or triol polymerized with a di-or tri-function isocyanate, such as isophorone diisocyanate. The gel/solid bipropellant propulsion system comprises the SSG in combination with an oxidizer storage/extrusion vessel system, a combustion chamber system, and a system controller which controls initial ignition of the SSG to produce fuel rich combustion gas which pressurize the system. The system controller monitors pressures and flow rates of fuel and gel oxidizer.

Abstract: A control system for supplying uncured propellant into the combustion char of a missile. The system includes a moving injector cooperating with a pressurized putty-like uncured propellant. This combination provides the missile with a propulsion system having rapid wide range throttling, shut off and restart capabilities.

Abstract: Slurried rocket propellants and a spinning rocket motor wherein the propents have viscosities which enable them to form central cores when spun in spinning rocket motors, the motor having a diaphragm-like base plate which assists in transferring forward momentum through the propellant.

Abstract: An improved projectile suitable for use in artillery pieces, though preferably in the higher calibres, is disclosed wherein projectile range upon launching by the gun is considerably extended by means of a propellant rocket motor in combination therewith which motor is characterized by containing in its combustion chamber a flowable propellant charge in the form of a fluidizable, shapeable propellant charge composition which under the high radial acceleration forces imparted to the projectile when fired from a rifled gun barrel, flows and shapes itself into the shape of a hollow cylinder and, when ignited in flight, burns in the manner of a solid propellant grain of the same shape to aid in propelling the projectile a greater distance than is possible with the gun alone.