166 results about "Rocket propellant" patented technology

An oxidizer package for a propellant system for a motor in which the oxidizer is separated from fuel grain, the oxidizer package comprising oxidizer material and an ignition system therefor in a wrapping or sealing material. A hybrid rocket comprising oxidizer material and fuel grain, the oxidizer material being separated from the fuel grain and being in the form of a single package or plurality of packages of oxidizer material and an ignition system therefor, said packages generally conforming to the shape of the rocket. A grid of a pyrotechnic material. A propulsion system for a hybrid rocket comprising oxidizer material in a matrix, mesh, wool, foamed metal or wires of structural or pyrotechnic material.

The invention relates to a ferrocene high-nitrogen ionic compound and a preparation method thereof. The structural formula of the compound is disclosed as Formula (1), wherein X is C or N; R is C[m]H[2m+1], and m is 1-16; and Y<-> is N[3]<-> or [N(NO[2])[n](CN)[2-n]]<-> (n is 0-2), or [C(NO[2])[n](CN)[3-n]]<-> (n is 0-3), or high-nitrogen heterocyclic anion or polynitrophenol anion or di-tetrazole anion. Since anions and cations have Coulomb electrostatic interaction, the ferrocene high-nitrogen ionic compound has the advantages of high heat stability and high catalytic performance, and can be used as a catalyst in a rocket propellant; the ferrocene high-nitrogen ionic compound has low steam pressure and is nonvolatile under natural conditions, and therefore, can solve the problems of high migration tendency and high volatility of the existing ferrocene combustion regulator in the propellant; and meanwhile, the synthesis method is simple and easy to implement, has the advantage of low cost, and is applicable to industrialized application.

The invented method for measuring the health of a solid rocket propellant includes embedding at least one piezoelectric capacitance sensor in the propellant, where the capacitance of the sensor is a function of a modulus of the propellant, and where the position is selected to measure manifestations of stress failure as a consequence of changes in the shear modulus. The capacitance of the sensor is measured at a predetermined frequency. The capacitance of the piezoelectric capacitance sensor is converted into a digital representation which is then converted into the digital representation of a modulus (or gradient modulus). In subsequent analysis, the modulus (or gradient of the modulus) is correlated to the health of the solid rocket propellant.

A propellant is disclosed, comprising, as binder, an ethylene copolymer especially ethylene/vinyl acetate copolymer. The binder may be silane-grafted and moisture curable. A solid propellant composition may contain a plasticizer that is solid or semi-solid at 20° C., and an additive to increase one or more of elongation, adhesion and tack. Examples of the solid or semi-solid plasticizer are selected from microcrystalline wax, macrocrystalline wax, an oxidized hydrocarbon polyolefin and a polyketone wax. Examples of the additive are selected from an aliphatic hydrocarbon, an aromatic, a hydrogenated hydrocarbon resin and a derivative of a rosin. Preferably, the binder composition contains 10-30% by weight of liquid plasticizer, 0-30% by weight of solid or semi-solid plasticizer and 20-40% by weight of at least one said additive. The propellant is particularly useful as a rocket propellant. A method of manufacture is disclosed.

The invention is a composition for a high burning-rate solid rocket propellant, where the composition includes a binder compounded with a soluble energetic additive; a metallic fuel; and an oxidative fuel. The resulting composition has a tactical Class 1.3 hazard rating, and a linear regression rate that is substantially equivalent to a tactical Class 1.1 hazard rating obtainable using solid rocket propellants. The composition may include a heat-conducting element, a plasticizer, a curing component, a combustion catalyst, and curing catalyst.

Propellant management systems and methods are provided for controlling the delivery of liquid propellants in a space launch vehicle utilizing multiple rockets. The propellant management systems and methods may be configured to enable substantial simultaneous depletion of liquid propellants in each of a plurality of active rockets during operation of various booster stages of the launch vehicle.

The invention provides a type of aliphatic diisocyanate with a novel chemical structure, which is C21-36 aliphatic diisocyanate, has the same excellent performance with other traditional aliphatic isocyanates, and is used for preparing polyurethane varnish, coating, elastomer, adhesive, textile finishing agent, rocket propellant and the like. The invention also provides a preparation method of this type of substance, which comprises the following steps that: (a) unsaturated dicarboxylic acid with a special structure or the ester solution thereof are catalyzed and hydrogenised to prepare saturated diacid; (b) the saturated diacid is dissolved into inert solvent and added with chloride agent to react and prepare binary acid chloride; (c) sodium azide is added in to react and prepare the corresponding azide; and (d) the azide is isomerized and decomposed to prepare an aliphatic diisocyanate crude product. The method is characterized by lower condition requirements, safety, environmental-friendliness, fewer side effects, high yield and easy wide popularization in industry.

The invention discloses four brake rockets and brake systems for motor vehicles, and relates to the technologies of machine manufacturing and jet propulsion. In the invention, a single component liquid rocket, a dual component liquid rocket, a solid rocket and a solid-liquid mixed rocket, and six motor vehicle brake systems respectively formed by the four rockets are provided; and the original delivery system is eliminated, when emergency braking is required, the brake rocket is started immediately and responds quickly in centiseconds, and a rocket propellant rapidly burns to generate high-pressure high-temperature gas which is jet out at high speed from a tail pipe, so that a powerful thrust is erupted to counteract the inertia force of a vehicle, shorten the prints of tires, reduce traffic accidents and improve the safety of the vehicle. The rockets and brake systems for motor vehicles are suitable for long distance coaches, large trucks, sport utility vehicles, tool vehicles, motorcycles, electric vehicles, hybrid electric vehicles, special vehicles, various cars, pickup trucks, racing cars, tricycles for agricultural use and quadricycles for agricultural use, and are especially suitable for various vehicles which need to be driven for a long distance and driven on mountain roads.

The invention discloses an integrated propellant supply system of a rocket based combined circulating engine. The integrated propellant supply system consists of a liquid oxygen path supply system, a kerosene path supply system and a fuel gas system; the liquid oxygen path supply system provides an oxidant for the engine; the kerosene path supply system provides fuels for the engine; the fuel gas system provides turbine driving fuel gas for a turbine; and the liquid oxygen path supply system and the kerosene path supply system are symmetrically arranged with respect to a fuel gas generator 14. The supply system takes a fuel gas generator circulating system with a simple structure as a basic structural form for discharging the turbine driving fuel gas into a low-pressure ramjet flow path to carry out complementary combustion, so that an engine complementary combustion circulating system with a relatively simple structure and excellent performance is formed; moreover, the system has a large range of regulating capacity, and also meets supply needs of a main rocket propellant and engine secondary fuels of the rocket based combined circulating engine. The propellant supply system increases an energy utilization rate and improves engine performance, and can be used for wide-envelop multi-mode RBCC engine system integrating.

The invention relates to energy and environment filed, and discloses a nano nickel fuel oil additive. The nano nickel fuel oil additive comprises the following raw materials by weight percent: 0.3%-0.8% of metal nickel nano powder, 5%-10% of methyl tert-butyl ether, 10%-15% of C5 alcohol, 5%-10% of C6 alcohol, 53.2%-72.7% of methyl alcohol, 5%-8% of rocket propellant and 2%-3% metal oxide or metal inorganic salt. The nano nickel fuel oil additive can be applied to various fuel oil such as gasoline, diesel fuel, blended fuel oil, heavy oil, bio-oil and the like, and can be widely applied to automobiles, heavy vehicles, trains, steamships, boilers and the like. The nano nickel fuel oil additive has good catalytic and cracking effects and can enable fuel oil to burn completely and evenly, thereby improving unit fuel oil calorific value so as to achieve optimum burning effect, decreasing pollution emission, clearing carbon deposition in an engine, increasing motive power, lowering noise, and achieving energy saving and emission reduction effects.

An invented apparatus for nondestructively remotely measuring the health of an energetic material, includes a piezoelectric capacitance sensor having an exterior surface that is substantially inert to the energetic material. The piezoelectric capacitance sensor provides an analog signal that is commensurately responsive to the modulus of material in intimate contact with the sensor. The apparatus also includes an interrogator for interrogating the sensor as to a capacitance of the piezoelectric capacitance sensor. The interrogator converts the analog signal of the capacitance into a digital representation. The apparatus further includes a means of communicating the digital representation to a remote communication device.

The invention discloses a fullerene ethylenediamine nitrate as well as a preparation method and an application thereof. Firstly, fullerene C60 and ethylenediamine are taken as raw materials, fullerene ethylenediamine is prepared by the aid of a nucleophilic addition principle, and the fullerene ethylenediamine reacts with nitric acid so that the fullerene ethylenediamine nitrate is obtained. The fullerene ethylenediamine nitrate has the advantages of oxidant ammonium nitrate (AN), can avoid disadvantages of hygroscopicity, and crystal transformation of AN, and can be used as an oxidant to be applied in a novel solid rocket propellant or explosive.

The invention discloses a method for preparing aluminum nanoparticles coated with dispersion stabilizers by a liquid-phase chemical reduction method. The method is characterized by including: purifying commercially available mesitylene; dispersing aluminum chloride in the mesitylene; and in the presence of nitrogen, adding polyethylene glycol or polyethylene glycol dimethyl ether serving as the dispersion stabilizer and lithium aluminum hydride in the mesitylene dispersed with the aluminum chloride according to the mass ratio of 1-2.5:0.5-1:0.5-1 among the aluminum chloride, the lithium aluminum hydride and the dispersion stabilizer, stirring for reacting 12-24 hours at the temperature of 164-166 DEG C, cooling, performing centrifugal separation, abandoning supernatant liquid, removing residual mesitylene solvents, washing by low-temperature methyl alcohol, performing ultrasonic washing and centrifugal separation, abandoning supernatant liquid and performing vacuum drying for lower materials so that the aluminum nanoparticles coated with the dispersion stabilizers are obtained. The prepared aluminum nanoparticles coated with the dispersion stabilizers are uniform in size and good in dispersity, have certain activity and are applicable to the fields of rocket propellants, explosives and powders, solar back plates and the like.

The invention relates to fullerene poly(glycidyl nitrate), a preparation method and an application thereof, wherein the fullerene poly(glycidyl nitrate) has the chemical structure formula represented by a formula (I). The invention further relates to the preparation method, which comprises: adopting monomethyl-terminated poly(glycidyl nitrate) (PGN) and malonyl chloride as raw materials, carrying out the esterification and bromination two-step reaction to prepare bromomalonate dipoly(glycidyl nitrate), and reacting with fullerene to prepare the fullerene poly(glycidyl nitrate). According to the present invention, the fullerene derivative can be used in the solid rocket propellant as a novel energetic combustion catalyst; and experiment results prove that the product yield can be 82%, and the platform combustion rate can be increased by 65% while the pressure index is reduced to 0.21 when the product of the present invention is applied in the solid propellant as the novel combustion catalyst. The formula I is defined in the instruction, wherein n is 2-20.

The invention provides a dynamic testing device and a dynamic testing method for a burning speed of an initiative laser type solid rocket propellant. The dynamic testing device comprises a laser emitting part, a photovoltaic conversion part and a signal processing part, wherein the laser emitting part comprises a laser emitting unit and a laser slice light converting unit; the photovoltaic conversion part is used for receiving the transmission light of the laser slice light passing through the powder strip and converting a light signal of the transmission light into an electric signal; the signal processing part is used for processing the electric signal, acquiring the data corresponding to the electric signal and acquiring the burning speed of the powder strip on the basis of the data; the photovoltaic conversion part comprises a plurality of photovoltaic conversion units which are arranged longitudinally and in parallel with the powder strip; the photovoltaic conversion units are parallel to each other and are vertical to the powder strip. The burning speed of the propellant can be dynamically acquired by recording the condition of the change in mutational site of the transmission light signal along with the time after the powder strip is ignited. The dynamic testing device and dynamic testing method for the burning speed of the initiative laser type solid rocket propellant provided by the invention can overcome the defects of easiness in being influenced by pressure and low test precision of a photoelectric method and have the advantages of simple structure, non-contact mode and high test precision.