RU2516711C1 - Staroverov's rocket propellant - 15 (versions) - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: rocket propellant comprises fuel and oxidiser. Rocket propellant features the following composition at the following ratio of components in wt %: beryllium borane - 34.63±10, ammonia dinitramide - 55.50±10, beryllium hydride - 9.87±5, or beryllium borane - 23.78±10, ammonia dinitramide - 76.22±10, or lithium borane - 35.85±10, ammonia dinitramide - 51.06±10, lithium hydride - 13.09±5, or aluminium borane - 23.66±10, ammonia dinitramide - 57.76±10, aluminium hydride - 18.58±5, or decaborane - 39.64±10, ammonia dinitramide - 60.36±10. Other versions are produced using the reaction with ammonia (wt %): beryllium borane - 44.61±10, ammonia dinitramide - 35.75±10, ammonia - 19.63±5. All said reactions can be realised with the help of the other oxidiser, that is, nitrogen hexaoxide, N₃O₆.

EFFECT: emission of pure hydrogen solely.

11 cl

Description

The invention relates to solid propellant and hybrid rocket engines.

Known rocket engines, see, for example, "Unpackaged engine with self-feeding", US Pat. No. 2431052. All existing chemical rocket engines use the principle of high-temperature heating of gas or a gas-dust working fluid (dust is solid fractions of decomposed solid rocket fuel). This is done in order to increase the flow rate of the working fluid from the jet nozzle. This speed is determined, firstly, by the speed of sound in the gas and, secondly, by the degree of expansion of the gas in the expanding supersonic jet nozzle and reaches 4000 m / s in the best engines. Moreover, engine parts operate in very intense thermal conditions, even taking into account their cooling.

Meanwhile, the speed of sound in hydrogen even at normal temperature and pressure of 1330 m / s. And if you also slightly increase the temperature of hydrogen, then the speed of sound in it and the speed of its outflow from the nozzle will increase sharply. For example, hydrogen with a temperature of only 650 ° C (this is below its ignition temperature) will have a sound speed of 2360 m / s and will be able to accelerate itself in the jet nozzle and disperse dust particles to a speed of about 4300 m / s. That is, a “cold rocket engine” is obtained in which, due to adiabatic expansion, the gas at the outlet of the jet nozzle can have approximately the ambient temperature.

This is the basis of the idea of this invention. The purpose of the invention is to increase the speed of a jet stream and the specific impulse of a rocket engine. To do this, the engine must produce pure hydrogen and solids. A suitable chemical reaction for this may be the triple reaction of beryllium borohydride, beryllium hydride and ammonium dinitramide:

$$2Be(BH\mathrm{four})2+NH\mathrm{four}N(NO2)2+2BeH2=\mathrm{four}BeO+\mathrm{four}BN+12H2\backslash \mathrm{one}\backslash$$

Intermediate reactions are possible: the formation of water, its reaction at such temperatures with beryllium and boron, the formation of ammonia, the reaction of it or nitrogen at such temperatures with boron oxide and the production of boron nitride. The ratio of components: beryllium borohydride - 34.63 ± 10%, ammonium dinitramide - 55.50 ± 10%, beryllium hydride - 9.87 ± 5%.

Possible reaction with boron oxidation:

$$Be(BH\mathrm{four})2+NH\mathrm{four}N(NO2)2=BeO+B2O3+2N2+6H2\backslash 2\backslash$$

The ratio of components: beryllium borohydride - 23.78 ± 10%, ammonium dinitramide - 76.22 ± 10%.

If the take-off trajectory passes over populated areas, then beryllium and its toxic compounds can be replaced with lithium or aluminum and their compounds.

$$\mathrm{four}LiBH\mathrm{four}+NH\mathrm{four}N(NO2)2+\mathrm{four}LiH=\mathrm{four}Li2O+\mathrm{four}BN+12H2\backslash 3\backslash$$

Although the structure of LiBH4 is likely to be Li2 (BH4) 2, so the previous reaction can be written as follows:

$$2Li2(BH\mathrm{four})2+NH\mathrm{four}N(NO2)2+\mathrm{four}Li=\mathrm{four}Li2O+\mathrm{four}BN+12H2\backslash 3\mathrm{but}\backslash$$

In any case, the ratio of components: lithium borohydride - 35.85 ± 10%, ammonium dinitramide - 51.06 ± 10%, lithium hydride - 13.09 ± 5%.

Or the same reaction with aluminum is possible:

$$\mathrm{four}Al(BH\mathrm{four})3+3NH\mathrm{four}N(NO2)2+\mathrm{four}AlH3=\mathrm{four}Al2O3+12BN+36H2\backslash \mathrm{four}\backslash$$

The ratio of components: aluminum borohydride - 23.66 ± 10%, ammonium dinitramide - 57.76 ± 10%, aluminum hydride - 18.58 ± 5%. The structure of aluminum borohydride is possible Al2 (BH4) 6.

The engine will be relatively low toxic:

$$2B10H\mathrm{fourteen}+3NH\mathrm{four}N(NO2)2=\mathrm{four}B2O3+12BN+\mathrm{twenty}H2\backslash 5\backslash$$

The ratio of components: decaborane - 39.64 ± 10%, ammonium dinitramide -60.36 ± 10%.

Possible reaction in a hybrid engine with increased specific hydrogen evolution:

$$\mathrm{four}Be(BH\mathrm{four})2+NH\mathrm{four}N(NO2)2+\mathrm{four}NH3=\mathrm{four}BeO+8BN+24H2\backslash 6\backslash$$

Reaction ratio: beryllium borohydride - 44.61 ± 10%, ammonium dinitramide - 35.75 ± 10%, ammonia - 19.63 ± 5%.

A reaction with complete or partial oxidation of the resulting hydrogen is also possible.

Theoretically, a stable compound N3O6 (hereinafter referred to as "nitrogen dioxide") has been discovered, and in practice, reactions with it are possible with it:

$$3Be(BH\mathrm{four})2+2N3O6=3BeO+3B2O3+3N2+12H2\backslash 7\backslash$$

The ratio of components: beryllium borohydride 29.61 ± 10%, nitrogen hexoxide - 70.39 ± 10%.

Or the same triple reaction using the available nitrogen:

$$3Be(BH\mathrm{four})2+2N3O6+6B=3BeO+3B2O3+6BN+12H2\backslash 8\backslash$$

The ratio of components: beryllium borohydride 26.02 ± 10%, nitrogen hexoxide - 61.86 ± 10%, boron - 12.12 ± 5%.

The same reaction will produce more hydrogen if tetraborane is added instead of boron:

$$\mathrm{fifteen}Be(BH\mathrm{four})2+10N3O6+3B10H\mathrm{fourteen}=\mathrm{fifteen}BeO+\mathrm{fifteen}B2O3+\mathrm{thirty}BN+81H2\backslash 9\backslash$$

The ratio of components: beryllium borohydride 24.91 ± 10%, nitrogen hexoxide 59.35 ± 10%, decaborane 15.74 ± 5%.

Or another triple reaction is possible, similar to the reaction \ 1 \:

$$3Be(BH\mathrm{four})2+2N3O6+9BeH2=12BeO+6BN+21H2\backslash 10\backslash$$

The ratio of components: beryllium borohydride - 23.26 ± 10%, nitrogen dioxide - 56.17 ± 10%, beryllium hydride - 20.20 ± 10%.

An interesting reaction in a hybrid engine with increased hydrogen evolution:

$$12Be(BH\mathrm{four})2+2N3O6+\mathrm{eighteen}NH3=12BeO+24BN+75H2\backslash \mathrm{eleven}\backslash$$

The ratio of components: beryllium borohydride - 44.34 ± 10%, nitrogen hexoxide - 26.39 ± 10%, ammonia - 29.27 ± 10%.

Claims (11)

1. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has a fuel with the following ratio of components in wt.%: Beryllium borohydride - 34.63 ± 10%, ammonium dinitramide - 55.50 ± 10%, beryllium hydride - 9, 87 ± 5%. 2. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has a fuel with the following ratio of components in wt.%: Beryllium borohydride - 23.78 ± 10%, ammonium dinitramide - 76.22 ± 10%. 3. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has fuel with the following ratio of components in wt.%: Lithium borohydride - 35.85 ± 10%, ammonium dinitramide - 51.06 ± 10%, lithium hydride - 13, 09 ± 5%. 4. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has fuel with the following ratio of components in wt.%: Aluminum borohydride - 23.66 ± 10%, ammonium dinitramide - 57.76 ± 10%, aluminum hydride - 18, 58 ± 5%. 5. Missile fuel containing fuel and an oxidizing agent, characterized in that it has fuel with the following ratio of components in wt.%: Decaboran - 39.64 ± 10%, ammonium dinitramide - 60.36 ± 10%. 6. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has fuel with the following ratio of components in wt.%: Beryllium borohydride - 44.61 ± 10%, ammonium dinitramide - 35.75 ± 10%, ammonia - 19.63 ± 5% 7. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has a fuel with the following ratio of components in wt.%: Beryllium borohydride 29.61 ± 10%, nitrogen dioxide 70.39 ± 10%. 8. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has fuel with the following ratio of components in wt.%: Beryllium borohydride 26.02 ± 10%, nitrogen dioxide - 61.86 ± 10%, boron - 12.12 ± 5%. 9. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has a fuel with the following ratio of components in wt.%: Beryllium borohydride 24.91 ± 10%, nitrogen hexane - 59.35 ± 10%, decaboran - 15.74 ± 5%. 10. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has a fuel with the following ratio of components in wt.%: Beryllium borohydride - 23.26 ± 10%, nitrogen dioxide - 56.17 ± 10%, beryllium hydride - 20, 20 ± 10%. 11. Rocket fuel containing fuel and an oxidizing agent, characterized in that it has fuel with the following ratio of components in wt.%: Beryllium borohydride - 44.34 ± 10%, nitrogen dioxide - 26.39 ± 10%, ammonia - 29.27 ± 10%.