Ballistic solid rocket propellant

FIELD: explosives.

SUBSTANCE: ballistic solid rocket propellant includes combustion modifying agent which consists of lead copper complex of phthalic acid or nickel lead complex of phthalic acid as combustion catalyst, chrome (III) - copper (II) - oxides or dioxides of titanium, or titanium disilicide, or calcium carbonate as combustion stabiliser, technical carbon and 1,2-dibutoxybenzol. Combustion catalyst is included in the propellant in quantity of 1.5-4.0 wt %, combustion stabilising agent 0.4 - 3.0 wt %, technical carbon 0.1 - 1.0 wt %, 1,2-dibutoxybenzol - 0.5 - 2.0 wt %.

EFFECT: low dependence of propellant combustion velocity on pressure, and increased propellant chemical durability.

1 tbl

 

The invention relates to the development of ballistic solid rocket fuels (BTRC) to the different systems of rocket technology (Pturs and others).

During the development of solid rocket propellant ballistic type as energy supplements are used, mainly, HMX, RDX, dazin, substance C-2, metal powders of aluminum, magnesium or mixtures thereof. The introduction of these additives in the composition of fuels leads to a significant increase of the index ν in the act of burning speed to 0.6 to 0.8. The conventional catalytic additives in ballistic fuels - lead-copper, lead, Nickel compounds, lead compounds, copper, cobalt and others with various organic ligands (Patent RU 2191765, 2189371, 2179165) does not achieve the desired measure ν is not more than 0.3 in the operating pressure range of 80-120 kg/cm2. Known modifier burning speed ballistic fuels under the patent 2140945 from 10.11.1999 g, IPC SW 47/02, which is used to provide a high dependence of the rate of combustion pressure (a measure ν to 0.9).

As a prototype made fuel for patent 2191765 from 27.10.2007 g, IPC SW 25/22, 06D 5/06, in which the modifier of combustion is lead-copper complex phthalic acid (FMS), carbon black and calcium carbonate. To ensure a high level of energy in the composition HMX.

An object of the invention is to develop a modifier of combustion for BTRT, providing small dependence of the rate of combustion pressure.

The technical result of the invention is achieved through the use of a modifier consisting of a lead-copper (FMS) or lead-Nickel (FTS) complex phthalic acid, carbon black, 1,2-debutante, chromium(III)-copper(II) oxide, or titanium dioxide, or titaniun disilicide, or calcium carbonate in combination with a useful ratio of components BTRT.

The proposed combustion modifier is a mechanical mixture of the components in the following ratio, wt.%:

FMS or
FTS1,5...4,0
Carbon0,1...1,0
1,2-debutaniser0,5...2,0
Chromium(III)-copper(II)oxide or
titanium dioxide or disilicide
titanium or calcium carbonate3,0 0,4...
Fuel rest

Patentable invention is illustrated in the examples in the table.

95,4
Name of indicatorThe placeholderOBROBROBROBROBROBR
FMS1,5-4,21,54,0----
FTS---1,54,03,02,0
Carbon0,2-1,10,70,11,00,50,80,7
1,2-debutaniser-2,00,5 1,01,51,31,5
Calcium carbonate0,4-2,30,4-----
Titanium dioxide--2,0-1,0--
Titanium disilicide-----2,0-
Chromium(III)-copper(II) oxide---3,0--0,4
FuelRest95,4for 93.493,593,092,9
The index ν in the act of burning0,2-0,73Minus 0,090,220,120,150,130,1
The rate of outgassing At 100°C, cm3/GC0,0420,060,0460,051being 0.0360,055
A single impulse, J1kg·s/kg RK/RA=40/1 kgf/cm2213-220,9220,8219,9220,0219,8to 219.5220,5

The given examples show that the introduction of an additional component modifier - 1,2-debutante greatly reduces the dependence of the rate of combustion pressure within the operating range for rocket technology products. The mechanism of reducing the dependence of the rate of combustion pressure is to improve the quality of distribution of a basic catalyst combustion FMS or FTS in the fuel mass due to its h is a partial dissolution in 1,2-debuttanti and distribution of mass in the form of a solution at the molecular level. The solubility of these components in 1,2-debuttanti in the temperature range 20...50°C is:

FMS - 12 g/l, FTS - 22 g/l (according to the FSUE "December").

An additional positive effect of the proposed integrated modifier is to provide high chemical resistance, implying a smaller 1.5-3.0 times the speed of gas when heated at 100°C, which leads to increase the warranty period of storage of the compositions containing the specified modifier.

Ballistic solid rocket propellant containing a combustion modifier, wherein the modifier of combustion consists of a lead-copper complex phthalic acid or lead-Nickel complex of phthalic acid as a catalyst combustion, chromium (III) - copper (II) oxide or titanium dioxide, or titaniun disilicide, or calcium carbonate as a stabilizer of combustion, carbon black and 1,2-debutante, and the catalyst combustion is contained in the fuel in an amount of 1.5-4.0 wt.%, the stabilizer combustion of 0.4 to 3.0 wt.%, carbon black 0.1 to 1.0 wt.%, 1,2-debutaniser 0.5 to 2.0 wt.%.



 

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