RU2378525C1 - Solid propellant rocket engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention is related to the field of rocket engineering, namely to solid propellant rocket engines, mostly to assisted takeoff and cruise engines of cruise missiles, tactical missiles, and also to multiple artillery rocket systems. Solid propellant rocket engine comprises body, nozzle block, strongly fixed charge, igniter with perforated body, filled with pyro composition in the form of lead charge and pellets. Perforation in body is arranged in the form of cells. Between lead charge and pellets there is a ring installed, which has diametral link arranged in cross section in the form of triangle and directed with one of its tops towards lead charge. Triangle base makes 0.3-0.5 of pellet diametre. Pellets are arranged around cylindrical gas supply tube, length of which makes 0.7-0.9 of pellet length.

EFFECT: invention makes it possible to provide for high reliability of rocket engine operation and simultaneous ignition of the whole surface of solid propellant charge.

4 dwg

Description

The invention relates to the field of rocket technology, namely to solid propellant rocket engines (solid propellant rocket engines), mainly to cruise missile launch and propulsion engines, tactical missiles, and also to multiple launch rocket engines.

A known design of a solid propellant solid propellant rocket motor containing a housing with a recessed nozzle, a charge with a blind channel, an ignitor mounted on the recessed part of the nozzle, consisting of a housing filled with pyrosuspipe in the form of a tubing ring with perforations from holes directed into the channel and additional perforations in the form of holes directed into the zone pairing of the burning end and the charge channel - patent RU 2313685, IPC F02K 9/95 04/13/2006. The disadvantage of the rocket engine under consideration is that an engine of this design with a local direction of the flame force in the interface zone of the burning end and the channel will have a prolonged, unstable output to the calculated mode.

A known design of a solid propellant solid propellant rocket engine containing a housing, a nozzle, a charge of solid fuel, an ignition device in the form of a solid propellant micromotor with a perforated housing, a section of the nozzle-hole of the igniter is separated from the charge surface at a distance of 2-8 equivalent nozzle-hole diameters, and the angle of inclination of the nozzle-hole to flammable surface is not less than 45 ° - patent RU 2258151, IPC F02K 9/95, 9/30, 12.30.2003. The disadvantage of this solid propellant rocket motor is that the micromotor ignites a local portion of the surface of the charge combustion, does not simultaneously ignite the entire burning surface of the charge.

In both cases, in the presence of a developed combustion surface due to the presence of gap compensators, the proposed structures will not ignite the entire combustion surface.

As a prototype, the authors chose patent RU 2313685, IPC F02K 9/95, published December 27, 2007, s. 2006112363 from 04/13/2006.

The technical task of the present invention is to provide quick access to the calculated mode due to the simultaneous ignition of the entire burning surface of the charge.

The technical result is achieved by the fact that in a solid propellant solid propellant rocket engine containing a housing, a nozzle block, a strongly bonded charge, an igniter with a perforated housing filled with a pyrocomposition in the form of a transfer charge and checkers, perforation in it is made in the form of cells, and in the end face directed to the nozzle, a central a hole exceeding the size of the perforation, between the transfer charge and the checkers placed a ring having a diametrical bridge made in cross section in the form of a triangle and directed one of the vertices towards edatochnogo charge and the base of the triangle is 0.3-0.5 diameter checkers, the checkers are arranged around a cylindrical tube gazovodnoy whose length is 0.7-0.9 checkers length, and the rear end gazovodnoy tube interfaced with the central opening of the housing.

The invention is illustrated by drawings.

Figure 1 - General view of a rocket engine of solid fuel, where:

1 - housing; 2 - nozzle block; 3 - a strongly bonded charge; 4 - igniter.

Figure 2 - igniter, where:

5 - perforated housing with a Central hole; 6 - transfer charge; 7 - ring with a diametrical jumper; 8 - checkers; 9 - gas tube, 10 - pyrocomposition.

Figure 3 - the location of the pieces around the gas tube, where:

8 - checkers; 9 - gas pipe.

Figure 4 - redistribution of gas flows, where:

3 - a strongly bonded charge; 5 - perforated housing with a Central hole; 6 - transfer charge; 7 - ring with a diametrical jumper; 8 - checkers; 9 - gas tube, 10 - pyrocomposition.

The invention consists in the following.

Ignition of the charge, bonded to the body 1 of the rocket engine of solid fuel, is carried out by the ignitor 4. When igniting the pyrocomposition 10 of the transfer charge 6, the combustion products, dissected by the diametrical jumper of the ring 7, are directed to the ends and side surface of the checkers 8, igniting them, since the jumper prevents direct outflow the combustion products of the pyro-composition through the gas tube 9. Some of the combustion products of the pieces 8 through the cells of the perforated body with the Central hole 5 is directed to the surface a channel of the strongly bonded charge 3, flowing around and igniting it, and part of the combustion products is directed into the gas pipe 9 and expires through the central hole of the perforated housing 5, providing further ignition of the channel surface and the slots of the strongly bonded charge 3. The combustion products of the fuel of the strongly bonded charge 3 expire through the nozzle block 2.

The diametrical jumper of the ring 7 is made in cross section in the form of a triangle. Moreover, when the size of the base of the triangle of the cross-section of the bridge is less than 0.3 of the diameter of the checker, part of the combustion products bypasses the checker, flowing through the gas pipe 9, which may not provide ignition of the checkers; when the size of the base of the triangle of the cross section is more than 0.5 of the diameter of the checker, the ignition of the end face of the checker deteriorates due to its overlap with the base of the triangle.

The maximum length of the gas pipe 0.9 lengths of the checkers is selected from the condition of ensuring the free flow of gases from the combustion of checkers into the gas pipe; the minimum length of the gas tube 0.7 of the diameter of the checkers is determined from the condition for excluding the fracture of the checkers when the combustion products act on their end, which can lead to non-calculated combustion.

Thus, the proposed technical solution, in comparison with the closest analogue, provides ignition of the charge and operation of the solid propellant rocket motor with a reliability of at least 0.995 and allows you to get the time to reach the calculated mode of the engine with the required parameters.

The performance of the solid propellant solid propellant rocket engine made in accordance with the invention is confirmed by fire bench tests in the temperature range of ± 50 ° C under the experimental conditions of FSUE NIIPM.

Claims (1)

A solid fuel rocket engine comprising a housing, a nozzle block, a strongly bonded charge, an igniter with a perforated housing filled with a pyro-composition in the form of a transfer charge and checkers, characterized in that the perforation in the housing is made in the form of cells, a ring having a ring between the transfer charge and the checkers a diametrical jumper made in the cross section in the form of a triangle and directed by one of the vertices towards the transfer charge, and the base of the triangle is 0.3-0.5 diameter of the checker, and the checker ki are located around a cylindrical gas tube, the length of which is 0.7-0.9 the length of the checker.

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