RU2267024C1 - Solid-propellant rocket engine - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: proposed solid-propellant rocket engine contains combustion chamber with front and nozzle faces, powder charge with unrestricted nozzle end face and igniter on nozzle face. Igniter in arranged in space formed by unrestricted nozzle end face of charge and cavity in nozzle face. Support made of flexibly deformable material is installed on front face of combustion chamber.

EFFECT: improved efficiency of nozzle igniter.

2 dwg

Description

The invention relates to rocket technology, in particular, to solid propellant rocket engines (solid propellant rocket engines).

Known solid propellant solid propellant with an external powder charge and an ignitor of the prechamber type [1]. The igniter is a prechamber tube with a powder hinge placed in the central channel of the charge. Such an igniter is essentially an “engine in an engine” and provides reliable ignition of a powder charge.

However, such an igniter cannot be used in engines having a powder charge without a central channel. In this case, the igniter is usually located on the nozzle bottom of the engine chamber. An example of such a design is a solid propellant rocket motor [2], which contains a combustion chamber with front and nozzle bottoms, a powder charge, and an igniter on the nozzle bottom. The powder charge is made with an unarmored nozzle end face.

A common drawback of such designs is the low, compared with the prechamber, efficiency of the nozzle igniter, due to its location near the nozzle. When the igniter is activated, the gases fill it with the pre-nozzle volume and are partially ejected through the nozzle before reaching the ignited surface of the powder charge.

An object of the present invention is to increase the efficiency of a nozzle igniter.

This problem is solved in that in a solid propellant rocket engine containing a combustion chamber with front and nozzle bottoms, a powder charge with an unarmored nozzle end and an igniter on the nozzle bottom, the igniter is placed in a cavity formed by the nozzle end of the powder charge and a recess in the nozzle bottom. At the same time, a support made of elastically deformable material is installed on the front bottom of the combustion chamber.

In this design, the cavity with the igniter serves as a kind of prechamber, in which the hitch of the igniter intensively burns, igniting the adjacent surface of the powder charge. The support of elastically deformable material at the front bottom of the chamber plays the role of a valve: with increasing pressure, the support is compressed, igniter gases are discharged from the cavity through the gap formed, preventing possible destruction of the cavity walls. Moreover, the higher the initial temperature of the charge, the more intense the pressure is released from the cavity, thereby automatically reducing the intensity of ignition of the charge and preventing possible pressure overshoots.

The drawings show the proposed engine in a section (figure 1 is a longitudinal section, figure 2 is a transverse). The engine includes a combustion chamber 1 with a front bottom 2 and a nozzle bottom 3, a powder charge 4 armored over part of the surface and a nozzle igniter 5. The ignitor 5 is placed in a cavity formed by the nozzle unarmored end face of the charge 4 and a recess 6 made in the heat-resistant coating 7 of the nozzle bottom 3 An electric valve 8 is installed in the cavity with the igniter 5 and is mounted on the nozzle bottom 3. At the front bottom 2 of the combustion chamber 1, a support 9 of elastically deformable material is installed under the end of the charge 4. In practice, rubber may be the most acceptable option for an elastically deformable material.

The engine operates as follows.

When the electric valve 8 is activated, a hitch of the igniter 5 is ignited, which ignites the adjacent surface of the charge 4. In this case, the cavity with the igniter serves as a kind of prechamber. Under the action of pressure in the cavity, the charge 4 moves to the front bottom 2 of the chamber 1, deforming the support 9. Through the resulting gap, the combustion products of the igniter sample and the ignited part of the powder charge expire into the pre-nozzle volume, igniting the remaining unarmored surface of the charge.

Thus, the placement of the igniter in the cavity formed by the nozzle unarmored end face of the powder charge and the recess in the nozzle bottom, significantly increases the efficiency of the nozzle igniter without complicating the design of the engine.

Sources of information

1. Patent of Russia No. 2133371, 1999, IPC 6 F 02 K 9/24.

2. T. M. Melkumov and others. "Rocket engines." Ed. "Mechanical Engineering", 1976, p. 373, Fig. 19.3.

Claims (1)

A solid propellant rocket engine comprising a combustion chamber with front and nozzle bottoms, a powder charge with an unarmored nozzle end and an igniter on the nozzle bottom, characterized in that the igniter is placed in a cavity formed by an unarmored nozzle end face and a recess in the nozzle bottom, and at the front bottom combustion chamber mounted support of elastically deformable material.

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