RU2383768C1 - Controlled solid propellant rocket engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry and can be used in designing controlled rockets. Proposed engine comprises cylindrical housing with semi-spherical shoulder ring jointed with housing heck, nozzle device, deflector and ball support. Circular ledge is arranged on aforesaid shoulder ring, while nozzle device represents nozzle holes arranged regularly on aforesaid neck in the plane perpendicular to housing lengthwise axis. Axis of every nozzle hole passes above said circular ledge. Neck has bottom concaved into housing to interact, via ball support, with deflector. Ball support center is located on lengthwise axis, below circular ledge. Deflector represents V-plate with ring arranged on its peripheral part and overhanging the circular kedge to form a slot. Inner surface of the ring represents a sphere mating the ledge outer surface.

EFFECT: producing required control forces in plane perpendicular to engine axis by simple compact device, higher reliability reduced linear sizes.

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Description

The invention relates to rocket technology and can be used in the design of guided missiles.

The task of controlling and stabilizing the rocket is associated with the formation of control (lateral) force at certain moments relative to the center of mass of the rocket, forcing it to maneuver in the right direction or maintain a given direction of movement.

The desire, as far as possible, to maintain in all cases the simplicity and reliability of the solid propellant rocket engine has led to the creation of a large number of various structural schemes of power actuators of thrust vector control systems. Each of them has its own set of advantages and disadvantages and is implemented in practice if, under the appropriate given conditions, it is optimal in the adopted criteria scheme (efficiency, cost, time, minimum mass, etc.).

In some cases, gas rudders are used to control the thrust vector, as in the well-known solid-fuel accelerating propulsion system equipped with gas rudders rigidly connected to the rockers, grooves are made on the rockers of the gas rudders to engage with the air rudders (RF Patent No. 2209331, F02K 9/80 September 12, 2001).

The efficiency of gas rudders is low: as a rule, a few percent of engine thrust.

In other cases, it is advisable to use a rotary nozzle block, as in a known propulsion system (GB Patent No. 2086321, F02K 9/90, 08/15/1979). Such designs, being very complex, also require the use of a complex control mechanism.

The closest in technical essence and the achieved positive effect to the proposed invention is a solid propellant rocket engine (solid propellant rocket engine). (Ya.M. Shapiro, G.Yu. Masing, N.E. Prudnikov. Fundamentals of designing solid-fuel rockets. Military Publishing House. M., 1968. See pages 220-221, Fig. 6.22).

In the design of this solid propellant rocket motor to control the thrust vector, 2 deflectors are used - spherical nozzles mounted on the output section of the engine nozzle. Turning the nozzle in the desired direction is carried out using steering machines. Each nozzle has its own ball bearings.

On powerful missiles with a long operating time (several tens of seconds), where a constant change in the trajectory or its correction is required, the use of a deflector is quite effective. However, in missiles with a short engine operating time (a few seconds), for example, of the air-to-air class, the use of a deflector in the above design does not allow for quick maneuver of the rocket during flight, since the angle of rotation of the deflector is very limited. In addition, the use of two nozzles for regulating traction over a wide range greatly complicates the design.

The objective of the present invention is to provide a control engine with "deep" regulation, allowing you to create the required control forces in any direction in the plane perpendicular to the axis of the engine (rocket) using a simple compact device.

The essence of the invention lies in the fact that in the control solid propellant rocket motor containing a cylindrical body, connected with the neck of the shoulder girdle, a nozzle device, a deflector, a ball joint, an annular protrusion is formed on the shoulder girdle, and the nozzle device is made in the form of uniformly arranged on the neck in the plane perpendicular the axis of the housing, nozzles, the axis of each of which passes above the annular protrusion. The neck has a bottom concave in the housing, interacting with the deflector by means of a ball bearing, the center of which is located on the longitudinal axis below the annular protrusion, the deflector is made in the form of a V-shaped plate with a ring on its peripheral part, hanging over the annular protrusion with the formation of a gap, the inner surface the ring has the shape of a sphere and is made mating outer surface of the protrusion.

Thanks to the new features of a solid propellant rocket propulsion vehicle, the missile becomes more reliable and more maneuverable during flight.

The task is achieved in that the deflector is mated to the engine housing through one ball bearing located along the axis of the engine. This allows it to move (swing) in any plane passing through the axis of the engine in which it is required to create a lateral control force. The presence of only one ball joint greatly simplifies the task of ensuring its reliable operation (minimum friction, geometry accuracy, location accuracy, etc.).

The use of a multi-nozzle device and a bottom concave into the body makes it possible to reduce the linear dimensions of the engine.

In addition, gas jets flowing out of a multi-nozzle device form a gas ring of relatively small width. This circumstance makes it possible to have a small angular movement of the peripheral part of the deflector to completely open or close the outflowing gas jet and to obtain, respectively, the maximum lateral thrust in the desired direction.

The execution of the surfaces of the plate and the protrusion of the reciprocal makes it possible to have a minimum technological gap between them, thereby ensuring conditions for a minimum of gas overflow.

The proposed technical solution is not known from the patent and technical literature.

The invention is illustrated by drawings depicting a longitudinal section of the engine in different phases:

figure 1 shows the control solid propellant rocket motor in the initial position,

figure 2 shows the control solid propellant rocket motor with the extreme position of the deflector corresponding to the maximum control force.

The control solid-propellant solid propellant rocket motor has a cylindrical body 1, conjugated with the neck 2 of the shoulder girdle 3, a nozzle device in the form of nozzle holes 4 evenly spaced on the neck 2, the deflector 5 in the form of a V-shaped plate, on the peripheral part of which a ring is made 6. On the shoulder girdle 3 is made annular protrusion 7. The nozzle holes 4 are evenly located on the neck 2 in the plane A, perpendicular to the longitudinal axis of the housing 1. The axis of each nozzle hole 4 extends above the level of the annular protrusion 7.

The neck 2 has a bottom 8 concave in the housing 1, in the center of which a spherical support 9 is mounted, interacting with the deflector 5, the center of the spherical support 9 being located on a longitudinal axis extending beyond the plane A below the annular projection 7. The inner surface B of the ring 6 has an inscribed shape spheres, and the outer part of the annular protrusion 7 repeats this form, and the center of the inscribed sphere coincides with the center of the ball joint 9 and is located beyond the plane A. Between the ring 6 of the deflector 5 and the annular protrusion 7 in the initial position of the solid-propellant rocket motor there are rings I slit S.

A docking flange 11 is mounted on the shoulder girdle 3 using racks 10. Steering machines 12 are mounted on the flange 11, interacting through the rods 13 with the peripheral part of the plate.

The device operates as follows.

When the control solid propellant is turned on in the initial position (Fig. 1), the combustion products expire through the nozzle openings 4 into the cavity D formed by the deflector 5, the neck 2 with a concave bottom 8 and the protrusion 7. Then, the combustion products expire outward through the annular gap C, creating traction along longitudinal axis of the engine (no lateral draft).

When you turn on the control solid propellant rocket motor in the extreme position (figure 2), part of the nozzle holes 4 opens for direct outflow of the gas stream out in the direction perpendicular to the longitudinal axis of the engine. A gas stream from another part of the nozzle openings 4, completely covered by the deflector 5, flows along the cavity D towards the formed gap for direct outflow. Thus, a lateral thrust of the engine (control force) is created.

The movement of the deflector 5 in the initial, extreme or intermediate position in any plane passing through the longitudinal axis of the engine is carried out using actuators - steering machines 12 through the rods 13 according to the missile control program.

Claims (1)

A solid propellant control rocket engine comprising a cylindrical body coupled to the neck with a hemispherical shoulder girdle, a nozzle device, a deflector, a ball bearing, characterized in that an annular protrusion is formed on the shoulder girdle, and the nozzle device is made in the form of uniformly arranged on the neck in the plane perpendicular to the longitudinal axis of the housing, nozzle holes, the axis of each of which passes above the annular protrusion, and the neck has a bottom concave into the housing, interacting with by means of a ball joint, the center of which is located on the longitudinal axis below the annular protrusion, the deflector is made in the form of a V-shaped plate with a ring on its peripheral part hanging over the annular protrusion to form a slit, the inner surface of the ring having the shape of a sphere and having a corresponding outer surface protrusion.

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