KR810001576B1 - Missile - Google Patents

Abstract

A missile steered by constant burning thrust reaction motors. These motors(24,30,32) are integral with the tail panels(20,26,28) of the missile to enhance the effect patricularly during the boost phase of flight. The motors provide thrust along the chord of the tail panel and are moved about the axis(22) of rotation of the tail panel(20) by the servo motor(34) associated with the tail panel(20). The servo motors(34,36,38) are activated by central missile control circuitry. Rocket steering of the missile at low speed is thus achieved with the minimum of complication and no extra control circuitry.

Description

missile

1 is a schematic diagram of a missile of the present invention having a recoil motor integrally coupled to the rear wing.

2 is a diagram showing the missile control system for the missile shown in FIG.

3 is a cross-sectional view taken along line 3-3 of FIG. 1 after positioning the rear wings of FIG. 1 by a servo motor to change the direction of the missile.

4 is a partial cross-sectional view for illustrating another feature of the present invention.

The present invention relates to missiles, and in particular to missile control and propulsion systems, and more particularly, to control systems that include recoil control and aerodynamic control.

Conventional missiles have tail panels mounted to enable movement about axes generally perpendicular to the axis of the missile fuselage. Each of these rear wings is connected to a servo motor, which rotates the vanes around their respective axes. This servo motor is operated by a central missile control circuit. While the missile is flying along the same straight line as the axis of its fuselage, the rear wing and its chord are positioned parallel to the course. In this position, even if aerodynamic forces act on the rear wing, the missile's direction cannot be easily changed. To change direction, the rear wing is rotated about the missile fuselage axis, ie about the airflow. The aerodynamic forces exerted on the missile by air currents hitting the rear wing surface are perpendicular to the missile fuselage axis and have components that provide the moment necessary to redirect the missile. By harmoniously positioning the rear wings with each other, the missile's course and direction can be controlled.

The boost phase in typical missiles is characterized by very low rear wing effects. Therefore, in the conventional missile, the body of the missile is made aerodynamically stable at launch by making the missile heavy to ensure safe launch of the missile and to compensate for the low effect of the control surface. However, in this case, after the booster burns, the load decreases accordingly, and a problem arises where the initial starting body oscillates, and as a result, more stability is required than the aerodynamic one.

One known method for improving the control of the boost face is to supplement the aerodynamic control system with a recoil control system and use the thrust of the recoil motor, such as a jet engine, to change the direction of the missile. It is provided. Known recoil control systems for missiles require separate recoil motors for each of the three missile control channels, three missile control channels for controlling pitch, yaw and roll. Shall be. For control to take place, each recoil motor must have its own servo motor positioning system or be able to control various thrusts. Both of these structures have limited practical utility due to cost problems and complexity.

In the missile according to the present invention, a rebound motor which is integrally coupled to each rear wing and which is relatively inexpensive and continuously burns is used to improve the control effect, particularly at the boost face during missile flight. Without the incidence of the rear wing, the thrust of the control recoil motor would only cooperate with the main missile propulsion system to provide additional propulsion to the missile along the weight of the missile fuselage. The control of each missile channel is achieved by positioning the rear wing around the axis of rotation by the servo drive force. As a result, it is possible to achieve full recoil / gas dynamic control on these missiles with minimal modification, that is, at minimal cost.

During the boost phase, it is also possible to launch aerodynamically unstable missiles by using a complete recoil / gas dynamic control system as described above. In the case of an end combustion rocket motor, the fuselage becomes neutral after the motor burns. In this neutrally stable missile, the effective load capacity of the marshall can be increased from 50% to 100%. In boost boost face recoil control, even if a fluctuation in the form of a combination of rain and lateral fluctuations can be controlled, it is possible to change the direction of the missile during the boost face. This is an important feature for rapid recoil missile systems and is particularly important for vertical launch vehicles.

Hereinafter, the present invention will be described in more detail with reference to the accompanying drawings.

1 shows a missile according to the present invention having a load chamber, or warhead 14, at one end and a cylindrical missile fuselage 12 having a main missile propulsion means 16, such as, for example, a rocket engine. 10 is a schematic diagram. The axis of the cylindrical body 12 is shown by an axis 18. The engine 16 provides thrust in the same straight line as the shaft 18.

The rear wing 20 is mounted to the body 12 so as to rotate around the shaft 22. The rear wing 20 is integrally coupled with a recoil motor such as, for example, a rocket engine 24. The motor 24 may be a separate rocket engine, or a nozzle connected to another source of high pressure gas, such as, for example, the main propulsion engine 16. In either case, the motor 24 needs to be mounted or integrally coupled to the rear wing 20 so that the thrust of the motor 24 is in the same straight line as the aerodynamic chord of the rear wing 20. The rear wings 26 and 28 each including the motors 30 and 32 are rotatably mounted to the body 12 similarly to the rear wing 20.

As shown in FIG. 2, the rear wings 20, 26, 28 are respectively controlled by servo motors 34, 36, 38 mounted on the body 12 or inside the body. . For example, when the servo motor 34 is operated, the rear wing 20 and the motor 34 rotate around the shaft 22. The other wings move in the same way. The figure shows a missile 10 having three rear wings equidistantly mounted on the circumference of the lower part of the fuselage 12, but in special types of missiles or, if necessary, rear wings are arranged in other ways. Of course you can.

The effect of the rotation of the rear wing on the course of the missile 10 is to rotate the rear wing 20 by the servo motor 34 of FIG. 3, and then cut the rear wing 20 along the line 3-3 of FIG. Will be understood by reference to one cross section). The flight direction is the direction of arrow A, which is the same as the axis 18 direction, and the thrust direction of the engine 16 is the direction of arrow B. Arrow B also indicates the relative direction of the air flow. The airflow force C acting on the hind wings 20 is perpendicular to the wing surface, and is therefore perpendicular to the wings of the wing extending along the line 40. As a component of the force (C), the fuselage (D), which reduces the speed of the missile, and the body (not shown) can rotate the missile 10 around an axis extending through the center of rotation (not shown). There is an axial component (E) acting at a point on the shaft 22 to exert a moment on 12). As long as the axial component E is present, the rear wings 20, 26, 28 can rotate in harmony to control the course of the missile 10. Since the aerodynamic forces (C) are relatively small, this aerodynamic control is very inefficient when the missile's airspeed is low, i.e. during the boost phase at launch. This low rear wing effect can be partially compensated by the control circuit 42 shown in FIG. 2, which increases the amount of rotation of the vanes about each axis during the boost phase. . Response time and limited flight problems limit this compensation. In any case, the control circuit 42 activates the servos in response to information or commands provided by the direction detector 44 located inside the missile and the ground control circuit 46 partially protruding out of the missile.

Referring again to FIG. 3, the aerodynamic forces obtained by the rotation of the rear blades 20 relative to the relative airflow improve the operation of the continuously burning thrust recoil motor 24. The thrust of the motor 24 occurs along the chord 40 and is indicated by the force F in the figure. The component of the force (F) is the additional propulsion force (G) to supplement the thrust of the main propulsion device (16), and the aerodynamic force component (E) to apply moment to the fuselage 12 to change the missile's course. Similarly, it is an axial thrust component H that exerts a reaction force on the body 12.

Since the motors 24, 30, 32 (see FIG. 2) operate along the chords of the trailing wings 20, 26, 28, the control circuit 42 is specifically designed to control the recoil motor. The moments applied simultaneously by the aerodynamic control and recoil control systems are controlled without the need for a defined additional control circuit. The dual control system, which is advantageously located under the control of a common control circuit and servo motor, serves to complement each other during operation. When the speed is low and the resulting aerodynamic forces are small, the recoil motor provides the thrust needed to control the missile's direction as the rear wing rotates to change the missile's direction. As the speed is increased and the resulting aerodynamic force is increased to a level suitable for missile directional control, the reaction force is no longer needed or reduced (by combustion or the like).

4 shows an arrangement in which the aforementioned effects can be obtained. 4 is a side view of the rear wing 20, the rear wing 20 is rotatable about the shaft 22 under the control of the control circuit 42 as described with reference to FIG. In order to reduce the thrust level as a function of combustion time, the tip is sharp, ie tapering towards the end. This reduction in thrust compensates for the aerodynamic control forces formed as the missile speed increases over time after launch, and thus the influence of the servo motor 34 and the control circuit 42 connected to the rear wing 20. The control force for the given direction of the rear wing 20 is kept more constant.

By this aspect of the present invention, the control safety is enhanced, thereby reducing the need to operate the entire control system.

In order to explain how the present invention is advantageously applied, although a specific arrangement of the thrust vector vector aerodynamic control plane integrated according to the present invention has been described, it is a matter of course that the present invention is not limited thereto.

Claims (1)

Cylindrical missile fuselage: A main propulsion device that acts along the fuselage's axis to propel a missile and can be pivoted around an axis perpendicular to the cylindrical surface of the fuselage and aerodynamically. It has a number of rear wings for control and a servo motor connected to each rear wing to control the angular position of the rear wing relative to the missile fuselage and a control circuit for operating the servo motor to control the flight of the missile. It is integrally mounted to each rear wing of the missile and is rotatable about the rear wing, generating thrust in the chord direction to enhance the aerodynamic control of the missile, and in the absence of aerodynamic forces, To have a recoil thrust motor that burns continuously to improve torque Missiles of Jing.

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