KR20020079073A - Jet tap thrust vector control system for rocket - Google Patents

Abstract

PURPOSE: A jet tap thrust vector control system for rocket is provided, which has a good competitive power by reducing the whole cost of the rocket by controlling a direction of the rocket easily without adding an additional driving apparatus. CONSTITUTION: According to a rocket, a heat resistant material(90) is installed on a part where a flame in a high temperature and a high pressure contacts inward a TVC body(8) installed in a ball band method on a bottom of a rocket nozzle(N). The first and the second and the third and the fourth DC motor(21,22,23,24) and the first and the second and the third and the fourth decelerator(31,32,33,34) are installed with a gap of 90 degree on the body. The first and the second and the third and the fourth jet tab and the first and the second and the third and the fourth angle sensor(41,42,43,44) are installed on each deceleration axis. The first and the second and the third and the fourth controller(11,12,13,14) are installed on one side of the TVC body. A power line of the DC motors and a signal line of the angle sensors are connected with the controllers.

Description

Jet Tap Thrust Vector Control System for Rocket

The present invention relates to a thrust vector control system of a vertical launch rocket, and more particularly, mounted on the rear of the nozzle of the rocket used as a means of transporting objects in the air or space to control the vector (direction) of the thrust. The present invention relates to a jet step thrust vector control system with improved posture control.

Rockets are largely divided into satellite launchers and missiles, and the two classes are divided according to what each rocket carries.

In other words, if they carry satellites, they are called projectiles. If they are loaded with weapons, they are called missiles.

As described above, a method for attitude control of a rocket is described. For a missile used for military purposes, a stationary launching system is conventionally used, and a launching device capable of mechanically rotating displacement of an azimuth and elevation toward a target before launching the missile is used. The initial posture control did not place much weight on the target, and the control method was obtained by changing the angle of aerodynamic blade used for posture control in the terminal control section relatively close to the target.

In addition, some missiles with vertical firing systems are using TVC. Gimbal, Moving Nozzle, Jet Vane TVC, Jet Tap TVC, Side Injection TVC, Jetavator are used.

These devices are all operated in such a way as to drive the nozzle as a whole, mechanically drive part of the nozzle, or add a new device to the rear of the nozzle so that the direction of thrust is deflected.

The main task of the missile is to ascend as soon as the missile is ignited, usually leaving the canister by high pressure gas, immediately entering roll control, setting the pitch reference point to the target point, and then entering the pitch control to make a horizontal flight towards the target point. will be.

In addition, control is performed to restore the desired posture when the posture is changed by an unexpected air gust during the mission.

This is the mission of the TVC, and in the case of small rockets, the TVC is usually removed within three seconds of the mission, but for medium and large rockets it is mounted until the booster burns out, and then it is separated with the booster.

Roll control is very important because if you cannot roll control at the same time as the rocket rises, you need to perform yaw control again after completing pitch control to reach the target.

In addition, the reason why the tap method is preferred is that there is no thrust consumption during non-operation and the driving control force may be small.

The present invention has been made in order to solve the problems as described above, the purpose is to easily control the direction of the rocket without the addition of a separate drive device to reduce the overall price of the rocket, the competitive rocket To provide a thrust vector control system.

The purpose of the rocket, the heat-resistant material is mounted on the part of the TVC body which is mounted in a ball-bend method that can be separated in the lower part of the rocket nozzle, the flame contact of high temperature and high pressure, the first, The second, third and fourth DC motors and the first, second, third and fourth reducers are mounted, and the first, second, third and fourth jet steps and the first, Second, third, and fourth angle sensors are mounted, and first, second, third, and fourth controllers are provided on one side of the TVC body, respectively, and the first, second, third, and fourth DCs are provided. Jet step thrust for vertical launch rocket, characterized in that the power line of the motor and the signal line of the first, second, third, fourth angle sensor is connected to the first, second, third, fourth controller. Achieved by a vector control system.

1A is an outline view schematically illustrating a control principle of a rocket thrust vector control system according to the present invention.

1B is an outline view schematically showing a structure before mounting a thrust vector control system of a rocket according to the present invention;

Figure 1c is an external view schematically showing a structure equipped with a thrust vector control system of the rocket according to the present invention,

Figure 1d is an external view showing the appearance after mounting the thrust vector control system of the rocket according to the present invention,

Figure 2 is a bird's eye view showing the position and controller of the drive unit including each jet step in the present invention,

Figure 3a is a rear view of the rocket shown for explaining the installation position of the conventional non-controllable jet step

3B is a cross-sectional view taken along the line A-A of FIG. 3A

Figure 3c is a rear view of the rocket shown for explaining the installation position of the conventional roll controllable jet step

3D is a cross-sectional view taken along the line B-B in FIG. 3C

Figures 4a and 4b is a rear view of the rocket shown for explaining the installation angle of the jet step in the present invention

4C is a cross-sectional view taken along the line C-C in FIG. 4B

Figure 4d and Figure 4e is a rear view of the rocket shown for installing the installation angle of the jet step in the present invention

[Explanation of symbols on the main parts of the drawings]

1, 2, 3, 4: 1st, 2nd, 3rd, 4th jet step

5, 6, 7, 8: 1st, 2nd, 3rd, 4th jet step (no existing roll control type)

11, 12, 13, 14: first, second, third, fourth controller

15, 16, 17, 18: 1st, 2nd, 3rd, 4th jet step (roll controllable type)

21, 22, 23, 24: 1st, 2nd, 3rd, 4th DC motor

25, 26, 27, 28: 1st, 2nd, 3rd, 4th auxiliary jet step (roll controllable type)

31, 32, 33, 34: first, second, third, fourth reducer

41, 42, 43, 44: first, second, third, fourth angle sensor

50 ~ 59: Steel Ball

61, 62: 1st, 2nd explosion bolt

71, 72: 1st, 2nd band

80: TVC body

90: heat resistant material

R: rocket body N: rocket nozzle

T: JetTab TVC System

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

The virtual line of Figure 1a shows the TVC operation, the solid line represents the TVC non-operation, the center is the center of gravity of the rocket, the thrust acts on the lower side and the control force acts on the left side.

As shown in FIG. 1B, the rocket without a TVC is installed with a rocket nozzle N at the bottom of the rocket body R.

As shown in Fig. 1C, the TVC (T) of the present invention is mounted below the nozzle (N).

And to reduce the drag caused by the air force as shown in Figure 1d extends the outer shell of the rocket body (R) to the end of the TVC (T) TVC (T) enters into the rocket body (R).

As shown in FIG. 2, the heat-resistant material 90 is mounted at a portion where the flame of the high temperature and high pressure touches the inside of the TVC body 80, and the first, second, third, and fourth DCs are disposed at 90 ° intervals to the body 80. The motors 21, 22, 23, 24 and the first, second, third, and fourth reducers 31, 32, 33, 34 are mounted, and the first, second, third, Fourth jet taps 1, 2, 3 and 4 and first, second, third and fourth angle sensors 41, 42, 43 and 44 are mounted.

The first, second, third, and fourth controllers 11, 12, 13, and 14 are installed at one side of the TVC body 80, and the first, second, third, and fourth DC motors 21, The power lines of the 22, 23, 24, and the signal lines of the first, second, third, and fourth angle sensors 41, 42, 43, 44 are first, second, third, and fourth controllers 11, 12. , 13, 14) so that the first, second, third, and fourth jetsteps 1, 2, 3, and 4 may exhibit an arbitrary angle within a 90 degree range according to an external control command. To control.

Mounting of the rocket nozzle (N) and the TVC body 80 is 10 steel balls (50) with 10 holes drilled in the TVC body 80 after the annular projection of the rocket nozzle (R) is fitted into the TVC body (80). 59) and the first and second explosion bolts through the holes drilled at the ends of the first and second steel bands 71 and 72 so as to prevent the ball from falling out. Fit (61, 62).

In the case of a small rocket, the TVC (T) may be detached from the rocket nozzle (N) to reduce the weight and drag caused by the TVC (T) after the mission of turning the rocket in the desired direction within the initial 3 seconds.

The separation procedure is performed by applying electrical signals to the first and second explosion bolts 61 and 62 so that the first and second explosion bolts 61 and 62 are disconnected. The TVC T is separated from the rocket nozzle N while being separated by the restoring force and the steel balls 50 to 59 are released.

The shape of the jet vane, the mounting position and the operating range are as follows.

As shown in FIGS. 3A and 3B, the conventional non-controllable jet step TVC includes first, second, third and fourth jet steps 15, 16, 17, and 18 on the same plane as the virtual surface formed by the end of the rocket nozzle. It is possible to control pitch and yaw, but not roll control.

To improve this, as shown in FIGS. 3C and 3D, the first, second, third and fourth jetsteps 15, 16, 17 and 18 and the respective first, second, third and fourth auxiliary jets are shown. It was configured to mount eight jet steps inclined at a predetermined angle with a surface formed by the flame contact surfaces of the steps 25, 26, 27, and 28 and the end of the rocket nozzle N.

However, this method has to double the structural weight of the drive including the jet step, and suffer a significant loss in weight-to-performance ratio.

In the present invention, as shown in FIG. 4A, the nozzle is installed to avoid the flame outlet of the nozzle during non-operation, and the flame contact surfaces of the first, second, third, and fourth jet steps 1, 2, 3, and 4 are nozzles N. FIG. It is wedge shaped to have an angle of 5 to 10 degrees with the exit surface, and the first and third jet steps 1 and 3 and the second and fourth jet steps 2 and 4 are mounted to have opposite angles to each other. Pitch control, yaw control, and roll control are possible with only four of the first, second, third, and fourth jet steps (1, 2, 3, 4).

Referring to the pitch control method, as shown in FIGS. 4B and 4C, when only the first and fourth jet steps 1 and 4 simultaneously enter the flame outlet of the nozzle N, an upward pitch force is generated. As a result, a negative pitch moment is generated to allow the nose to descend downward about the center of gravity of the rocket R.

On the contrary, when only the second and third jet steps 2 and 3 enter the flame outlet of the nozzle N at the same time, a downward pitch force is generated and the nose is upward from the center of gravity of the rocket R. A positive pitch moment is generated to be heard.

Referring to the yaw control method, as shown in FIG. 4D, when only the third and fourth jet steps 3 and 4 enter the flame outlet of the nozzle N at the same time, a yaw force on the left side is generated and the rocket ( A positive yaw moment is generated to allow the nose to lean right around the center of gravity of R).

On the contrary, if only the first and second jet steps 1 and 2 enter the flame outlet of the nozzle N at the same time, yaw force is generated to the left and the nose is tilted to the left centering on the center of gravity of the rocket R. Negative yaw moments are generated.

Referring to the roll control method, as shown in FIG. 4E, when only the first and third jet steps 1 and 3 enter the flame outlet of the nozzle N at the same time, the roll force of the right side may be reduced in the first jet step 1. Roll force is generated and the roll force of the left side is generated in the third jet step 3, so that the roll moment of the positive star is lowered downward from the center of gravity of the rocket R as a whole. ) Is generated.

On the contrary, when only the second and fourth jet steps 2 and 4 enter the flame outlet of the nozzle N at the same time, the roll force of the right side is generated in the second jet step 2 and the fourth jet step 4 is applied. In the left roll force (Roll Force) is generated a negative roll moment (star) in which the starboard ascends upward from the center of gravity of the rocket (R) as a whole.

As described above, the present invention has no thrust consumption during non-operation, so that the roll control is possible with a simple system in the preferred jet step thrust vector control system, which enables initial rapid targeting of the vertical launch rocket. It is cost effective and competitive.

Claims (5)

In the rocket, a heat-resistant material (90) mounted to the portion where the flame of the high temperature and high pressure touches the inside of the TVC body (80) that is mounted in a ball-bend method that can be separated in the lower part of the rocket nozzle (N), First, second, third, and fourth DC motors 21, 22, 23, and 24 and first, second, third, and fourth reducers 31, 32 mounted on the body 80 at intervals of 90 degrees. , 33, 34), The first, second, third and fourth jet steps 1, 2, 3 and 4 and the first, second, third and fourth angle sensors 41, 42, 43 44) and, First, second, third, and fourth controllers 11, 12, 13, and 14 installed on one side of the TVC body 80; Power lines of the first, second, third, and fourth DC motors 21, 22, 23, and 24 and signal lines of the first, second, third, and fourth angle sensors 41, 42, 43, and 44. A jet step thrust vector control system for a vertically launched rocket, characterized in that it is configured to be connected to the first, second, third, and fourth controllers (11, 12, 13, 14). The first jet step (1) according to claim 1, wherein the first jet step (1) is inclined 5 to 100 degrees with the nozzle exit surface so as to generate a negative pitch and negative yaw moment. 2) is inclined 5 to 10 degrees with the nozzle exit surface to generate a positive pitch and negative yaw moment, the third jet step 3 is a positive pitch and positive The nozzle exit surface is inclined 5 to 10 degrees to generate a positive yaw moment, and the fourth jet step 4 has a nozzle to generate a negative pitch and a positive yaw moment. A jet stepped thrust vector control system for a rocket, characterized by being inclined at an angle of 5 to 10 degrees with an exit surface. The rocket jet step type according to claim 1, wherein the first and third jet steps 1 and 3 and the second and fourth jet steps 2 and 4 are mounted to have opposite angles to each other. Thrust vector control system. The method of claim 1, wherein the first and fourth jet steps 1 and 4 are simultaneously driven to control negative pitches, and the second and third jet steps 2 and 3 are simultaneously driven. Controls the positive pitch, The third and fourth jet steps 3 and 4 are simultaneously driven to control positive yaw, and conversely, the first and second jet steps 1 and 2 are simultaneously driven to obtain negative ( Controls yaw of-), The first and third jet steps 1 and 3 are simultaneously controlled to control positive rolls, and the second and fourth jet steps 2 and 4 are simultaneously controlled and negative (-). The jet step type thrust vector control system for a rocket, characterized in that for controlling a roll. The mounting of the rocket nozzle (N) and the TVC body (80) is performed by ten holes drilled in the TVC body (80) after the annular projection of the rocket nozzle (R) is inserted into the TVC body (80). Insert 10 steel balls (50 to 59) and wrap the first and second steel bands (71, 72) so that the balls do not fall out, and through the holes drilled at the ends of the first and second steel bands (71, 72). A rocket jet step thrust vector control system, characterized in that the first and second explosion bolts (61, 62) are mounted.