JP2560132B2 - Rocket thrust direction control device - Google Patents

Description

Description: TECHNICAL FIELD The present invention relates to a thrust control device for controlling the thrust direction of a rocket, and in particular, when the thrust direction control is not required during flight of a rocket, the thrust gas is out of the combustion gas injection range. The present invention relates to a device that can store jet vanes.

[Prior Art] As a conventional rocket thrust direction control device of this type,
For example, there is one as shown in FIGS. 16 to 19. First
In FIG. 16, reference numeral 1 is a rocket body, and this rocket body 1
Is composed of a rocket motor (not shown), a guidance control device, a payload, and the like.

At the end of the rocket body 1 (upper part in Fig. 16),
Mainly as shown in FIG. 17, a nozzle 2 for injecting combustion gas
Is provided. A rocket thrust direction control device 3 is arranged so as to cover the nozzle 2.

This rocket thrust direction control device 3 includes a rocket body 1
A rear body 4 is detachably attached to the rearmost part of the through a V clamp 5 and a separation bolt 6. The separating bolt 6 is loaded with gunpowder inside, and explodes due to a command electric signal so that the bolt itself is cut off. A spring 14 for pushing out the rear body 4 is arranged between the rear body 4 and the rocket body 1.

Further, as shown in FIG. 18, a total of four jet vanes 7 for controlling the thrust direction are installed in the rear body 4 so that they can be independently driven orthogonally to the radial direction of the opening of the nozzle 2. That is, each jet vane 7 is fixed to the support shaft 8 as shown in FIG. 17, and is provided at the outlet portion 2a of the nozzle 2 so as to project inward. The support shaft 8 is rotatably supported by a base 10 fixed to the rear body 4 via a bearing 9, and a torque arm 11 is fixed to the rear end of the support shaft 8.

Then, the one end portion 11a of the torque arm 11 is
As shown in the figure, a ball screw 12 is rotatably provided, and an output shaft 13a of an electric servomotor 13 is screwed onto the ball screw 12. The ball screw 12 is vertically moved by the rotation of the output shaft 13a. The base end of the electric servomotor 13 is rotatably arranged on the rear body 4, as shown in FIG.

A fan-shaped gear 11b is formed on the other end of the torque arm 11 as shown in FIG.
Meshes with potentiometer 15 and always jet vane 7
The rudder angle is converted into a resistance value proportional to this rudder angle and monitored.

Further, although not shown, a thermal battery for driving a servo amplifier or an electric servomotor 13 is attached to the rear body 4 in addition to the above.

In order to control the direction of the rocket, the electric servomotor 13 is driven by the steering angle command from the servo amplifier. Then, the output shaft 13a rotates and the ball screw 12 moves to the output shaft 13a.
The vertical movement of the torque arm 11 causes the jet vane 7 to be set to a predetermined steering angle via the support shaft 8. At this time, the steering angle command from the servo amplifier is calculated from the error value between the current flight course of the rocket and the target course, and the jet vane 7 steering angle position by the potentiometer 15, and changes every moment to control the thrust direction. I am trying to do it.

And when thrust direction control is no longer needed,
The command signal causes the explosive charge of the separation bolt 6 to explode, cutting the bolt itself. When the separation bolt 6 is cut, the clamping force of the V-clamp 5 is released and spreads in the radial direction, so that the rear body 4 is unconstrained from the rocket body 1 and separated from the rocket body 1 by the force of the spring 14 to Or it falls on the sea.

[Problems to be Solved by the Invention] However, in such a conventional device, a rocket thrust direction control device is provided in order to reduce thrust loss due to the jet vane 7 to zero when thrust direction control is no longer necessary. Since 3 is separated, in a rocket in which the rocket thrust direction control device 3 is actuated only to make a turn immediately after the launch in a narrow space launch or vertical launch on the ground, a heavy load (rocket thrust direction The fall of the control device 3) may damage the equipment on the ground.

[Means for Solving the Problems] The present invention has been made with attention paid to such problems.
A plurality of jet vanes are arranged in the nozzle of the rocket body along the radial direction of the nozzle opening, and the rudder angle adjusting means rotates the jet vane around the radial direction of the nozzle opening to adjust the rudder angle. However, in a rocket thrust direction control device that controls the thrust direction of the rocket by the lateral thrust generated according to the steering angle of the jet vane, the accommodating portion of the jet vane is out of the injection range of the combustion gas from the nozzle. A rocket thrust direction control device that is provided inside the rocket body and that has a storage means that drives the jet vane and stores the thrust vane in the storage portion when the thrust direction control is unnecessary during flight of the rocket. It is characterized by

[Operation] According to such means, when controlling the thrust direction of the rocket, the thrust direction is controlled by rotating the jet vane to adjust the steering angle by the steering angle adjusting means.

When the thrust direction control is unnecessary during flight of the rocket, the jet vane is stored in the storage portion by the storage means. This housing is located outside the injection range of the combustion gas from the nozzle and is provided inside the rocket body, so the jet vanes stored here do not become a resistance to the combustion gas injection, There is no air resistance inside. Also, because the rocket thrust direction control device is not separated from the rocket body as in the past,
There is no risk of damaging ground equipment if dropped.

[Examples] The present invention will be described below based on Examples.

1 to 4 are views showing a first embodiment of the present invention.

First, the configuration will be described. In the figure, reference numeral 2 is the rocket body 1
The rocket thrust direction control device 21 for controlling the thrust direction of the rocket is provided behind the nozzle 2 at the rearmost part of the nozzle 2.

This rocket thrust direction control device 21 is arranged so that four jet vanes 22 are independently driven behind the nozzle 2 along the radial direction at right angles to each other, as in the conventional case. .

Specifically, the jet vane 22 is fixed to the first support shaft 23, and the support shaft 23 is attached to the rotating member 24 as a pair of first bearings 25.
It is set to be rotatable via. A second support shaft 26 projects from the rotating member 24 in a direction orthogonal to the second support shaft 26. The second support shaft 26 is supported by a support member 28 fixed to the rocket body 1 via a second bearing 27. There is. As a result, the first support shaft 23 is rotated about the axial direction of the jet vane 22 via the first bearing 25, whereby the steering angle of the jet vane 22 is controlled, and the second support shaft 23 is controlled. Rotating member via bearing 27
By rotating 24, the jet vane 22 is rotated as shown by the chain double-dashed line and the solid line in FIG.

The first support shaft 23 and the rotating member 24 are driven by different mechanisms.

That is, by rotating the first support shaft 23, the jet vane
The rudder angle adjusting means for controlling the rudder angle of 22 is as follows.

That is, from the central portion 23a of the first support shaft 23, the shaft 23
A rod 29 is provided so as to project in a direction orthogonal to the rod 29, and a bearing 30 is attached to a tip end portion 29a of the rod 29. This bearing 30
A ball screw 31 is rotatably mounted on the ball screw 31, and the output shaft of the electric servomotor 32 is mounted on the ball screw 31.
32a is screwed. Also, this electric servo motor 32
The lower end portion 32b shown in FIG. 2 is rotatably attached to the rocket body 1. The rotation of the output shaft 32a causes the jet vane 22 to rotate via the ball screw 31, the rod 29, the first support shaft 23, and the like. Further, a potentiometer 33 that detects the rotation angle of the first support shaft 23, that is, the steering angle of the jet vane 22 is fixed to the rotating member 24.

On the other hand, the storing means for rotating the rotating member 25 to store the jet vane 22 as shown by the chain double-dashed line in FIG. 1 is as follows.

That is, the arm 34 is fixed to the tip end portion of the second support shaft 26 of the rotating member 24, and the engaging portion 35a of the solenoid 35 is engaged with the one end portion 34a of the arm 34 as shown in FIG. Along with being stopped, a tension spring 36 is connected to the other end 34b of the arm 34. When the locking portion 35a of the solenoid 35 is separated from the one end 34a of the arm 34, the tension spring 36
Arm 34 is rotated by the pulling force of the jet vane.
22 is rotated as shown by the chain double-dashed line in FIG.
It is designed to be stored in. The housing portion 1 a is provided outside the injection range of the combustion gas from the nozzle 2 and inside the rocket body 1.

 Next, the operation will be described.

To control the thrust direction of the rocket, rotate the output shaft 32a of the electric servo motor 32 and the ball screw 31
Is moved up and down in the direction of the arrow in FIGS. 2 and 4, and rod 29
The first support shaft 23 is rotated via the first bearing 25.
As a result, the jet vane 22 is set to a predetermined steering angle as shown by the chain double-dashed line in FIG. 4, and the rocket thrust direction is controlled.

In this case, use the potentiometer 33 to
The rotation of 23, that is, the rudder angle of the jet vane 22 is monitored, and the monitored jet vane 22 rudder angle signal is returned to the servo amplifier and calculated to be a predetermined rudder angle based on the processing condition. Controlled.

Next, when the rocket no longer needs thrust direction control, the solenoid 35
Is turned on, the locking portion 35a is attracted, and the engagement state with the arm 34 is released. Then, the force of the tension spring 36 causes the rotating member 24 to rotate via the arm 34. The first support shaft 23 is rotated integrally with the rotating member 24, and the jet vane 22 is rotated from the state shown by the solid line in FIG. The gas is outside the gas injection range and is housed in the housing portion 1a provided inside the rocket body 1.

At that time, since the axis of the second support shaft 26 and the axis of the rod 29 intersect at one point on the axis of the first support shaft 23, the second support shaft
Even if the axes of 26 and rod 29 are not aligned, the rotating member 2
4, The 1st support shaft 23 and the rod 29 will rotate smoothly.

As a result, the jet vane 22 stored in the storage unit 1a
Does not become the resistance to combustion gas injection, and does not become the air resistance during flight. Further, unlike the conventional case, the rocket direction control device 21 is not separated from the rocket body 1 unlike the conventional case, so that the ground equipment and the like are not damaged.

5 to 7 are views showing a second embodiment of the present invention.

The rocket thrust direction control device 41 of this embodiment is of a type that accommodates only the jet vanes 42, and has a feature that it has a simple structure with a reduced number of rotation drive parts.

That is, the jet vane 42 is screwed to the rotary storage member 43 in the shape of a rectangular tube whose lower side is open. The rotary housing member 43 is rotatably fitted to a shaft 44a provided so as to project from both sides of the rotor 44. The axis of the shaft 44a of the rotor 44 is provided so as to be orthogonal to the axis of the jet vane 42.

The rotor 44 is rotatably supported by a hollow shaft portion 46a of a support member 46 via a radial bearing 45. The support member 46 is a mount fixed to the rocket body 1.
It is attached to 47.

A solenoid 48 is disposed inside the support member 46, and a rotary shaft 49 slid by the solenoid 48 is slidably inserted into the hollow shaft portion 46a. The rotary shaft 49 has a plate 49a that is attracted by the solenoid 48 at one end, and the other end 49b is engaged with and disengaged from the engagement groove 43a of the rotary housing member 43. The rotary shaft 49 is biased rightward in FIG. 6 by a spring 51.

Further, between the rotary storage member 43 and the rotor 44, a rotor
A torsion spring 50 for urging the rotary storage member 43 to rotate with respect to 44 is arranged.

Further, reference numeral 52 in the drawing denotes a torque arm integral with the rotor 44, and a ball screw 53 is rotatably coupled to the tip of the torque arm. And the electric screw 54 on the ball screw 53
The output shaft 54a is screwed.

 Next, the operation will be described.

In order to control the thrust direction of the rocket, the output shaft 54a of the electric servomotor 54 is rotated, the ball screw 53 is reciprocated, and the torque arm 52 is converted into swing. As a result, the rotor 44 and the rotary storage member 43 are integrally rotated via the radial bearing 45, and this rotation imparts a steering angle to the jet vane 42.

At this time, the steering angle of the jet vane 42 is monitored by a potentiometer (not shown), and the signal is returned to the servo amplifier (not shown) as in the above embodiment.

When the rocket no longer needs thrust direction control,
The jet vane 24 rudder angle is at the zero degree position (the position shown by the solid line in FIG. 7) according to the time sequence of the timer (not shown).
The solenoid 48 is turned on and the rotary shaft 49
Is attracted against the biasing force of the spring 51. When the rotary shaft 49 is sucked, the other end 49b is engaged with the engaging groove 43a of the rotary housing member 43.
Break away from Then, due to the rotational torque of the torsion spring 50, the rotary storage member 43 causes the shaft 44 of the rotor 44 to move.
Since it rotates in the direction of the arrow in FIG. 5 around a, the jet vane 42 fixed to the rotary storage member 43 is
Is outside the injection range of the combustion gas from and is housed in the housing portion 1a provided inside the rocket body 1.

8 and 9 show a third embodiment of the present invention.

In the rocket thrust direction control device 61 of this embodiment, the space near the jet vane 62 is small, and when there is no installation space for the electric servomotors 63, 64 near the jet vane 62, the jet vane is inserted via the rods 65, 66. It is characterized by swinging 62.

The jet vane 62 is screwed to a support shaft 67, and the support shaft 67 is rotatably fitted to a rotary member 68 via a radial bearing or the like about the jet vane 62 shaft center. The rotating member 68 has a shaft portion projecting in a direction orthogonal to the axis of the jet vane 62, and the shaft portion is rotatably fitted to the support member 69.

It should be noted that the rotating member is formed by an electric solenoid (not shown).
68 is normally locked to a support member 69.

A torque arm 70 is fixed to the other end of the support shaft 67. The torque arm 70 is located symmetrically with respect to the support shaft 67, and has rotatably U-shaped members at both ends.
71 and 72 are attached. Rotating members 73 and 74 are attached to the U-shaped members 71 and 72, and upper ends of rods 65 and 66 are fixed to the rotating members 73 and 74.

The lower ends of the rods 56 and 66 are, as shown in FIG.
It is mounted on ball screws 77 and 78 with ball sockets 79 and 80, and is swingable. The output shafts 83, 84 of the electric servomotors 63, 64 are fitted to the ball screws 77, 78. The electric servomotors 63, 64 are fixed to a mounting member 85 protruding from the nozzle 2 as shown in FIG.

 Next, the operation will be described.

In order to control the thrust direction of the rocket, a pair of electric servomotors 63 and 64 are operated in opposite phases. Therefore, it goes without saying that the steering angle command signal from the servo amplifier (not shown) is inverted. As a result, when both output shafts 83, 84 are rotated in the reverse direction, both ball screws 77, 78 move in opposite directions, the support shaft 67 is rotated via the rods 65, 66, and the steering angle of the jet vane 62 is changed. Is controlled. Where rod 6
Two rods 5, 66 are used because the rods 65, 66 are thin and prevent the rods 65, 66 from bending in the pressing direction.

When the rocket no longer needs thrust direction control, a timer function (not shown) or the like turns on an electric solenoid (not shown) to unlock the rotating member 68 and the support member 69. Then, Pull signals of the same phase are input to the pair of electric servomotors 63 and 64, the output shafts 83 and 84 are rotated in a predetermined direction, and the ball screws 77 and 78 are moved downward (direction of arrows in the figure), The rods 65 and 66 are pulled downward. As a result, the rotating member 68 rotates with respect to the support member 69,
As shown by the chain double-dashed line in FIG. 8, the jet vane 62 is
It is stored outside the injection range of the combustion gas from the nozzle 2 and in the storage portion 1 a provided inside the rocket body 1.

Furthermore, FIGS. 10 and 11 show a fourth embodiment of the present invention.

The rocket thrust direction control device 91 of this embodiment is a method of linearly accommodating the jet vanes 92. Further, it has a feature that the jet vane 92 can be taken in and out as needed.

Reference numeral 2 is a nozzle, reference numeral 92 is a jet vane, and the spline shaft 93 to which the jet vane 92 is fixed is slidable and rotatable in a bearing 94 fixed to the rocket body 1 in the arrow direction in the figure. A torque arm 95 is supported by the spline shaft 93 and is spline-coupled to the spline shaft 93.

A ball screw 96 is rotatably attached to a tip portion 95a of the torque arm 95, and an output shaft 98 of an electric servomotor 97 is screwed to the ball screw 96.

Further, the connecting member 99 is provided at the rear end portion 93a of the spline shaft 93.
One end of the connecting member 99 is rotatably connected, and a ball screw 100 is provided at the other end of the connecting member 99. An output shaft 102 of an electric servomotor 101 fixed to a mount 103 is screwed onto the ball screw 100.

 Next, the operation will be described.

To control the thrust direction of the rocket, the output shaft 98 of the electric servomotor 97 is rotated to reciprocate the ball screw 96 up and down, and the spline shaft 93 is rotated via the torque arm 95 to rotate the jet vane. Give the 92 a rudder angle.

At this time, the steering angle of the jet vane 92 is monitored by a potentiometer (not shown), and the signal is fed back to the servo amplifier (not shown), as described above.

When the rocket no longer needs thrust direction control, the output shaft 102 of the electric servomotor 101 is rotated by a timer function (not shown) or the like, and the ball screw 100 is moved leftward as shown by the chain double-dashed line in the figure. .

As a result, the spline shaft 93 is slid to the left in the drawing via the connecting member 99 so that the jet vane 92 is connected to the nozzle 2 as shown by the chain double-dashed line in FIG.
Outside the injection range of the combustion gas from the above, and is housed in the housing section 1a provided inside the rocket body 1.

After that, when the rocket needs thrust direction control, the output shaft 102 of the electric servomotor 101 is rotated in the direction opposite to that when the jet vane 92 is stored, and the jet vane 92 is advanced to the position shown by the solid line. .

 FIG. 12 shows a fifth embodiment of the present invention.

In the rocket thrust direction control device 111 of this embodiment, a jet vane 112 is fixed to a support shaft 113, the support shaft 113 is rotatably attached to a rotating member 115 via a bearing 114, and the support shaft 113 is also provided. A first bevel gear 116 is fixed to this.
Further, a potentiometer 117 that detects the amount of rotation of the support shaft 113 is fixed to the other end of the support shaft 113.

On the other hand, the rotating member 115 is provided with a pair of shaft portions 118 protruding in a direction orthogonal to the support shaft 113, and these shaft portions 118 are rotatably supported by the base 120 via bearings 119. The one shaft 118 is hollow, and the rotary shaft 121 is inserted therein, and the second bevel gear 122 disposed at one end of the rotary shaft 121 meshes with the first bevel gear 116. An arm 123 is projectingly provided at the other end of the rotary shaft 121, and a ball screw 124 is rotatably attached to a tip end of the arm 123, and a steering angle adjusting motor is attached to the ball screw 124. The output shaft 126 of 125 is screwed.

Further, the lever 127 is attached to the other shaft portion 118 of the rotating member 115.
Is fixed, and a ball screw 128 is rotatably attached to the tip of the lever 127.
The output shaft 130 of the storage motor 129 is screwed into the.

Next, the operation of the rocket thrust direction control device having such a configuration will be described.

To control the thrust direction of the rocket, the rudder angle adjusting motor 125 is driven to rotate the output shaft 126. Then, the second bevel gear 122 is rotated via the ball screw 124,
By rotating the first bevel gear 116 meshing with this, the jet vane 112 is set to a predetermined steering angle. The swing angle of the jet vane 112 in this case is detected by the potentiometer 117 and fed back to the servo amplifier.

On the other hand, when thrust direction control is not required, the storage motor 129 is driven to drive the output shaft 130 and the ball screw 128.
The lever 127 is rotated via. Then, the rotating member 115
Is rotated via the bearing 119, the jet vane 112 is rotated upward, and the accommodating portion 1a similar to that of the above embodiment is obtained.
Is stored in.

13 to 15 are views showing a sixth embodiment of the present invention.

In the rocket thrust direction control device 141 of this embodiment, a jet vane 142 is fixed to a support shaft 143, and the support shaft 143 is rotatably supported by a rotating member 145 via a bearing 144. A hollow shaft portion 146 is projectingly provided on the rotating member 145 in a direction orthogonal to the support shaft 143, and the shaft portion 146 is rotatably supported by a base 147 via a bearing 148.

A clutch engagement member 149 is fixed to the support shaft 143, and a torque arm 150 is fixed to one end of the clutch engagement member 149. This torque arm 150
A ball screw 151 is rotatably provided at the tip of the electric screw, and an electric servomotor 152 is attached to the ball screw 151.
Output shaft 153 is screwed.

Further, the shaft 146 of the rotating member 145 has a rod 154.
A clutch 155 that engages and disengages with the clutch engaging member 149 is provided at one end of the rod 154.
Further, the clutch 155 has an engaging recess 158 of the rotating member 145.
It is designed to engage and disengage. And this rod 154
To the other end of the solenoid 156 for engaging the clutch 155.
Is provided. The rod 154 is biased by a spring 157 in the clutch disengagement direction.

Next, the operation of the rocket thrust direction control device having such a configuration will be described.

In order to control the thrust direction of the rocket, the rod 154 is slid by the urging force of the spring 157 and the clutch 155 is moved.
Is disengaged from the clutch engagement member 149 to bring the support shaft 143 into a free state.

In this state, the clutch 155 has the engagement recess 15 of the rotating member 145.
The rotary member 145 is fixed to the base 147 by being locked to the base plate 147.

When the output shaft 153 of the electric servomotor 152 is rotated from this state, the support shaft 143 rotates via the ball screw 151 and the like via the bearing 144, and the jet vane 142 is set to a predetermined steering angle, Thrust direction is controlled.

On the other hand, when control of the thrust direction is not required, the solenoid 156 is turned on to engage the clutch 155 with the clutch engagement member 149 against the biasing force of the spring 157. When the electric servomotor 152 is driven in this state, the rotating member 145, the support shaft 143, the jet vane 142, etc. rotate integrally through the bearing 148, and the solid line and the alternate long and two short dashes line in FIG. As shown in FIG. 3, the jet vane 142 is rotated by 90 ° and is housed in the housing portion 1 a provided outside the injection range of the combustion gas from the nozzle 2 and provided inside the rocket body 1.

[Effects of the Invention] As described above, according to the present invention, when the rocket does not need thrust direction control, the jet vane is housed in the housing portion. Since it is not necessary to separate the rocket thrust direction control device from the rocket body, damage to ground equipment due to separated falling objects can be prevented, and in particular, it is possible to safely launch in a narrow space or vertically launch on the ground. Further, the jet vane is outside the injection range of the combustion gas from the nozzle,
And because it is stored in the storage section provided inside the rocket body, this jet vane does not become a resistance to combustion gas injection, and it does not become an air resistance during flight. Demonstrate.

[Brief description of drawings]

1 to 4 are views showing a first embodiment of a rocket thrust direction control device of the present invention, FIG. 1 is a sectional view taken along the vertical direction of the device, and FIG. 2 is a perspective view of the device. FIG. 3 is a sectional view of the same apparatus taken along the horizontal direction, and FIG.
FIG. 5 is a front view seen from the direction, FIG. 5 to FIG. 7 are views showing a second embodiment of the present invention, FIG. 5 is a sectional view corresponding to FIG. 1, and FIG. A sectional view taken along line VI, FIG. 7 is a front view corresponding to FIG. 4, FIGS. 8 and 9 are views showing a third embodiment of the present invention, and FIG. 8 is corresponding to FIG. Sectional view, FIG. 9 corresponds to FIG. 4, FIG. 10 and FIG.
FIG. 11 is a view showing a fourth embodiment of the present invention, FIG. 10 is a plan view of the same apparatus, FIG. 11 is a sectional view corresponding to FIG. 1, and FIG. 12 is a fifth embodiment of the present invention. A sectional view taken along the horizontal direction,
13 to 15 are views showing a sixth embodiment of the present invention. FIG. 13 is a sectional view corresponding to FIG. 1, FIG. 14 is a sectional view corresponding to FIG. 3, and FIG. Sectional view taken along the line XV-XV in FIG. 14, FIGS. 16 to 19 are views showing a conventional example, FIG. 16 is a front view showing the entire rocket, and FIG. 17 is a conventional rocket thrust direction control. FIG. 18 is a sectional view showing the device, FIG. 18 is a plan view of the device, and FIG. 19 is a sectional view taken along line XIX-XIX in FIG. 1 …… Rocket body 2 …… Nozzle 21,41,61,91,111,141 …… Rocket thrust direction control device 22,42,62,92,112,142 …… Jet vane

 ─────────────────────────────────────────────────── --- Continuation of the front page (72) Inventor Shigeyuki Ogawa 2 Takara-cho, Kanagawa-ku, Yokohama, Kanagawa Nissan Motor Co., Ltd. (56) Reference JP-A-2-277952 (JP, A)

Claims (1)

(57) [Claims] 1. A plurality of jet vanes are arranged in a nozzle of a rocket body along a radial direction of a nozzle opening, and the jet vane is rotated by a steering angle adjusting means around the radial direction of the nozzle opening. In the rocket thrust direction control device for controlling the thrust direction of the rocket by the lateral thrust generated according to the rudder angle of the jet vane, the housing of the jet vane is burned from the nozzle. A storage means is provided that is outside the gas injection range and is provided inside the rocket body, and that drives the jet vane to store in the storage portion when thrust direction control is unnecessary during flight of the rocket. A rocket thrust direction control device characterized by the above.