KR101581251B1 - Guidance system for flying object and flying object having the same - Google Patents

Abstract

The present invention relates to a turbomolecular pump including a turbine portion having an inlet for introducing a fluid into an inner space, a fluid passage connected to the turbine portion to form the inner space, And a lateral force generating unit for generating a lateral force by using the relative rotational movement between the turbine unit and the lateral force generating unit and the flying body to control the flying direction of the flying body rotatably coupled to the turbine unit and the lateral force generating unit, And a roll control unit for controlling the discharge direction of the fluid.

Description

TECHNICAL FIELD [0001] The present invention relates to a flight posture control apparatus,

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to an attitude control apparatus for conducting an inductive steering of a vehicle.

Background Art [0002] A conventional air vehicle posture control system has an electric driving device using a motor, a power transmission device, a battery and a control circuit, and a hydraulic or pneumatic driving device using a complicated flow path, a cylinder, and a high-pressure energy source. Such a system is complicated in structure, has a high manufacturing cost, and is large in size, so it is difficult to apply to small-sized air vehicles such as small missiles and shells.

In addition, conventionally, an aerodynamic surface (blade) control method is generally used to control the posture of a flying object. Since the posture control system using the wing controls the attitude of the airplane using the protruding wings, interference may occur with an external structure such as a launch tube. Especially when flying objects are dropped on the floor, the wings can be damaged. In order to solve this problem, some patents suggested a wing folding type attitude control device. In this case, there is a disadvantage that the structure is complicated because an additional wing expansion device is required.

Also, in the case of the posture control system using the existing wing, when the wing is deployed, the wing occupies a large space in the entire diameter of the flight body. The space occupied by the wings in the radial direction of the flying body is large, so that the space of the body portion where the payload is mounted is relatively small.

Therefore, development of a device capable of controlling the attitude of a flying body with a simple structure without using a conventional wing structure and a complicated driving device to control the attitude of the flying body can be considered.

The object of the present invention is to provide a flight posture control apparatus for controlling the posture of a flying object by using a fluid flowing through a turbine structure.

According to another aspect of the present invention, there is provided an apparatus for controlling a body posture, comprising: a turbine section having an inlet for introducing fluid into an internal space; A lateral force generating unit for generating a lateral force by discharging the fluid introduced into the inner space by a flow path formed in at least one region of the outer periphery of the turbine unit and the lateral force generating unit, And a roll control unit for controlling the discharge direction of the fluid using the relative rotational motion between the turbine unit and the lateral force generating unit and the flying body.

According to an embodiment of the present invention, the turbine unit or the lateral force generating unit may further include an aerodynamic force fin mounted on the outer circumference of the turbine unit or the lateral force generating unit to stably change the flow of the fluid.

According to another embodiment of the present invention, the roll control unit includes a coil for surrounding the outer circumference of the flying body to be rotated together with the flying body, and a permanent magnet mounted on the inner circumference of the turbine unit or the lateral force generating unit, And electricity can be obtained from the induced electromotive force generated in the coil by the relative rotational motion generated between the turbine unit and the lateral force generating unit and the flying body.

The roll control unit controls a rotational speed of the turbine unit and the lateral force generating unit to adjust a discharge direction of the fluid so that a breaking force is generated between the coil and the permanent magnet by controlling the intensity of a current flowing through the coil .

According to another embodiment of the present invention, the turbine portion includes a plurality of blades radially extending around a rotation axis of the turbine portion to rotate the turbine portion by changing the flow of the fluid flowing into the inner space can do.

According to another embodiment of the present invention, the flow path for discharging the fluid may be inclined so that a part of the fluid discharged from the lateral force generating unit may flow toward the front or rear of the turbine portion.

According to another embodiment of the present invention, the turbine unit, the lateral force generating unit, and the turbine unit and the lateral force generating unit, which are disposed between the turbine unit and the lateral force generating unit and the flying body, And a bearing portion that rotatably moves with respect to the flying body.

In order to achieve the above object, the present invention proposes a flight vehicle equipped with a flight posture control device. The airplane includes a projectile formed to be able to fly, and an airplane posture control device installed at one end of the projectile to control the attitude of the projectile, and according to any one of claims 1 to 7.

In the present invention, the flow of fluid introduced into the turbine is discharged in one region to generate a lateral force, and electricity is generated by the flow of the introduced fluid. By regulating the discharge direction of the fluid by using the generated electricity, So that it is easy to manufacture and at the same time has a small manufacturing cost.

In addition, the present invention has an advantage of minimizing interference due to the blade structure or jamming of the periphery of the apparatus by driving the apparatus with the turbine unit and the lateral force generating unit without using a wing structure for controlling the posture of the air vehicle . In addition, since the wing structure is not provided, the interior space of the body of the air vehicle body can be relatively expanded and utilized.

1 is a perspective view of a flying body having an air bearing posture control device according to an embodiment of the present invention;
FIG. 2 is a side view showing a flying body having the air vehicle posture control device shown in FIG. 1. FIG.
3 is a cross-sectional view showing a flying body having the air vehicle posture control device shown in FIG.
FIG. 4 is a perspective view showing the air vehicle posture control apparatus shown in FIG. 1. FIG.
5 is a front view of the air vehicle posture control apparatus shown in FIG.
FIG. 6 is a perspective view showing a state in which an aerodynamic pin is mounted on an outer periphery of a flying body having the aviator posture control device shown in FIG. 1. FIG.
FIG. 7 is a front view showing a state in which an aerodynamic pin is mounted on an outer periphery of a flying body having the aviator control system shown in FIG. 6;

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a flight posture control apparatus and a flight vehicle having the same will be described in detail with reference to the accompanying drawings.

In the present specification, the same or similar reference numerals are given to different embodiments in the same or similar configurations. As used herein, the singular forms "a", "an" and "the" include plural referents unless the context clearly dictates otherwise.

FIG. 1 is a perspective view showing a flying body 10 having an airborne posture control apparatus 100 according to an embodiment of the present invention. FIG. 2 is a perspective view showing an airborne posture control apparatus 100 FIG. 3 is a cross-sectional view illustrating a flying body 10 having the air bearing posture control apparatus 100 shown in FIG. 1, and FIG. 4 is a cross-sectional view showing the air bearing posture control apparatus 100, and FIG. 5 is a front view showing the air vehicle posture control apparatus 100 shown in FIG.

1 to 5, the airborne posture control apparatus 100 according to an embodiment of the present invention includes a turbine unit 110, a lateral force generating unit 120, and a roll control unit 130.

The turbine section (110) has an inlet to allow fluid to flow into the interior space. For example, as shown in FIG. 5, the turbine unit 110 may include a plurality of turbine units 110 each having a radial type centered on the rotational axis of the turbine unit 110, for rotating the turbine unit 110 by changing the flow of the fluid flowing into the internal space. And a plurality of blades 112 that are formed to extend from the blade 112. [ In addition, the rotational direction and rotational speed of the turbine section 110 can be adjusted by adjusting the tilting angle of the blade 112.

The lateral force generating part 120 is coupled with the turbine part 110 to form the inner space and generate the lateral force by discharging the fluid introduced into the inner space. Specifically, the lateral force generating unit 120 includes a flow path 122 formed in at least one region of the outer periphery, and at least a part of the flow path forming unit 120 may be integrally formed so as to rotate together when the turbine unit 110 rotates. Accordingly, when the fluid introduced through the turbine section 110 is discharged to the one region, a lateral force acting on the side of the lateral force generating section 120 can be generated in the direction in which the fluid is discharged .

The flow path 122 for discharging the fluid may be inclined so that a part of the fluid discharged from the lateral force generating unit 120 flows to the front or rear of the turbine unit 110. Accordingly, the acting direction of the lateral force can be formed more variously.

The roll control unit 130 adjusts the discharge direction of the fluid by rotating the turbine unit 110 and the side force generating unit 120. The turbine portion 110 and the lateral force generating portion 120 are rotatably coupled to the flying body 10 and are rotated using the relative rotational movement between the turbine portion 110 and the output generating portion 120 and the flying body 10 A lateral force is generated on the flying body 10 to control the flying direction of the flying body 10.

For example, the control system 100 may be disposed between the turbine unit 110 and the lateral force generating unit 120 and the flying body 10 so as to fly the turbine unit 110 and the lateral force generating unit 120 And a bearing unit 150 that rotatably moves with respect to the body 10. The turbine portion 110 and the lateral force generating portion 120, which are decoupled by the structure, and the flying body 10 have different rotational characteristics because they are not identical in rotational direction and rotational speed.

Specifically, the roll control unit 130 includes a coil 132 and a permanent magnet 134, and can acquire electricity by the relative rotational motion. The roll control unit 130 adjusts the intensity of a current flowing through the coil 132, 132 and the permanent magnets 134. In this case,

The coil 132 is mounted so as to surround the outer circumference of the flying body 10 so as to be rotatable together with the flying body 10. The coil 132 may be formed as a conductor capable of electric movement.

The permanent magnet 134 may be mounted on the inner circumference of the turbine section 110 or the lateral force generating section 120 so as to face and enclose at least a part of the coil 132. When the rotation occurs in the flying body 10 or the turbine 110 and the lateral force generating unit 120, a gap between the decoupled turbine unit 110 and the lateral force generating unit 120 and the flying body 10 A relative rotational motion is generated. At this time, the roll control unit 130 can acquire electricity by the induced electromotive force generated in the coil 132. The electric power thus obtained can be used for operation of an electronic device such as a global positioning system (GPS) or various control devices.

The roll control unit 130 generates a breaking force between the coil 132 and the permanent magnet 134 by adjusting the magnitude of the current flowing through the coil 132 so that the flow path 122, The posture of the flying body 10 can be controlled by stopping at a specific position.

For example, the roll control unit 130 may use an electric load (not shown) when the flow path 122 is located at a place where the lateral force is generated in a state where the lateral force generating unit 120 is rotated Thereby increasing the amount of current flowing through the coil 132 to generate the braking force between the coil 132 and the permanent magnet 134, thereby fixing the flow path 122 at the corresponding position. Then, when the posture of the body 10 is adjusted, the amount of current flowing through the coil 132 is reduced again to remove the braking force generated in the lateral force generating unit 120.

The breaking force acting between the flight body 10 and the posture control apparatus 100 is not caused by the magnetic force between the flight body 10 and the posture control apparatus 100 described above, ) Or the like.

The lateral force generating unit 120 of the air vehicle posture control apparatus 100 forms the flow path 122 for discharging the fluid to be inclined perpendicularly or at a predetermined angle with respect to the traveling direction of the flying body 10, Thereby generating lateral force on the body 10. At this time, the roll control unit 130 of the flight posture control apparatus 100 controls the rotation speed of the lateral force generating unit 120 to adjust the position of the flow path 122 through which the fluid is discharged, Can be controlled.

Hereinafter, a flight vehicle (not shown) according to another embodiment of the present invention will be described.

The airplane (not shown) includes a projectile (not shown) and a flight posture control device 100.

The projectile is formed to be movable in the air. For example, the projectile may include both weapons such as guided weapons, non-guided weapons, and general air vehicles flying over the air.

The flight attitude control device 100 may be installed at one end of the projectile so as to control the flight attitude of the projectile.

Although the above-described air vehicle posture control apparatus 100 according to an embodiment of the present invention has been described by way of example of the projectile moving in the air, it is also possible to control the posture of the underwater moving means have. In this case, the airborne posture control apparatus 100 is installed at one end of the underwater moving means and can control the posture of the underwater moving means by introducing a liquid fluid, which is not a gas, into the interior of the turbine section 110 have.

Hereinafter, an aerodynamic force fin 140 provided in the turbine section 110 of the present invention will be described with reference to FIGS. 6 and 7. FIG.

FIG. 6 is a perspective view illustrating a state in which an aerodynamic pin is mounted on an outer periphery of a flight body having the flight posture control device shown in FIG. 1, and FIG. 7 is a perspective view of the outer periphery of the flight body having the flight posture control device shown in FIG. In which an aerodynamic pin is mounted.

Referring to FIGS. 6 and 7, the airborne posture control apparatus 100 may further include an aerodynamic pin 140.

The aerodynamic pin 140 may extend in one direction from the outer circumference of the turbine section 110 or the lateral force generating section 120 to stably change the flow of the passing fluid to improve the flight stability of the flying body 10. [ . 6, the air force fins 140 may be formed on the outer circumference of the lateral force generating portion 120 or may be formed on the outer circumference of the turbine portion 110 and the lateral force generating portion 120 at least A part may be formed.

However, the scope of the present invention is not limited to the configuration and method of the embodiments described above, and all or some of the embodiments may be selectively combined so that various modifications may be made to the embodiments. In addition, the present invention can be applied to all equivalents of inventions, such as inventions that can be modified, added, deleted, or replaced at the level of those skilled in the art, It belongs to the scope is self-evident.

100: Flight posture control device 110:
120: side force generating unit 130: roll control unit
132: coil 134: permanent magnet
140: aerodynamic pin 150: bearing part

Claims (8)

Flying body;
A turbine section having an inlet for introducing fluid into the internal space;
A turbine portion coupled to the turbine portion and coupled to the turbine portion, the turbine portion being rotatable by decoupling the turbine portion from the turbine portion, the turbine portion being rotatable with respect to the turbine portion, A lateral force generating unit for generating a lateral force by discharging the lateral force; And
And a roll control unit for controlling the discharge direction of the fluid by using the relative rotational motion between the turbine unit and the lateral force generating unit and the flying body to control the flying direction of the flying body by adjusting the direction of the lateral force The airbag posture control device. The method according to claim 1,
Further comprising an aerodynamic force fin mounted on an outer circumference of the turbine unit or the lateral force generating unit for stably changing a flow of fluid passing through the turbine unit or the lateral force generating unit. The method according to claim 1,
The roll control unit includes:
A coil surrounding the outer periphery of the flying body to be rotated together with the flying body; And
And a permanent magnet mounted on an inner circumference of the turbine portion or the lateral force generating portion to face the coil,
And the electric power is obtained from the induced electromotive force generated in the coil by the relative rotational motion generated between the turbine unit and the lateral force generating unit and the flying body. The method of claim 3,
The roll control unit controls a rotational speed of the turbine unit and the lateral force generating unit to adjust a discharge direction of the fluid so that a breaking force is generated between the coil and the permanent magnet by controlling the intensity of a current flowing through the coil Wherein the control unit is configured to control the airbag. The method according to claim 1,
Wherein the turbine section includes a plurality of blades radially extending around a rotation axis of the turbine section to rotate the turbine section by changing a flow of the fluid flowing into the internal space. The method according to claim 1,
Wherein the flow path for discharging the fluid is inclined so that a part of the fluid discharged from the lateral force generating unit can flow to the front or rear of the turbine unit. The method according to claim 1,
The turbine unit and the lateral force generating unit are disposed between the turbine unit and the lateral force generating unit and the flying body so that the turbine unit and the lateral force generating unit and the flying body rotate relative to each other, And a bearing unit for controlling the orientation of the air bearing member. A projectile formed to be able to fly; And
And a flying object posture control device according to any one of claims 1 to 7, provided at one end of the projectile to control the posture of the projectile.

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