KR101700401B1 - Direction finding apparatus using variable sweep wings - Google Patents

Abstract

The present invention relates to a direction detecting device using a variable blade capable of adjusting the angle of a wing provided with an antenna for detecting a position of a target according to a direction of a target, thereby reducing the weight of the wing and improving the direction detection performance.
A direction detecting apparatus using a variable wing according to the present invention is a direction detecting apparatus for detecting a direction of a target by mounting an antenna 10 on a wing 2 of a flying object 1, 2 is installed at the opposite end of the flying object 1 and the blades 2 are installed to rotate in a predetermined angle range with respect to the flying object 1.

Description

[0001] DIRECTION FINDING APPARATUS USING VARIABLE SWEEP WINGS [0002]

The present invention relates to a target direction detecting apparatus for detecting a target direction using an antenna attached to a wing of a vehicle, and more particularly, to a target direction detecting apparatus for detecting a target position by controlling an angle of a wing provided with an antenna The present invention relates to a direction detecting device using a variable wing, which can reduce a weight of a wing and improve a direction detecting performance.

Interferometer method and amplitude comparison method are mainly used as a method for detecting the direction of a target in a flying object.

The interferometer system detects the direction of a target by obtaining a phase difference of a signal received from two or more antennas arranged in a space to obtain angle information of the target, and arranging left and right antennas can detect the azimuth of the target Antenna arrangement can be used to detect the elevation angle of the target. By combining the two methods, it is possible to detect the position of the target in space.

The size comparison method includes arranging two or more antennas spaced apart from each other in a direction of a main beam in a space and then calculating angle information of the target from a difference in magnitude of a signal received by each antenna In a way to obtain, the main beam must be spaced apart from the bore-sight axis and is generally implemented by giving a glancing angle to the antenna.

In the actual field, the above-mentioned two schemes are used in parallel to compensate for the disadvantages of each scheme.

On the other hand, in a flight such as a cannon or a missile, the angle of the target is extracted by using the wings 102 and 102 'with the antenna 110 attached to the flight body 101 to guide the flight body 101 accurately to the target A difference in direction detection performance may occur depending on the angle of the vanes 102 and 102 'installed on the air body 101 and the angles of the vanes 102 and 102' and the antenna 110 .

For example, as shown in FIG. 1, when the longitudinal direction of the wing 102 installed in the form of a straight line in the air vehicle 101 and the antenna 110 are parallel to each other, the interferometer type direction detection can be performed. Direction detection of size comparison method is impossible.

As shown in FIG. 2, when the antenna 110 is installed by giving a leaning angle to the wing 102 of a straight wing shape in the air vehicle 101, both the interferometer system and the size comparison system can be applied, There is a problem that the weight of the wing 102 increases because the width of the wing for mounting the antenna is widened although the direction detection performance is improved.

3, when the wing 102 'is formed in the flight body 101 in the form of a forward or backward wing and the antenna 110 is installed in parallel with the longitudinal direction of the wing 102' There is a problem that the distance between the antennas 110 is reduced and the direction detection performance of the interferometer system is deteriorated.

Meanwhile, the following prior art document discloses a 'target detection system using a frequency modulator (FM)'.

KR 10-0133968 B1

SUMMARY OF THE INVENTION The present invention has been made in order to solve the above problems, and it is an object of the present invention to provide an antenna for detecting the direction of a target in a flying object such as a cannon or a missile, The present invention is directed to a direction detecting apparatus using a variable wing.

According to another aspect of the present invention, there is provided a direction detecting device for detecting a direction of a target by mounting an antenna on a wing of a flying object, the antenna comprising: And the wing is installed to rotate in a predetermined angle range with respect to the flying object.

And the antenna is installed parallel to the wing.

And the swing angle of the antenna is determined by the rotation of the wing.

And a signal processing unit for receiving a signal output from the antenna and calculating a position of the target.

And an induction flight unit for controlling the flight of the airplane so that the airplane flies to the position of the target calculated from the signal processing unit.

The induction flight unit adjusts the output of the propulsion engine provided in the airplane so that the airplane reaches the target, and adjusts the angle of the tailplane.

And the wing is varied within a predetermined angle with respect to the flying object to detect the position of the target.

And the wing is fixed with a straight wing perpendicular to the flying object when the wing enters within a predetermined distance from the target.

According to the direction detecting apparatus using the variable blade according to the present invention having the above-described configuration, in a state where the antenna is provided in parallel with the wing, In this way, the aircraft can detect the direction of the target, so that the position of the target can be accurately calculated.

Accordingly, the target arrival performance of the flight vehicle is improved by inducing the flight vehicle to the position of the calculated target.

FIG. 1 is a schematic view showing a state where an antenna is installed parallel to the wing at an end of a wing installed in a straight body in a flying body according to a related art.
FIG. 2 is a schematic view showing a state in which the antenna is installed in a state in which the antenna is rotated at a lean angle in FIG. 1;
FIG. 3 is a schematic view showing a state where an antenna is installed parallel to the wing at an end of a wing installed in a flight vehicle according to the prior art.
4 is a perspective view showing a state in which a direction detecting device using a variable cam according to the present invention is mounted on a flight vehicle.
FIG. 5 is a perspective view showing the position of a wing and an antenna in a state in which the wing is adjusted to a retracting blade in FIG. 4; FIG.
6 is a plan view showing a state in which a direction detecting device using a variable cam is applied to a guided vehicle according to the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a direction detecting apparatus using a variable wing according to the present invention will be described in detail with reference to the accompanying drawings.

The directional detection device using a variable blade according to the present invention is characterized in that an antenna 10 is installed parallel to the wing 2 at an end of a wing 2 of a flying object 1, To be rotated within a predetermined range.

The direction detecting apparatus using the variable wing according to the present invention is formed into a shape as shown in Fig. 4 when it is a rectilinear wing, and a state as shown in Fig.

FIG. 6 shows a state in which a directional detection device using a variable damper according to the present invention is mounted on a guided vehicle. That is, as an example of the air vehicle 1, a directional detection device using a variable wing according to the present invention may be used so that the orbit up to the target is guided to the target after being fired from the projectile.

 Therefore, the direction detecting apparatus using the variable carbide according to the present invention will be described below using the guided vehicle.

A flying object (2) is provided on a flying object (1) provided as a guided vehicle for flying.

The vanes 2 are installed not to be fixed to the air vehicle 1 but to be variable within a certain range. A wing rotation part (21) for rotating the wing (2) so that the wing (2) varies within a predetermined angle range with respect to the flying object (1) And a power transmission means such as a drive source and a gear such as a motor.

An antenna (10) is installed parallel to the vane (2) at the end of the vane (2). The antenna 10 is installed in parallel to the wing 2 but the wing 2 can rotate within a predetermined angle range with respect to the air vehicle 1 so that the angle of rotation of the wing 2 The antenna 10 is imparted with a leaning angle.

 That is, the direction of the target is detected by an interferometer method when the wing 2 is straight wing (when the wing and the air body are perpendicular to each other), and when the angle of the wing 2 is variable, Location can be detected.

The signal processing unit 22 is installed on one side of the air vehicle 1 and processes a signal output from the antenna 10. [ The signal processing unit 22 can calculate the position of the target by varying the angle of the vane 2, applying both the interferometer method and the size comparison method, and processing signals output from the respective methods.

On the other hand, the air vehicle 1 includes components for taking charge of functions unique to the air vehicle. For example, FIG. 6 illustrates an example where the air vehicle 1 is a guided vehicle. In the forward direction of the air vehicle, a fuse 11 for generating an explosion signal when a target arrives, and a warhead 12 for generating an explosive force in the target Lt; / RTI >

A propulsion engine 14 for propelling the airplane 1 from a projectile to a target and a tail blade drive 15 for driving a tail blade for controlling the direction of the airplane 1 are provided at the rear of the airplane 1, ).

The navigation system further includes an induction navigation unit 13 for guiding the air vehicle 1 from the projectile to a position close to the target and a control unit 13 for controlling the air vehicle 1 to reach the desired position An induction flight unit 23 is provided. The guidance flight unit 23 controls the air vehicle 1 so that the flight vehicle 1 of the target calculated from the signal processing unit 22 can reach.

Hereinafter, the operation of the direction detecting apparatus using the variable core according to the present invention will be described.

The direction detecting apparatus using the variable cam according to the present invention may preferably detect the direction of the target with respect to the entire flight of the air vehicle 1 so that the air vehicle 1 can fly toward the target, ) Is applied at the end of control.

That is, the air vehicle 1 is fired from a projectile and then guided from the beginning to the mid-stage by the guiding navigation unit 13 and the guided flight unit 23, and then guided by the variable- Device.

When the flight body 1 enters the terminal induction phase, the angle of the wing is adjusted so that the wing 2 becomes the forward wing, the straight wing and the backward wing. When the wing 2 repeats the forward wing, the straight wing and the backward wing, a signal is output from the antenna 10, and the signal processing unit 22 outputs the signal output from the antenna 10, And calculates the position.

When the position of the target is calculated in the signal processing unit 22, the signal processing unit 22 controls the induction flying unit 23 so that the flight body 1 can fly to the calculated target position. That is, the induction flight unit 23 can adjust the speed of the air vehicle 1 by controlling the output of the propulsion engine 14 of the air vehicle 1. The induction flight unit 23 controls the tail blade drive unit 15 that controls the angle of the tail blade.

When the air vehicle 1 traces the target and approaches the target, the target is located in front of the air vehicle 1, so that the target is located in an area which does not cause ambiguity of direction detection in the interferometer system. Therefore, when the air vehicle 1 approaches within a predetermined distance from the target, the wing 2 is fixed with a straight blade so as to track the target through an interferometer system. The signal processing unit 22 calculates the position of the target using the signal output from the antenna 10 in a state where the wing 2 is fixed with a straight blade, And controls the flying object 1 so that the flying object 1 faces the target.

1: Aircraft
2: wing
10: Antenna
11: Fuse
12: Warhead
13: Guidance Navigation Department
14: Propulsion engine
15:
21:
22: Signal processor
23: induction flight section
101: Aircraft
102, 102 ': wing
110: antenna

Claims (8)

A direction detecting apparatus for detecting an orientation of a target by mounting an antenna on a wing of a flight body,
The antenna is installed at the opposite end of the air vehicle in the wing,
Wherein the wing is installed to rotate in a predetermined angular range with respect to the air vehicle,
Wherein a swing angle of the antenna is determined by rotation of the wing during flight of the air vehicle,
Wherein the wing is positioned within a predetermined angle with respect to the flying object to detect the position of the target,
Wherein the wing rotates and is fixed with a straight blade perpendicular to the flying object when the wing moves within a predetermined distance from the target while the flying object is flying toward the target.

The method according to claim 1,
Wherein the antenna is installed in parallel with the wing.

delete The method according to claim 1,
And a signal processing unit for receiving a signal output from the antenna and calculating a position of a target.

5. The method of claim 4,
And an induction flight unit for controlling the flight of the airplane so that the airplane flies to the position of the target calculated from the signal processing unit
And a direction detecting device for detecting the direction of the vehicle.

6. The method of claim 5,
Wherein the induction flight unit adjusts an output of a propulsion engine provided in the airplane so as to reach the target, and adjusts the angle of the tail blade.



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