JPS63140300A - Deflection control system of missile - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to an azimuth control method for a flying object, and in particular a method for correcting the movement of the flying T and flying rA positions of n objects due to wind displacement.
Regarding 2.

Ci: L's previous technique tfi) The conventional azimuth control method (Yu, eye) was the $11 Uzuro method to keep the azimuth of the flying 11 objects relative to the 7 points constant at the instep.

, [Problem to be solved by the invention] Therefore, in the conventional azimuth angle il+60 method, M t
As shown in Figure 1, when the flying object 1 flies from the light point 0 to the target point P on a flight path t8A, if a kite with wind speed V blows as shown by the arrow, the azimuth angle with respect to N (north) While keeping θ unchanged, the flying object 1 is swept down the river and follows the flight path B. As a result, the wind speed is V9 launch point O
If the flight time from to reaching the target point P is t, then
When the flight time t that the flying object 1 is supposed to reach the target point P has elapsed, the flying object 1 is swept away by a distance of ■·t from the target point P, and in the end, the flying object 1 reaches the target point P by a distance of t, +1 There was a problem with not being able to reach it.

Therefore, the present invention provides a method for controlling the azimuth angle of a flying object, in which the movement of the flying position of the R group is automatically corrected due to the influence of the bird, allowing the flying object to accurately reach the target point. The purpose is to

(Means for Solving the Problems) The present invention aims to solve the above problems and achieve the purpose.
The following measures were taken. In other words, a detection means for detecting the lateral acceleration of the flying object is mounted on the flying object, and based on the lateral acceleration detected by the detection means and the attitude angle of the flying object, the ship flying organization Based on the steering angle command corresponding to the calculated amount of movement of the projectile, the azimuth angle is corrected υI (In) so that the flying group reaches the target point. I decided to do it.

[Effect]

By taking such measures, the amount of movement of the flying object in the horizontal direction is calculated using the attitude angle of the flying object as the reference azimuth angle, and the azimuth and azimuth angle maintenance are calculated to correct this amount of movement. Since the steering angle command including the time is output,
The movement of the flying object's flight y and n positions due to the influence of the movement is corrected on its own.

Embodiment FIG. 1 is a block diagram showing the configuration of an embodiment of the present invention. In Fig. 1, 11 is a gyro, and a flying object 1
0 (not shown in Figure 1) is detected and an attitude angle signal S
Outputs 1. Reference numeral 12 denotes a detection sensor consisting of an accelerometer or the like, which is mounted on the flying object 10 so as to detect the lateral acceleration of the flying object 10, and outputs a detection signal or t5 lateral acceleration signal 82. These beliefs @SI, S2 are controlled
(Supplied to the meter 13. The control meter tHJ13 calculates the amount of movement of the flying object 10 by the wind, based on the attitude angle signal S1 of the flying object 10 and the lateral acceleration signal 82. A steering angle command is calculated in accordance with the calculated amount of movement of the flying object 10, and a steering angle Ih command signal S3 is supplied to the servo device 14. The servo device 14 responds to the steering angle command signal S3. Then, the steering angle is controlled υll so that the flying object 10 reaches the target point, and the azimuth angle is corrected 1 and 1.
Perform 1ηO.

FIGS. 2 and 3 are diagrams showing the operation of this embodiment.

As shown in FIG. 2, the flying object 10 launched from the launch point ○ toward the target point P flies along the flight χ, I path A so as to keep the reference azimuth α constant. Now, suppose that while the flying object 10 is in flight, a wind with a circumferential speed of V is blown from the direction of the arrow. Then, the flying object 10 is swept away by a distance MX while keeping the reference azimuth α constant. At this time, if the reference azimuth angle α is kept constant and there is no means to correct the influence of the wind, the flying object 10
will fly along flight path B and move to a position such as 10'. However, in this example, since a means for correcting the influence of wind is provided, azimuth angle control is performed as follows.

In the Motominoura example, the "self-attitude angle" of the flying object 10 - "
Since the reference azimuth angle α is the same, the amount of shift X that is perpendicular to the reference azimuth angle α is determined by the attitude angle signal S1 multiplied by 1q by the gyro 11 and the detection by an accelerometer etc. mounted on the flying object 10. This can be calculated using the signal S2 indicating the lateral acceleration ny detected by the sensor 12. That is, as shown in FIG. 3, Jgtl! When the azimuth angle α and the lateral acceleration ny perpendicular to the reference azimuth angle α are detected, the control 61]i! tt313113 is the control azimuth angle β necessary to calculate the flowed displacement 11■X by integrating the lateral acceleration ny, and correct the displacement ff1X in parentheses by 14.
and its holding time t, and sends out a steering angle command signal S3. By sequentially repeating and executing such control, the flying object 10 flies along the flight path C shown in FIG. 2. In this way, the flying object 10 reaches the target point P while the movement of the flight 111 position due to the influence of the kite is corrected.

In this way, in this example, [Yu, a 7. 'i i,
Detection sensor 12 consisting of an accelerometer etc. mounted on a 10
Based on the lateral acceleration ny detected by
0 detects the amount of transfer X caused by the flow, and this transfer ff
Since the azimuth of the flying object 10 is sequentially corrected and controlled in accordance with 1 It becomes possible to guide accurately.

Note that the present invention is not limited to the above embodiments,
Of course, various modifications can be made to the cylinder without departing from the scope of the present invention.

〔Effect of the invention〕

According to the present invention, the attitude angle of the flying object is the reference azimuth angle,
The amount of movement of the flying object in the lateral direction is calculated, and a steering angle command including the azimuth angle and azimuth angle holding time to correct this amount of movement is output, so the flying position of the flying object due to the influence of the wind is calculated. It is possible to provide a method for controlling the azimuth angle of a flying object, in which the movement of the flying object is automatically corrected, and the flying object can accurately reach the target point.

[Brief explanation of the drawing]

1 to 3 are diagrams showing an embodiment of the present invention, in which FIG. 1 is a block diagram showing the configuration, and FIGS. 2 and 3 are diagrams for explaining the operation. FIG. 4 is a diagram for explaining the drawbacks of the conventional example. 1.10...R group, 11...gyro, 12...
・Detection sensor, 13...Control meter tigt, i4...
Servo device. Applicant Sub-Agent Patent Attorney Takehiko Suzue Figure 1 Figure 2 Figure 3 Figure 4

Claims (1)

[Claims] A detection means for detecting lateral acceleration of the flying object is mounted on the flying object, and based on the lateral acceleration detected by the detection means and the attitude angle of the flying object, it is determined whether the flying object is blown away by the wind. The present invention is characterized in that the azimuth angle is corrected and controlled so that the flying object reaches the target point based on a steering angle command corresponding to the calculated amount of movement of the flying object. Azimuth control method for flying objects.