JP2673294B2 - Aircraft control test method and its equipment - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gliding-type aircraft control test method for simulating an actual flying environment on the ground without acquiring a flying vehicle, and acquiring and evaluating data relating to the aircraft control. Regarding the device.

[0002]

2. Description of the Related Art Conventionally, as a test apparatus for controlling a body without firing a flying body, Japanese Patent Laid-Open No. 3-5050
A flying object test apparatus described in Japanese Patent No. 0 has been proposed. As shown in FIG. 6, this flying body testing apparatus is an attitude control device (TVC) mounted on the flying body F while allowing the flying body F to have rotational freedom in the machine body pitch direction P and the machine body roll direction R. A device for performing a performance test of the device 20. A base member is a support member 21 for rotatably supporting the flying body F in either one of the machine body pitch direction P and the machine body roll direction R. (Table) 2
The bearing is supported rotatably in the other direction of freedom with respect to 2.

FIG. 6 shows the structure of this flying body test apparatus.
When the actual flying object F is set in the test device and activated as shown in Fig. 3, each control function unit (not shown) mounted on the flying object F causes the attitude control device (TVC) to operate.
(Equipment) 20 operates in the same manner as in the actual flying state, and at the same time, since the flying body F has the degree of freedom in the pitch and roll directions with respect to the test member (table) 22, the displacement of each degree of freedom is Will be accompanied. By connecting each control function unit mounted on the flying body F to an external measurement display function unit in advance, the output signal of each control function unit is monitored to detect the attitude control device (TVC device) 20. You can evaluate your work.

However, this flying body testing device is
The flying body F itself is bearing-supported by the support body 21,
Since the free flight state is not simulated, the aerodynamic force is not applied to the flying body F, and therefore, the acquisition and evaluation of the data regarding the aircraft control under the flying environment (the direct evaluation of the flight path) are performed. I can't.

Conventionally, when aerodynamic force is applied to a flying body to obtain data on the body control under a flying environment,
The wind tunnel has been used, but the effect of the rocket motor jet was not measurable at this time. Further, the aerodynamic data obtained by the wind tunnel test is a characteristic in a stable uniform fluid, and the initial stable flight (path) cannot be accurately evaluated.

In order to evaluate the initial stable flight (path) with high accuracy, the main test of launching a flying object is very effective, but data acquisition and evaluation cannot be performed in one launch test. , Even if you have done hundreds of firing tests,
Since the conditions are different each time, stable data acquisition and evaluation cannot be obtained. Moreover, hundreds of firing tests cannot be performed in practice due to safety and cost.

[0007]

Therefore, according to the present invention, it is possible to acquire and evaluate data regarding airframe control by simulating a free-flying state of a flying body on the ground without firing the flying body. In particular, it is an object of the present invention to provide an aircraft control test method for a flying vehicle and a device therefor capable of acquiring and evaluating data on low-speed flying performance immediately after launch.

[0008]

[Means for Solving the Problems] A method for testing a vehicle body control of a flying vehicle according to the present invention for solving the above-mentioned problems is a vehicle body supporting mechanism capable of rotating a flying vehicle in a yaw direction, a pitch direction and a roll direction. Support and then slide the measuring platform equipped with this airframe support mechanism on the rails using the rocket motor for acceleration to give aerodynamic force to the flying vehicle and at the same time ignite the rocket motor of the flying vehicle. Simulate the free flight of the body, then operate the flight body steering device,
According to that, the behavior of the flying vehicle is measured on the measurement stand, the actual external force and the actual moment are measured, and the actual external force and the actual moment are applied to control the flying vehicle to measure the dynamic flying. It is characterized by evaluating shoaling performance.

Further, the airframe body control test apparatus according to the present invention for carrying out the above-mentioned test method includes a rail,
A measurement platform that slides while being held by the rails, an acceleration rocket motor and a braking device that are equipped on the measurement platform, a measurement device that is built in the measurement platform, and a flying object that is provided on the measurement platform in the yaw direction. , A machine body support mechanism that rotatably supports the pitch direction and the roll direction.

[0010]

As described above, in the airframe control test method for a flying object of the present invention, it is possible to simulate free flight of a flying object, and by operating the flying device steering device, The behavior, that is, changes in the aircraft attitude in the yaw direction, pitch direction, and roll direction can be measured, and since the external body force and actual moment are applied to the flying vehicle to control the flying vehicle, the same as in the main test for launching a flying vehicle The dynamic flight performance can be evaluated. In particular, it is possible to obtain and evaluate data relating to the aircraft aerodynamic performance and control performance (flying route) in the low speed range immediately after launch.

Further, as described above, the airframe body control test apparatus according to the present invention has the airframe support mechanism for rotatably supporting the airframe in the yaw direction, the pitch direction and the roll direction. The mechanism is provided on a sliding measurement pedestal that is held by rails, and this measurement pedestal is equipped with an acceleration rocket motor, so the above-mentioned airframe control test method can be carried out smoothly and easily, and under the same conditions. The airframe control test method can be repeatedly carried out, and thus stable airframe control data can be acquired and evaluated.

[0012]

[Embodiment] An embodiment of a method and apparatus for controlling a body of a flying vehicle according to the present invention will be described. First, an embodiment of an apparatus for carrying out the airframe control test method of a flying object will be described with reference to the drawing. As shown in FIG. 1, a rail 2 is laid and fixed in a straight line on a long base 1 having a length of 300M. A measurement stand 3 is slidably held on the rail 2 by a slider 4 provided on the bottom surface. A braking device 5 for speed control and stopping is installed on the front side of the measurement platform 3, and an acceleration rocket motor 6 is installed on the rear side. Inside the measuring gantry 3, a measuring device (not shown) incorporating an electronic circuit having a data communication function for controlling the measuring gantry 3 and controlling the machine body is provided. A body support mechanism 7 that supports the flying body F rotatably in the yaw direction, the pitch direction, and the roll direction is provided on the measurement base 3. In this machine body support mechanism 7, as shown in FIG. 2, a yaw shaft 9 is rotatably supported by a vertical hollow shaft 8 standing on the measurement stand 3 as shown in FIG. As shown in FIG. 2, the middle of a semicircular support arm 10 having an upward opening is fixed and the support arm 1
The pitch shafts 11 are horizontally provided at both ends of the pitch 0, and the cylindrical machine tool support 12 is provided at the tips of the pitch shafts 11.
1 is rotatably supported through a bearing 13 as shown in FIG.
The flying body F is rotatably supported in the roll direction via a bearing 14 as shown in FIG.

Next, an explanation will be given of a method for controlling the aircraft body control of the aircraft carried out by using the aircraft body control test apparatus constructed as described above. As shown in FIG. A cylindrical machine body support 12 of the mechanism 7 is rotatably supported on the outer periphery of the mechanism via bearings 14. As a result, the flying body F can rotate in the roll direction on the machine body support 12, and can rotate in the pitch direction on the pitch axis 11 via the machine body support 12, and the machine body support 12, the pitch axis 11, The yaw shaft 9 can be rotated in the yaw direction on the hollow shaft 8 via the support arm 10. Next, the measurement platform 3 equipped with the machine body support mechanism 7 is attached to the acceleration rocket motor 6
Is used to slide on the rail 2 at 300 m / sec to apply aerodynamic force to the flying body F and at the same time ignite the rocket motor M of the flying body F to simulate the free flying of the flying body F. Next, the steering device (not shown) of the flying body F is operated, and the aerodynamic force corresponding thereto is applied to the airframe.
Then, not only the actual external force and the actual moment are measured, but also the behavior of the flying body F, that is, the attitude of the vehicle in the yaw direction, the pitch direction, the roll direction, the acceleration, and the like are controlled, and the measurement device built in the measurement pedestal 3 is used. The dynamic flight performance of the flying body F can be evaluated by measuring (not shown). Thus, it is possible to simulate the actual flying environment of the flying body F on the ground without launching the flying body F, and obtain and evaluate the data regarding the aircraft control, especially the low speed immediately after launching the flying body. It is possible to obtain and evaluate data on airframe aerodynamic performance and control performance (flying route) in the area.

The above-mentioned machine control test method can be carried out in the machine control test apparatus repeatedly under the same conditions to obtain and evaluate stable machine control data.

[0015]

As described above, according to the airframe control test method for a flying vehicle of the present invention, without launching a flying vehicle,
It is possible to simulate the free-flying state of the flying object on the ground and acquire and evaluate the data related to the aircraft control. Especially, the data related to the low-speed flying performance immediately after the launch can be acquired and evaluated. It is most suitable as the final ground confirmation test method for the airframe control (autopilot) system before the test.

Further, according to the airframe body control test apparatus of the present invention, the above-mentioned airframe control test method can be smoothly and easily carried out, and further, the airframe control test method can be repeatedly carried out under the same conditions. , It is possible to acquire and evaluate stable data regarding airframe control.

[Brief description of the drawings]

FIG. 1 is a diagram showing a method for testing a vehicle body control of a flying vehicle using a vehicle body control testing apparatus for a flying vehicle of the present invention.

FIG. 2 is an enlarged perspective view showing a machine body support mechanism in the machine body control test apparatus of FIG.

FIG. 3 is an enlarged vertical sectional view of a portion A of FIG.

FIG. 4 is an enlarged sectional view of a B part in FIG.

FIG. 5 is an enlarged sectional view of a portion C in FIG. 2;

FIG. 6 is a perspective view showing a conventional flying body test apparatus.

[Explanation of symbols]

 2 Rails 3 Measuring platform 5 Braking device 6 Rocket motor for acceleration 7 Airframe support mechanism 9 Yaw axis 11 Pitch axis 12 Airframe support tool F Flying vehicle M Rocket motor

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Hideaki Sato 1 Kawasaki-cho, Kakamigahara-shi, Gifu Kawasaki Heavy Industries, Ltd. Gifu factory (56) Reference JP-A-6-64598 (JP, A) JP HEI 3-50500 (JP, A)

Claims (2)

(57) [Claims] 1. A flying object is controlled in a yaw direction, a pitch direction,
Support the machine support mechanism that can rotate in the roll direction, and then slide the measurement platform equipped with this machine support mechanism on the rail using the rocket motor for acceleration to apply aerodynamic force to the flying body and fly at the same time. The rocket motor of the body is ignited to simulate the free flight of the flying body, and then the flight vehicle steering device is operated to measure the behavior of the flying body in response to the measurement on the measuring stand, and the external force and the actual moment. A method for testing the aircraft control of a flying vehicle, characterized in that the dynamic flight performance is evaluated by measuring and measuring the aircraft while controlling the flying vehicle by applying its actual external force and actual moment. 2. A rail, a measurement platform held by the rail and sliding, a rocket motor for acceleration and a braking device equipped on the measurement platform, a measurement device built in the measurement platform, and a measurement platform on the measurement platform. An airframe control test device for a flying body, which is equipped with a body support mechanism that supports the flying body so that it can rotate in the yaw, pitch, and roll directions.