JPH08183497A - Flying body control method and control device - Google Patents

Abstract

PURPOSE: To provide a flying body control method and a control device that can secure directional stability even when directional stability by a rudder cannot be secured due to the damage of the rudder. CONSTITUTION: Using a thrust deflecting means 4 formed of a thrust deflecting nozzle 41 for generating moment related to the yawing direction of an airframe by deflecting the direction of jet exhaust, and a driver 42 for the thrust deflecting nozzle 41, a control device adjusts the angle of the thrust deflecting nozzle 41 so as to correct the change of a yaw angle. Directional stability can therefore be secured even when a rudder 2 is out of function.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft control method and control apparatus. More specifically, the present invention relates to a control method and a control device for a flying body that enables stable flight even when the rudder is damaged.

[0002]

2. Description of the Related Art Conventionally, the yaw angle of an aircraft such as an aircraft is adjusted by controlling the rudder angle of a rudder. Therefore, if the rudder is damaged due to battle or rupture of the airtight chamber, the yaw angle cannot be adjusted, and so-called Dutch roll occurs and the steering becomes impossible. As a result, it becomes difficult to maintain normal flight, and in the worst case, a situation of a crash occurs. For example, this is the Nikko aircraft accident. Therefore, there is a demand for a device that can control the yaw direction even if the rudder is damaged.

Regarding the yaw direction control of this air vehicle, Japanese Patent Publication No. Sho 49-18397 has a plurality of deflection segments for the purpose of providing yaw control of the aircraft during vertical takeoff and landing operations. In a device for deflecting a gas flow in a jet engine, in particular an aircraft turbine jet engine, in a deflected position of the deflection segment. A plate disposed in the plane of the discharge area of the restricted flow in cooperation with at least one deflecting segment extending from the inside of the curve into the discharge flow And the plate has an emission edge, the angular position of the emission edge with respect to the longitudinal vertical plane of the deflecting device being on at least one side of the plane. Deflection device being characterized in that no way is caused to change is proposed.

However, the deflection device relates to the vertical take-off and landing operation of the vertical take-off and landing aircraft,
No consideration is given to yaw control during flight at cruising speed. It therefore has the disadvantage that it cannot replace the rudder if it is damaged during flight at cruising speed.

For this reason, there is an eager desire for the appearance of a control method and a control device for an aircraft which can ensure directional stability even when the rudder is damaged.

[0006]

SUMMARY OF THE INVENTION The present invention has been made in view of the above problems of the prior art. Even when the rudder is damaged and it becomes impossible to secure the directional stability by the rudder, An object of the present invention is to provide a control method and a control device for an aircraft that can ensure directional stability.

[0007]

A method of controlling an aircraft according to the present invention is a method of controlling an aircraft which uses thrust deflecting means for generating a moment in the yaw direction of the airframe by deflecting the direction of jet exhaust. And a procedure for detecting the yaw angle change and a step for operating the thrust deflection means so as to correct the yaw angle change.

More specifically, the control method for an aircraft according to the present invention uses a rudder and thrust deflecting means for generating a moment in the yaw direction of the aircraft by deflecting the direction of jet exhaust. The control method includes a procedure for detecting a yaw angle change, a procedure for instructing a rudder operation to correct the yaw angle change, and whether or not the rudder has worked based on the instruction. Is determined not to be functioning, a procedure for switching to control by the thrust deflecting means is included.

On the other hand, the control device for an aircraft according to the present invention comprises yaw angle change detection means, thrust deflection means for generating a moment in the yaw direction of the machine body, and control means for controlling the thrust deflection means. It is characterized by

More specifically, the control device for an aircraft according to the present invention is a thrust deflection for generating a moment in the yaw direction of the airframe by deflecting the yaw angle change detection means, the rudder, and the jet exhaust direction. Means and a control unit, the control unit having a control unit for controlling the rudder and the thrust deflection unit, a determination unit, and a switching unit, and whether the rudder is functioning by the determination unit. If the rudder is judged not to function by the judging means, the switching means switches from control by the rudder to control by the thrust deflecting means.

[0011]

When the yaw angle change detecting means detects that the yaw angle has changed, the control means controls the rudder so as to correct the change. Then, the determining means determines whether or not the yaw angle change is corrected by the data from the yaw angle change detecting means. As a result, when it is determined that the yaw angle change is not corrected, the yaw direction control is switched from the rudder to the thrust deflecting means by the switching means. Then, the control means calculates the thrust deflection angle for correcting the yaw angle change, sets the nozzle injection angle of the thrust deflection means to the above angle, and deflects the jet exhaust to correct the yaw direction of the machine body.

[0012]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will now be described based on embodiments with reference to the accompanying drawings, but the present invention is not limited to such embodiments.

FIG. 1 shows a control device for a flying vehicle used in a method for controlling a flying vehicle of the present invention. The flying vehicle control device includes a yaw angle change detecting means 1 for detecting a change in a yaw angle and a rudder 2.
The rudder drive device 3 for driving the rudder 2, the thrust deflection nozzle 41, the thrust deflection nozzle drive device 42 for driving the thrust deflection nozzle 41, and the controller 5 are the main parts. In this embodiment, the thrust deflection nozzle 41
And the thrust deflection nozzle drive device 42 constitute the thrust deflection means 4.

The thrust deflection nozzle 41 is for generating a rotational force in the yaw direction on the machine body by deflecting the direction of jet exhaust from the jet engine. More specifically, for example, as shown in FIG. 2, a first variable member 411 provided on the exhaust side of the jet engine and a second variable member whose rear end is joined to the front end of the first variable member 411. A variable nozzle including the member 412 (JS
ABE 87-7062 p. 49 (see Figure 7).

As shown in the block diagram of FIG. 2, the thrust deflection nozzle drive device 42 has a tip of a drive shaft, which is conventionally used for a variable nozzle 41 of this type, connected to a link mechanism of the thrust deflection nozzle 41. 42 fixed in place on the jet engine housing
1, 422.

The control unit 5 has rudder control means 52 for controlling the rudder 2 based on the yaw angle change signal from the arithmetic processing means 51 and the yaw angle change detection means 1, as in the conventional control device for an air vehicle. Other, thrust deflection nozzle control means 5
3, a switching unit 54 for switching between the rudder control unit 52 and the thrust deflection nozzle control unit 53, and a determination unit 55 for performing a determination for issuing a switching instruction to the switching unit 54. Specifically, for example, it is configured by adding a control program corresponding to a computer conventionally used for controlling an air vehicle.

Although the detailed description of the structure of the yaw angle change detecting means 1 is omitted, it is similar to the conventionally known yaw angle change detecting sensor for detecting the yaw angle change based on the angular velocity change of the machine body in the yaw direction. Is configured. Also,
Although detailed explanations of the structures of the rudder 2 and the drive unit 3 are omitted, they are the same as those conventionally used.

Next, the control of the flying vehicle by the flying vehicle control device thus constructed will be described.

The yaw angle change detecting means 1 detects the yaw angle change and inputs it to the arithmetic processing means 51 of the control section 5.

The arithmetic processing means 51 is a rudder control means 52.
The rudder angle for correcting the yaw angle change is calculated, and the operation amount of the rudder drive device 3 corresponding to the rudder angle is calculated.

The control unit 5 drives the rudder drive device 3 by the operation amount calculated by the rudder control means 52 to change the rudder angle of the rudder 2.

The yaw angle change detecting means 1 detects the yaw angle change and feeds it back to the arithmetic processing means 51 of the control section 5.

The arithmetic processing means 51 transfers the fed-back value to the judging means 55 and judges whether or not the rudder is functioning. This determination is made, for example, by comparing the magnitude of the previously input yaw angle change with the magnitude of the newly input yaw angle change, and the newly input yaw angle change is greater than the previously input value. If it is not small, it is determined that the rudder is not functioning.

When it is determined by the determination result of the determination means 55 that the rudder is not functioning, the arithmetic processing means 51 instructs the switching means 54 to switch from the rudder control to the thrust deflection nozzle control.

The switching means 54 switches from the rudder control to the thrust deflection nozzle control according to the above instruction.

The thrust deflection nozzle control means 53 calculates the thrust deflection angle and the operation amount of the thrust deflection nozzle driving device 42.

The control unit 5 operates the thrust deflection nozzle drive device 42 by the calculated operation amount, and the thrust deflection nozzle 41 is operated.
Deflect the injection angle of.

Next, the simulation of the directional stability control by the control method of the present invention was conducted in the modes of rudder control / non-control / thrust deflection nozzle control. The result is shown in FIG. From FIG. 3, when the rudder control is stopped,
It can be seen that the Dutch roll mode instability occurs due to the lateral gust disturbance, but the instability is also stably transferred by the thrust deflection nozzle control. Therefore, it is understood that the thrust deflection nozzle control also maintains the stability in the yaw angle direction similarly to the rudder control.

As described above, according to the present embodiment, even if the yaw angle control by the rudder becomes impossible due to damage to the rudder or the like,
Since the yaw angle can be controlled by the thrust deflection nozzle, stable flight can be maintained.

[0030]

As described above, according to the present invention, since the direction control can be performed by both the rudder and the thrust deflection nozzle, the rudder is damaged due to an accident or a battle, and the direction control by the rudder is impossible. In this case, the directional stability is ensured, and the excellent effect of being able to avoid a fall or the like can be obtained.

[Brief description of drawings]

FIG. 1 is a block diagram of a control device used in a control method of the present invention.

FIG. 2 is a schematic view of an example of a thrust deflection nozzle.

FIG. 3 is a graph showing simulation results of directional stability control according to the control method of the present invention.

[Explanation of symbols]

 1 yaw angle change detection means 2 rudder 3 rudder drive device 4 thrust deflection means 41 thrust deflection nozzle 411 first variable member 412 second variable member 42 thrust deflection nozzle drive device 421 actuator 422 actuator 5 control section 51 arithmetic processing means 52 rudder control Means 53 Thrust Deflection Nozzle Control Means 54 Switching Means 55 Judging Means

Claims (4)

[Claims] 1. A method of controlling an aircraft using thrust-deflecting means for generating a moment in the yaw direction of an airframe by deflecting the jet exhaust direction, the procedure including detecting a yaw angle change, and the yaw angle. And a step of operating the thrust deflecting means so as to correct the change. 2. A method for controlling an aircraft using a rudder and thrust deflecting means for generating a moment in the yaw direction of the airframe by deflecting the direction of jet exhaust, the method comprising detecting a yaw angle change. , A procedure for instructing a rudder operation to correct the yaw angle change, and whether or not the rudder has functioned based on the instruction, and when it is determined that the rudder has not functioned, control by the thrust deflection means A method for controlling an air vehicle, comprising: 3. A control device for an air vehicle, comprising yaw angle change detection means, thrust deflection means for generating a moment in the yaw direction of the airframe, and control means for controlling the thrust deflection means. . 4. A yaw angle change detection means, a rudder, and thrust control means for generating a moment in the yaw direction of the airframe by deflecting the direction of jet exhaust, and a control section. It has a control means for controlling the rudder and thrust deflection means, a judging means, and a switching means, and the judging means judges whether the rudder is functioning or not, and the judging means makes the rudder function. The control device for an aircraft, wherein the switching means switches from control by the rudder to control by the thrust deflecting means when it is determined that the control is not performed.