JPH082498A - Exciting device for aircraft - Google Patents

Abstract

PURPOSE:To provide an exciting device for an aircraft which can carry out plural times of excitation during flight without varying the structural and aerodynamic characteristic of a main plane. CONSTITUTION:A compressed air bomb 3 provided in a main plane end part 2 or a winglet is connected to a nozzle 4 provided.in the main plane end part 2 or the winglet through piping 6, and a control device 5 which is on-off controlled inside an aircraft body to open and close connection between the compressed air bomb 3 and the nozzle 4 is addedly provided in the piping, and compressed air in the compressed air bomb 3 is jetted from the nozzle 4 by on-off controlling the control device 5 for carrying out excitation.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a vibration device for an aircraft which vibrates the aircraft during flight during a flight test or the like.

[0002]

2. Description of the Related Art There are the following conventional vibration methods for aircraft during flight tests. (1) Excitation of rudder surface (2) Excitation by rocket motor (3) Excitation by exciter vane The above-mentioned excitation of rudder surface means that the control surface of aileron, spoiler, etc. is operated suddenly or sinusoidally. It is a method of vibrating. Excitation by a rocket motor is a method in which a rocket motor attached to the tip of a wing is excited by impulse injection. Excitation by the excitation vane is shown in Fig. 4.
As shown in FIG. 2, the vibration vane 10 attached to the outside of the body such as the wing tip of the main wing 1 is moved in the pitch direction as shown by the arrow to vibrate.

[0003]

The above-mentioned conventional vibration methods have the following problems, respectively. (1) Excitation of the rudder surface There is no need to change the structure of the airframe, but since the rudder surface is forcibly operated, it will differ from the original main wing condition. Moreover, only the roll direction (anti-symmetric) excitation of the main wing can be performed. (2) Vibration by rocket motor If you change the mounting position and injection direction of the rocket motor,
Symmetrical and antisymmetrical excitations are possible, but rocket motor injection can only be used once and 1 per flight
You can only excite once. (3) Excitation by the excitation vane Since the excitation vane is attached to the outside, the inertial specifications and the planar shape of the main wing change, which is different from the original structural and aerodynamic conditions. Further, since it is necessary to overcome the large aerodynamic force and inertial force acting on the vibration vane, the force required for driving the vane is also large, which complicates the mechanism.

The present invention solves the above-mentioned problems of the conventional method, and provides an aircraft vibration exciter capable of vibrating a plurality of times without changing the structural and aerodynamic conditions of the main wing. It is what

[0005]

According to the present invention, there is provided a vibrating device for an aircraft, wherein a compressed air cylinder provided in a main wing and a compressed air cylinder connected to the compressed air cylinder via a pipe arranged in the main wing are provided on a main wing surface. And a control device which is provided in the pipe connecting the compressed air cylinder and the nozzle and is controlled from the inside of the machine body to open and close the connection between the compressed air cylinder and the nozzle.

[0006]

In the present invention, by controlling the control device from the inside of the machine body, the air in the compressed air cylinder is jetted from the nozzles on the surface of the main wing, and the aircraft is vibrated. The compressed air cylinder, the piping that connects the air cylinder and the nozzle, and the control device are located inside the main wing, and it is possible to incorporate the vibration generator into the main wing by modification that does not significantly change the mass characteristics of the main wing. It does not change the structural or aerodynamic conditions of the main wing.
In addition, it is possible to excite multiple times within the range allowed by the capacity of the compressed air cylinder, and by arranging the nozzles appropriately on the upper and lower surfaces of the main wing, symmetrical excitation and anti-symmetric excitation can be performed. Is also possible.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIG. Reference numeral 1 is a main wing, 2 is a removable main wing tip portion, 3 is a compressed air cylinder, 4 is a nozzle, and 5 is a controller.

The compressed air cylinder 3 is removably arranged in the wing tip portion 2, and the nozzle 4 is attached to the wing lower surface of the wing tip portion 2 so as to open downward. , The compressed air cylinder 3 and the nozzle 4 are the wing tips 2
They are connected by a pipe 6 arranged inside, and a control device 5 is attached to the pipe 6. The control device 5 is controlled to be turned on and off wirelessly from the inside of the machine body to open and close the connection between the compression cylinder 3 and the nozzle 4.

In this embodiment, the compressed air in the compressed air cylinder 3 is controlled by turning on / off the control device 5 installed inside the wing wing tip 2 wirelessly from the inside of the fuselage. Nozzle 4 provided on the lower surface of the wing, and the main wing 1 is vibrated by its reaction.

If the nozzles 4 are provided on the lower surfaces of the left and right main blade tip portions 2 and the compressed air is jetted simultaneously from the left and right nozzles 4, symmetrical vibration can be performed. By injecting compressed air from the nozzle 4 on the lower surface of the blade of the blade tip 2, only one main blade can be vibrated.

Further, when the installation position of one of the nozzles 4 of the left and right main blade tip portions 2 is changed from the blade lower surface to the blade upper surface, antisymmetric vibration can be performed.

A second embodiment of the present invention will be described with reference to FIG. In this embodiment, the nozzle 4 is provided on the lower surface of the blade of the main wing tip 2 in the first embodiment, and yet another nozzle 4 is provided on the upper surface of the blade of the main wing tip 2.

In this embodiment, the nozzles 4 are attached to both the upper surface and the lower surface of the main blade tip 2 so that the compressed air in the compressed air cylinder 3 can be jetted to either the upper surface side or the lower surface side of the blade. It is the one. By providing the nozzles 4 on the left and right main wing tip portions 2, it becomes possible to select symmetrical excitation or antisymmetric excitation.

A third embodiment of the present invention will be described with reference to FIG. In this embodiment, a detachable winglet 7 is provided at the wing tip of the main wing 1, and a compressed air cylinder 3 is detachably disposed in the winglet 7 to remove the winglet 7.
The nozzle 4 provided at the tip of the compressed air cylinder 3 is connected to the compressed air cylinder 3 by a pipe 6 extending inside the winglet 7, and the pipe 6 is connected to the compressed air cylinder 3 and the nozzle 4 by wireless on / off control from inside the machine. A control device 5 for opening and closing the communication is attached.

In this embodiment, by injecting the compressed air in the compressed air cylinder 3 from the nozzle 4, it is possible to vibrate the aircraft during flight as in the first and second embodiments.

In the first to third embodiments, the nozzle is provided at the wing tip or the winglet, and the compressed air cylinder, the control device and the compressed air cylinder are connected to the nozzle in the wing tip or the winglet. Since the piping is arranged, it is possible to install the vibration exciter without changing the shape of the entire wing surface including the wing tip or winglet, and it is therefore possible to change the structural and aerodynamic conditions of the wing. Absent. Moreover, it is possible to perform the vibration a plurality of times within the range allowed by the capacity of the compression cylinder.

Also, in any of the first to third embodiments, the wing tip or the winglet portion is removable, so that the wing tip incorporating the vibrating device for the vibration test is used. Alternatively, the winglet portion may be separately manufactured and replaced with a normal wing tip portion or winglet portion during a vibration test, so that the vibration device can be attached to the machine without any modification.

[0018]

According to the present invention, a vibrating device including a compressed air cylinder, a nozzle, a pipe connecting the compressed air cylinder and the nozzle, and a control device provided in the pipe is built in a wing tip or a winglet. Therefore, it provides a vibrating device that can make multiple vibrations during flight within the range allowed by the compressed air capacity in the compressed air cylinder without changing the original wing conditions both structurally and aerodynamically. can do.

[Brief description of drawings]

1 shows a first embodiment of the present invention, FIG. 1 (a) is a front view thereof, and FIG. 1 (b) is a side view thereof.

FIG. 2 shows a second embodiment of the present invention, FIG. 2 (a) is a front view thereof, and FIG. 2 (b) is a side view thereof.

FIG. 3 is a perspective view showing a part of a third embodiment of the present invention by cutting away.

FIG. 4 is a perspective view of a vibration device for an aircraft using a conventional vibration vane.

[Explanation of symbols]

 1 wing 2 wing wing tip 3 compressed air cylinder 4 nozzle 5 controller 6 piping 7 winglet 10 vibration vane

Claims (1)

[Claims] 1. A compressed air cylinder provided in a main wing, a nozzle connected to the compressed air cylinder via a pipe arranged in the main wing, and a nozzle provided on a surface of the main wing, and a compressed air cylinder connected to the nozzle. An oscillating device for an aircraft, comprising a control device which is provided in a pipe and is controlled from the inside of the machine body to open and close a connection between a compressed air cylinder and a nozzle.