JPH02262497A - Aircraft having variable tail unit - Google Patents

Abstract

PURPOSE:To obtain both functions of horizontal and vertical tails, reduce the weight and resistance, and improve the performance of an aircraft by providing a pair of tail units which are revolvable around shafts in the plane axial direc tion of the aircraft. CONSTITUTION:Connecting members 2B are provided on the body 3 sides of a pair of right/left tail units 2 the attack angle alpha of which is variable of an aircraft 1, and each tail unit 2 is revolvably installed around the axial line of a shaft 2A in the aircraft axial direction via the connecting member 2B. The end portion of the connecting member 2B is pivotally installed on one end of a vertically provided actuator 6 the other end of which is pivotally supported by the body 3. The actuator 6 is controlled by a control signal generat ed by a signal processor which receives an electric signal from a control lever or an electric signal from a navigation system such as an acceleration sensor, a pitch rate sensor, etc., according to the motion of an aircraft body.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an aircraft having a tail that rotates around an axis in the aircraft axis direction.

[Conventional technology]

An example of a conventional aircraft tail structure is generally a structure in which a pair of left and right horizontal stabilizers 21 and a single vertical stabilizer 22 are fixed to the aircraft body, as shown in FIG.

[Problem to be solved by the invention]

The above conventional aircraft has the following drawbacks.

In other words, in order for an aircraft in flight to ascend (descend) or change its flight path, such as changing direction, independent structures with the functions of a horizontal stabilizer and a vertical stabilizer are required, resulting in increased weight,
This causes an increase in resistance, etc.

The present invention seeks to solve the above-mentioned drawbacks of conventional aircraft.

[Means to solve the problem]

The present invention includes a pair of tail fins that are rotatable around an axis in the axial direction of an aircraft, and a device that rotates each of the tail fins around the axis.

[Effect]

The present invention combines the functions of a horizontal stabilizer and a vertical stabilizer by rotating each of a pair of tail fins around an axis in the aircraft axis direction, thereby reducing weight and drag, thereby improving aircraft performance.

Also, if you rotate one tail fin upward and the other downward in the opposite direction to make the tail fin vertical, then turn the rudder.
It is also possible to perform movements such as horizontal turns of the aircraft.

〔Example〕

A first embodiment of the present invention will be described with reference to FIGS. 1 to 3.

Reference numeral 2 denotes a pair of left and right tail wings of the aircraft 1 whose angle of attack can be changed by a device not shown in the figure α in FIG. Each tail 2 is attached via the connecting portion 2B so as to be rotatable about the axis 2A in the aircraft axis direction, and the end of the connecting portion 2B is connected to the fuselage in the vertical direction with one end pivoted to the fuselage. It is pivotally connected to the other end of the actuator 6 located at.

On the other hand, as shown in FIG. 3, the aircraft 1 receives electrical signals from a control stick 13 that receives input from the pilot, and from a navigation system 14 such as an acceleration sensor and a pitch rate sensor based on aircraft motion. A control valve 17 is provided to which a signal from a signal processor 15 to which an electric signal is input is input, and the output of the control valve 17 is input to each of the actuators 6.

In this embodiment, the actuator 6 is actuated via the signal processor 15 and the control valve 17 by electrical signals from the control stick 13 and the navigation system 14 operated by pilot input, and the vertical movement of the actuator 6 moves the tail 2 in the axial direction. The tails 2 are rotated around the two people, and each tail 2 moves to a position tilted with respect to the horizontal plane, as shown by θ in FIG.

A second embodiment of the present invention will be explained with reference to FIG. The aircraft is equipped with a control stick 13, a navigation system 14, a signal processor 15, and a control valve 17 similar to those in the first embodiment, and the output of the control valve 17 is transmitted to the actuator 6°7 of each tail fin 2. It is now entered. Actuator 6 is! It is a hydraulic type that moves up and down in response to hydraulic output from the ttlJ control valve 17, and its lower end is pivoted to the body 3, and the actuator 7 is connected to the control valve 1.
It is an electric type that rotates around a horizontal axis in response to electrical output from 7. The other end of the actuator 6 and one end of the actuator 7 are pivotally connected to each other, and the other end of the actuator 7 is connected to a power transmission device 8. Each tail fin 2 has a first axis of rotation 4 in its direction, and the tail fin 2
A power transmission mechanism 12 with a bevel gear provided on the body side of the
and a power transmission mechanism 9 having bevel gears of the power transmission device are arranged facing each other on the rotating shaft 4, and both are arranged facing each other on a second rotating shaft 5 in the machine axis direction intersecting the rotating shaft 4. They are connected via a power transmission mechanism 10.11 having a bevel gear.

As mentioned above, the upper g-pi power transmission mechanism 9.12 is freely connected to a shaft 18 disposed on the rotating shaft 4, and the same shaft 18 is rotatable around the rotating shaft 5. Note that 16 is an actuator operating source connected to the control valve 7, and 18 is a power source connected to the signal processor 15.

In this embodiment configured as described above, when the actuator-like knee j17 is actuated and rotated by the output from the control valve 17, the power transmission mechanism 9 rotates via the power delivery device 8, and the power transmission is performed. Mechanism 10.1
By rotating the power transmission 12 around the rotation axis 4 via the tail 2, the angle of attack of the tail 2 is changed. On the other hand, when the actuator 6 is actuated by the output from the control valve 17 and moves up and down, the power transmission mechanism 9 connected by the shaft 18
- 12 integrally rotate around a rotation axis 5 in the machine axis direction, and in conjunction with this, the tail 2 rotates around the rotation axis 5 and moves up and down.

A third embodiment of the present invention will be described with reference to FIG.

In this embodiment, in the first embodiment described above, a control surface 19 that can rotate around the axis 21 is provided on the tail 2, and an actuator 20 for operating the control surface 19 is attached.

In each of the above-mentioned embodiments, the tail 2 can be rotated up and down by the actuator rotor in two directions in the aircraft axis direction, and can move up and down, thereby combining the functions of the horizontal stabilizer and the vertical stabilizer. You can have it. Moreover, the position of the tail fin 2 can be set freely, and desired performance can be obtained.

Furthermore, it is also possible to horizontally turn the aircraft by moving one tail fin downward and the other tail fin upward, positioning them vertically in the vertical direction, and adjusting their angle of attack or rudder angle.

〔Effect of the invention〕

The present invention has the following effects.

(1) A pair of tail wings can be rotated around an axis in the aircraft axis direction to have both the functions of a horizontal stabilizer and a vertical stabilizer,
Eliminating the need for vertical or horizontal stabilizers reduces weight, drag, and improves aircraft performance.

(2) In the case of a fighter aircraft, the radar reflection area of the enemy is reduced in accordance with the above (1), thereby increasing secrecy and survivability.

[Brief explanation of drawings]

FIG. 1 is an overall view of the first embodiment of the present invention, and FIG.
3 is a control block diagram of the same embodiment, FIG. 4 is an explanatory diagram of the second embodiment of the present invention, and FIG. 5 is a diagram of the third embodiment of the present invention. The explanatory drawings, FIG. 6, show an example of a conventional aircraft, and FIG. 6 is a side view of the same, and FIG. 6 is a front view of the same. 1... Aircraft, 2... Tail, 2 people... Rotating axis, 3... Fuselage, 4.5... Rotating axis, 6,7
... actuator, 8... power transmission device, 9.10, 11, 12... power transmission mechanism, 13...
Control frame, etc., 14... Navigation system, 15... Signal processor, 16... Actuator operation source, 17... Control valve. Figure 3 Figure 2 En 3 River 1x Figure 4 躬Figure 5

Claims (1)

[Claims] a pair of tail wings rotatable around an axis in the axial direction of the aircraft;
and a device for rotating each of the tail wings around the axis.