JPH1016890A - Expansion aerodynamic surface - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an expansion aerodynamic surface for forming a lifting surface by expanding a plate-like small wing from both gunwales of the body of an airplane and using this also as a steering wing or a brake. SOLUTION: An expansion aerodynamic surface includes pivot shafts 15 erected in recesses 14 plotted in left and right gunwale sides so as to be obliquely moved freely in pitch directions and a plurality of plate-like small wings 20 having base end parts pivotally attached to the pivot shafts 15, housed in the recesses 14 being laminated in the directions of the pivot shafts 15 and expanded like fans around the pivot shafts 15 to form lifting surfaces. Thus, the expansion aerodynamic surface is used as a high lifting device and, by changing the areas of the lifting surface surfaces of the left and right gunwale sides or incidence angles, this is used as a steering wing for producing roll motion and further, by making the lifting force surfaces to be large pitch angles by the turn of the pivot shafts, this is used as a speed brake.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention is applied to aircraft,
It consists of a pivot shaft erected in a recess defined on the fuselage side and a plurality of small wings pivotally attached to the pivot shaft, and the small wing is rotated around the pivot axis to move outward from the side of the ship. Use the lift generated on the lift surface as a high lift device and a roll control device by forming the lift surface by deploying it, or use the developed lift surface at a large angle of attack to use it as a speed brake and deploy it. The small wings that form the lift surface are rotated and folded, condensed, and stacked to form a stacked body.
Related to a deployed aerodynamic surface that can be stored in a recess.

[0002]

2. Description of the Related Art FIG. 4 shows an example of a conventional deployed aerodynamic surface which is usually housed in an aircraft, deployed outside the aircraft at the time of use, operated, and exerts its function. . This deployed aerodynamic surface is called a globe vane 04, and is designed to simultaneously reduce the flight performance due to the retreat of the wind pressure center occurring in the supersonic range of the aircraft 01 and to increase the drag, and simultaneously from both sides of the fuselage 02 during supersonic flight. Deployed in front of the wing 03, the center of wind pressure is advanced by the lift generated in the globe vane 04, lowering the longitudinal stability of the aircraft 01, improving flightability, and the strength of the shock wave generated during supersonic flight. Is alleviated by this glove vane 04,
This is to reduce the increase in resistance. Therefore, the glove vane 04 is not used during supersonic flight, and also during flight other than when flightability is required.
It is stored on both sides of the ship.

[0003] As another example of the conventional deployed aerodynamic surface,
There is one shown in FIG. This deployed aerodynamic surface has a flap of 0
5, which is widely used as a high-lift device. That is, in order to generate a large lift at the time of takeoff and landing of the aircraft 01, the flap 05 is deployed rearward from the trailing edge of the wing 03 to increase the lift surface, and the separation from the upper surface of the wing 03 to the flap 05 is prevented. A high lift is generated by increasing the number of members while preventing them. Therefore, the flap 05 is housed inside the main wing 03 during normal flight except when generating a large lift at the time of takeoff and landing at low speed.

[0004] As can be understood from the above-described conventional aerodynamic surface, the aerodynamic surface equipped on the conventional aircraft 01 is the same as the (high) lift generating device described above except that the increase in the resistance of the globe vane 04 is reduced. Just used, it is used as a steering wing required for controlling the flight direction or attitude of the aircraft, or as a speed brake required for decelerating the aircraft during landing to achieve the function of the aircraft 01. In order to achieve these functions, which are necessary when the aircraft is in flight, separate functions are required for each function,
The devices are usually provided separately. That is, devices such as a high-lift device, a steering wing, and a speed brake are provided, and a mechanism for controlling and operating these devices is provided in the aircraft 01.

Therefore, depending on the operation status of the entire body as a system, unnecessary mechanisms and devices may appear. For example, the flap 05 used as a conventional high-lift device shown in FIG. 5 described above is used only when the flight speed at takeoff and landing is extremely low and the aircraft needs to be levitated in the air. On the other hand, the main wing 03 is used during normal flight.
It is usually stored inside and not used. The flap 05 may be equipped with a special type of air combat flap that is not used in a large-sized transport aircraft or the like, but such a flap is used only in an operational state.

[0006] The same applies to the above-mentioned steering wings and speed brakes. In the former, when controlling the attitude of the body, such as when changing the flight direction or changing the flight altitude. In the latter, there are no mechanisms or devices that are unnecessary as a system except when used for deceleration during landing.

[0007] As described above, the conventional aircraft is a body of a system in which mechanisms and devices that are unnecessary in use are superimposed and equipped, which complicates the mechanisms and increases the number of devices. It is necessary to equip the airplane, which complicates the flight operation, requires skill, and increases the weight of the airframe, thereby deteriorating the operation efficiency.

[0008]

SUMMARY OF THE INVENTION According to the present invention, in order to solve the above-mentioned problems of the conventional aircraft, a single device can achieve the functions of the high lift device, the steering wing and the speed brake, thereby achieving an efficient operation. It is an object of the present invention to provide an effective deployment aerodynamic surface for constructing a flexible airframe system.

[0009]

Therefore, the deployed aerodynamic surface of the present invention is as follows.

(1) In the recesses provided on the port side and the starboard side in the aircraft fuselage, respectively, it is rotated around a pitch axis provided in the entire width direction of the aircraft to freely tilt in the pitch direction. In order to be able to move, a pivot axis is provided upright in the yaw axis direction, which is provided in the entire height direction of the aircraft. The pivot axis is provided in the body axis direction of the aircraft. In the roll axis direction, it is desirable to be erected near the center of gravity of the aircraft. Further, the inclination angle of the pivot axis in the pitch direction can be set independently on the port side and the starboard side, and the magnitude thereof is pivotally connected to the pivot axis, and rotates around the pivot axis to form a lifting surface. It is desirable to be able to incline the lift surface to such an extent that the flow of air flowing over the winglet surface causes separation.

(2) The base end is pivotally supported on the pivot shaft,
It is piled up in the pivot axis direction and consists of a plurality of plate-like objects that are stacked, and by individual rotation around the pivot axis, it is deployed like a fan at the time of fan opening, and
The lift surface, which allows the deployment area to be varied, is formed outward from the side of the aircraft fuselage, and the lift surface formed by deployment is pivoted about a pivot axis.
A plurality of winglets were provided which were condensed and formed into a stack so that they could be accommodated in the recess. In addition, it is preferable that the small wings pivotally attached to the pivot shafts respectively erected on the port side and the starboard side can be independently rotated, deployed, or accommodated. .

The deployed aerodynamic surface of the present invention is formed into a stacked body by the above-mentioned means by a deploying wing mechanism provided with a hydraulic or electric motor mounted in the recess on the left and starboard sides of the fuselage, and is provided in the recess. While shifting the angle of the small wings vertically adjacent to each other around the pivot axis,
When individually rotated, a lift surface added to a wing surface of a wing or the like usually provided on an aircraft is formed outward from the fuselage side. The area of the added lifting surface can be changed depending on the degree of rotation of the small wings, and the lifting surface can be formed only on the port side or the starboard side of the fuselage.

Further, in order to rotate the small wing, a pivot shaft having a base end pivotally attached thereto is rotated around a pitch axis by an inclination mechanism provided in the recess to change the inclination angle in the pitch direction. By changing this angle of inclination,
The above-described lift surface, which is developed perpendicularly to the pivot axis and outward from the fuselage side, can change the angle of attack, which is the angle of inclination with respect to the external uniform airflow, and the lift due to the degree of rotation of the winglet described above. The magnitude of the lift generated on the lift surface can be adjusted not only by changing the size of the surface area, but also by changing the inclination of the pivot axis in the pitch direction.

As described above, the wing is rotated while being shifted from the wing with respect to the pivot axis so that the area of the lift surface formed by the wing is maximized, and the pivot is further lifted in the pitch direction. The inclined aerodynamic surface can be used as a high-lift device by inclining it to an angle at which the lift generated on the surface is maximized. Furthermore, by changing the angles of attack of the lift surfaces formed on the left and starboard sides, respectively,
Alternatively, by forming a lift surface only on one side, the vehicle can be used as a steering wing that generates a body roll motion.

Further, the inclination angle of the pivot axis in the pitch direction is further increased, and the angle of attack of the lift surface is set to a large angle of attack at which the flow of air flowing on the lift surface formed by the small wings causes separation. As a result, it can be used as a speed brake. Further, by making the small wing on one of the left and right starboard sides function as a speed brake, it can be used as a rudder for generating yaw motion.

When it is not necessary to use the wings as a high-lift device, a steering wing or a speed brake, the wings that have been deployed to form a lift surface are rotated and folded by the deploying wing mechanism, and the wings are folded. Can be stacked and stored in the recess. As a result, the resistance during normal flight that does not require a high-lift device, a steering wing, or a speed brake can be reduced, and the operating efficiency can be increased.

[0017]

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view showing an embodiment of a deployed aerodynamic surface of the present invention. FIG. 1 is a view showing a first embodiment of a deployed aerodynamic surface according to the present invention, and FIG.
1B is a plan view, FIG. 1B is a side view taken along a line AA shown in FIG. 1A, and FIG. 1C is a side view taken along a line B-A shown in FIG.
It is a front view in B. In the drawings showing the embodiments, the same members as those shown in FIGS. 5 and 6 are denoted by the same reference numerals, and description thereof will be omitted.

As shown in the figure, recesses 14 are defined on both sides of the fuselage 02 near the position of the center of gravity of the aircraft 01 in the direction of the roll axis (body axis) 11. In the recess 14, a pivot shaft 15 rotatable around the pitch axis 12 is provided upright in the yaw axis 13 direction. The pivot shaft 15 is rotated by an electric or hydraulic drive tilt mechanism (not shown) provided in the recess 14.
2 around a predetermined angle 16, ie, a small wing 2
The angle with respect to the uniform flow of the lift surface 21 formed by developing 0 can be set to an angle of about 20 ° to 25 ° at which separation occurs in the flow of air flowing on the lift surface 21.

The pivot shaft 15 is pivotally supported at its base end by three plate-shaped small wings 20. The small wings 20 are provided in the recess 14 and are electrically driven or not shown. The hydraulically driven deployment wing mechanism rotates around the pivot shaft 15 and lifts the lifting surface 21 outward from the recess 14.
Is formed, and the developed lifting surface 21 is condensed to be stacked and accommodated in the recess 14.

That is, as shown in the figure, a deployment wing mechanism mounted in a recess 14 on the left and starboard sides of the fuselage 02 (only the port side is shown in the figure, and the starboard side is not shown). By rotating the three small wings 20 accommodated in the recess 14 in a stacked state around the pivot shaft 15 while shifting the angle of the vertically adjacent small wings 20, the normal aircraft The lift surface 21 added to the wing surface such as the main wing 03 mounted on the
It is formed outward from the zero side.

As described above, the winglets 20 on the left and starboard sides are deployed to the maximum to form the lift surface 21, and the pitch axis 1
By rotating the pivot shaft 15 around 2 and setting an elevation angle in the same direction on the lift surfaces 21 formed on the left and starboard sides, it is possible to use the lift surface 21 as a high lift device. In addition, by installing the pivot shaft 15 at a position where the lift generated on the lift surface 21 is generated near the center of gravity of the aircraft 01, the lift surface 21 provides high lift while suppressing the moment in the pitch direction of the fuselage. Can be obtained.

The area of the lift surface 21 is smaller than that of the small wing 20.
Further, the pivot shaft 15 rotates around the pitch axis 12 to change the angle of attack of the lift surface 21 with respect to the uniform airflow, which can change the tilt angle 16 in the pitch direction. Therefore, by adjusting both of them, the magnitude of the lift generated on the lift surface 21 can be adjusted.

FIG. 2 is a view showing a second embodiment of the developed aerodynamic surface of the present invention. FIG. 2 (a) is a plan view and FIG. 2 (b).
FIG. 2A is a side view taken along the line CC shown in FIG.
FIG. 3C is a front view taken along the line DD shown in FIG. In the present embodiment, the winglets 20 on only one side are deployed to form a lift surface 21 or the winglets 20 on both sides are formed.
In the deployed state, the magnitude of the rotation angle of the pivot shaft 15 around the pitch axis 3 on both sides is changed or the direction is changed to create a difference in the lift L generated on the left and right lift surfaces 21, and the aircraft 01 It can be used as a roll control device that generates a rolling moment.

As described above, the developed aerodynamic surface of the present embodiment changes the elevation angle 16 of the lift surface 21 formed on each of the left and starboard sides, or changes the lift surface 21 only on one of the sides.
Is formed, it can be used as a steering wing that generates roll motion on the fuselage.

FIG. 3 shows a third embodiment of the developed aerodynamic surface of the present invention. FIG. 3 (a) is a plan view and FIG. 3 (b).
FIG. 3A is a side view taken along the line EE shown in FIG.
FIG. 3C is a front view taken along the line FF shown in FIG. In the present embodiment, the winglets 20 on both sides are deployed to the maximum, and the pivot shafts 15 on both sides are connected to the pitch axis 3.
By tilting around and giving the maximum angle in the same direction (pitch direction), the angle of attack of the lift surface 21 formed by the small wings 20 is increased, the flow on the lift surface 21 is separated, and the speed is increased. -It can be used as a brake.

Further, the small wings 20 on only one of the left and right starboard sides are used as steering wings for generating a motion of the body around the yaw axis at a high angle of attack so as to function as a speed brake. Can also be. It should be noted that even when the lift surface 21 is used as the steering blade for generating the roll motion shown in FIG. 2, the speed brake shown in FIG.
The magnitude of the moment or the magnitude of the braking force can be varied by changing the magnitude of the force, as in the case of using as a high-lift generator.

[0027]

As described above, according to the developed aerodynamic surface of the present invention, according to the structure shown in the claims, (1) the winglets are developed around the pivot axis to form a lift surface, By rotating the shaft around the pitch axis, the lift surface has an angle of attack, and can be used as a high lift device during takeoff and landing. Further, by adjusting both the magnitude of the pitch angle and the magnitude of the effective aerodynamic area according to the deployment angle, the magnitude of the lift can be arbitrarily controlled.

(2) The size of the lift surface is changed by adjusting the pitch angles of the lift surfaces on the left and starboard sides and / or the degree of deployment of the small wings. To be used as a roll control device.

(3) By further increasing the pitch angle and separating the flow on the lift surface, it can act as a resistance plate and have a function as a speed brake. The lift surface can be made to act as a resistance plate to have a function as a rudder.

(4) During normal flight (cruise flight), the small wings are stored in a narrow recess in a superimposed state, so that the resistance can be reduced.

As described above, the deployed aerodynamic surface of the present invention is required to be provided with superimposed mechanisms and devices which are unnecessary in a use situation, so that the mechanisms become complicated and many devices are required. The flight operation became complicated, skill was required, the weight of the aircraft increased, and the operating efficiency was degraded.
The problem of the conventional aircraft is eliminated, which greatly contributes to the construction of an efficient airframe system of the aircraft, thereby realizing an excellent aircraft.

[Brief description of the drawings]

FIG. 1 is a view showing a first embodiment of a developed aerodynamic surface according to the present invention, wherein FIG. 1 (a) is a plan view, and FIG. 1 (b) is a side view taken along the line AA shown in FIG. 1 (a). Fig. 1 (c) is the same as Fig. 1 (a).
Front view in the direction of arrow BB shown in FIG.

FIG. 2 is a view showing a second embodiment of the developed aerodynamic surface of the present invention, wherein FIG. 2 (a) is a plan view, and FIG. 2 (b) is a side view taken along the line CC shown in FIG. 2 (a). FIG. 2 (c) is a view of FIG. 2 (a).
Front view in the arrow DD shown in FIG.

3A and 3B are views showing a third embodiment of the developed aerodynamic surface of the present invention, wherein FIG. 3A is a plan view, and FIG. 3B is a side view taken along the line EE shown in FIG. FIG. 3 (c) shows FIG. 3 (a).
Front view in the direction of arrow FF shown in FIG.

FIG. 4 is a side view of a conventional aircraft provided with a globe vane as a deployed aerodynamic surface,

FIG. 5 is a perspective view of a conventional aircraft provided with a flap as a developed aerodynamic surface, and FIG.
(B) is a figure which shows the time of a flap extension.

[Description of Signs] 01 Aircraft 02 Fuselage 03 Main wing 04 Globe vane as conventional deployment aerodynamic surface 05 Flap as conventional deployment aerodynamic surface 11 Roll axis 12 Pitch axis 13 Yaw axis 14 Recess 15 Pivot axis 16 Rotation of pivot axis Angle (pitch angle) 20 Small wing 21 Lifting surface

Claims (1)

[Claims] 1. A pivot shaft, which is erected in a manner provided to be freely tiltable in a pitch direction, in a recess provided on each of a left side and a starboard side of an aircraft fuselage, and a base end portion is pivotally supported by the pivot shaft. Stacked in the pivot axis direction, by rotating around the pivot axis, forming a lifting surface developed in a fan shape on the side of the aircraft fuselage, and condensing the developed lifting surface into a stack, A deployed aerodynamic surface comprising a plurality of small wings housed in the recess.