CN209795809U

CN209795809U - Flap control mechanism of light sport aircraft

Info

Publication number: CN209795809U
Application number: CN201920474493.0U
Authority: CN
Inventors: 彭进业
Original assignee: ZHUHAI CITY HAIWEI TECHNOLOGY Co Ltd
Current assignee: ZHUHAI CITY HAIWEI TECHNOLOGY Co Ltd
Priority date: 2019-04-10
Filing date: 2019-04-10
Publication date: 2019-12-17
Anticipated expiration: 2029-04-10

Abstract

The utility model discloses and provides a simple structure, reduce the drag, allow each flap to control alone and totally enclose the flap control mechanism of light sport aircraft in the flap structure, the flap control mechanism of light sport aircraft includes flap and flap actuating mechanism, the flap actuating mechanism locates in the flap and is used for making each the flap can be controlled independently and expand; the utility model discloses be applied to aircraft structure technical field.

Description

Flap control mechanism of light sport aircraft

Technical Field

The utility model belongs to the technical field of the aircraft structure technique and specifically relates to a light-duty motion aircraft's wing flap control mechanism.

Background

The majority of light-sport aircraft of the prior art use hydraulic actuators to provide a steering solution for flaps and ailerons through a linkage system. The actuators on many commercial aircraft consist of a screw that moves a nut up and down the length of the screw to move one or more brackets that lock onto the control surface assembly. In aircraft having a plurality of flaps, each flap being driven by its own screw mechanism, each screw being driven by a shaft which is connected to the screw along the length of the wing by a bevel gear or worm gearbox, the construction is mechanically complex, heavy and costly to manufacture and maintain. Furthermore, it does not allow for individual activation and automated control of each flap mechanism. The control precision of a component control mechanism of the traditional light-weight moving airplane is low, and the operation sensitivity of the airplane is low; the control difficulty of the pilot on the aircraft during flight operation is increased; and the existing designs result in wing structures with protruding mechanisms, requiring the addition of fairings, resulting in increased fluid drag.

Disclosure of Invention

The utility model aims to solve the technical problem that overcome prior art not enough, provide a simple structure, reduce the resistance, allow every wing flap independent control and the light-duty motion aircraft's of totally enclosed in the wing flap structure wing flap control mechanism.

The utility model adopts the technical proposal that: a flap control mechanism for a light-weight sport aircraft includes flaps and flap drive mechanisms disposed within the flaps for enabling each of the flaps to be independently manipulated for deployment.

Further, the flap driving mechanism comprises a combined motor set, a flap moving mechanism and a driving shaft; the combined motor group is arranged in the middle of the flap and is arranged in parallel with the leading edge of the flap, the combined motor group drives the flap motion mechanism through the driving shaft, and the driving shaft extends to the side surface of the flap and is provided with a gear at the tail end of the driving shaft.

Further, the flap motion mechanism comprises a rack, a rocker arm, a first roller set and a second roller set which are arranged on the rocker arm, and a first track and a second track which are matched with the first roller set and the second roller set; the rack is fixed on the wing, and the gear is meshed on the rack and is used for providing a variable flap moving path.

Further, the flap drive mechanism is completely contained within the flap.

further, the combined motor set comprises a first motor and a second motor which are connected with each other.

The utility model discloses beneficial effect with the prior art contrast is: because a light-duty motion aircraft's flap control mechanism include flap and flap actuating mechanism, flap actuating mechanism locates in the flap and be used for making every the flap can be controlled independently and expand, is equipped with two motors through actuating mechanism at the flap and provides power for two axles, has a pinion in the outside of every axle, pinion drive one has the rocking arm of four rollers, the roller is gone on locking the track on the rib structure. Two motors, rather than one, are used to move the flap in case of failure of either motor. Each motor can provide sufficient power to operate the flap mechanism. During the extension of the flap, the track path is designed to enable the flap to linearly extend outwards along the front half part of the track motion and then move downwards to increase the flap angle. This track path design allows the flap to extend and stop before beginning downward motion. In this position, the flaps can increase chord and aerodynamic lift without increasing induced drag, effectively providing a flap control mechanism for a lightweight motion aircraft that is simple in construction, reduces drag, allows each flap to be individually controlled, and is completely enclosed within the flap structure.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

Fig. 2 is a schematic side view of the flap driving mechanism of the present invention.

Detailed Description

The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings.

As shown in fig. 1 and 2, the flap control mechanism of a light sport aircraft according to the present invention includes a flap and a flap driving mechanism, wherein the flap driving mechanism is disposed in the flap and is used for enabling each flap to be independently controlled and deployed.

Further, the flap driving mechanism comprises a combined motor set 1, a flap motion mechanism and a driving shaft 2; the combined motor set 1 is arranged in the middle of the flap and is arranged in parallel with the leading edge of the flap, the combined motor set 1 drives the flap motion mechanism through the driving shaft 2, the driving shaft 2 extends to the side surface of the flap, and the tail end of the driving shaft 2 is provided with a gear 3.

Further, the flap motion mechanism comprises a rack 4, a rocker arm 5, a first roller set 6 and a second roller set 7 arranged on the rocker arm 5, and a first track 8 and a second track 9 matched with the first and second roller sets; the rack 4 is fixed on the wing, and the gear 3 is engaged on the rack 4 and is used for providing a variable flap moving path.

Further, the flap drive mechanism is completely contained within the flap.

Further, the combined motor set 1 comprises a first motor and a second motor which are connected with each other.

Two shafts are powered by two motors fitted to the flap drive mechanism, a pinion on the outside of each shaft driving a rocker arm with four rollers that ride on tracks locked to the rib structure. Two motors, rather than one, are used to move the flap in case of failure of either motor. Each motor can provide sufficient power to operate the flap mechanism. During the extension of the flap, the track path is designed to enable the flap to linearly extend outwards along the front half part of the track motion and then move downwards to increase the flap angle. This track path design allows the flap to extend and stop before beginning downward motion. In this position, the flap can increase chord and aerodynamic lift without increasing induced drag. When the motor unit receives a signal to extend the flap, the driving shaft 2 starts to rotate, and the gear 3 is driven to move on the rack 4. The gear wheel 3 carries the rocker arm 5 and the flap together on the gear rack 4. When the rocker arm 5 and the gear 3 move, the two groups of roller groups move on the two groups of tracks; the two sets of tracks provide a stable path for the movement of the flaps, a compact design, a complete enclosure in the flap configuration, a clean aerodynamic profile, thus reducing drag, which is lighter than current designs, makes maintenance easy and inexpensive, and allows individual control of each flap, which has great advantages in asymmetric loading conditions, such as on military aircraft, when a bomb is dropped from the wing.

The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are covered by the protection scope of the present invention, therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A flap control mechanism of a light-duty sport aircraft, characterized in that: the flap control mechanism of the light-weight sport aircraft comprises flaps and flap drive mechanisms, wherein the flap drive mechanisms are arranged in the flaps and are used for enabling each flap to be independently operated and unfolded.

2. The flap control mechanism for a light sport aircraft according to claim 1, wherein: the flap driving mechanism comprises a combined motor set (1), a flap motion mechanism and a driving shaft (2); the combined motor set (1) is arranged in the middle of the flap and is arranged in parallel with the leading edge of the flap, the combined motor set (1) drives the flap motion mechanism through the driving shaft (2), the driving shaft (2) extends to the side face of the flap, and a gear (3) is arranged at the tail end of the driving shaft (2).

3. The flap control mechanism of a light sport aircraft according to claim 2, characterized in that: the flap motion mechanism comprises a rack (4), a rocker arm (5), a first roller set (6) and a second roller set (7) which are arranged on the rocker arm (5), and a first track (8) and a second track (9) which are matched with the first roller set and the second roller set; the rack (4) is fixed on the wing, and the gear (3) is meshed on the rack (4) and is used for providing a variable flap moving path.

4. The flap control mechanism for a light sport aircraft according to claim 1, wherein: the flap drive mechanism is completely contained within the flap.

5. The flap control mechanism of a light sport aircraft according to claim 2, characterized in that: the combined motor set (1) comprises a first motor and a second motor which are connected with each other.