A flap control mechanism for a light sport aircraft

Abstract

The present invention discloses and provides a flap control mechanism for a light sport aircraft that has a simple structure, reduces drag, allows each flap to be individually controlled, and is completely enclosed within the flap structure. The flap control mechanism for the light sport aircraft includes flaps and a flap drive mechanism. The flap drive mechanism is arranged within the flap and is used to enable each flap to be independently controlled and deployed. The present invention is applicable to the field of aircraft structure technology.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft structures, in particular to a flap control mechanism for a light sports aircraft. Background Art

[0002] Most existing light sport aircraft utilize hydraulic actuators through a linkage system to control flaps and ailerons. The actuators on many commercial aircraft consist of a screw that drives a nut that moves up and down along its length, thereby actuating one or more brackets locked to the control surface assembly. On aircraft with multiple flaps, each flap is actuated by its own screw mechanism, each driven by a shaft connected to the screw along the length of the wing via a bevel or worm gearbox. This structure is mechanically complex, heavy, and expensive to manufacture and maintain. Furthermore, it does not allow for individual movement and automated control of each flap mechanism. This results in low control accuracy and insensitive control of the component control mechanisms in traditional light sport aircraft, making it more difficult for pilots to control the aircraft during flight. Furthermore, existing designs result in the mechanism protruding from the wing structure, requiring the addition of fairings, which increases fluid drag. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art and provide a flap control mechanism for a light sport aircraft that is simple in structure, reduces drag, allows each flap to be controlled individually and is completely enclosed in the flap structure.

[0004] The technical solution adopted by the present invention is: a flap control mechanism of a light sport aircraft comprises flaps and a flap driving mechanism, wherein the flap driving mechanism is arranged in the flaps and is used to enable each flap to be independently controlled and deployed.

[0005] Furthermore, the flap drive mechanism includes a combined motor group, a flap motion mechanism and a drive shaft; the combined motor group is arranged in the middle of the flap and is arranged parallel to the leading edge of the flap, and the combined motor group drives the flap motion mechanism through the drive shaft. The drive shaft extends to the side of the flap and a gear is installed at the end of the drive shaft.

[0006] Furthermore, the flap movement mechanism includes a rack, a rocker arm, a first roller group and a second roller group provided on the rocker arm, and a first track and a second track cooperating therewith; the rack is fixed on the wing, and the gear is engaged with the rack and is used to provide a variable flap movement path.

[0007] Furthermore, the flap drive mechanism is completely contained within the flap.

[0008] Furthermore, the combined motor group includes a first motor and a second motor connected to each other.

[0009] The present invention offers significant advantages over existing technologies. The flap control mechanism for a light sport aircraft comprises flaps and a flap drive mechanism, which is located within the flaps and allows each flap to be independently deployed. The flap drive mechanism utilizes two motors to power two shafts. Each shaft has a pinion on the outside, which drives a rocker arm with four rollers that travel on tracks locked to the rib structure. Two motors, rather than just one, are used to move the flaps, preventing failure of any one motor. Each motor provides sufficient power to operate the flap mechanism. During flap extension, the flaps extend linearly outward along the first half of their trajectory, then move downward to increase the flap angle. This trajectory allows the flaps to extend and stop before beginning their downward movement. In this position, the flaps increase chord and aerodynamic lift without increasing induced drag, effectively providing a flap control mechanism for a light sport aircraft that is simple in structure, reduces drag, allows for individual flap control, and is fully enclosed within the flap structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0011] Figure 2 It is a schematic diagram of the side structure of the flap drive mechanism of the present invention. DETAILED DESCRIPTION

[0012] The technical solutions of the present invention will be described clearly and completely below with reference to the accompanying drawings of the present invention.

[0013] like Figure 1 、 Figure 2 As shown, the flap control mechanism of a light sport aircraft according to the present invention comprises flaps and flap driving mechanisms. The flap driving mechanisms are arranged in the flaps and are used to enable each flap to be independently controlled and deployed.

[0014] Furthermore, the flap drive mechanism includes a combined motor group 1, a flap motion mechanism and a drive shaft 2; the combined motor group 1 is arranged in the middle of the flap and is arranged parallel to the leading edge of the flap, and the combined motor group 1 drives the flap motion mechanism through the drive shaft 2. The drive shaft 2 extends to the side of the flap and a gear 3 is installed at the end of the drive shaft 2.

[0015] Furthermore, the flap movement mechanism includes a rack 4, a rocker arm 5, a first roller group 6 and a second roller group 7 provided on the rocker arm 5, and a first track 8 and a second track 9 cooperating therewith; the rack 4 is fixed on the wing, and the gear 3 is engaged with the rack 4 and is used to provide a variable flap movement path.

[0016] Furthermore, the flap drive mechanism is completely contained within the flap.

[0017] Furthermore, the combined motor group 1 includes a first motor and a second motor connected to each other.

[0018] The flap drive mechanism is equipped with two motors, each powered by a pinion on the outside of the shaft. These pinions drive a rocker arm with four rollers that ride on tracks locked to the rib structure. Two motors, rather than just one, are used to move the flaps to prevent failure of any one motor. Each motor provides sufficient power to operate the flap mechanism. During flap extension, the trajectory is designed so that the flaps extend straight outward along the first half of the trajectory, then move downward to increase the flap angle. This trajectory allows the flaps to extend and then stop before beginning their downward motion. In this position, the flaps increase chord and aerodynamic lift without increasing induced drag. When the motor assembly receives the signal to extend the flaps, drive shaft 2 begins rotating, driving gear 3 on rack 4. Gear 3 then moves rocker arm 5 and the flaps along rack 4. As the rocker arm 5 and gear 3 move, the two sets of roller groups move on the two sets of tracks; the two sets of tracks provide a stable path for the movement of the flaps. The compact design, completely enclosed in the flap structure, provides a clean aerodynamic profile, thereby reducing drag. It is lighter than current designs, making maintenance easy and low-cost. The design allows each flap to be controlled individually, which is a great advantage in asymmetric loading conditions, such as on military aircraft when bombs are dropped from the wings.

[0019] The above description is only a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by technicians in this technical field within the technical scope disclosed by the present invention should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. A flap control mechanism for a light sport aircraft, characterized in that: The flap control mechanism of a light sport aircraft comprises flaps and flap drive mechanisms, wherein the flap drive mechanisms are arranged in the flaps and are used to enable each flap to be independently controlled and deployed, and the flap drive mechanisms comprise a combined motor group (1), a flap motion mechanism, and a drive shaft (2); the combined motor group (1) is arranged in the middle of the flaps and is arranged parallel to the leading edge of the flaps, the combined motor group (1) drives the flap motion mechanism via the drive shaft (2), and the drive shaft (2) extends to the front of the flaps. A gear (3) is mounted on the side and at the end of the drive shaft (2). The flap movement mechanism comprises a rack (4), a rocker arm (5), a first roller group (6) and a second roller group (7) provided on the rocker arm (5), and a first track (8) and a second track (9) matched therewith. The rack (4) is fixed on the wing, and the gear (3) is engaged with the rack (4) and is used to provide a variable flap movement path. The flap extends outward in a straight line in the first half of the trajectory movement and then moves downward to increase the flap angle.

2. A flap control mechanism for a light sport aircraft according to claim 1, characterized in that: The flap drive mechanism is completely contained within the flap.

3. The flap control mechanism for a light sport aircraft according to claim 1, characterized in that: The combined motor group (1) comprises a first motor and a second motor which are connected to each other.

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