Operating device of ultra-light aircraft aileron

Abstract

A control device of an ultra-light aircraft aileron comprises a steering column and a transverse sliding rod which are arranged in a cockpit, the steering column is connected with the transverse sliding rod through a steel wire rope and a fixed pulley, the steering column is pressed leftwards, the transverse sliding rod slides leftwards, the steering column is pressed rightwards, and the transverse sliding rod slides rightwards; transmission mechanisms are symmetrically connected to the two ends of the transverse sliding rod and used for driving the left aileron and the right aileron to deflect in the opposite directions. The transmission mechanism comprises a first connecting rod, a triangular hinging plate and a second connecting rod, the triangular hinging plate is hinged in the wing, the first connecting rod is hinged between the end part of the transverse sliding rod and the triangular hinging plate, the second connecting rod is hinged between the triangular hinging plate and a rib plate of the aileron, and the second connecting rod and the rib plate form a crank connecting rod mechanism. According to the aileron control device, a complex power-assisted oil cylinder and an electric control system are omitted, the aileron is controlled through the steel wire rope, the fixed pulley and the transmission mechanism, and the aileron control device has the advantages of being light in weight, simple in structure and the like and meets the design requirements of ultra-light aircrafts.

Description

Technical Field

[0001] The invention relates to the technical field of ultralight aircraft, in particular to a control device for an aileron of an ultralight aircraft. Background Art

[0002] As the country gradually relaxes low-altitude control, ultralight aircraft have entered the public's field of vision. Ultralight aircraft have the advantages of small size, light weight, simple structure, simple operation, easy maintenance, short take-off distance, and low take-off site requirements.

[0003] In order to improve the maneuverability and playability of ultralight aircraft, ailerons are installed on the wings, and the aircraft can achieve lateral deflection and roll by controlling the ailerons. When the pilot presses the joystick to the left, the left aileron deflects upward, the right aileron deflects downward, and the aircraft rolls to the left; conversely, when the pilot presses the joystick to the right, the right aileron deflects upward, the left aileron deflects downward, and the aircraft rolls to the right. However, most of the existing aileron control structures are used for medium and large aircraft, and have problems such as complex structure, inconvenient operation, and difficult maintenance, and are not suitable for ultralight aircraft. Therefore, it is necessary to design an aileron control structure with a simple structure that is suitable for light aircraft. Summary of the invention

[0004] In order to overcome the shortcomings of the background technology, the present invention discloses an aileron control device for an ultralight aircraft, the purpose of which is to simplify the structure and meet the design requirements of the ultralight aircraft.

[0005] In order to achieve the above-mentioned invention object, the present invention adopts the following technical scheme:

[0006] The invention discloses an aileron control device for an ultralight aircraft, comprising a control rod and a transverse slide rod arranged in a cockpit, wherein the control rod is connected to the transverse slide rod through a steel wire rope and a fixed pulley, and the transverse slide rod slides to the left when the control rod is pressed to the left, and slides to the right when the control rod is pressed to the right; transmission mechanisms are symmetrically connected to the two ends of the transverse slide rod, and the transmission mechanisms are used for driving the left and right ailerons to deflect in opposite directions.

[0007] After implementing the above technical solution, the beneficial effects are as follows: the aileron control device abandons the complex booster cylinder and electronic control system, and uses a steel wire rope, a fixed pulley and a transmission mechanism to realize the control of the aileron. It has the advantages of light weight and simple structure, and meets the design requirements of ultralight aircraft.

[0008] To further improve the technical solution, the transmission mechanism includes a first connecting rod, a triangular hinged plate and a second connecting rod, wherein the triangular hinged plate is hinged in the wing, the first connecting rod is hinged between the end of the transverse sliding rod and the triangular hinged plate, the second connecting rod is hinged between the triangular hinged plate and the rib of the aileron, and forms a crank-connecting rod mechanism with the rib.

[0009] After implementing the above technical solution, the beneficial effects are as follows: the first connecting rod, the triangular hinge plate and the second connecting rod realize the transmission of the control force in different directions, and the second connecting rod and the rib plate constitute a crank connecting rod mechanism, which can push the aileron to deflect upward or downward, so that the aircraft can achieve lateral deflection and roll.

[0010] To further improve the technical solution, both ends of the second connecting rod are screwed with universal joint ball heads, the universal joint ball heads are hinged with the triangular hinge plate and the rib plate, and the second connecting rod is adjustable in length.

[0011] After the above technical solution is implemented, the beneficial effects are: the universal joint ball head can realize the articulation of components in different planes, and the second connecting rod is adjustable in length, which is conducive to adjusting the upper deflection angle and the lower deflection angle of the aileron.

[0012] To further improve the technical solution, one end of the first connecting rod is screwed with a fork hinge, and the other end is screwed with a universal joint ball head, the fork hinge is hinged to the end of the transverse sliding rod, the universal joint ball head is hinged to the triangular hinge plate, and the first connecting rod is adjustable in length.

[0013] After the above technical solution is implemented, the beneficial effect produced is that the first connecting rod is adjustable in length, which facilitates the connection and adjustment of the first connecting rod and the transverse sliding rod.

[0014] To further improve the technical solution, a transverse slide bar is arranged on the top of the cockpit, and connecting plates are provided at both ends of the transverse slide bar, and the connecting plates are hinged with fork hinges; a slide groove and a slide sleeve are fixed on the top of the cockpit, the transverse slide bar can slide in the slide sleeve, and the connecting plate slides in the slide groove.

[0015] After the above technical solution is implemented, the beneficial effects are as follows: the connecting plate slides in the slide groove, which can limit the rotational freedom of the transverse slide bar; the transverse slide bar can slide in the sliding sleeve, which can deflect the aileron on one side downward and the aileron on the other side upward.

[0016] To further improve the technical solution, the control column includes a main control column and a co-control column, the main control column and the co-control column are hinged to the bottom of the cockpit through a third connecting rod, and the two ends of the third connecting rod are respectively connected to the two ends of the transverse sliding rod through a wire rope and a fixed pulley.

[0017] After implementing the above technical scheme, the beneficial effects produced by the present invention are: setting a main driving lever and a co-driving lever can enable two passengers to have driving authority; the two ends of the third connecting rod are respectively connected to the two ends of the transverse sliding bar through a wire rope and a fixed pulley, and pressing the main driving lever or the co-driving lever can drive the transverse sliding bar to slide in the pressing direction. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Attached Figure 1 Shown is a schematic diagram of the overall structure of an aileron control device for an ultralight aircraft.

[0019] Attached Figure 2 Shown is a schematic diagram of the structure of the control rod and the third link.

[0020] Attached Figure 3 Shown is a schematic structural diagram of a transverse sliding bar.

[0021] Attached Figure 4 Shown is a schematic structural diagram of a transmission mechanism.

[0022] Attached Figure 5 Shown is a schematic diagram of the action of the right aileron when the joystick is pressed right.

[0023] Attached Figure 6 Shown is a schematic diagram of the action of the left aileron when the joystick is pressed to the right.

[0024] In the attached figure:

[0025] 1. Cockpit; 11. Slideway; 12. Slide sleeve;

[0026] 2. Control column;

[0027] 3. The third connecting rod;

[0028] 4. Wing; 41. Wing spar; 42. Wing rib; 43. Articulation axis;

[0029] 5. Aileron; 51. Rib; 52. Tubular beam;

[0030] 6. Wire rope;

[0031] 7. Fixed pulley;

[0032] 8. lateral sliding bar; 81. connecting plate; 82. connecting column;

[0033] 9. Transmission mechanism; 91. First connecting rod; 92. Triangular hinge plate; 93. Second connecting rod. DETAILED DESCRIPTION

[0034] The preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the scope of protection of the present invention. It should be noted that in the description of the present invention, the terms "front", "rear", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside" and the like indicating directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, which are only for the convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention. It should also be noted that in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or the internal connection of two elements. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0035] Refer to the attached Figure 1 An ultralight aircraft aileron control device includes a control rod 2 and a transverse slide bar 8 arranged in a cockpit 1. The control rod 2 is connected to the transverse slide bar 8 through a steel wire rope 6 and a fixed pulley 7. Transmission mechanisms 9 are symmetrically connected to the two ends of the transverse slide bar 8. The transmission mechanism 9 is used to drive the left and right ailerons 5 to deflect in opposite directions. The structure and function thereof are described in detail below.

[0036] Refer to the attached Figure 2 , attached Figure 2 The structure diagram of the steering column and the third connecting rod is shown. In this embodiment, a steering column 2 is hinged to the main driving position and the co-pilot position of the cockpit 1, and the two steering columns 2 are hinged to the bottom of the cockpit 1 through the third connecting rod 3, and a steel wire rope 6 is connected to each end of the third connecting rod 3. The main driving position and the co-pilot position both have driving authority, and pressing any steering column 2 to the left can move the third connecting rod 3 to the right and pull the steel wire rope 6 on the left. Similarly, pressing any steering column 2 to the right can move the third connecting rod 3 to the left and pull the steel wire rope on the right.

[0037] Refer to the attached Figure 3 , attached Figure 3 The figure shows the structure diagram of the horizontal sliding bar. Figure 3It can be seen that a slide groove 11 and a slide sleeve 12 are fixed on the top of the cockpit 1, and a connecting plate 81 and a connecting column 82 are provided at both ends of the transverse slide bar 8. The transverse slide bar 8 can slide in the slide sleeve 12, and the connecting plate 81 slides in the slide groove 11. The slide groove 11 cooperates with the connecting plate 81 to limit the rotational freedom of the transverse slide bar 8 and prevent the transverse slide bar 8 from rotating.

[0038] The connecting column 82 is used to connect the steel wire rope 6. The two steel wire ropes 6 connected to the third connecting rod 3 are finally connected to the connecting column 82 through the reversal of multiple sets of fixed pulleys 7. In this way, pressing the steering rod 2 to the right can make the transverse slide bar 8 slide to the right; pressing the steering rod 2 to the left can make the transverse slide bar 8 slide to the left.

[0039] See attached Figure 4 , attached Figure 4 The figure shows the schematic diagram of the transmission mechanism. Figure 4 It can be seen that the wing 4 is mainly composed of two wing spars 41, a plurality of wing ribs 42 and a skin (not shown in the figure), and a hinge shaft 43 is arranged at the rear of the wing 4. The aileron 5 is mainly composed of a plurality of ribs 51, a tubular beam 52 and a skin (not shown in the figure), wherein the ribs 51 are hinged to the hinge shaft 43.

[0040] The transmission mechanism 9 is arranged in the wing 4, and the transmission mechanism 9 includes a first connecting rod 91, a triangular hinge plate 92 and a second connecting rod 93, wherein the triangular hinge plate 92 is hinged in the wing 4, the first connecting rod 91 is hinged between the end of the transverse sliding rod 8 and the triangular hinge plate 92, and the second connecting rod 93 is hinged between the triangular hinge plate 92 and the rib plate 51 of the aileron 5, and forms a crank connecting rod mechanism with the rib plate 51.

[0041] Specifically, both ends of the second connecting rod 93 are screwed with universal joint ball heads, and the second connecting rod 93 is respectively hinged to the triangular hinge plate 92 and the rib plate 51 through the universal joint ball heads, so that the hinge of components in different planes can be achieved. Due to the screw connection structure, the length of the second connecting rod 93 can also be adjusted.

[0042] One end of the first connecting rod 91 is screwed with a fork hinge, and the other end is screwed with a universal joint ball head, the fork hinge is hinged to the end of the transverse slide bar 8, and the universal joint ball head is hinged to the triangular hinge plate 92. Similarly, the first connecting rod 91 can also be adjusted in length.

[0043] The first connecting rod 91, the triangular hinge plate 92 and the second connecting rod 93 are hinged to each other to realize the transmission of the control force from the lateral direction to the longitudinal direction. The second connecting rod 93 and the rib plate 51 form a crank connecting rod mechanism, which can push the aileron 5 to deflect upward or downward to realize the lateral deflection and roll of the aircraft.

[0044] See attached Figure 5 , attached Figure 5The figure shows the action of the right aileron when the joystick is pressed right. Figure 5 It can be seen that when the joystick 2 is pressed right, the lateral slide bar 8 slides rightward, driving the right aileron 5 to deflect upward, and at the same time driving the left aileron 5 to deflect downward. After the right aileron 5 deflects upward, the lift is reduced, and after the left aileron 5 deflects downward, the lift is increased, so that the aircraft obtains a moment of deflection to the right, and the aircraft rolls to the right.

[0045] Refer to the attached Figure 6 , attached Figure 6 The figure shows the action of the left aileron when the joystick is pressed to the right. Figure 6 It can be seen that when the joystick 2 is pressed to the left, the right aileron 5 deflects downward, while the left aileron 5 deflects upward, and the aircraft rolls to the left.

[0046] Compared with the aileron control device of the existing aircraft, the present aileron control device abandons the complicated power-assisting oil cylinder and the electronic control system, and realizes the control of the aileron by using the steel wire rope, the fixed pulley and the transmission mechanism. It has the advantages of light weight and simple structure, and meets the design requirements of the ultralight aircraft.

[0047] Although the embodiments of the present invention have been shown and described, it is understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the protection scope of the present invention is defined by the attached claims and their equivalents.

Claims

1. A control device for an ultralight aircraft aileron, characterized in that: It includes a control stick and a transverse slide bar arranged in the cockpit. The control stick is connected to the transverse slide bar through a wire rope and a fixed pulley. When the control stick is pressed to the left, the transverse slide bar slides to the left, and when the control stick is pressed to the right, the transverse slide bar slides to the right. Transmission mechanisms are symmetrically connected at both ends of the transverse slide bar, and the transmission mechanisms are used to drive the left and right ailerons to deflect in opposite directions.

2. The control device for an ultralight aircraft aileron as claimed in claim 1, characterized in that: The transmission mechanism includes a first connecting rod, a triangular hinge plate and a second connecting rod, wherein the triangular hinge plate is hinged in the wing, the first connecting rod is hinged between the end of the transverse sliding rod and the triangular hinge plate, and the second connecting rod is hinged between the triangular hinge plate and the rib plate of the aileron, and forms a crank connecting rod mechanism with the rib plate.

3. The control device for an ultralight aircraft aileron as claimed in claim 2, characterized in that: Universal joint ball heads are screwed at both ends of the second connecting rod, the universal joint ball heads are hinged with the triangular hinge plate and the rib plate, and the second connecting rod is adjustable in length.

4. The control device for an ultralight aircraft aileron as claimed in claim 2, characterized in that: One end of the first connecting rod is screwed with a fork hinge, and the other end is screwed with a universal joint ball head. The fork hinge is hinged to the end of the transverse sliding rod, and the universal joint ball head is hinged to the triangular hinge plate. The first connecting rod is adjustable in length.

5. The control device for an ultralight aircraft aileron as claimed in claim 4, characterized in that: The transverse slide bar is arranged on the top of the cockpit, and connecting plates are arranged at both ends of the transverse slide bar, and the connecting plates are hinged with the fork hinges; a slide groove and a slide sleeve are fixed on the top of the cockpit, the transverse slide bar can slide in the slide sleeve, and the connecting plate slides in the slide groove.

6. The control device for an ultralight aircraft aileron as claimed in claim 1, characterized in that: The control rod comprises a main control rod and a co-control rod, which are hinged to the bottom of the cockpit through a third connecting rod, and the two ends of the third connecting rod are respectively connected to the two ends of the transverse sliding rod through a wire rope and a fixed pulley.

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