Flapairon linkage system and aircraft

Abstract

The present invention discloses a flaperon linkage system and an aircraft, wherein the flaperon linkage system comprises two flapers, two push-pull flexible shafts, a flaperon control mechanism and a flaperon linkage mechanism; the two push-pull flexible shafts are used to be installed on the fuselage, and the two push-pull flexible shafts are connected to the two flapers in a one-to-one transmission manner; the flaperon control mechanism is connected to the two push-pull flexible shafts in driving connection, and is used to drive the two flapers to rotate around an axis respectively through the two push-pull flexible shafts, and the two flapers rotate in different directions and angles to control the steering of the aircraft; the flaperon linkage mechanism is connected to the two push-pull flexible shafts in driving connection, and is used to drive the two flapers to rotate synchronously around an axis through the two push-pull flexible shafts, and the two flapers rotate synchronously in the same direction and angle to assist in adjusting the lift pressure of the aircraft. The technical solution of the present invention solves the problem that the existing aircraft cannot achieve short-distance takeoff and landing.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a flaperon linkage system and an aircraft. Background Art

[0002] The wings of an airplane mainly include a main wing and a tail wing, the main wing is connected with flaps and ailerons, and the tail wing is connected with elevators and rudders, wherein flaps are used to adjust the lift of the airplane for takeoff and the resistance for landing, ailerons are used to perform steering operations on the airplane, and elevators are used to control the elevation angle of the airplane for takeoff. At present, light airplanes on the market are mainly divided into two categories, one is a light airplane with both flaps and ailerons, each of which is equipped with an independent control mechanism, which can perform steering operations and adjust the lift for takeoff and landing, and the control structure of flaps and ailerons of such light airplanes is complex, and the control structure occupies a large space of the main body of the airplane, and such airplanes are generally high-end airplanes with relatively high prices; the other type of light airplane is only equipped with ailerons, and the ailerons are connected with a special control mechanism to realize the steering function of the airplane, but during the process of takeoff and landing of such airplanes, the ailerons cannot rotate synchronously in the same direction, resulting in a fixed angle of the ailerons relative to the wings, and short-distance takeoff and landing cannot be achieved on a short runway, and the angle of the ailerons relative to the wings can only be adjusted manually before takeoff. Summary of the invention

[0003] The main purpose of the present invention is to provide a flaperon linkage system, aiming to solve the problems that the existing flaperon control system of light aircraft cannot achieve linkage control, occupies a large space and cannot achieve short-distance takeoff.

[0004] To achieve the above object, the flaperon linkage system proposed in the present invention comprises:

[0005] Two flap ailerons;

[0006] Two push-pull flexible shafts are used to be installed on the fuselage, and the two push-pull flexible shafts are in one-to-one transmission connection with the two flaperons;

[0007] A flaperon control mechanism is connected to the two push-pull flexible shafts and is used to drive the two flapers to rotate around an axis through the two push-pull flexible shafts. The two flapers rotate in different directions and angles to control the steering of the aircraft; and

[0008] The flaperon linkage mechanism is connected to the two push-pull flexible shafts for driving the two flapers to rotate synchronously around an axis through the two push-pull flexible shafts, and the directions and angles of the synchronous rotation of the two flapers are the same to assist in adjusting the lift pressure of the aircraft.

[0009] Optionally, the two push-pull flexible shafts are symmetrically arranged along a center line, and each push-pull flexible shaft comprises a telescopic shaft, an input shaft, an intermediate flexible shaft and an output shaft, the input shaft, the intermediate flexible shaft and the output shaft are connected in sequence, and the telescopic shaft is movably arranged in the input shaft, the intermediate flexible shaft and the output shaft; one end of the telescopic shaft extends out of the input shaft and is drivingly connected to the flaperon control mechanism, and the other end of the telescopic shaft extends out of the output shaft and is fixedly connected to the corresponding flaperon;

[0010] The flaperon control mechanism is used to drive the telescopic shafts of the two push-pull flexible shafts to reciprocate along the axis direction of the input shaft, the intermediate flexible shaft and the output shaft, so as to drive the two flaperons to rotate around an axis respectively;

[0011] The flaperon linkage mechanism is drivingly connected to the output shafts of the two push-pull flexible shafts, and is used to drive the output shafts of the two push-pull flexible shafts to rotate along an axis, so that the telescopic shafts of the two push-pull flexible shafts drive the two flapers to rotate synchronously around an axis.

[0012] Optionally, the flaperon linkage mechanism comprises a rotating shaft, two ends of the rotating shaft are fixedly connected with two connecting rod assemblies, and the two ends of the rotating shaft are connected one-to-one with the output shafts of the two push-pull flexible shafts through the two connecting rod assemblies;

[0013] The rotating shaft has multiple rotation positions. When the rotating shaft is driven to different rotation positions, the rotating shaft drives the output shafts of the two push-pull flexible shafts to rotate along an axis to a preset position through the two connecting rod assemblies, so that the telescopic shafts of the two push-pull flexible shafts drive the two flapers to rotate synchronously around an axis to a preset position.

[0014] Optionally, the connecting rod assembly includes a connecting rod and a fixing part, the connecting rods of the two connecting rod assemblies are symmetrically arranged and respectively fixedly connected to the two ends of the rotating shaft, and the fixing parts of the two connecting rod assemblies are fixedly connected to the corresponding connecting rods and are drivingly connected to the output shafts of the two push-pull flexible shafts.

[0015] Optionally, the flaperon linkage mechanism also includes a remote control lever and a shift seat, the shift seat is used to be installed on the body of the aircraft, one end of the remote control lever is fixedly connected to the rotating shaft, the remote control lever drives the rotating shaft to rotate around an axis, and the shift seat is provided with a plurality of gear slots, and the remote control lever can be switched and clamped in each of the gear slots so that the rotating shaft is in different rotation positions.

[0016] Optionally, the flaperon control mechanism includes an operating rod, a connecting shaft and a mounting plate, the input shafts of the two push-pull flexible shafts are used to be connected and fixed to the body of the aircraft, the mounting plate is rotatably connected to the body of the aircraft, the telescopic shafts of the two push-pull flexible shafts extend out of one end of their respective input shafts and are respectively connected to the mounting plates, one end of the connecting shaft is connected to the mounting plate, and the operating rod is connected to the connecting shaft; the operating rod drives the mounting plate to rotate clockwise or counterclockwise along an axis through the connecting shaft, so as to drive the telescopic shafts of the two push-pull flexible shafts to drive the two flapers to rotate correspondingly around an axis;

[0017] Optionally, the mounting plate is arranged in an inverted triangle shape, the mounting plate comprises an axial hole and two symmetrically arranged corners, one end of the telescopic shafts of the two push-pull flexible shafts extending out of their respective corresponding input shafts are respectively fixedly connected to the two corners of the mounting plate, and one end of the connecting shaft passes through the axial hole and is fixedly connected to the mounting plate;

[0018] The operating lever is placed stationary so that the mounting plate connected to the operating lever through the connecting shaft is in an upright state, so that the distances between the ends of the two telescopic shafts and their corresponding input shafts are the same, so that the angles of the two flaperons driven by the two telescopic shafts are the same; the operating lever is swung so that the connecting shaft drives the mounting plate to rotate clockwise or counterclockwise along an axis, and the mounting plate drives the two telescopic shafts to deflect around an axis so that the distances between the ends of the two telescopic shafts and their corresponding input shafts are different, the corresponding telescopic shaft far away from the input shaft pulls the corresponding flaperon to rotate a corresponding angle, and the corresponding telescopic shaft close to the input shaft pushes the corresponding flaperon to rotate a corresponding angle, so that the two telescopic shafts drive the two flaperons to rotate at different angles and directions.

[0019] The present invention further provides an aircraft, comprising an aircraft body and the flaperon linkage system described in any of the above embodiments, wherein the flaperon linkage system is installed on the aircraft body.

[0020] Optionally, the aircraft is an airplane.

[0021] The technical solution of the present invention is that in the flap-aileron linkage system, the flap and the aileron are integrally arranged to form the flap-aileron, the two flap-ailers of the aircraft are connected to each other with two push-pull flexible shafts in a one-to-one transmission manner, and the flap-aileron control mechanism and the flap-aileron linkage mechanism are drivingly connected with the two push-pull flexible shafts, wherein the flap-aileron control mechanism drives the two flap-ailers to rotate synchronously in opposite directions around an axis through the two push-pull flexible shafts, so that the rotation angles of the two flap-ailers are different, thereby controlling the steering of the aircraft and realizing the function of the aileron; the flap-aileron linkage mechanism drives the two flap-ailers to rotate synchronously in the same direction around an axis through the two push-pull flexible shafts, so that the two flaps rotate synchronously at the same angle, thereby changing the angle of the flap-aileron relative to the overall wing, thereby adjusting the lift of the aircraft for takeoff and the resistance for landing, thereby realizing the function of the flap. The flaperon control mechanism and the flaperon linkage mechanism are linked to each other through a push-pull flexible shaft. During takeoff and landing of the aircraft, the lift of the aircraft is adjusted by driving the push-pull flexible shaft through the flaperon linkage mechanism. When the aircraft performs a turning operation during flight, the turning of the aircraft is achieved by driving the push-pull flexible shaft through the flaperon control mechanism. In this way, the linkage control of the flaps and the ailerons can be achieved, avoiding the situation that the flaps and the ailerons are independently configured with control mechanisms and occupying too much space in the aircraft, simplifying the control system structure and facilitating operation. In addition, compared with aircraft only equipped with ailerons, the flaperon linkage system can automatically adjust the angle of the flaperons to adapt the aircraft to runways of different lengths, and can achieve fast short-distance takeoff and landing in emergency situations. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0023] Figure 1 It is a structural schematic diagram of an embodiment of a flaperon linkage system of the present invention;

[0024] Figure 2 for Figure 1 Schematic diagram of the push-pull flexible shaft structure of the center flap aileron linkage system;

[0025] Figure 3 for Figure 1 The schematic diagram of the structure of the flaperon control mechanism of the center flaperon linkage system;

[0026] Figure 4 for Figure 1 A schematic diagram of the structure of the flaperon linkage mechanism of the center flaperon linkage system;

[0027] Figure 5 for Figure 1A partial enlarged view of the middle A;

[0028] Figure 6 for Figure 1 A partial enlarged view of point B in the middle;

[0029] Figure 7 for Figure 1 Front view of the center flaperon linkage system;

[0030] Figure 8 for Figure 1 A schematic diagram of a state in which the rotation axis of the center flaperon linkage mechanism is in the third position;

[0031] Fig. 9 for Figure 1 A schematic diagram of a state in which the rotation axis of the center flaperon linkage mechanism is in a second position;

[0032] Fig.10 for Figure 1 A schematic diagram of a state in which the rotation axis of the center flaperon linkage mechanism is in a first position;

[0033] Fig.11 for Figure 8 Sectional view of the center flaperon linkage system along section DD;

[0034] Fig.12 for Figure 8 A schematic diagram of a flaperon control mechanism of a center flaperon linkage system;

[0035] Fig.13 for Fig.12 Enlarged view of point E in the middle;

[0036] Fig.14 for Fig. 9 A schematic diagram of the structure of the mounting plate of the flaperon control mechanism of the center flaperon linkage system;

[0037] Fig.15 for Figure 1 Schematic diagram of the structure of the shift seat of the flaperon linkage mechanism of the center flaperon linkage system; Description of the figure numbers:

[0038] Label name Label name 1 Flapair linkage system 331 Shaft hole 10 Flapairon 332 corner 20 Push-pull flexible shaft 340 Cable 210 Telescopic shaft 40 Flapairon linkage 220 Input shaft 410 Rotation axis 230 Intermediate flexible shaft 420 Connecting rod assembly 240 Output shaft 421 link 30 Flapairon control mechanism 422 Fixings 310 Joystick 430 Joystick 320 Connecting shaft 440 Shift seat 330 Mounting Plate 441 Gear slot

[0039] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0040] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" 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 a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0042] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0043] The present invention provides a flaperon linkage system 1 .

[0044] Specifically, the flaperon linkage system 1 is installed on an aircraft, and the flight attitude of the aircraft is adjusted by controlling the angle of the flaperon relative to the wing. When the aircraft is turning, the left and right flaperons 10 are driven to rotate in the opposite direction relative to the wing, so that the lift of the left and right wings is different, thereby generating a lift difference. The lift difference generates a rolling moment on the aircraft, causing the aircraft to tilt to one side, and then the aircraft is turned by using the rudder on the tail wing; when the aircraft takes off and lands, the left and right flaperons 10 are driven to rotate in the same direction relative to the wing at the same angle, and the angle of the flaperons 10 on both sides relative to the wing as a whole is increased, thereby increasing the lift or drag of the wing, and the lift or drag generated by the left and right wings is the same, so that the aircraft can take off and land. The flaperon linkage system can be installed on light aircraft, airships, etc., and will be described in detail below using a light aircraft as an example.

[0045] Reference Figures 1 to 4 , Figure 1 It is a structural schematic diagram of an embodiment of a flaperon linkage system 1 of the present invention; Figure 2 for Figure 1 A schematic diagram of the structure of the push-pull flexible shaft 20 of the center flap aileron linkage system 1; Figure 3 for Figure 1 A schematic structural diagram of the flaperon control mechanism 30 of the center flaperon linkage system 1; Figure 4 for Figure 1 A schematic structural diagram of the flaperon linkage mechanism 40 of the center flaperon linkage system 1.

[0046] In the embodiment of the present invention, the flaperon linkage system 1 includes two flaperons 10, two push-pull flexible shafts 20, a flaperon control mechanism 30 and a flaperon linkage mechanism 40; Figure 1 As shown, the flap and aileron of the light aircraft are integrated to form a flaperon 10, and the flaperon 10 has the functions of both flaps and ailerons. The two flaperons 10 are rotatably connected to the tail ends of the left and right wings of the light aircraft. Two push-pull flexible shafts 20 are installed on the fuselage of the aircraft and are in one-to-one transmission connection with the two flaperons 10. The push-pull flexible shafts 20 can drive the flaperons 10 to rotate relative to the wing, thereby changing the relative angle between the flaperons 10 and the wing so that the shape of the wing and the airflow changes, thereby controlling different postures of the light aircraft.

[0047] The flaperon control mechanism 30 is connected to the two push-pull flexible shafts 20. During the flight of the aircraft, the flaperon control mechanism 30 drives the two flapers 10 to rotate synchronously in opposite directions around an axis through the push-pull flexible shafts 20, and the two flapers 10 rotate at different angles, thereby changing the airflow on the left and right wings of the aircraft. The left and right wings form different lifts, thereby generating a deflection torque, thereby turning the aircraft.

[0048] The flaperon linkage mechanism 40 is driven and connected to the two push-pull flexible shafts 20. During the take-off and landing of the aircraft, the flaperon linkage mechanism 40 drives the two flapers 10 to rotate synchronously and in the same direction around an axis through the push-pull flexible shafts 20, and the two flapers 10 rotate at the same angle, thereby changing the angle of the flaperons 10 relative to the entire wing, thereby adjusting the lift of the aircraft for take-off and the resistance for landing.

[0049] The technical solution of the present invention is to form a flaperon 10 by integrally arranging the flap and aileron of the aircraft. The two flaperons 10 of the aircraft are connected to two push-pull flexible shafts 20 in a one-to-one transmission manner. The flaperon control mechanism 30 and the flaperon linkage mechanism 40 are drivingly connected to the two push-pull flexible shafts 20, wherein the flaperon control mechanism 30 drives the two flaperons 10 to rotate synchronously in opposite directions around an axis through the two push-pull flexible shafts 20, so that the two flaperons 10 rotate at different angles, thereby controlling the steering of the aircraft and realizing the function of the aileron; the flaperon linkage mechanism 40 drives the two flaperons to rotate synchronously in the same direction around an axis through the two push-pull flexible shafts 20, so that the two flaps rotate synchronously at the same angle, thereby changing the angle of the flaperon relative to the overall wing, thereby adjusting the lift of the aircraft for takeoff and the resistance for landing, and realizing the function of the flap. The flaperon control mechanism 30 and the flaperon linkage mechanism 40 are linked and controlled through the push-pull flexible shaft 20. When the aircraft takes off and lands, the flaperon linkage mechanism 40 drives the push-pull flexible shaft 20 to adjust the lift of the aircraft. When the aircraft performs a turning operation during flight, the flaperon control mechanism 30 drives the push-pull flexible shaft 20 to achieve the turning of the aircraft. In this way, the flap and the aileron can be linked and controlled, avoiding the occupancy of too much space in the aircraft by independently configuring control mechanisms for the flaps and the ailerons, simplifying the structure of the control system and making it easy to operate. In addition, compared with an aircraft only equipped with ailerons, the flaperon linkage system 1 integrates the flaps and the ailerons and has the function of flaps. When the aircraft takes off and lands, the flaperon linkage system 1 can be controlled to adjust the two flapers 10 to rotate synchronously in the same direction and at the same angle, thereby changing the lift of the wing for takeoff and the resistance for landing, so that the aircraft can take off and land on runways of different lengths, especially in emergency situations, to achieve fast short-distance takeoff and landing.

[0050] Reference Figure 1 , Figure 2 and Figure 6 , the two push-pull flexible shafts 20 are symmetrically arranged along a center line, which is the center line of the aircraft body. Each push-pull flexible shaft 20 includes a telescopic shaft 210, an input shaft 220, an intermediate flexible shaft 230 and an output shaft 240, the input shaft 220, the intermediate flexible shaft 230 and the output shaft 240 are connected in sequence, the telescopic shaft 210 is movably arranged in the input shaft 220, the intermediate flexible shaft 230 and the output shaft 240, the telescopic shaft 210 can reciprocate along the axial direction of the input shaft 220, the intermediate flexible shaft 230 and the output shaft 240, the length of the telescopic shaft 210 is fixed, and the telescopic shaft 210 and the intermediate flexible shaft 230 can be bent and deformed; wherein, one end of the telescopic shaft 210 extends out of the input shaft 220 and is drivingly connected to the flaperon control mechanism 30, and the other end of the telescopic shaft 210 extends out of the output shaft 240 and is fixedly connected to the corresponding flaperon 10;

[0051] In order to realize the turning of the aircraft, the flaperon control mechanism 30 drives the telescopic shaft 210 of the two push-pull flexible shafts 20 to reciprocate along the axis direction of the input shaft 220, the intermediate flexible shaft 230 and the output shaft 240, driving the two flaperons 10 to rotate synchronously in opposite directions around an axis, so that the directions and angles of the two flaperons relative to the wing are different, so that the lift of the left and right wings is different, thereby generating a deflection torque to turn the aircraft;

[0052] In order to adjust the lift pressure of the aircraft at any time and make the aircraft suitable for takeoff and landing on runways of different lengths, the flaperon linkage mechanism 40 is connected to the output shaft 240 of the two push-pull flexible shafts 20, and the output shaft 240 used to drive the two push-pull flexible shafts 20 can rotate synchronously along an axis, so that the telescopic shaft 210 of the two push-pull flexible shafts 20 drives the two flaperons 10 to rotate synchronously in the same direction around an axis by the same angle, so that the lift or resistance of the left and right wings is the same; when taking off and landing on a long runway, the two flaperons 10 are driven to deviate from the wing by a small rotation angle; when taking off and landing on a short runway, the two flaperons 10 are driven to deviate from the wing by a large rotation angle.

[0053] Reference Figure 1 , Figure 4 and Figure 5 The flaperon linkage mechanism 40 includes a rotating shaft 410, which is rotatably connected to the fuselage of the light aircraft. The rotating shaft 410 can rotate around its own axis. Two connecting rod assemblies 420 are fixedly connected at both ends of the rotating shaft 410. The two ends of the rotating shaft 410 are fixedly connected to the output shafts 240 of the two push-pull flexible shafts 20 through the two connecting rod assemblies 420. The connecting rod assembly 420 is rotated around the axis of the rotating shaft 410 by driving the rotating shaft 410 to rotate, and then the connecting rod assembly 420 drives the two push-pull flexible shafts 20 to rotate. The output shaft 240 of the shaft 20 rotates around the axis of the rotating shaft 410, and the intermediate flexible shaft 230 is bent and deformed accordingly. Since the length of the telescopic shaft 210 is fixed, the telescopic shaft 210 moves along the axis of the output shaft 240, thereby driving the two flap ailerons 10 to rotate; wherein, by connecting the connecting rod assembly 420 at both ends of the rotating shaft 410, only a small driving force needs to be applied to drive the output shafts 240 of the two push-pull flexible shafts 20 to rotate synchronously through the connecting rod assembly 420, and the operation is more labor-saving.

[0054] It can be understood that the rotating shaft 410 has multiple rotation positions. When the rotating shaft 410 is driven to be in different rotation positions, the rotating shaft 410 drives the output shafts 240 of the two push-pull flexible shafts 20 to rotate along an axis to a preset position through the two connecting rod assemblies 420, so that the telescopic shafts 210 of the two push-pull flexible shafts 20 drive the two flap ailerons 10 to rotate synchronously around an axis to a preset angle; by setting the rotation position, the two flap ailerons 10 can achieve step-by-step rotation, which can make the flap ailerons 10 stably maintain a rotation angle, and the structure is more stable. Figures 8 to 10The embodiment of the present application has three preset rotation positions. When the two flaperons are in the first position, the flaperon linkage mechanism 40 drives the flaperon 10 to rotate at the maximum angle. Fig.10 When the two flaperons 10 are in the third position, the flaperon linkage mechanism 40 drives the flaperon 10 to rotate at the minimum angle, such as Figure 8 When the two flaperons 10 are in the second position, the flaperon linkage mechanism 40 drives the flaperon 10 to rotate at an intermediate angle, such as Fig. 9 shown.

[0055] Further, refer to Figure 4 The connecting rod assembly 420 includes a connecting rod 421 and a fixing member 422. The two connecting rods 421 of the two connecting rod assemblies 420 are respectively fixedly connected to the two ends of the rotating shaft 410. In order to make the output shafts 240 of the two push-pull flexible shafts 20 rotate synchronously in the same direction and at the same angle, the two connecting rods are symmetrically arranged. The two fixing members 422 are respectively fixedly connected to the corresponding connecting rods 421 and fixedly connected to the output shafts 240 of the corresponding push-pull flexible shafts 20; wherein, the connecting rod 421 and the rotating shaft 410 can be fixedly connected by screws, can be fixed by welding, or can be connected by interference fit. In order to facilitate later inspection and maintenance, the embodiment of the present application preferably uses screws. The fixing member 422 is provided with a connecting hole, and the output shaft 240 of the push-pull flexible shaft 20 is penetrated through the connecting hole and locked by threads. For the convenience of installation and disassembly, the fixing member 422 is connected to the connecting rod 421 by screws. Of course, in other embodiments, the fixing member 422 can also be integrally formed with the connecting rod 421.

[0056] It can be understood that the rotating shaft 410 is connected to a driving mechanism, and the driving mechanism drives the rotating shaft 410 to rotate around its own axis. For example, the rotating shaft 410 can be driven by a motor and a transmission mechanism, or by a manual rocker 430. In order to reduce production costs, reduce aircraft weight, and reduce vibration during flight, the embodiment of the present application preferably uses a manual rocker 430 to drive the rotating shaft 410, and the manual rocker 430 drive is faster and more convenient to operate than the motor drive. Figure 4 The flaperon linkage mechanism 40 also includes a rocker 430 and a shift seat 440. The shift seat 440 is installed in the cockpit of the aircraft and fixed to the fuselage. One end of the rocker 430 is fixedly connected to the rotating shaft 410 by a screw. The rocker 430 drives the rotating shaft 410 to rotate around its own axis. The shift seat 440 is provided with a plurality of gear slots 441. The rocker 430 can be switched and clamped in each of the gear slots 441, so that the rotating shaft 410 is limited to different rotation positions, so that the flaperon 10 maintains a certain angle relative to the wing.

[0057] Reference Figure 1 and Figure 3The flaperon control mechanism 30 is used to control the steering of the aircraft, and includes an operating rod 310, a connecting shaft 320 and a mounting plate 330. The input shafts 220 of the two push-pull flexible shafts 20 are used to be connected and fixed with the fuselage of the light aircraft, and the mounting plate 330 is rotatably connected to the fuselage. The telescopic shafts 210 of the two push-pull flexible shafts 20 extend out of one end of each input shaft 220 and are respectively fixedly connected to the mounting plate 330, and one end of the connecting shaft 320 is fixedly connected to the mounting plate 330. The operating rod 310 is drivingly connected to the connecting shaft 320; the swing operating rod 310 rotates the connecting shaft 320 to drive the mounting plate 330 to rotate clockwise or counterclockwise along the axis of the connecting shaft 320, thereby driving the telescopic shafts 210 of the two push-pull flexible shafts 20 to drive the two flaperons 10 to rotate synchronously in opposite directions around an axis, so that the lift of the left and right wings is different, thereby generating a deflection torque that turns the aircraft, and the aircraft can turn;

[0058] Specifically, refer to Figure 1 , Fig.13 as well as Fig.14 The mounting plate 330 is arranged in an inverted triangle shape, and includes an axial hole 331 and two symmetrically arranged corner portions 332. The telescopic shafts 210 of the two push-pull flexible shafts 20 extend out of one end of the corresponding input shaft 220 and are respectively fixedly connected to the two corner portions 332 of the mounting plate 330. One end of the connecting shaft 320 is passed through the axial hole 331 and is fixedly connected to the mounting plate 330 by screws.

[0059] When the aircraft is in a horizontal flight state, the stationary operating rod 310 makes the mounting plate 330 in an upright state, such as Fig.11 , so that the ends of the two telescopic shafts 210 are at the same distance from the corresponding input shafts 220, so that the angles of the two flaperons driven by the two telescopic shafts 210 are the same; when the aircraft is turning, such as Fig.12 and Fig.13 As shown, the swing operating rod 310 causes the connecting shaft 320 to drive the mounting plate 330 to rotate clockwise or counterclockwise along the axis of the connecting shaft 320, and the mounting plate 330 drives one end of the two telescopic shafts 210 extending from their respective input shafts 220 to deflect around the axis of the connecting shaft 320. Since one end of the two telescopic shafts 210 extending from their respective input shafts 220 is respectively fixed to the two corners 332 of the mounting plate 330, the ends of the two telescopic shafts 210 are different from the respective corresponding input shafts 220 after deflection, wherein the end of one telescopic shaft 210 is far away from its corresponding input shaft 220, and the end of the other telescopic shaft 210 is close to its corresponding input shaft 220. Since the length of the telescopic shaft 210 is fixed, the corresponding telescopic shaft 210 far away from the input shaft 220 pulls the corresponding flaperon 10 to rotate a corresponding angle, and the corresponding telescopic shaft 210 close to the input shaft 220 pushes the corresponding flaperon 10 to rotate a corresponding angle, so that the two telescopic shafts 210 drive the two flaperons 10 to rotate synchronously in opposite directions.

[0060] Further, refer to Figure 3 The operating rod 310 is hinged to the connecting shaft 320, and the operating rod 310 can rotate around the hinge shaft. The operating rod 310 can also be connected to a cable 340, and the cable 340 is connected to the elevator driving connection on the tail of the aircraft. The cable 340 is used in conjunction with the flaperon linkage mechanism 40. By pushing the operating rod 310 to drive the cable 340 to pull the elevator to rotate relative to the tail, the pitch angle of the nose of the aircraft during takeoff and landing is controlled.

[0061] The present invention also provides an aircraft, which includes an aircraft body and a flaperon linkage system 1. The specific structure of the flaperon linkage system 1 refers to the above embodiment. Since the present subject 2 adopts all the technical solutions of all the above embodiments, it at least has all the beneficial effects brought by the technical solutions of the above embodiments, which will not be described one by one here. Among them, the flaperon linkage system 1 is installed on the aircraft body.

[0062] Optionally, the aircraft can be an airplane, especially a light airplane. The light airplane equipped with the flaperon linkage system 1 described in the above embodiment not only has a simple control structure and is easy to operate, but also occupies a small space and is light in weight, and can be suitable for runways of different lengths.

[0063] The above descriptions are only optional embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A flaperon linkage system, used in an aircraft, the aircraft comprising an airframe, characterized in that: include: Two-flap ailerons, the two-flap ailerons are rotatably connected to the tail ends of the left and right wings of the light aircraft; Two push-pull flexible shafts are used to be installed on the fuselage, and the two push-pull flexible shafts are in one-to-one transmission connection with the two flaperons; A flaperon control mechanism is connected to the two push-pull flexible shafts and is used to drive the two flapers to rotate synchronously and oppositely around an axis through the two push-pull flexible shafts. The two flapers rotate at different angles to control the steering of the aircraft. as well as A flaperon linkage mechanism is connected to the two push-pull flexible shafts and is used to drive the two flapers to rotate synchronously and in the same direction around an axis through the two push-pull flexible shafts, and the two flapers rotate synchronously at the same angle to assist in adjusting the lift pressure of the aircraft; The two push-pull flexible shafts are symmetrically arranged along a center line, and each push-pull flexible shaft comprises a telescopic shaft, an input shaft, an intermediate flexible shaft and an output shaft, wherein the input shaft, the intermediate flexible shaft and the output shaft are connected in sequence, and the telescopic shaft is movably arranged in the input shaft, the intermediate flexible shaft and the output shaft; one end of the telescopic shaft extends out of the input shaft and is drivingly connected to the flaperon control mechanism, and the other end of the telescopic shaft extends out of the output shaft and is fixedly connected to the corresponding flaperon; The flaperon control mechanism is used to drive the telescopic shafts of the two push-pull flexible shafts to reciprocate along the axial directions of the corresponding input shaft, the intermediate flexible shaft and the output shaft, so as to drive the two flapers to rotate synchronously in opposite directions around an axis; The flaperon linkage mechanism is drivingly connected to the output shafts of the two push-pull flexible shafts, and is used to drive the output shafts of the two push-pull flexible shafts to rotate along an axis, so that the telescopic shafts of the two push-pull flexible shafts drive the two flapers to rotate synchronously and in the same direction around an axis.

2. The flaperon linkage system according to claim 1, characterized in that: The flaperon linkage mechanism comprises a rotating shaft, two ends of the rotating shaft are fixedly connected with two connecting rod assemblies, and the two ends of the rotating shaft are connected one-to-one with the output shafts of the two push-pull flexible shafts through the two connecting rod assemblies; The rotating shaft has multiple rotation positions. When the rotating shaft is driven to different rotation positions, the rotating shaft drives the output shafts of the two push-pull flexible shafts to rotate along an axis to a preset position through the two connecting rod assemblies, so that the telescopic shafts of the two push-pull flexible shafts drive the two flapers to rotate synchronously around an axis to a preset position.

3. The flaperon linkage system according to claim 2, characterized in that: The connecting rod assembly includes a connecting rod and a fixing part. The connecting rods of the two connecting rod assemblies are symmetrically arranged and fixedly connected to the two ends of the rotating shaft respectively. The fixing parts of the two connecting rod assemblies are fixedly connected to the corresponding connecting rods and are drivingly connected to the output shafts of the two push-pull flexible shafts.

4. The flaperon linkage system according to claim 2, characterized in that: The flaperon linkage mechanism also includes a remote control lever and a shift seat. The shift seat is used to be installed on the body of the aircraft. One end of the remote control lever is fixedly connected to the rotating shaft. The remote control lever drives the rotating shaft to rotate around an axis. The shift seat is provided with a plurality of gear slots. The remote control lever can be switched and clamped in each of the gear slots so that the rotating shaft is in different rotation positions.

5. The flaperon linkage system according to claim 1, characterized in that: The flaperon control mechanism includes an operating lever, a connecting shaft and a mounting plate. The input shafts of the two push-pull flexible shafts are used to be connected and fixed to the body of the aircraft. The mounting plate is rotatably connected to the body of the aircraft. The telescopic shafts of the two push-pull flexible shafts extend out of one end of their respective input shafts and are respectively connected to the mounting plates. One end of the connecting shaft is connected to the mounting plate, and the operating lever is drivingly connected to the connecting shaft. The operating lever drives the mounting plate to rotate clockwise or counterclockwise along an axis through the connecting shaft, so as to drive the telescopic shafts of the two push-pull flexible shafts to drive the two flapers to rotate synchronously in opposite directions around an axis.

6. The flaperon linkage system according to claim 5, characterized in that: The mounting plate is arranged in an inverted triangle shape, and the mounting plate includes an axial hole and two symmetrically arranged corners, and the telescopic shafts of the two push-pull flexible shafts extend out of one end of the corresponding input shafts and are respectively fixedly connected to the two corners of the mounting plate, and one end of the connecting shaft passes through the axial hole and is fixedly connected to the mounting plate; The operating lever is placed stationary so that the mounting plate connected to the operating lever through the connecting shaft is in an upright state, so that the distances between the ends of the two telescopic shafts and their corresponding input shafts are the same, so that the angles of the two flaperons driven by the two telescopic shafts are the same; the operating lever is swung so that the connecting shaft drives the mounting plate to rotate clockwise or counterclockwise along an axis, and the mounting plate drives one end of the two telescopic shafts extending out of their respective input shafts to deflect around an axis so that the distances between the ends of the two telescopic shafts and their corresponding input shafts are different, the corresponding telescopic shaft far away from the input shaft pulls the corresponding flaperon to rotate by a corresponding angle, and the corresponding telescopic shaft close to the input shaft pushes the corresponding flaperon to rotate by a corresponding angle, so that the two telescopic shafts drive the two flaperons to rotate at different angles and directions.

7. An aircraft, characterized in that: It comprises an airframe and a flaperon linkage system as described in claims 1 to 6, wherein the flaperon linkage system is installed on the airframe.

8. The aircraft according to claim 7, characterized in that The aircraft is an airplane.

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