Aircraft mechanical control system

Abstract

The invention relates to the technical field of airplane mechanical control, in particular to an airplane mechanical control system.A foot operation system comprises a left foot operation rod and a right foot operation rod which are rotatably arranged on a foot operation fixing base, the upper end of an oil cylinder is hinged to a pedal, the lower end of the oil cylinder is hinged to an oil cylinder fixing base, and the oil cylinder is connected with a foot control system. The elevator control rocker arm is connected with the foot operating system, the hand operating system comprises a left handle and a right handle, the left handle and the right handle are connected with the vertical rod fixing seat through a vertical rod, and the mixed control system comprises a rudder system, an elevator system and an aileron system. According to the system, through the innovative design of a foot operating system and a hand operating system, mechanical control over multiple control surfaces of an airplane can be achieved, a pilot can achieve action control over the airplane in the air and on the ground through one hand and two feet, and therefore accurate and synchronous control over a rudder system, an elevator system and an aileron system is achieved.

Description

Technical Field

[0001] This invention relates to the field of aircraft mechanical control technology, and in particular to an aircraft mechanical control system. Background Technology

[0002] In the field of existing aircraft mechanical control, traditional aircraft control systems often suffer from problems such as complex structure, slow response, and inconvenient operation. In particular, when pilots perform directional control, elevator adjustment, and aileron control, they need to complete the task through multiple independent and unrelated mechanical components. This not only increases the difficulty of pilot operation but also reduces flight safety and efficiency.

[0003] Specifically, traditional directional control systems often employ complex cable or linkage mechanisms, which suffer from drawbacks such as low transmission efficiency and easy wear. The control of elevator and aileron systems often relies on multiple independent push-pull rods and reversing devices, resulting in high system redundancy and increased maintenance costs.

[0004] Furthermore, the existing technology lacks an integrated and efficient mechanical control device that can simultaneously achieve precise and synchronous control of direction, elevator, and ailerons, thus limiting further improvements in aircraft handling performance. Summary of the Invention

[0005] The main objective of this invention is to overcome the shortcomings of the prior art and provide an aircraft mechanical control system.

[0006] The technical solution adopted by this invention to achieve its technical objective is: an aircraft mechanical control system, comprising: A foot control system includes a left foot lever and a right foot lever, which are rotatably mounted on a foot control base; Foot pedals are installed on the left and right foot levers; The upper end of the hydraulic cylinder is hinged to the foot pedal, and the lower end is hinged to the hydraulic cylinder mounting base. The elevator control arm is connected to the foot operating system; The hand operating system includes a left handle and a right handle, which are connected to a pole fixing base via a pole. The hybrid control system includes the rudder system, elevator system, and aileron system; The foot operating system is used to control the rudder system via the elevator control arm through the movement of the foot pedal, and to control the aircraft brakes via the hydraulic cylinder. The hand operating system is used to control the elevator system and the aileron system to achieve the take-off, landing and stable flight of the aircraft by moving the left handle and / or the right handle.

[0007] Preferably, the foot operating system further includes a first rudder push-pull rod, the elevator control rocker arm is connected to the first rudder push-pull rod, and the first rudder push-pull rod is connected to the rudder system of the hybrid control system.

[0008] Preferably, the rudder system includes a first rudder plate and a second rudder plate, the first rudder push-pull rod is connected to the first rudder plate, the first rudder plate is connected to the second rudder plate via the second rudder push-pull rod, and the second rudder plate is connected to the rudder via a first flexible shaft.

[0009] Preferably, the manual operating system further includes a first elevator push-pull rod and an aileron swerve, the first elevator push-pull rod and the aileron swerve being connected to the elevator system and the aileron system of the hybrid control system, respectively.

[0010] Preferably, the elevator system includes a third reversing plate and a fourth reversing plate, the first elevator push-pull rod is connected to the third reversing plate, the third reversing plate is connected to the fourth reversing plate through the second elevator push-pull rod, the fourth reversing plate is connected to the T-shaped control rocker arm through the second flexible shaft, the steering plate, and the steering rod, and the T-shaped control rocker arm is connected to the elevator.

[0011] Preferably, the aileron system includes a fifth swashplate and a sixth swashplate. The aileron swashplate is connected to the fifth swashplate via a third flexible shaft. The fifth swashplate is connected to the sixth swashplate via a first aileron push-pull rod. The sixth swashplate is connected to the third aileron push-pull rod via a second aileron push-pull rod and a seventh swashplate. The third aileron push-pull rod is connected to the aileron rudder.

[0012] Preferably, the foot operating system further includes a handbrake handle for locking the hydraulic pressure of the hydraulic cylinder.

[0013] Preferably, the hand operating system further includes a synchronization rod, which connects the pole fixing seat and the aileron reversing plate to realize synchronous control of the left and right handles.

[0014] Preferably, the left foot lever and the right foot lever are connected by a linkage gear to achieve synchronous reverse movement.

[0015] Compared with the prior art, the beneficial effects of the present invention are: The aircraft's mechanical control system, through its innovative foot and hand operating system design, enables the mechanical control of multiple control surfaces. Pilots can control the aircraft's movements in the air and on the ground using only one hand and two feet, thus achieving precise and synchronized control of the rudder, elevator, and aileron systems.

[0016] Specifically, by employing a linkage gear to achieve synchronous and reverse movement of the foot control stick, the stability and response speed of directional control are improved. Furthermore, the direct hinge between the hydraulic cylinder and the foot pedal simplifies the brake system structure and enhances braking efficiency. Moreover, the gear linkage of the foot control system reduces the number of linkage control components and ensures the adjustable relative position of the left and right systems (due to the staggered gear installation). When the brake cylinder is depressed, differential brake control allows for ground-based turning; synchronous braking brings the aircraft to a stop on the ground; and pressing the left or right foot pedals controls the rudder for in-flight turning.

[0017] Meanwhile, the hand control system, through the design of the synchronization lever and reversing plate, enables synchronized control of the left and right hand levers, enhancing the maneuverability of the aircraft during takeoff and landing and stable flight.

[0018] Furthermore, this device adopts a modular design, with each system connected by efficient transmission components such as push-pull rods and flexible shafts, reducing system complexity and maintenance costs while improving overall reliability and service life. The mechanical linkage layout ensures connection strength, and the end-end fisheye bearing guarantees a certain amount of adjustable displacement, eliminating installation errors. The flexible shaft layout solves the problem of long transmission distances and limited space on the control surfaces of high-wing aircraft, reducing structural weight while ensuring transmission efficiency. Nuts arranged on the threads of the flexible shaft fixing points allow for a certain amount of adjustable displacement, eliminating installation errors. The hybrid control rod design reduces structural mounting components without affecting the rotation of each moving part.

[0019] Therefore, the aircraft mechanical control system of this patent has significant advantages in improving aircraft handling performance, reducing pilot operating difficulty, and improving flight safety and efficiency. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of an aircraft's mechanical control system.

[0021] Figure 2 This is a schematic diagram of the front structure of the foot operating system.

[0022] Figure 3 This is a schematic diagram of the back structure of the foot operating system.

[0023] Figure 4 This is a schematic diagram of the overall system architecture of the foot operating system.

[0024] Figure 5 This is a schematic diagram of the front structure of a hand operating system.

[0025] Figure 6 This is a schematic diagram of the back structure of the hand operating system.

[0026] Figure 7 for Figure 1 A schematic diagram of the structure of the medium-duty mixing control system.

[0027] Figure 8 This is a schematic diagram of the rudder system.

[0028] Figure 9 This is a schematic diagram of the elevator system.

[0029] Figure 10 This is a schematic diagram of the aileron system.

[0030] in: 1-Foot operating system; 101-First vertical lever; 102-First horizontal lever; 103-Horizontal axis; 104-Rudder control rocker arm; 105-Left foot lever; 106-Right foot lever; 107-Foot control mounting base; 108-Foot pedal; 109-First bushing; 110-Hydraulic cylinder; 111-Pin; 112-Hydraulic cylinder mounting base; 113-First rudder push-pull lever; 114-Spherical bearing; 115-Linkage gear; 116-Brake oil pipe; 17-Brake caliper; 118-Brake disc; 119-Handbrake lever; 2-Hand operating system; 201-Left lever; 202-Right lever; 203-Second upright; 204-Upright lever mounting bracket; 205-Second crossbar; 206-Second bushing; 207-Aileron directional control plate; 208-Short stick; 209-Hand operating mounting plate; 210-Third bushing; 211-First elevator push-pull rod; 212-Synchronizer rod; 3-Rudder system; 301- 302-First reversing mounting bracket; 303-Second rudder push-pull rod; 304-Second reversing plate; 305-First flexible shaft; 306-Rudder; 307-First flexible shaft mounting bracket; 4-Elevator system; 401-Third reversing mounting bracket; 402-Third reversing plate; 403-Second elevator push-pull rod; 404-Fourth reversing plate; 405-Second flexible shaft; 406-Elevator; 407-Second flexible shaft mounting bracket; 408 - T-type control rocker arm; 409- Steering plate; 410- Steering rod; 5- Aileron system; 501- Fourth reversing mounting bracket; 502- Fifth reversing plate; 503- First aileron push-pull rod; 504- Sixth reversing plate; 505- Third flexible shaft; 506- Third flexible shaft mounting bracket; 507- Aileron rudder; 508- Second aileron push-pull rod; 509- Seventh reversing plate; 510- Fifth reversing mounting bracket; 511- Third aileron push-pull rod; 6- Mixing control rod. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. However, it should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of the invention. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0032] In the description of this invention, it should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to or indirectly connected to the other element.

[0033] In the description of this invention, it should be noted that the terms "center," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.

[0034] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances. Example 1:

[0035] Please see Figures 1-4 An aircraft mechanical control system includes a foot control system 1. The foot control system 1 includes a first upright stick 101, a first horizontal stick 102, a horizontal axis 103, and a rudder control rocker arm 104. The first upright stick 101, the first horizontal stick 102, the horizontal axis 103, and the rudder control rocker arm 104 are welded together to form an integral foot control stick.

[0036] The first horizontal bar 102 is divided into a left foot control bar 105 and a right foot control bar 106. The two ends of the left foot control bar 105 and the right foot control bar 106 are fixed and rotatably mounted on two foot control fixing seats 107. The outer wall of the foot control bar is in contact with the inner wall of the foot control fixing seat 107. The foot control fixing seat 107 is a split type, which is fixed by bolts to form a whole.

[0037] Both the left foot lever 105 and the right foot lever 106 are equipped with foot pedals 108. Each foot pedal 108 has a first bushing 109 fixed to its left and right sides. The inner wall of the first bushing 109 is in contact with the outer wall of the horizontal axis 103. The foot pedal 108 can rotate around the horizontal axis 103, which is fixed to one side of the top of the first upright 101.

[0038] The upper end of the hydraulic cylinder 110 is hinged to the foot pedal 108 via a pin 111, and the lower end of the hydraulic cylinder 110 is hinged to the hydraulic cylinder mounting base 112 via a pin 111. The connection method of the pin 111 does not affect the relative rotation between the two parts.

[0039] The rudder control rocker arm 104 is fixed to the fisheye bearing 114 of the first rudder push-pull rod 113 by bolts.

[0040] The left foot lever 105 and the right foot lever 106 are linked by the linkage gear 115 and move in opposite directions.

[0041] Furthermore, in this embodiment, the foot operating system also includes a handbrake handle 119, which is used to close the internal valve of the brake valve, lock the oil pressure, and stop the aircraft.

[0042] Specifically, in use, when the pilot uses his foot to push the lower end of the foot pedal 108 (at the horizontal axis 103), the left and right foot levers can rotate, the linkage gear 115 moves relative to each other, the left and right foot levers rotate synchronously, the first vertical lever 101 and the first horizontal lever 102 rotate around the foot control fixed seat 107, and the rudder control rocker arm 104 drives the first rudder push-pull rod 113 to move back and forth, thereby achieving the purpose of controlling the rudder.

[0043] When the pilot presses the upper part of the foot pedal 108 (the connection point of the upper part of the hydraulic cylinder 110) with his toes, the foot pedal 108 rotates around the horizontal axis 103, pressing down the hydraulic cylinder 110. The hydraulic pressure is transmitted to the brake caliper 117 through the brake oil pipe 116, locking the brake disc 118. Pressing the left foot pedal brakes the left wheel, pressing the right foot pedal brakes the right wheel, and pressing both pedals at the same time brakes both tires.

[0044] When the handbrake lever 119 is pulled, the internal valve of the brake valve is closed, and the oil pressure is locked. The pilot can stop the aircraft without pressing the foot pedal. When the handbrake lever is released, the oil pressure is released, the brakes fail, and the left and right wheels move. Implementation: 2:

[0045] Please see Figure 1 , Figure 5 , Figure 6 Based on the above embodiments, the aircraft mechanical control system includes a hand operating system 2, which includes a left handle 201 and a right handle 202. The left handle 201 and the right handle 202 are fixed to the second upright 203 by bolts. The outer wall of the second upright 203 contacts the inner wall of the upright fixing seat 204 and is fixedly connected by bolts. The upright fixing seat 204 can rotate around the second bushing 206 in the second crossbar 205.

[0046] Three short rods 208 are welded and fixed on the second crossbar 205. The two lower short rods 208 are bolted to the inner bushing of the hand operation fixing plate 209, so that they can rotate around the third bushing 210 inside the hand operation fixing plate 209. The upper short rod 208 is bolted to the first elevator push-pull rod 211, so as to control the first elevator push-pull rod 211.

[0047] Furthermore, in this embodiment, the hand operating system 2 also includes two synchronization rods 212. The fisheye bearing at one end of the two synchronization rods 212 is fixedly connected to the upright fixing seat 204 by bolts. The fisheye shaft at the other end of the two synchronization rods 212 is movably fixed together with the aileron directional plate 207 by bolts, thereby controlling the aileron directional plate 207 and thus realizing the synchronous control of the hand operating system by the left and right handles.

[0048] Specifically, in use, by operating the left handle 201 and the right handle 202 respectively, the upright fixing seat 204 can rotate around the second bushing 206 in the second crossbar 205, thereby driving the aileron directional plate 207 to move through the synchronizing rod 212, and controlling the aileron directional plate 207.

[0049] Then, by operating the left handle 201 and the right handle 202 separately / synchronously, the left handle 201 and the right handle 202, through the second upright 203, the upright fixing seat 204, and the second crossbar 205, cause the two lower short rods 208 to rotate around the hand operation fixing plate 209, and the upper short rod 208 controls the first elevator push-pull rod 211.

[0050] The solution in this embodiment can be selectively combined with solutions in other embodiments. Implementation: 3:

[0051] Please see Figure 1 , Figure 7 , Figure 8 Based on the above embodiments, the aircraft mechanical control system includes a hybrid control system, which includes a rudder system 3, an elevator system 4, and an aileron system 5.

[0052] The rudder system 3 includes a first reversing mounting base 301, which is fixed to the aircraft and is hinged to a first reversing plate 302. One end of the first reversing plate 302 is hinged to a first rudder push-pull rod 113, and the other end is hinged to a second rudder push-pull rod 303. One end of the second rudder push-pull rod 303 is hinged to a second reversing plate 304, which rotates around the mixing control rod 6. The second reversing plate 304 is connected to the rudder 306 via the first flexible shaft 305 and the first flexible shaft fixing seat 307. The rudder 306 is rotatably connected to the first flexible shaft 305, and the rudder 306 rotates around the first flexible shaft 305.

[0053] Specifically, in use, the driver presses the left and right foot pedals to control the foot operating system 1 to move back and forth, which drives the first rudder push-pull rod 113 to push and pull. The first rudder push-pull rod 113 drives the first reversing plate 302 to rotate on the first reversing fixed seat 301, thereby driving the second rudder push-pull rod 303 to move up and down. The second rudder push-pull rod 303 is connected to the second reversing plate 304, causing the second reversing plate 304 to rotate around the control rod 6. The rotation of the second reversing plate 304 causes the first flexible shaft 305 to push and pull, thereby driving the rudder 306 to rotate and deflect, thus changing the navigation direction.

[0054] The solution in this embodiment can be selectively combined with solutions in other embodiments. Implementation: 4:

[0055] Please see Figure 1 , Figure 7 , Figure 9 Based on the above embodiments, the aircraft mechanical control system, elevator system 4 includes a third reversing fixed seat 401, which is fixed on the aircraft and is hinged to a third reversing plate 402. One end of the third reversing plate 402 is hinged to a first elevator push-pull rod 211, and the other end is hinged to a second elevator push-pull rod 403. One end of the second elevator push-pull rod 403 is hinged to a fourth reversing plate 404, which also rotates around the control lever 6. The fourth reversing plate 404 is hinged to a steering plate 409 via a second flexible shaft 405 and a second flexible shaft fixing seat 407. The steering plate 409 is rotatably mounted on the aircraft. One end of the steering plate 409 is hinged to a steering rod 410. The steering rod 410 is hinged to a T-shaped control rocker arm 408. The T-shaped control rocker arm 408 is fixedly connected to an elevator 406.

[0056] The bushings on both sides of the elevator 406 are fixed to the aircraft, and T-shaped control arms 408 are fixed at both ends. The bushings are inserted at the connection between the elevator 406 and the T-shaped control arms 408, and the T-shaped control arms 408 are connected to the elevator 406 as a whole.

[0057] Specifically, in use, the pilot pushes and pulls the control system 2, which moves the first elevator push-pull rod 211 back and forth. The first elevator push-pull rod 211 drives the third reversing plate 402 to rotate on the third reversing fixed seat 401, thereby driving the second elevator push-pull rod 403 to move up and down. The second elevator push-pull rod 403 is connected to the fourth reversing plate 404, causing the fourth reversing plate 404 to rotate around the control lever 6. The rotation of the fourth reversing plate 404 causes the second flexible shaft 405 to push and pull, thereby driving the steering plate 409 to rotate. The steering plate 409 pulls the steering rod 410 to move, thereby driving the steering rod 410 to rotate through the T-shaped control rocker arm 408. The T-shaped control rocker arm 408 causes the elevator 406 to flip up and down, realizing the take-off and landing of the aircraft.

[0058] The solution in this embodiment can be selectively combined with solutions in other embodiments. Implementation: 5:

[0059] Please see Figure 1 , Figure 7 , Figure 10 Based on the above embodiments, the aircraft mechanical control system, the aileron system 5 includes a fourth reversing fixed seat 501, which is fixed on the aircraft and is hinged to a fifth reversing plate 502. One end of the fifth reversing plate 502 is hinged to the aileron reversing plate 207 via a third flexible shaft 505 and a third flexible shaft fixed seat 506, and the other end is hinged to a first aileron push-pull rod 503. One end of the first aileron push-pull rod 503 is hinged to a sixth reversing plate 504, which also rotates around the mixing control rod 6. The sixth reversing plate 504 is hinged to the second aileron push-pull rod 508, and the second aileron push-pull rod 508 is hinged to the fifth reversing fixing seat 510 through the seventh reversing plate 509. The fifth reversing fixing seat 510 is fixed on the aircraft. Meanwhile, one end of the seventh reversing plate 509 is hinged to the second aileron push-pull rod 508, and the other end is hinged to the third aileron push-pull rod 511. The third aileron push-pull rod 511 is hinged to the aileron rudder 507, which is hinged to the aircraft.

[0060] Specifically, in use, the driver controls the left and right hand operating system 1, causing the aileron directional plate 207 to rotate. The rotation of the aileron directional plate 207 causes the third flexible shaft 505 to push and pull, thereby causing the fifth directional plate 502 to rotate around the fourth directional fixing seat 501. The fifth directional plate 502, through the first aileron push-pull rod 503, causes the sixth directional plate 504 to rotate around the mixing control rod 6. The sixth directional plate 504 causes the second aileron push-pull rod 508 and the seventh directional plate 509 to rotate around the fifth directional fixing seat 510. At the same time, the other end of the seventh reversing plate 509 moves along with the third aileron push-pull rod 511. At this time, the aileron push-pull rod 3 moves back and forth, causing the aileron rudder 507 to rotate on the aircraft, thus realizing the switching on and off of the aileron rudder 507.

[0061] The solution in this embodiment can be selectively combined with solutions in other embodiments.

[0062] The working principle and specific usage procedure of the aircraft's mechanical control system are as follows: The pilot controls the movement of the foot pedal 108 through the left foot stick 105 and right foot stick 106 in the foot operating system 1, and then manipulates the rudder system 3 through the rudder control rocker arm 104 and the first rudder push-pull stick 113 to achieve heading control. At the same time, the foot pedal 108 controls the aircraft brake through the hydraulic cylinder 110. By moving the left handle 201 and the right handle 202 in the hand operating system 2, the elevator system 4 and the aileron system 5 are respectively operated through the first elevator push-pull rod 211 and the aileron reversing plate 207 to achieve the take-off and landing and stable flight of the aircraft. The rudder system 3 transmits motion to the rudder 306 through components such as the first reversing plate 302 and the second rudder push-pull rod 303. The elevator system 4 transmits motion to the elevator 406 through components such as the third reversing plate 402, the second elevator push-pull rod 403, the steering plate 409, and the steering rod 410. The aileron system 5 transmits motion to the aileron 507 through components such as the fifth reversing plate 502 and the first aileron push-pull rod 503.

[0063] It should be noted that although the above embodiments have been described herein, this does not limit the scope of patent protection of this invention. Therefore, any changes and modifications made to the embodiments described herein based on the innovative concept of this invention, or equivalent structural, procedural, or functional transformations made using the description and drawings of this invention, directly or indirectly applying the above technical solutions to other related technical fields, are all included within the scope of protection of this invention.

Claims

1. An aircraft mechanical control system, characterized in that, include: The foot operating system (1) includes a left foot lever (105) and a right foot lever (106), which are rotatably mounted on the foot operating base (107); Foot pedals (108) are provided on the left foot lever (105) and right foot lever (106); The upper end of the cylinder (110) is hinged to the foot pedal (108), and the lower end is hinged to the cylinder mounting base (112); The rudder control rocker arm (104) is connected to the foot operating system (1); The hand operating system (2) includes a left handle (201) and a right handle (202), wherein the left handle (201) and the right handle (202) are connected to the upright fixing seat (204) via the upright (203); The mixed control system includes a rudder system (3), an elevator system (4), and an aileron system (5). The foot operating system (1) is used to control the rudder system (3) via the movement of the foot pedal (108) through the rudder control rocker arm (104), and to control the aircraft brakes via the hydraulic cylinder (110). The hand operating system (2) is used to control the elevator system (4) and the aileron system (5) to achieve the take-off and landing and stable flight of the aircraft by moving the left handle (201) and / or the right handle (202).

2. The aircraft mechanical control system according to claim 1, characterized in that, The foot operating system (1) also includes a first rudder push-pull rod (113), the rudder control rocker arm (104) is connected to the first rudder push-pull rod (113), and the first rudder push-pull rod (113) is connected to the rudder system (3) of the hybrid control system.

3. The aircraft mechanical control system according to claim 2, characterized in that, The rudder system (3) includes a first rudder plate (302) and a second rudder plate (304). The first rudder push-pull rod (113) is connected to the first rudder plate (302). The first rudder plate (302) is connected to the second rudder plate (304) through the second rudder push-pull rod (303). The second rudder plate (304) is connected to the rudder (306) through the first flexible shaft (305).

4. The aircraft mechanical control system according to claim 1, characterized in that, The manual operating system (2) also includes a first elevator push-pull rod (211) and an aileron swivel plate (207), which are respectively connected to the elevator system (4) and the aileron system (5) of the hybrid control system.

5. The aircraft mechanical control system according to claim 4, characterized in that, The elevator system (4) includes a third reversing plate (402) and a fourth reversing plate (404). The first elevator push-pull rod (211) is connected to the third reversing plate (402). The third reversing plate (402) is connected to the fourth reversing plate (404) through the second elevator push-pull rod (403). The fourth reversing plate (404) is connected to the T-shaped control rocker arm (408) through the second flexible shaft (405), the steering plate (410), and the steering rod (411). The T-shaped control rocker arm (408) is connected to the elevator (406).

6. The aircraft mechanical control system according to claim 4, characterized in that, The aileron system (5) includes a fifth swivel plate (502) and a sixth swivel plate (504). The aileron swivel plate (207) is connected to the fifth swivel plate (502) via a third flexible shaft (505). The fifth swivel plate (502) is connected to the sixth swivel plate (504) via a first aileron push-pull rod (503). The sixth swivel plate (504) is connected to the third aileron push-pull rod (511) via a second aileron push-pull rod (508) and a seventh swivel plate (509). The third aileron push-pull rod (511) is connected to the aileron rudder (507).

7. The aircraft mechanical control system according to claim 1, characterized in that, The foot operating system (1) also includes a handbrake handle (119) for locking the oil pressure of the hydraulic cylinder (110).

8. The aircraft mechanical control system according to claim 1, characterized in that, The hand operating system (2) also includes a synchronization rod (212), which connects the pole fixing seat (204) and the aileron reversing plate (207) to realize the synchronous control of the left handle (201) and the right handle (202).

9. The aircraft mechanical control system according to claim 1, characterized in that, The left foot lever (105) and the right foot lever (106) are connected by a linkage gear (115) to achieve synchronous reverse movement.

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