A main auxiliary linkage, brake independent, two-seat aircraft rudder simulation structure
The mechanical linkage of the rudder of a two-seat aircraft is achieved through intra-group and inter-group linkages, integrating independent braking functions and simulated force sensing. This solves the problems of complex linkage mechanisms and lack of braking functions in existing technologies, and improves the realism and accuracy of flight simulation.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- SHANGHAI UNIV OF ENG SCI
- Filing Date
- 2026-04-09
- Publication Date
- 2026-06-12
AI Technical Summary
Existing simulation structures for the rudder of two-seat aircraft suffer from complex linkage mechanisms, difficult installation and debugging, lack of force simulation, and inability to realistically simulate independent control of left and right foot brakes.
Mechanical linkage is achieved by using intra-group and inter-group linkages, integrating independent braking function, and providing a realistic operating feel by combining simulated lever unit. The operating quantity and braking signal are sensed by rudder potentiometer.
It achieves reliable linkage of the rudder of a two-seat aircraft, realistically simulates the feel of operation and braking function, improves the realism and accuracy of flight simulation, and reduces manufacturing costs.
Smart Images
Figure CN122201090A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of flight simulator technology, and more specifically, to a rudder simulation structure for a flight simulator, particularly a rudder simulation structure for a two-seat aircraft that enables linkage between the left and right seats and independent control of the left and right foot braking functions. Background Technology
[0002] In flight simulation training, the rudder system is a key component for pilots to control the aircraft's yaw attitude. For flight simulators with two seats (such as trainer aircraft) or multiple crews, it is usually necessary to set up two sets of rudder pedals, one for the front seat (instructor / captain) and one for the rear seat (student / first officer).
[0003] Existing two-seat aircraft rudder simulation structures often employ complex linkage mechanisms or electronic signal coupling methods to achieve linkage between the left and right seat pedals. However, these structures have the following shortcomings: First, the linkage mechanism is complex, difficult to install and debug, and prone to gaps and loosening, affecting the realism of the foot feel and the accuracy of the simulation; second, there is a lack of effective force simulation during linkage, making it impossible to realistically reproduce the drag and self-centering feel of the aircraft rudder under airflow; third, and more importantly, in real aircraft (such as some trainer aircraft or general aviation aircraft), the rudder pedals integrate braking functions, and the left and right foot brakes are independently controlled, while existing simulation structures often simplify or ignore this function, or use a single brake master cylinder, failing to simulate the real flight training scenario of independent braking of the left and right wheels.
[0004] Therefore, how to provide a simulation structure that is compact, reliable in linkage, can realistically simulate the feel of rudder operation in a two-seat aircraft, and has independent braking function is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention
[0005] The present invention aims to solve at least one of the above-mentioned problems in the prior art, and provides a two-seat aircraft rudder simulation structure with reliable left and right linkage, independent braking function, and realistic force simulation.
[0006] To achieve the aforementioned technical objective, the technical solution adopted by the present invention is as follows:
[0007] A simulation structure for a two-seat aircraft rudder with primary and secondary linkage and independent braking includes a rudder mounting floor. Two sets of rudders, primary and secondary, are mounted on the mounting floor. Each rudder set includes two pedal structures, left and right, each capable of sliding left and right on the mounting floor. The mounting floor also includes a left-right potentiometer, two intra-group linkages, and one inter-group linkage. Each pedal structure includes a rudder stick, a control surface, a torsion spring, a rudder potentiometer, a slider, and a multi-functional connecting plate. The lower end of the rudder stick is fixedly connected to the slider, and the upper end is hinged to the control surface. One end of the torsion spring is connected to the control surface, and the other end is connected to the upper end of the rudder stick. The rudder potentiometer is mounted on the rudder stick to sense the rotation angle between the control surface and the rudder stick. One end of the multi-functional connecting plate is fixedly mounted on the rudder stick. The slider is slidably mounted on the rudder mounting floor. The left-right potentiometer senses the left and right positions of the pedal structures. The intra-group linkage includes an intra-group central shaft and an intra-group linkage rod. The middle position of the moving rod is fixed on the central axis of the group rod. The central axis of the group rod is rotatably positioned on the rudder mounting floor and located between the two pedal structures in the same group of rudders. The two ends of the group linkage rod are respectively hinged to the multi-functional connecting plates of the two pedal structures in the same group of rudders, so that one pedal structure in the same group of rudders moves forward and the other pedal structure is forced to move backward. The inter-group linkage includes the inter-group rod central axis and the inter-group linkage rod. The middle position of the inter-group linkage rod is fixed on the inter-group rod central axis. The inter-group rod central axis is rotatably positioned on the rudder mounting floor and located between the two groups of rudders. The left end of the inter-group linkage rod is hinged to the multi-functional connecting plate of the right pedal structure in the left rudder and the right end is hinged to the multi-functional connecting plate of the left pedal structure in the right rudder, so that the pedal structures on the same side in the two rudders move forward and backward together. The rudder potentiometer and the left and right potentiometers can be connected to the signals of the external simulation analysis equipment respectively.
[0008] To optimize the technical solution, further measures include:
[0009] A rudder potentiometer mounting plate is fixedly installed on the rudder stock, and the rudder potentiometer is fixedly installed on the rudder potentiometer mounting plate.
[0010] According to the claim, a simulation structure for a two-seat aircraft rudder with main and auxiliary linkage and independent braking is characterized in that: the pedal structure further includes a brake linkage, one end of which is hinged to the control surface, and the other end is slidably connected to the control stick; a control potentiometer is used to sense the position of the other end of the brake linkage to generate a braking signal.
[0011] The pedal structure also includes a brake limiting plate, which is hinged in the middle to the upper part of the rudder stick. The upper end is hinged to the rudder surface, and the lower end is movably installed in an arc-shaped limiting groove in the middle of the rudder stick via a pin. The two ends of the arc-shaped limiting groove can limit the rotation angle of the brake limiting plate, thereby limiting the rudder surface.
[0012] The rudder mounting base is equipped with a left and right potentiometer bracket, and the left and right potentiometers are fixedly installed in the left and right potentiometer bracket.
[0013] The rudder mounting base has four sliding rails extending in the left and right directions, and the slider is slidably installed in the corresponding sliding rail.
[0014] Both ends of the intra-group linkage rod and the inter-group linkage rod are provided with left-right oriented strip grooves. The multi-functional connecting plate is hinged to the intra-group linkage rod and the inter-group linkage rod by means of hinge bolts passing through the strip grooves.
[0015] A simulated lever unit is also installed on the rudder mounting base. The simulated lever unit includes a front rocker arm structure, a rear rocker arm structure, a cam, and a tension spring. The cam is fixedly mounted on the inter-group linkage. The front and rear rocker arm structures are respectively located on the left and right sides of the central axis of the inter-group linkage. The front and rear rocker arm structures have the same structure, both including: a rocker arm seat, a rocker arm, and a rocker arm bearing. The rocker arm seat is fixed on the rudder mounting base. One end of the rocker arm is rotatably mounted on the rocker arm seat, and the other end is rotatably connected to the central axis of the rocker arm bearing. The outer surface of the rocker arm bearing of the front rocker arm structure abuts against the front side of the cam, and the outer surface of the rocker arm bearing of the rear rocker arm structure abuts against the rear side of the cam. The two ends of the tension spring are respectively mounted on the corresponding rocker arm bearings. The tension spring provides simulated force for the rotation of the inter-group linkage through the front and rear rocker arm structures and the cam. The magnitude and trend of this simulated force are set to be similar to or the same as the operating force when the real rudder pedal moves left and right by adjusting the elastic coefficient of the tension spring.
[0016] The central shafts of the inner and outer rods are rotatably mounted on the rudder mounting floor via connecting bearings.
[0017] Compared with the prior art, the beneficial effects of the present invention are as follows:
[0018] First, this invention cleverly achieves mechanical linkage of the rudder in a two-seat aircraft by setting up intra-group and inter-group linkages. The intra-group linkage ensures a seesaw-like linkage between the left and right pedals of the same seat, while the inter-group linkage achieves synchronous advance and retreat of the pedals on the same side of the left and right seats by cross-connecting the pedals on opposite sides of the two rudder groups. This purely mechanical linkage structure is simple and reliable, has no electronic delay, and can realistically reproduce the operating logic of the aircraft rudder.
[0019] Secondly, the pedal structure of this invention integrates independent braking function. Through the cooperation of the control surfaces, control stick, torsion spring, brake linkage, and control potentiometer, the pilot can independently control the left and right brakes by pressing the control surfaces. The torsion spring provides the control surface return force, and the control potentiometer accurately senses the braking stroke, providing independent braking signals to the simulation software, which can realistically simulate the complex operation scenario of independent braking of the left and right wheels of an aircraft.
[0020] Third, this invention provides a realistic feel simulation for rudder operation by setting up a simulated lever unit. When the pilot depresses the pedal to rotate the inter-group linkage, the cam fixed on it pushes the front or rear rocker arm, thereby stretching the tension spring. The tension generated by the spring is fed back to the pedal through the cam and linkage mechanism, simulating the aerodynamic load and self-centering force experienced by the rudder of a real aircraft when it deflects. By adjusting the spring constant, the operating feel of different aircraft models can be precisely matched, greatly improving the realism of flight simulation.
[0021] Fourth, the invention features a compact structure and a rational layout. All functional modules are integrated into the rudder mounting base, facilitating overall installation and maintenance. The cooperation between the slider and the slide rail ensures smooth left and right movement of the pedals. Each hinge point employs a bearing and slot design, ensuring both flexibility of movement and providing necessary installation and adjustment margins, thus reducing the requirements for machining and assembly precision.
[0022] Fifth, while achieving a highly realistic operating experience, this invention simplifies the structure, reduces electronic components, and adopts a modular design, thereby comprehensively reducing manufacturing, development, and maintenance costs. It is particularly suitable for large-scale application by flight simulation training institutions with limited budgets but a pursuit of high simulation accuracy. Attached Figure Description
[0023] Figure 1 This is a schematic diagram of the structure of the present invention;
[0024] Figure 2 for Figure 1 AA cross-section view;
[0025] Figure 3 for Figure 2 BB cross-section;
[0026] Figure 4 A detailed diagram of the pedal structure;
[0027] Figure 5 This is a perspective view of the present invention.
[0028] The attached diagram is labeled as follows: 1-Rudder mounting base; 11-Slide rail; 2-Pedal structure; 21-Rudder stick; 22-Rudder surface; 23-Torsion spring; 24-Rudder potentiometer; 25-Slider; 26-Multi-functional connecting plate; 27-Rudder potentiometer mounting plate; 28-Brake linkage; 29-Brake limit plate; 3-Left and right potentiometer; 31-Left and right potentiometer bracket; 4-Intra-group linkage; 41-Intra-group rod central axis; 42-Intra-group linkage rod; 5-Inter-group linkage; 51-Inter-group rod central axis; 52-Inter-group linkage rod; 6-Simulated force bar unit; 61-Cam; 62-Tension spring; 63-Rock arm seat; 64-Rock arm; 65-Rock arm bearing. Detailed Implementation
[0029] To make the objectives, technical solutions, and advantages of this application clearer, the application is described and illustrated below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments provided in this application without inventive effort are within the scope of protection of this application.
[0030] Obviously, the accompanying drawings described below are merely some examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without any inventive effort. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, any changes to design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as insufficient disclosure of the content of this application.
[0031] Please see Figure 1 and Figure 5 This invention provides a simulated rudder structure for a two-seat aircraft with a linked main and co-pilot configuration and independent braking. It mainly includes a square rudder mounting floor 1 as the mounting base. Two sets of rudders are mounted on the rudder mounting floor 1: one for the pilot's seat and the other for the co-pilot's seat. Each rudder set consists of two independent pedal structures 2, for a total of four pedal structures 2, corresponding to the pilot's left foot, pilot's right foot, co-pilot's left foot, and co-pilot's right foot, respectively. Each pedal structure 2 is configured to slide along the left-right direction of the rudder mounting floor 1.
[0032] To enable the sliding installation of the pedal structure 2, four parallel slide rails 11 extending in the left-right direction are fixedly installed on the rudder mounting base 1. Each pedal structure 2 has a slider 25 fixedly connected to its bottom. The slider 25 is slidably installed in the corresponding slide rail 11, thereby guiding the pedal structure 2 to slide smoothly in a straight line, reducing friction and shaking, and improving the operating feel.
[0033] To achieve linkage between the left and right pedal structures 2 within the same group, this invention provides two intra-group linkages 4. Each intra-group linkage 4 corresponds to a set of rudders and is installed between the two pedal structures 2 of that set of rudders. Specifically, the intra-group linkage 4 includes an intra-group rod central axis 41 rotatably mounted on the rudder mounting floor 1, and an intra-group linkage rod 42. The middle position of the intra-group linkage rod 42 is fixedly connected to the intra-group rod central axis 41, allowing the intra-group linkage rod 42 to rotate together with the intra-group rod central axis 41. The two ends of the intra-group linkage rod 42 are respectively hinged to the multi-functional connecting plates 26 of the left and right pedal structures 2. When the pilot depresses the left pedal and slides it forward, the multi-functional connecting plate 26 of the left pedal pulls the left end of the intra-group linkage rod 42 forward, causing the intra-group linkage rod 42 to rotate around the intra-group rod central axis 41, while its right end is forced to move backward, thereby pushing the right pedal structure 2 to slide backward. The reverse is also true. This achieves a seesaw-like linkage between the left and right pedals of the same seat, which conforms to the operational logic of the left and right rudder pedals moving in opposite directions in a real aircraft.
[0034] To achieve linkage between the left and right rudder sets, this invention includes an inter-set linkage 5. The inter-set linkage 5 is installed between the two rudder sets. The inter-set linkage 5 includes an inter-set rod central axis 51 rotatably mounted on the rudder mounting floor 1, and an inter-set linkage rod 52. The middle position of the inter-set linkage rod 52 is fixedly connected to the inter-set rod central axis 51. Unlike intra-set linkages, the two ends of the inter-set linkage rod 52 are not connected to the two pedals within the same set, but rather in a cross-connection manner: its left end is hinged to the multi-functional connecting plate 26 of the right pedal structure 2 in the left rudder, and its right end is hinged to the multi-functional connecting plate 26 of the left pedal structure 2 in the right rudder. When the right pedal of the driver's seat is pressed down and slides forward, it pulls the left end of the inter-set linkage rod 52 forward, causing the inter-set linkage rod 52 to rotate around the inter-set rod central axis 51, while its right end moves backward, pulling the left pedal of the passenger seat backward. Due to the action of the interlocking mechanism 4, sliding the left pedal of the passenger seat backward forces the right pedal of the passenger seat to slide forward. The final effect is that the right pedals of the driver's seat and the right pedal of the passenger seat move forward simultaneously, while the left pedals of the driver's seat and the left pedal of the passenger seat move backward simultaneously, achieving synchronous linkage of the pedals on the same side of the driver and passenger seats.
[0035] To achieve the braking function of the pedal structure 2, each pedal structure 2 mainly includes a rudder stick 21, a rudder surface 22, a torsion spring 23, a rudder potentiometer 24, a slider 25, and a multi-functional connecting plate 26.
[0036] The rudder stick 21 is a roughly L-shaped or straight rod-shaped structure, with its lower end fixedly connected to the slider 25, thus mounting the rudder stick 21 onto the slide rail 11. The control surface 22 is the part that the pilot presses with their foot; its lower end is hinged to the upper end of the rudder stick 21 via a hinge axis, allowing the control surface 22 to rotate relative to the rudder stick 21 around this hinge axis. This rotation represents the braking operation. A torsion spring 23 is fitted onto this hinge axis, with one end connected to the control surface 22 and the other end connected to the upper end of the rudder stick 21. The torsion spring 23 always applies a force to the control surface 22 to return it to its initial position (i.e., the unpressed state), simulating the rebound force of the brake pedal.
[0037] The multi-functional connecting plate 26 is a key component. One end is fixedly mounted on the rudder 21, while the other end is used to hinge with the intra-group linkage 42 or inter-group linkage 52. Therefore, the multi-functional connecting plate 26 serves both as an interface for transmitting the left and right movement power of the pedal and as a base for transmitting braking action.
[0038] The rudder potentiometer 24 is mounted on the rudder stock 21 and is used to sense the travel of the brake operation. For ease of installation and adjustment, a rudder potentiometer mounting plate 27 is fixedly provided on the rudder stock 21, and the rudder potentiometer 24 is fixedly mounted on the rudder potentiometer mounting plate 27.
[0039] In a further preferred embodiment, to transmit braking action more precisely, the pedal structure 2 also includes a brake linkage 28. One end of the brake linkage 28 is hinged to the middle or upper part of the control surface 22, and the other end is slidably connected to the rudder stick 21. When the pilot depresses the control surface 22, the control surface 22 rotates about its hinge point with the rudder stick 21, causing one end of the brake linkage 28 to move. Since the other end of the brake linkage 28 is restricted to sliding on the rudder stick 21, the brake linkage 28 converts the rotation of the control surface 22 into a sliding motion along the rudder stick 21. The sensing end of the rudder potentiometer 24 is associated with this sliding end of the brake linkage 28, thereby enabling precise sensing of the position of the brake linkage 28 and generating an electrical signal proportional to the brake pedal travel, which represents the braking amount.
[0040] In another preferred embodiment, to ensure a reasonable range of braking travel and protect the mechanism, the pedal structure 2 is further provided with a brake limiting plate 29. The brake limiting plate 29 is approximately triangular, with its middle section hinged to the upper part of the rudder stalk 21, its upper end hinged to the back of the rudder surface 22, and its lower end movably mounted in an arc-shaped limiting groove in the middle of the rudder stalk 21 via a pin. When the rudder surface 22 rotates, the brake limiting plate 29 moves accordingly, and its lower pin slides within the arc-shaped limiting groove. The two ends of the arc-shaped limiting groove form a physical stop; when the pin slides to either end of the groove, further rotation of the brake limiting plate 29 is restricted, thereby limiting the maximum and minimum rotation angles of the rudder surface 22, thus providing a limiting and protective function.
[0041] To collect the rudder input, a left-right potentiometer 3 is installed on the rudder mounting base 1. Preferably, the left-right potentiometer 3 is fixedly mounted using a left-right potentiometer bracket 31. The sensing end of the left-right potentiometer 3 is associated with the moving part of the pedal structure 2, and is used to sense the left-right displacement of the pedal structure 2 in real time, which corresponds to the rudder deflection angle. The electrical signals generated by the rudder potentiometer 24 and the left-right potentiometer 3 can be connected to an external flight simulation computer or data acquisition equipment via cables for processing by the simulation software.
[0042] To improve the adaptability of the linkage mechanism and eliminate the risk of jamming, the ends of the intra-group linkage rod 42 and the inter-group linkage rod 52 are not provided with round holes, but with elongated slots extending in the left and right directions. The multi-functional connecting plate 26 is connected to the linkage rod by hinge bolts, which pass through the slots. This design allows for a certain amount of floating allowance in the left and right directions at the connection point between the multi-functional connecting plate 26 and the linkage rod during assembly and movement, thereby compensating for machining and assembly errors and ensuring the smoothness of the mechanism's movement.
[0043] To simulate the force feel during real rudder operation, including damping and self-centering sensations, the present invention preferably includes a simulated force bar unit 6. The simulated force bar unit 6 is mounted on the rudder mounting base 1 and associated with the inter-group linkage 5. The simulated force bar unit 6 includes a cam 61, a tension spring 62, and identical front and rear rocker arm structures. The cam 61 is fixedly mounted on the inter-group linkage rod 52, or may be fixedly connected to the central axis 51 of the inter-group linkage rod, and rotates together with the inter-group linkage rod 52. The front and rear rocker arm structures are respectively located on the left and right sides of the central axis 51 of the inter-group linkage rod. Each rocker arm structure includes a rocker arm seat 63 fixed on the rudder mounting base 1, a rocker arm 64 rotatably mounted on the rocker arm seat 63 at one end, and a rocker arm bearing 65 mounted on the other end of the rocker arm 64. The outer peripheral surface of the rocker arm bearing 65 of the front rocker arm structure abuts against the front side of the cam 61, and the outer peripheral surface of the rocker arm bearing 65 of the rear rocker arm structure abuts against the rear side of the cam 61. The two ends of the tension spring 62 are respectively connected to the shaft of the rocker arm bearing 65 or the rocker arm 64 of the front rocker arm structure and the rear rocker arm structure.
[0044] When the pilot depresses the pedal, causing the inter-group linkage 52 to rotate, the cam 61 fixed to it also rotates. The front side of the cam 61 pushes forward the rocker arm bearing 65 of the front rocker arm structure, causing the rocker arm 64 of the front rocker arm to swing forward. Since the tension spring 62 connects the left and right rocker arms, the swing of the front rocker arm stretches the tension spring 62. The stretched tension spring 62 generates a contracting force, which acts on the rear side of the cam 61 through the rear rocker arm, forming a torque that prevents the cam 61 from rotating further. This torque is ultimately fed back to the pedal through the linkage mechanism, becoming the "resistance" that the pilot needs to overcome. When the pilot releases the pedal, the contracting force of the tension spring 62 drives the entire mechanism to move in the opposite direction, returning the pedal to the neutral position. By carefully designing and adjusting the elastic coefficient of the tension spring 62, the magnitude and variation curve of this simulated force can be made similar to or exactly the same as the feel of operating the rudder of a specific model of real aircraft, thus providing a highly realistic simulation experience.
[0045] Finally, to ensure the flexibility and durability of each rotating shaft, the inner rod shaft 41 and the inter-group rod shaft 51 are preferably rotatably mounted in bearing seats provided on the rudder mounting floor 1 by means of rolling bearings or sliding bearings.
[0046] In summary, this invention provides a cleverly designed, fully functional, and highly realistic two-seat aircraft rudder simulation structure. It not only reliably achieves rudder linkage between the left and right seats through purely mechanical means, but also independently simulates the braking functions of the left and right feet, and is equipped with a realistic force simulation system, which can greatly enhance the training effect and immersion of flight simulators.
[0047] The embodiments described are preferred embodiments of the present invention, but the embodiments of the present invention are not limited to the embodiments described. Any changes, modifications, substitutions, combinations, or simplifications made without departing from the spirit and principle of the present invention shall be considered equivalent substitutions and shall be included within the protection scope of the present invention.
Claims
1. A simulated rudder structure for a two-seat aircraft with primary and secondary linkage and independent braking, comprising a rudder mounting floor (1), wherein primary and secondary rudders are mounted on the rudder mounting floor (1), each rudder set including left and right pedal structures (2), each pedal structure (2) being able to slide left and right on the rudder mounting floor (1), characterized in that: The rudder mounting base (1) is also equipped with a left-right potentiometer (3), two intra-group linkages (4), and an inter-group linkage (5). Each pedal structure (2) includes a rudder stick (21), a rudder surface (22), a torsion spring (23), a rudder potentiometer (24), a slider (25), and a multi-functional connecting plate (26). The lower end of the rudder stick (21) is fixedly connected to the slider (25), and the upper end is hinged to the rudder surface (22). One end of the torsion spring (23) is connected to the rudder surface (22), and the other end is connected to the upper end of the rudder stick (21). The rudder potentiometer (3) is also equipped with a left-right potentiometer (3), two intra-group linkages (4), and one inter-group linkage (5). 25) Installed on the rudder post (21) to sense the rotation angle between the rudder surface (22) and the rudder post (21). One end of the multi-functional connecting plate (26) is fixedly installed on the rudder post (21). The slider (25) is slidably installed on the rudder mounting base (1). The left and right potentiometer (3) is used to sense the left and right positions of the pedal structure (2). The internal linkage (4) includes the internal rod central shaft (41) and the internal linkage rod (42). The middle position of the internal linkage rod (42) is fixed on the internal rod central shaft (41). The central shaft (41) is rotatably mounted on the rudder mounting floor (1) and located between two pedal structures (2) in the same set of rudders. The two ends of the inter-group linkage rod (42) are respectively hinged to the multi-functional connecting plates (26) of the two pedal structures (2) in the same set of rudders, so that when one pedal structure (2) in the same set of rudders moves forward, the other pedal structure (2) is forced to move backward. The inter-group linkage (5) includes the inter-group rod central shaft (51) and the inter-group linkage rod (52), and the middle position of the inter-group linkage rod (52) is fixed at... On the central axis (51) of the inter-group rod, the central axis (51) of the inter-group rod is rotatably positioned on the rudder mounting floor (1) and located between the two rudders. The left end of the inter-group linkage rod (52) is hinged to the multi-functional connecting plate (26) of the right pedal structure (2) in the left rudder, and the right end is hinged to the multi-functional connecting plate (26) of the left pedal structure (2) in the right rudder, so that the pedal structures (2) on the same side in the two rudders move forward and backward together. The rudder potentiometer (24) and the left and right potentiometers (3) can be connected to the signal of the external simulation analysis equipment respectively.
2. The rudder simulation structure for a two-seat aircraft with primary and secondary linkage and independent braking as described in claim 1, characterized in that: A rudder potentiometer mounting plate (27) is fixedly installed on the rudder stick (21), and the rudder potentiometer (24) is fixedly installed on the rudder potentiometer mounting plate (27).
3. The rudder simulation structure for a two-seat aircraft with primary and secondary linkage and independent braking as described in claim 2, characterized in that: The pedal structure (2) also includes a brake linkage (28), one end of which is hinged to the rudder surface (22) and the other end is slidably connected to the rudder stick (21). The rudder potentiometer (24) is used to sense the position of the other end of the brake linkage (28) to generate a brake signal.
4. The rudder simulation structure for a two-seat aircraft with primary and secondary linkage and independent braking as described in claim 1, characterized in that: The pedal structure (2) also includes a brake limiting plate (29). The brake limiting plate (29) is hinged to the upper part of the rudder stick (21) in the middle, and the upper end is hinged to the rudder surface (22). The lower end is movably installed in an arc-shaped limiting groove in the middle of the rudder stick (21) through a pin. The two ends of the arc-shaped limiting groove can limit the rotation angle of the brake limiting plate (29), thereby limiting the rudder surface (22).
5. A simulation structure for a two-seat aircraft rudder with primary and secondary linkage and independent braking as described in claim 1, characterized in that: The rudder mounting base (1) is equipped with a left-right potentiometer bracket (31), and the left-right potentiometer (3) is fixedly installed in the left-right potentiometer bracket (31).
6. The rudder simulation structure for a two-seat aircraft with primary and secondary linkage and independent braking as described in claim 1, characterized in that: The rudder mounting base (1) is provided with four slide rails (11) extending in the left and right directions, and the slider (25) is slidably installed in the corresponding slide rail (11).
7. The rudder simulation structure for a two-seat aircraft with primary and secondary linkage and independent braking as described in claim 1, characterized in that: Both ends of the intra-group linkage rod (42) and inter-group linkage rod (52) are provided with left-right oriented strip grooves. The multi-functional connecting plate (26) is hinged to the intra-group linkage rod (42) and the inter-group linkage rod (52) by means of hinge bolts passing through the strip grooves.
8. A simulation structure for a two-seat aircraft rudder with primary and secondary linkage and independent braking as described in claim 1, characterized in that: The rudder mounting base (1) is also equipped with a simulated force bar unit (6). The simulated force bar unit (6) includes a front rocker arm structure, a rear rocker arm structure, a cam (61), and a tension spring (62). The cam (61) is fixedly mounted on the inter-group linkage rod (52). The front rocker arm structure and the rear rocker arm structure are respectively located on the left and right sides of the central axis (51) of the inter-group linkage rod. The front rocker arm structure and the rear rocker arm structure have the same structure, both including: a rocker arm seat (63), a rocker arm (64), and a rocker arm bearing (65). The rocker arm seat (63) is fixed on the rudder mounting base (1), and one end of the rocker arm (64) is rotatably mounted on the rocker arm seat (63). On one end, the other end is rotatably connected to the central shaft of the rocker arm bearing (65). The outer surface of the rocker arm bearing (65) of the front rocker arm structure abuts against the front side of the cam (61), and the outer surface of the rocker arm bearing (65) of the rear rocker arm structure abuts against the rear side of the cam (61). The two ends of the tension spring (62) are respectively installed on the corresponding rocker arm bearing (65). The tension spring (62) provides a simulated force for the rotation of the inter-group linkage rod (52) through the front and rear rocker arm structures and the cam (61). The magnitude and trend of this simulated force are set to be similar to or the same as the operating force when the real rudder pedal moves left and right by adjusting the elastic coefficient of the tension spring (62).
9. A simulation structure for a two-seat aircraft rudder with primary and secondary linkage and independent braking as described in claim 1, characterized in that: The central shaft (41) of the inner group rod and the central shaft (51) of the inter-group rod are rotatably mounted on the rudder mounting floor (1) via connecting bearings.