Rotor control device of simulator

Abstract

The utility model provides a rotor control device of an analog machine. The rotor control device comprises a periodic variable pitch control part, a total propeller pitch control part, a transverse control line system, a longitudinal control line system, a total propeller pitch control line system, a first transverse servo mechanism, a longitudinal servo mechanism, a second transverse servo mechanism and an automatic inclinator, the periodic variable-pitch control part is connected with the first transverse servo mechanism and the second transverse servo mechanism through a transverse control line system, and meanwhile, the periodic variable-pitch control part is connected with the longitudinal servo mechanism through a longitudinal control line system; the total propeller pitch control part is connected with the transverse control line system through the total propeller pitch control line system; the automatic inclinator is arranged on a rotor hub, and the first transverse servo mechanism, the longitudinal servo mechanism and the second transverse servo mechanism are connected with a point A, a point B and a point C of the automatic inclinator respectively. Through the synergistic effect of the components, lift force control over the rotor wings is jointly achieved, the sense of reality of simulated flight is improved, and the training effect is good.

Description

TECHNICAL FIELD

[0001] The utility model relates to helicopter teaching technical field especially is related to a rotor control device of simulator. BACKGROUND

[0002] Traditional helicopter flight training usually relies on real helicopters. However, the operation of real helicopters has high risk, has safety hazards, and has high maintenance cost. Therefore, it is particularly important to develop an economical, simple-to-operate simulator that can simulate the flight characteristics of a helicopter.

[0003] In the design of the simulator, the rotor control device is one of the core parts, which is responsible for simulating the control of the rotor of the helicopter, and directly affects the realism of the simulated flight and the training effect.

[0004] At present, the existing rotor control devices have the following technical problems: for example, the structure of some rotor control devices is complex, and the operation is cumbersome, which is not conducive to the rapid operation and mastery of students; some rotor control devices have simple structure, but the simulation effect is poor, and the control characteristics of the rotor of the helicopter cannot be accurately reflected.

[0005] Therefore, how to design a rotor control device with simple structure, simple operation and accurate simulation of the control characteristics of the rotor of the helicopter has become a problem to be solved at present.

[0006] Therefore, the utility model is provided. CONTENT OF THE UTILITY MODEL

[0007] In order to solve the above technical problems, the purpose of the utility model is to provide a rotor control device of a simulator. The technical effects produced by the preferred technical solutions in the many technical solutions provided by the utility model are described below.

[0008] To achieve the above purpose, the utility model provides the following technical solutions:

[0009] The rotor control device of the simulator provided by the utility model comprises a cyclic pitch control part, a collective pitch control part, a lateral control line system, a longitudinal control line system, a collective pitch control line system, a first lateral servo mechanism, a longitudinal servo mechanism, a second lateral servo mechanism and an automatic tilt device. The cyclic pitch control part is connected with the first lateral servo mechanism and the second lateral servo mechanism through the lateral control line system, and at the same time, the cyclic pitch control part is connected with the longitudinal servo mechanism through the longitudinal control line system. The collective pitch control part is connected with the lateral control line system through the collective pitch control line system. The automatic tilt device is arranged on a rotor hub, and the first lateral servo mechanism, the longitudinal servo mechanism and the second lateral servo mechanism are connected with point A, point B and point C of the automatic tilt device respectively.

[0010] Preferably, the total pitch control part comprises a main pilot total pitch control lever and a copilot total pitch control lever, and the main pilot total pitch control lever and the copilot total pitch control lever are connected through a total pitch torsion shaft; the total pitch control line system comprises a total pitch control connecting rod, a first total pitch compound rocker assembly and a second total pitch compound rocker assembly, and two ends of the total pitch torsion shaft are connected with the first total pitch compound rocker assembly and the second total pitch compound rocker assembly through the total pitch control connecting rod respectively.

[0011] Preferably, the cyclic pitch control part comprises a main pilot cyclic pitch control lever and a copilot cyclic pitch control lever, and the main pilot cyclic pitch control lever and the copilot cyclic pitch control lever are connected through a cyclic pitch torsion shaft.

[0012] The lateral control line system comprises a first lateral compound rocker assembly, a second lateral compound rocker assembly, a first lateral rocker, a second lateral rocker and a lateral control connecting rod, and the main pilot cyclic pitch control lever is connected with the first lateral compound rocker assembly, the first lateral rocker and the first lateral servo mechanism through the lateral control connecting rod in sequence.

[0013] The copilot cyclic pitch control lever is connected with the second lateral compound rocker assembly, the second lateral rocker and the second lateral servo mechanism through the lateral control connecting rod in sequence.

[0014] Preferably, the first lateral rocker is connected with the first total pitch compound rocker assembly, and the second lateral rocker is connected with the second total pitch compound rocker assembly.

[0015] Preferably, the first lateral compound rocker assembly and the second lateral compound rocker assembly are connected through the lateral control connecting rod.

[0016] Preferably, the longitudinal control line system comprises a first longitudinal rocker, a second longitudinal rocker and a longitudinal control connecting rod, the first longitudinal rocker is arranged on the cyclic pitch torsion shaft, and the second longitudinal rocker is connected with the second total pitch compound rocker assembly through the longitudinal control connecting rod in sequence.

[0017] The preferred technical scheme of the utility model can at least produce the following technical effects:

[0018] The utility model provides a rotor control device of analog machine, including cyclic pitch control part, total pitch control part, lateral control line system, longitudinal control line system, total pitch control line system, first lateral servo mechanism, longitudinal servo mechanism, second lateral servo mechanism and automatic inclinometer, cyclic pitch control part is connected with first lateral servo mechanism and second lateral servo mechanism through lateral control line system respectively, simultaneously, cyclic pitch control part is connected with longitudinal servo mechanism through longitudinal control line system, total pitch control part is connected with lateral control line system through total pitch control line system respectively, automatic inclinometer sets up on rotor hub, first lateral servo mechanism, longitudinal servo mechanism and second lateral servo mechanism are connected with A point, B point and C point of automatic inclinometer respectively, the utility model discloses through the synergies of cyclic pitch control part, total pitch control part, lateral control line system, longitudinal control line system, total pitch control line system, first lateral servo mechanism, longitudinal servo mechanism, second lateral servo mechanism and automatic inclinometer, the lift control of rotor is realized in common, improves the real feeling of analog flight, and training effect is good.

[0019] Cyclic pitch control part makes the rotor blade angle of attack periodic change, controls the tilt angle of rotor disc, thereby controls the direction of lift. When cyclic pitch control part moves forward and backward, by controlling longitudinal control line system and longitudinal servo mechanism, the B point of automatic inclinometer is driven to move, so that the automatic inclinometer tilts around X axis to realize the movement of helicopter around pitch axis. For example, when cyclic pitch control part is pushed forward, the B point of automatic inclinometer moves downward, and the A point and C point remain unchanged, and the result of periodic change of rotor blade angle of attack makes the rotor disc tilt forward. When cyclic pitch control part moves left and right, by controlling two lateral control line systems and corresponding first lateral servo mechanism and second lateral servo mechanism, the A point and C point of automatic inclinometer move reversely, so that the automatic inclinometer tilts around Y axis to realize the movement of helicopter around roll axis. For example, cyclic pitch control part is pushed rightward, so that the A point of automatic inclinometer moves downward, the C point moves upward, and the B point remains unchanged, and the result of periodic change of rotor blade angle of installation makes the rotor disc tilt rightward.

[0020] Total pitch control part changes the angle of attack of all rotor blades simultaneously, thereby changes the lift of rotor. When total pitch control part moves upward and downward, the A point, B point and C point of automatic inclinometer all move equally, and the automatic inclinometer moves parallelly, without affecting the periodic change of angle of attack. For example, total pitch control part is pulled upward, so that the A point, B point and C point of automatic inclinometer all move upward, and the total pitch of rotor increases. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical scheme in the embodiments of the present application or the prior art, the accompanying drawings required to be used in the following embodiment or prior art description will be briefly introduced. Obviously, the accompanying drawings in the following description only constitute some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0022] Figure 1 It is a structure schematic diagram of a rotor control device of a simulation machine provided by the present application.

[0023] Figure 2 It is a system principle diagram of a rotor control device of a simulation machine provided by the present application.

[0024] Figure 3 It is a working principle schematic diagram of an automatic tilting device of a rotor control device of a simulation machine provided by the present application.

[0025] Figure 4 It is a working principle diagram of a second total pitch rocker arm, a second connecting rocker arm and a second transverse rocker arm of a rotor control device of a simulation machine provided by the present application when a cyclic pitch control lever is rightward.

[0026] Figure 5 It is a working principle diagram of a second total pitch rocker arm, a third connecting rocker arm and a second longitudinal rocker arm of a rotor control device of a simulation machine provided by the present application when a cyclic pitch control lever is forward.

[0027] Figure 6 It is a working principle diagram of a second total pitch rocker arm, a third connecting rocker arm and a second longitudinal rocker arm of a rotor control device of a simulation machine provided by the present application when a total pitch control lever is upward.

[0028] In the drawings:

[0029] 1, cyclic pitch control part; 101, main pilot cyclic pitch control lever; 102, copilot cyclic pitch control lever; 103, cyclic pitch torsion shaft;

[0030] 2, total pitch control part; 201, main pilot total pitch control lever; 202, copilot total pitch control lever; 203, total pitch torsion shaft; 204, friction lock device;

[0031] 3, transverse control wire system; 301, first transverse compound rocker arm assembly; 302, second transverse compound rocker arm assembly; 303, first transverse rocker arm; 304, second transverse rocker arm; 305, transverse control connecting rod;

[0032] 4, longitudinal control wire system; 401, first longitudinal rocker arm; 402, second longitudinal rocker arm; 403, longitudinal control connecting rod;

[0033] 5. collective pitch control cable; 501. collective pitch control link; 502. first collective pitch bell crank; 503. first connecting bell crank; 504. first bell crank shaft; 505. second collective pitch bell crank; 506. second connecting bell crank; 507. third connecting bell crank; 508. second bell crank shaft;

[0034] 6. first lateral servo;

[0035] 7. longitudinal servo;

[0036] 8. second lateral servo;

[0037] 9. automatic tilt; 901. A point; 902. B point; 903. C point;

[0038] 10. roll axis; 11. pitch axis. DETAILED DESCRIPTION

[0039] In order to make the purpose, technical scheme and advantages of the utility model more clear, the technical scheme of the utility model will be described in detail below. Obviously, the described embodiment is only a part of the embodiment of the utility model, not all the embodiment. Based on the embodiment in the utility model, all other embodiments obtained by the ordinary skill in the art without making the creative labor belong to the range of the utility model.

[0040] As shown in Figures 1-5 The utility model provides a rotor control device of simulation machine, including cyclic pitch control part 1, collective pitch control part 2, lateral control cable 3, longitudinal control cable 4, collective pitch control cable 5, first lateral servo 6, longitudinal servo 7, second lateral servo 8 and automatic tilt 9, cyclic pitch control part 1 is connected with first lateral servo 6 and second lateral servo 8 through lateral control cable 3 respectively, simultaneously, cyclic pitch control part 1 is connected with longitudinal servo 7 through longitudinal control cable 4, collective pitch control part 2 is connected with lateral control cable 3 through collective pitch control cable 5 respectively, automatic tilt 9 is set up on rotor hub, and first lateral servo 6, longitudinal servo 7 and second lateral servo 8 are connected with A point 901, B point 902 and C point 903 of automatic tilt 9 respectively.

[0041] The utility model through cyclic pitch control part 1, collective pitch control part 2, lateral control cable 3, longitudinal control cable 4, collective pitch control cable 5, first lateral servo 6, longitudinal servo 7, second lateral servo 8 and the synergies of automatic tilt 9, the lift control of rotor is realized in common, improves the real feeling of simulation flight, and training effect is good.

[0042] The cyclic pitch control 1 changes the angle of attack of the rotor blades periodically, and controls the tilt angle of the rotor disc, thereby controlling the direction of the lift. When the cyclic pitch control 1 is moved forward and backward, the B point 902 of the automatic tilt device 9 is driven to move by operating the longitudinal control wire system 4 and the longitudinal servo 7, and the automatic tilt device 9 is tilted around the X axis to realize the movement of the helicopter around the pitch axis 11. For example, when the cyclic pitch control 1 is pushed forward, the B point 902 of the automatic tilt device 9 moves downward, and the A point 901 and the C point 903 remain unchanged, and the angle of attack of the rotor blades changes periodically, so that the rotor disc tilts forward. When the cyclic pitch control 1 is moved left and right, the A point 901 and the C point 903 of the automatic tilt device 9 are driven to move in opposite directions by operating the two lateral control wire systems 3 and the corresponding first lateral servo 6 and second lateral servo 8, and the automatic tilt device 9 is tilted around the Y axis to realize the movement of the helicopter around the roll axis 10. For example, when the cyclic pitch control 1 is pushed to the right, the A point 901 of the automatic tilt device 9 moves downward, and the C point 903 moves upward by an equal distance, and the B point 902 remains unchanged, and the angle of installation of the rotor blades changes periodically, so that the rotor disc tilts to the right. Wherein, the X axis is determined by the mounting point of the two lateral servos, and the Y axis is determined by the mounting point of the longitudinal servo 7.

[0043] The collective pitch control 2 changes the angle of attack of all the rotor blades at the same time, thereby changing the size of the lift of the rotor. When the collective pitch control 2 is moved up and down, the A point 901, the B point 902 and the C point 903 of the automatic tilt device 9 are all driven to move by an equal amount by the collective pitch control wire system 5, and the automatic tilt device 9 moves upward or downward parallel to the initial position without affecting the periodic change of the angle of attack. For example, when the collective pitch control 2 is pulled upward, the A point 901, the B point 902 and the C point 903 of the automatic tilt device 9 all move upward, so that the total pitch of the rotor increases.

[0044] Wherein, as shown in Figure 2 The lift (Fn) includes two parts: a vertical component (S) and a horizontal component (V). By adjusting the cyclic pitch control 1, the tilt angle of the rotor disc, i.e. the tilt angle of the automatic tilt device 9, can be changed, so that the horizontal component (V) can be changed. At the same time, by adjusting the collective pitch control 2, the size of the lift of the rotor, i.e. the vertical component S, can be changed.

[0045] Further, the first lateral servo 6, the longitudinal servo 7 and the second lateral servo 8 are all approximately simulated by servo cylinders, and the stroke is 100 mm. The aforementioned servos adopt a parallel double control mode.

[0046] Sensors are arranged on the lateral control cable 3, the longitudinal control cable 4 and the collective pitch control cable 5 to detect the movement of the cyclic control part 1 and the collective pitch control part 2 and feed back to the computer (simulation software), and the computer (simulation software) calculates the actuating stroke and speed of the electric push rod of the aforementioned servo mechanism according to the control signals of the cyclic control part 1 and the collective pitch control part 2 and outputs signals to control the tilting and up-and-down sliding actions of the automatic tilting device 9.

[0047] The included angle between the point A 901 and the point B 902 and the included angle between the point B 902 and the point C 903 are both 90 degrees.

[0048] As an optional embodiment, the collective pitch control part 2 comprises a main pilot collective pitch control lever 201 and a co-pilot collective pitch control lever 202, and the main pilot collective pitch control lever 201 and the co-pilot collective pitch control lever 202 are connected through a collective pitch torsion shaft 203; the collective pitch control cable 5 comprises a collective pitch control connecting rod 501, a first collective pitch compound rocker arm assembly and a second collective pitch compound rocker arm assembly, and the two ends of the collective pitch torsion shaft 203 are connected with the first collective pitch compound rocker arm assembly and the second collective pitch compound rocker arm assembly through the collective pitch control connecting rod 501 respectively.

[0049] Further, torsional springs are arranged between the two ends of the collective pitch torsion shaft 203 and the main pilot collective pitch control lever 201 and the co-pilot collective pitch control lever 202 to provide a simulated force feeling.

[0050] The main pilot collective pitch control lever 201 and the co-pilot collective pitch control lever 202 are respectively provided with the friction lock device 204 in the prior art to provide a balance force not less than the weight of the corresponding collective pitch control lever, and the friction force can be adjusted.

[0051] The main pilot collective pitch control lever 201 and the co-pilot collective pitch control lever 202 are used to generate a vertical lift signal, and the stroke range of both is 150mm-200mm.

[0052] As an optional embodiment, the cyclic control part 1 comprises a main pilot cyclic control lever 101 and a co-pilot cyclic control lever 102, and the main pilot cyclic control lever 101 and the co-pilot cyclic control lever 102 are connected through a cyclic torsion shaft 103;

[0053] The lateral control cable 3 comprises a first lateral compound rocker arm assembly 301, a second lateral compound rocker arm assembly 302, a first lateral rocker arm 303, a second lateral rocker arm 304 and a lateral control connecting rod 305, and the main pilot cyclic control lever 101 is connected with the first lateral compound rocker arm assembly 301, the first lateral rocker arm 303 and the first lateral servo mechanism 6 in sequence through the lateral control connecting rod 305;

[0054] The co-pilot cyclic control lever 102 is connected to the second lateral compound rocker assembly 302, the second lateral rocker 304 and the second lateral servo 8 in sequence through the lateral control connecting rod 305.

[0055] The main driver cyclic control lever 101 and the co-pilot cyclic control lever 102 are used to generate front, rear, left and right signals. In longitudinal operation, both can be moved forward by 70mm and pulled back by 120mm, and the lever force varies with the stroke, with the maximum value ≯10N. In lateral operation, both can be moved left or right by 100mm, and similarly, the lateral lever force also varies with the stroke, with the maximum value ≯10N.

[0056] As an optional implementation, the first lateral rocker 303 is connected to the first total pitch compound rocker assembly, and the second lateral rocker 304 is connected to the second total pitch compound rocker assembly.

[0057] As an optional implementation, the first lateral compound rocker assembly 301 and the second lateral compound rocker assembly 302 are connected through the lateral control connecting rod 305.

[0058] As an optional implementation, the longitudinal control line system 4 includes a first longitudinal rocker 401, a second longitudinal rocker 402 and a longitudinal control connecting rod 403, the first longitudinal rocker 401 is arranged on the cyclic control torsion shaft 103 and is connected to the second longitudinal rocker 402 and the longitudinal servo 7 in sequence through the longitudinal control connecting rod 403, and the second longitudinal rocker 402 is connected to the second total pitch compound rocker assembly.

[0059] Further, the first total pitch compound rocker assembly includes a first total pitch rocker 502, a first connecting rocker 503 and a first rocker shaft 504 connecting the first total pitch rocker 502 and the first connecting rocker 503. The first lateral rocker 303 located at the junction of the lateral control line system 3 and the total pitch control line system 5 is connected to the first connecting rocker 503.

[0060] The second total pitch compound rocker assembly includes a second total pitch rocker 505, a second connecting rocker 506, a third connecting rocker 507 and a second rocker shaft 508 connecting the second total pitch rocker 505, the second connecting rocker 506 and the third connecting rocker 507, the second connecting rocker 506 is connected to the second lateral rocker 304, and the third connecting rocker 507 is connected to the second longitudinal rocker 402. The second lateral rocker 304 and the second longitudinal rocker 402 located at the junction of the lateral control line system 3 and the longitudinal control line system 4 and the total pitch control line system 5 are connected to the second connecting rocker 506 and the third connecting rocker 507 respectively.

[0061] Both ends of the total pitch torsion shaft 203 are connected to the first total pitch rocker 502 and the second total pitch rocker 505 through the total pitch control connecting rod 501 respectively.

[0062] At the junction of the lateral control line 3, the longitudinal control line 4 and the total pitch control line 5, due to the arrangement of the first total pitch compound rocker assembly and the second total pitch compound rocker assembly, each line can be independently controlled without interference. For example, when the main pilot total pitch control lever 201 or the co-pilot total pitch control lever 202 is controlled, the total pitch is increased or decreased, and the inclination angle of the automatic tilting device 9 is not affected, that is, the cyclic pitch control remains unchanged. When the main pilot cyclic pitch control lever 101 or the co-pilot cyclic pitch control lever 102 is controlled, the total pitch value is not affected, that is, the automatic tilting device 9 is tilted, but the center remains at the original height.

[0063] The total pitch control line 5 uses the lateral control line 3 and the longitudinal control line 4 after the first total pitch compound rocker assembly and the second total pitch compound rocker assembly. Moving the main pilot total pitch control lever 201 or the co-pilot total pitch control lever 202 causes the three servo mechanisms to move by the same displacement, driving the automatic tilting device 9 to translate.

[0064] As shown in Figure 3 , when the cyclic pitch control lever is moved right or left, the second lateral rocker 304 is rotated about the connecting shaft with the second connecting rocker 506 as the rotation axis, the second total pitch rocker 505 remains stationary, and the first lateral rocker 303 is reversely rotated.

[0065] As shown in Figure 4 , when the cyclic pitch control lever is moved forward or backward, the second longitudinal rocker 402 is rotated about the connecting shaft with the third connecting rocker 507 as the rotation axis, and the second total pitch rocker 505 remains stationary.

[0066] As shown in Figure 5 , when the total pitch control lever is moved up or down, the second total pitch rocker 505 is rotated, and the second lateral rocker 304 and the second longitudinal rocker 402 are driven to move by the same displacement through the second connecting rocker 506 and the third connecting rocker 507.

[0067] Similarly, the working principle of the first lateral rocker 303 and the first total pitch rocker 502 is the same as above. When the cyclic pitch control lever is moved left or right, the first lateral rocker 303 is rotated about the connecting shaft with the first connecting rocker 503 as the rotation axis, the first total pitch rocker 502 remains stationary, and the second lateral rocker 304 is reversely rotated. When the total pitch control lever is moved up or down, the first total pitch rocker 502 is rotated, and the first lateral rocker 303 is driven to move by the same displacement through the first connecting rocker 503.

[0068] The working principle of the utility model is:

[0069] When the main pilot collective control lever 201 or the co-pilot collective control lever 202 is operated, the collective torsion shaft 203 is rotated, and then the first collective torsion rocker arm 502 and the second collective torsion rocker arm 505 are rotated through the transverse control connecting rod 305, and then the first transverse rocker arm 303 and the second transverse rocker arm 304 and the second longitudinal rocker arm 402 are displaced by the same amount through the first collective torsion rocker arm 502 and the second collective torsion rocker arm 505, and then the first transverse servo mechanism 6, the longitudinal servo mechanism 7 and the second transverse servo mechanism 8 are transmitted through the transverse control line system 3 and the longitudinal control line system 4, and the A point 901, the B point 902 and the C point 903 of the automatic tilt device 9 are driven to move by the same amount, so that the automatic tilt device 9 moves upward or downward parallel to the initial position, thereby changing the collective pitch of the rotor.

[0070] When the main pilot cyclic control lever 101 or the co-pilot cyclic control lever 102 is moved left and right, the first transverse composite rocker arm assembly 301 or the second transverse composite rocker arm assembly 302 is transmitted through the transverse control connecting rod 305, and then the first transverse rocker arm 303 or the second transverse rocker arm 304 is transmitted, and then the first transverse servo mechanism 6 and the second transverse servo mechanism 8 are transmitted, respectively, and the A point 901 and the C point 903 of the automatic tilt device 9 are driven to move in opposite directions, thereby changing the disc tilt angle of the rotor.

[0071] When the main pilot cyclic control lever 101 or the co-pilot cyclic control lever 102 is moved forward and backward, the cyclic torsion shaft 103 is rotated, and then the first longitudinal rocker arm 401 is transmitted through the longitudinal control connecting rod 403, and then the second longitudinal rocker arm 402 is transmitted through the third connecting rocker arm 507 to move correspondingly, and then the longitudinal servo mechanism 7 is transmitted, and the B point 902 of the automatic tilt device 9 is driven to move, thereby changing the disc tilt angle of the rotor.

[0072] It can be understood that the same or similar parts in the above-mentioned embodiments can be mutually referred to, and the contents not described in detail in some embodiments can be referred to the same or similar contents in other embodiments.

[0073] In the description of the utility model, it needs to be explained that, unless otherwise stated, the meaning of "multiple" is two or more than two; the directions or position relations indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail" are based on the directions or position relations shown in the drawings, and are only for the convenience of describing the utility model and simplifying the description, and cannot be understood as indicating or implying that the devices or elements indicated must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the utility model. In addition, the terms "first", "second", "third" and the like are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0074] In the description of the utility model, need explanation further, unless have explicit provision and limit, term " install ", " link ", " connect " should do broad sense understanding, for example, can be fixed connection, also can be detachable connection, or integrally connect, can be mechanical connection, also can be electric connection, can be direct connection, also can pass through intermediate medium indirectly connect.

[0075] In the description of the utility model, the description of reference term " one embodiment ", " some embodiments ", " example ", " specific example " or " one example " etc. Means that the specific features, structure, material or characteristic described in conjunction with the embodiment or example is contained in at least one embodiment or example of the application. In the specification, the illustrative representation of the above-mentioned terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structure, material or characteristic described can be combined in any one or more embodiments or examples in a suitable manner.

[0076] The above is only a specific embodiment of the utility model, but the protection scope of the utility model is not limited to this, any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the utility model, which should be covered in the protection scope of the utility model. Therefore, the protection scope of the utility model should be subject to the protection scope of the claims.

Claims

1. A rotor control device for a simulator, characterized by comprising: The cyclic pitch control part is connected with the first and second lateral servo mechanisms through the lateral control line system, and is connected with the longitudinal servo mechanism through the longitudinal control line system.

2. A rotor control device for a simulator according to claim 1, wherein The collective pitch control part includes a main pilot collective pitch control lever and a copilot collective pitch control lever, and the two levers are connected through a collective pitch torsion shaft.

3. A rotor control device for a simulator as claimed in claim 2, wherein The cyclic pitch control part includes a main pilot cyclic pitch control lever and a copilot cyclic pitch control lever, and the two levers are connected through a cyclic pitch torsion shaft. The lateral control line system includes a first lateral composite rocker assembly, a second lateral composite rocker assembly, a first lateral rocker, a second lateral rocker and a lateral control connecting rod. The first lateral rocker is connected with the first collective pitch composite rocker assembly, and the second lateral rocker is connected with the second collective pitch composite rocker assembly.

4. A rotor control device for a simulator according to claim 3, wherein The first and second lateral composite rocker assemblies are connected through the lateral control connecting rod.

5. A rotor control device for a simulator as claimed in claim 4, wherein The longitudinal control line system includes a first longitudinal rocker, a second longitudinal rocker and a longitudinal control connecting rod.

6. A rotor control device for a simulator according to claim 5, wherein The first longitudinal rocker is arranged on the cyclic pitch torsion shaft and is connected with the second longitudinal rocker and the longitudinal servo mechanism through the longitudinal control connecting rod. The second longitudinal rocker is connected with the second collective pitch composite rocker assembly.

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