Flap control system and airplane

Abstract

The utility model discloses a flap control system and an airplane. The flap control system comprises a first torque tube, a second torque tube, a flap actuator, a driving rocker arm and a coupling connecting piece. The coupling connecting piece is provided with a first end, a second end and a connecting section arranged between the first end and the second end, and the first end and the second end are fixed to the first torque tube and the second torque tube respectively; one end of the driving rocker arm is fixed to the connecting section, the other end of the driving rocker arm is connected with the flap actuator, and when the flap actuator works, the driving rocker arm can be driven to rotate, and meanwhile the first torque tube and the second torque tube on the coupling connecting piece are driven to rotate synchronously. According to the scheme, the principle and the structure are simple, and the flap actuator can conveniently drive the left flap and the right flap of the aircraft to work. The flap control system provided by the utility model is used for replacing a complex synchronous cross-linking mechanism and electrical control, so that the flap control is not easy to make mistakes, and the control is more reliable.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation flight control, in particular to a flap control system and an aircraft. Background Art

[0002] The flap is installed on the trailing edge of the wing, and the flap control system is a mechanism that controls the flap to move backward and downward around the rotation axis. As an important aircraft onboard system, the flap control system's normal operation will affect the aircraft's safety, especially the left and right flaps must be operated synchronously. At the same time, the flight speed for flap release is limited to prevent excessive load from damaging the flap structure.

[0003] The existing flap control system achieves the synchronization of the left and right flaps through a flexible shaft, or through a steel cable cross-linking mechanism, or by using two independent flap actuators to drive the left and right flaps respectively, and then combining the electrical control program of the computing software to achieve the synchronization of the left and right flaps. The above solutions all make the principle of the flap control system too complicated and the failure rate of the flap control system is high when it is used. Utility Model Content

[0004] Aiming at the above problems, the utility model provides a flap control system and an aircraft.

[0005] The technical solution adopted by the utility model is as follows:

[0006] The present application provides a flap control system, comprising: a first torque tube, a second torque tube, a flap actuator, a driving rocker arm, and a coupling connector;

[0007] The coupling connector has a first end, a second end, and a connecting section disposed between the first end and the second end, the first end and the second end being fixed to the first torque tube and the second torque tube respectively;

[0008] One end of the driving rocker arm is fixed on the connecting section, and the other end of the driving rocker arm is connected to the flap actuator. When the flap actuator is working, it will drive the driving rocker arm to rotate, and at the same time drive the first torque tube and the second torque tube on the coupling connection to rotate synchronously.

[0009] The first torque tube and the second torque tube are connected by a coupling connector, and the driving rocker arm is arranged on the coupling connector. When the flap actuator works, the first torque tube and the second torque tube can be driven to rotate synchronously, so as to achieve the synchronization of the movement of the left and right flaps of the aircraft. The scheme provided by the present application is simple in principle and structure, and the flap actuator can conveniently drive the left and right flaps of the aircraft to work. The flap control system provided by the present application is used to replace the complex synchronous cross-linking mechanism and electrical control, so that the flap control is not easy to make mistakes and the control is more reliable.

[0010] At the same time, the coupling connector connects the first torque tube and the second torque tube respectively. Compared with the traditional single torque tube structure, the requirements for the straightness of the first torque tube and the second torque tube are reduced, thereby reducing the manufacturing difficulty and cost.

[0011] Furthermore, the flap actuator includes an actuating body and a telescopic shaft, one end of the telescopic shaft is connected to the actuating body, and the other end is hinged to an end of the driving rocker arm away from the connecting section.

[0012] In actual use, the flap actuator may be an electric push rod, a power source for driving the telescopic shaft to perform telescopic movement is connected to the flap actuator, and the flap actuator is fixed inside the wing of the aircraft by fasteners.

[0013] Furthermore, the coupling connector is a coupler.

[0014] Furthermore, the flap control system also includes a first connecting component and a second connecting component, the first torque tube and the second torque tube are respectively sleeved on the first end and the second end of the coupling connector, the first connecting component is used to pass through the first torque tube and the first end of the coupling connector to fix the first torque tube to the first end of the coupling connector, and the second connecting component is used to pass through the second torque tube and the second end of the coupling connector to fix the second torque tube to the second end of the coupling connector.

[0015] Further, the first connection assembly or the second connection assembly comprises a long bolt, a nut and a cotter pin respectively, the long bolt is arranged along the radial direction of the coupling connection piece, and the nut and the cotter pin are used to set the end of the long bolt to achieve position limiting;

[0016] Alternatively, the first connection assembly or the second connection assembly is respectively a plurality of groups of fasteners arranged along the radial direction of the coupling connection member.

[0017] Furthermore, the flap control system also includes an unloading connection device, through which the driving rocker arm is fixed to the connecting section of the coupling connection member. When the first torque tube and / or the second torque tube is subjected to a load exceeding the bearing limit of the unloading connection device, the connection of the unloading connection device fails, allowing the driving rocker arm to rotate relative to the axial direction of the coupling connection member to achieve unloading.

[0018] Furthermore, a sleeve connection portion is formed at the connection end of the driving rocker arm and the coupling connection piece, and the driving rocker arm is sleeved on the connection section of the coupling connection piece through the sleeve connection portion;

[0019] The unloading connection device comprises a shear bolt, which is arranged along the radial direction of the sleeve connection part and / or the connection section and passes through the sleeve connection part and the connection section to limit the sleeve connection part of the driving rocker arm from rotating relative to the axial direction of the coupling connection piece;

[0020] The shear bolt has a thinning groove, and the larger the groove depth of the thinning groove is, the smaller the load that the shear bolt can bear is;

[0021] The shear bolt forms a shear fracture section at the thinning groove, and the shear fracture section is used to fracture when overloaded to make the connection of the unloading connection device invalid.

[0022] In actual use, when the flap control system is stuck or the flap works unexpectedly, the jamming load will be transferred to the flap control surface. If the jamming load cannot be unloaded, the flap control surface and other equipment will be damaged. In the existing flap control system, load monitoring is performed by setting load sensors and force sensors on the flaps. When the load on the flap control surface exceeds the set value, the power element of the flap control system is controlled to stop working to prevent the load from increasing and causing damage to the flap control surface and other equipment. The principle of this method is too complicated, the failure rate is high, and it cannot be accurately unloaded, and cannot guarantee the safe flight of the aircraft.

[0023] At present, only a flap speed limit sign is set next to the flap control handle to remind pilots to pay attention to the occurrence of flap control system jamming, but the design of the device structure itself does not consider methods or means to actively limit the load in the event of system jamming or unexpected flap operation.

[0024] In the case of system jamming or overload of the aerodynamic surface of the wing, by arranging the shear bolts, the load is transferred from the rudder surface through the first torque tube, the driving rocker arm and the coupling connector or the second torque tube, the driving rocker arm and the coupling connector to the shear bolts and unloaded by the breaking of the shear bolts, thereby preventing the flap control system from being damaged and ensuring the safety of the aircraft flight. At the same time, through the drive of the flap actuator and the action of the external airflow, the first torque tube and the second torque tube connected by the coupling connector can still be kept synchronized, and the left and right flap rudder surfaces of the aircraft respectively connected to the first torque tube and the second torque tube can be kept synchronized and recovered to the main wing of the aircraft, thereby improving the safety of the aircraft flight.

[0025] Furthermore, the thinning grooves include two, and the two thinning grooves respectively form two shear fracture sections, and the two shear fracture sections are respectively arranged corresponding to two sleeve overlapping parts formed when the sleeve connecting part is sleeved on the connecting section.

[0026] In actual use, the load applies shear force and torque to the shear bolt at the overlapping part of the sleeve connection part of the driving rocker arm and the connecting section of the coupling connector. The thinning groove is arranged corresponding to the overlapping part of the sleeve connection part and the connecting section to facilitate load unloading control.

[0027] Furthermore, the unloading connection device also includes a limit piece arranged at the end of the shear bolt, and the shear bolt cooperates with the limit piece to prevent the shear bolt from falling off from the sleeve connecting portion and the connecting section.

[0028] In actual use, the limiting member can be a nut.

[0029] Furthermore, the unloading connection device also includes a safety connecting piece, which is arranged on the driving rocker arm and is respectively connected to the two ends of the shear bolt. When the shear bolt breaks, the safety connecting piece is used to prevent the broken shear bolt and the limit piece on the shear bolt from falling off from the flap control system and affecting the movement of the system.

[0030] Furthermore, the safety connecting piece is a fuse, and safety connecting holes are respectively formed at two ends of the shear bolt. The fuse passes through the safety connecting holes at both ends of the shear bolt and is wound around the sleeve connecting part of the driving rocker arm.

[0031] Further, the flap control system further comprises a first flap rudder surface pull rod and a second flap rudder surface pull rod, one end of the first flap rudder surface pull rod is connected to the end of the first torque tube away from the coupling connector, and the other end of the first flap rudder surface pull rod is used to connect to the flap rudder surface on one side of the first torque tube;

[0032] One end of the second flap rudder surface pull rod is connected to the end of the second torque tube away from the coupling connector, and the other end of the second flap rudder surface pull rod is used to connect to the flap rudder surface on one side of the second torque tube.

[0033] Furthermore, the first torque tube and the second torque tube are respectively provided with a pull rod connection at one end away from the coupling connection;

[0034] The two ends of the first flap rudder surface tie rod are respectively used to hinge the tie rod connector and the flap rudder surface at the end of the first torque tube;

[0035] The two ends of the second flap rudder surface tie rod are respectively used to hinge the tie rod connector and the flap rudder surface at the end of the second torque tube;

[0036] The flap control system ultimately controls the deflection of the flap control surface through the flap control surface pull rod.

[0037] In actual use, the first torque tube, the second torque tube, the first flap rudder rod, the second flap rudder rod, the driving rocker arm and the coupling connector constitute a mechanical interconnection structure, which is independent of the flap actuator and realizes the synchronous movement of the left and right flap rudder surfaces in a more reliable way.

[0038] Furthermore, the first torque tube and the second torque tube are thin-walled tubular structures with large inner diameters, which are light in weight and high in rigidity.

[0039] The present application also provides an aircraft, comprising a left flap, a right flap and a flap control system, wherein the flap control system is used to connect the left flap and the right flap and make the left flap and the right flap move synchronously;

[0040] The flap control system is the flap control system described above.

[0041] The beneficial effects of the utility model are:

[0042] (1) The first torque tube and the second torque tube are connected by a coupling connector. When the flap actuator is working, the first torque tube and the second torque tube can be driven to rotate synchronously, thereby realizing the synchronization of the movement of the left and right flaps of the aircraft. The principle and structure of this scheme are simple, and the flap actuator can conveniently drive the left and right flaps of the aircraft to work. At the same time, compared with the traditional single torque tube structure, the straightness requirements of the first torque tube and the second torque tube are reduced, thereby reducing the manufacturing difficulty and cost.

[0043] (2) Shear bolts are introduced into the system. When the system is stuck or the aerodynamic surface is overloaded, the sticking load and aerodynamic load are transferred to the shear bolts, which are unloaded by deformation or shearing. The remaining connections remain unchanged, allowing the flaps and control surfaces to remain synchronized. The flap control system function is degraded, and the flaps and control surfaces can be deflected synchronously to ensure flight safety.

[0044] That is, the present application proposes a flap control system with a load limiting function, which can not only realize synchronous control of the flaps, but also has a simple structure and reliable control while adding the load limiting function, thereby ensuring the safety of aircraft flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 This is a schematic diagram of the first axis side structure of the flap control system of the utility model embodiment;

[0046] Figure 2 yes Figure 1 A is a schematic diagram of the partially enlarged structure of the middle part;

[0047] Figure 3 yes Figure 1 A schematic diagram of the partially enlarged structure of B in the middle;

[0048] Figure 4 It is a schematic diagram of the second axis side structure of the flap control system of the utility model embodiment (hiding the driving rocker arm);

[0049] Figure 5 yes Figure 4 A schematic diagram of the partially enlarged structure of C in the middle;

[0050] Figure 6 It is a partial top view structural schematic diagram of the flap control system of the embodiment of the utility model;

[0051] Figure 7 yes Figure 6 Schematic diagram of the cross-sectional structure of AA;

[0052] Figure 8 yes Figure 7 A schematic diagram of the partially enlarged structure of D in the middle;

[0053] Fig. 9 It is a schematic diagram of the axial structure of the shear bolt of the embodiment of the utility model;

[0054] Fig.10 It is a schematic diagram of the shaft side structure of the driving rocker arm of the embodiment of the utility model.

[0055] The reference numerals in the figures are:

[0056] 10. First torque tube; 20. Second torque tube; 30. Flap actuator; 301. Actuating body; 302. Telescopic shaft; 40. Driving rocker arm; 401. Sleeve connection; 50. Coupling connector; 501. First end; 502. Second end; 503. Connecting section; 60. First connecting assembly; 70. Second connecting assembly; 80. Unloading connecting device; 801. Shear bolt; 8011. Thinning groove; 8012. Shear fracture section; 8013. Safety connecting hole; 802. Limiting member; 803. Safety connecting member; 90. First flap rudder surface pull rod; 100. Second flap rudder surface pull rod; 110. Pull rod connector. DETAILED DESCRIPTION

[0057] The utility model is described in detail below in conjunction with the accompanying drawings.

[0058] like Figure 1 to Figure 5 As shown, the present application provides a flap control system, comprising: a first torque tube 10, a second torque tube 20, a flap actuator 30, a driving rocker arm 40 and a coupling connection 50;

[0059] The coupling member 50 has a first end 501, a second end 502 and a connecting section 503 disposed between the first end 501 and the second end 502. The first end 501 and the second end 502 are fixed to the first torque tube 10 and the second torque tube 20 respectively.

[0060] One end of the driving rocker arm 40 is fixed on the connecting section 503, and the other end of the driving rocker arm 40 is connected to the flap actuator 30. When the flap actuator 30 is working, it will drive the driving rocker arm 40 to rotate, and at the same time drive the first torque tube 10 and the second torque tube 20 on the coupling connector 50 to rotate synchronously.

[0061] The first torque tube 10 and the second torque tube 20 are connected by a coupling connector 50, and the driving rocker arm 40 is arranged on the coupling connector 50. When the flap actuator 30 works, the first torque tube 10 and the second torque tube 20 can be driven to rotate synchronously, so as to achieve the synchronization of the movement of the left and right flaps of the aircraft. The scheme provided by the present application has a simple principle and structure, and the flap actuator 30 can conveniently drive the left and right flaps of the aircraft to work. The flap control system provided by the present application is used to replace the complex synchronous cross-linking mechanism and electrical control, so that the flap control is not easy to make mistakes and the control is more reliable.

[0062] At the same time, the coupling connector 50 connects the first torque tube 10 and the second torque tube 20 respectively. Compared with the traditional single torque tube structure, the straightness requirements of the first torque tube 10 and the second torque tube 20 are reduced, thereby reducing the manufacturing difficulty and cost.

[0063] In this embodiment, the flap actuator 30 includes an actuating body 301 and a telescopic shaft 302 . One end of the telescopic shaft 302 is connected to the actuating body 301 , and the other end is hinged to an end of the driving rocker arm 40 away from the connecting section 503 .

[0064] In actual use, the flap actuator 30 may be an electric push rod, and a power source for driving the telescopic shaft 302 to perform telescopic movement is connected to the flap actuator 30 . The flap actuator 30 is fixed inside the wing of the aircraft by fasteners.

[0065] In this embodiment, the coupling connection member 50 is a coupler.

[0066] like Figure 1 and Figure 5 As shown, in this embodiment, the flap control system also includes a first connecting component 60 and a second connecting component 70. The first torque tube 10 and the second torque tube 20 are respectively sleeved on the first end 501 and the second end 502 of the coupling connector 50. The first connecting component 60 is used to be passed through the first torque tube 10 and the first end 501 of the coupling connector 50 to fix the first torque tube 10 to the first end 501 of the coupling connector 50. The second connecting component 70 is used to be passed through the second torque tube 20 and the second end 502 of the coupling connector 50 to fix the second torque tube 20 to the second end 502 of the coupling connector 50.

[0067] In this embodiment, the first connecting component 60 or the second connecting component 70 respectively includes a long bolt, a nut and a cotter pin. The long bolt is arranged along the radial direction of the coupling connector 50, and the nut and the cotter pin are used to set the end of the long bolt to achieve limiting.

[0068] In other embodiments, the first connection assembly 60 or the second connection assembly 70 is respectively a plurality of sets of fasteners arranged along the radial direction of the coupling connector 50 .

[0069] like Figure 1 to Figure 7 As shown, in this embodiment, the flap control system also includes an unloading connection device 80, and the driving rocker arm 40 is fixed to the connecting section 503 of the coupling connection member 50 through the unloading connection device 80. When the first torque tube 10 and / or the second torque tube 20 is subjected to a load exceeding the bearing limit of the unloading connection device 80, the connection of the unloading connection device 80 fails, so that the driving rocker arm 40 can rotate relative to the axial direction of the coupling connection member 50 to achieve unloading.

[0070] like Figure 1 , Figure 8 and Fig.10 As shown, in this embodiment, a sleeve connecting portion 401 is formed at the connecting end of the driving rocker arm 40 and the coupling connecting member 50, and the driving rocker arm 40 is sleeved on the connecting section 503 of the coupling connecting member 50 through the sleeve connecting portion 401;

[0071] The unloading connection device 80 includes a shear bolt 801, which is arranged along the radial direction of the sleeve connection part 401 and / or the connection section 503 and passes through the sleeve connection part 401 and the connection section 503 to limit the sleeve connection part 401 of the driving rocker arm 40 from rotating relative to the axial direction of the coupling connection member 50;

[0072] The shear bolt 801 has a thinning groove 8011. The larger the groove depth of the thinning groove 8011 is, the smaller the load that the shear bolt 801 can bear is.

[0073] The shear bolt 801 forms a shear fracture section 8012 at the thinning groove 8011 , and the shear fracture section 8012 is used to fracture when overloaded to make the connection of the unloading connection device 80 invalid.

[0074] In actual use, when the flap control system is stuck or the flap works unexpectedly, the jamming load will be transferred to the flap control surface. If the jamming load cannot be unloaded, the flap control surface and other equipment will be damaged. In the existing flap control system, load monitoring is performed by setting load sensors and force sensors on the flaps. When the load on the flap control surface exceeds the set value, the power element of the flap control system is controlled to stop working to prevent the load from increasing and causing damage to the flap control surface and other equipment. The principle of this method is too complicated, the failure rate is high, and it cannot be accurately unloaded, and cannot guarantee the safe flight of the aircraft.

[0075] At present, only a flap speed limit sign is set next to the flap control handle to remind pilots to pay attention to the occurrence of flap control system jamming, but the design of the device structure itself does not consider methods or means to actively limit the load in the event of system jamming or unexpected flap operation.

[0076] In the event of system jamming or overload of the aerodynamic surface of the wing, the present application sets a shear bolt 801 so that the load is transferred from the rudder surface through the first torque tube 10, the driving rocker arm 40 and the coupling connector 50 or the second torque tube 20, the driving rocker arm 40 and the coupling connector 50 to the shear bolt 801 and unloaded by the breaking of the shear bolt 801, thereby preventing the flap control system from being damaged and ensuring the safety of the aircraft flight. At the same time, through the drive of the flap actuator 30 and the action of the external airflow, the first torque tube 10 and the second torque tube 20 connected by the coupling connector 50 can still be kept synchronized, and the left and right flap rudder surfaces of the aircraft respectively connected to the first torque tube 10 and the second torque tube 20 can be kept synchronized and recovered to the main wing of the aircraft, thereby improving the safety of the aircraft flight.

[0077] like Figure 1 , Figure 8 and Fig. 9As shown, in this embodiment, the thinning grooves 8011 include two, and the two thinning grooves 8011 respectively form two shear fracture sections 8012, and the two shear fracture sections 8012 are respectively arranged corresponding to the two overlapping parts formed when the sleeve connecting part 401 is sleeved on the connecting section 503.

[0078] During actual use, the load applies shear force and torque to the shear bolt 801 at the overlapping portion of the sleeve connection part 401 of the driving rocker arm 40 and the connecting section 503 of the coupling connector 50, and the thinning groove 8011 is arranged corresponding to the overlapping portion of the sleeve connection part 401 and the connecting section 503 to facilitate load unloading control.

[0079] In this embodiment, the unloading connection device 80 further includes a stopper 802 disposed at the end of the shear bolt 801 , and the shear bolt 801 cooperates with the stopper 802 to prevent the shear bolt 801 from falling off from the sleeve connection portion 401 and the connection section 503 .

[0080] In actual use, the limiting member 802 may be a nut.

[0081] like Figure 1 and Figure 5 As shown, the unloading connection device 80 also includes a safety connection member 803, which is arranged on the driving rocker arm 40 and is respectively connected to the two ends of the shear bolt 801. When the shear bolt 801 is broken, the safety connection member 803 is used to prevent the broken shear bolt 801 and the limit member 802 on the shear bolt 801 from falling off from the flap control system and affecting the movement of the system.

[0082] like Figure 1 , Figure 5 and Fig. 9 As shown, in this embodiment, the safety connector 803 is a fuse, and the two ends of the shear bolt 801 are respectively formed with safety connection holes 8013, and the fuse passes through the safety connection holes 8013 at both ends of the shear bolt 801 and is wound around the sleeve connection part 401 of the driving rocker arm 40.

[0083] like Figure 1 and Figure 3 As shown, in this embodiment, the flap control system further includes a first flap rudder surface pull rod 90 and a second flap rudder surface pull rod 100, one end of the first flap rudder surface pull rod 90 is connected to the end of the first torque tube 10 away from the coupling connector 50, and the other end of the first flap rudder surface pull rod 90 is used to connect to the flap rudder surface on one side of the first torque tube 10;

[0084] One end of the second flap control surface tie rod 100 is connected to the end of the second torque tube 20 away from the coupling connector 50 , and the other end of the second flap control surface tie rod 100 is used to connect to the flap control surface on one side of the second torque tube 20 .

[0085] In this embodiment, the first torque tube 10 and the second torque tube 20 are respectively provided with a tie rod connection 110 at one end away from the coupling connection 50;

[0086] The two ends of the first flap control surface tie rod 90 are respectively used to hinge the tie rod connector 110 and the flap control surface at the end of the first torque tube 10;

[0087] The two ends of the second flap control surface tie rod 100 are respectively used to hinge the tie rod connector 110 and the flap control surface at the end of the second torque tube 20;

[0088] The flap control system ultimately controls the deflection of the flap rudder surface through the flap rudder surface pull rod.

[0089] In this embodiment, both ends of the first flap control surface pull rod 90 and the second flap control surface pull rod 100 are provided with universal joints, and are hingedly arranged through the universal joints. The universal joints can increase the freedom of movement of the aircraft flap control surfaces and make the movement more convenient.

[0090] In actual use, the first torque tube 10, the second torque tube 20, the first flap control surface pull rod 90, the second flap control surface pull rod 100, the driving rocker arm 40 and the coupling connector 50 constitute a mechanical interconnection structure, which is independent of the flap actuator 30 and realizes the synchronous movement of the left and right flap control surfaces in a more reliable manner.

[0091] In this embodiment, the first torque tube 10 and the second torque tube 20 are thin-walled tubular structures with large inner diameters, which are light in weight and high in rigidity.

[0092] The present application also provides an aircraft, comprising a left flap, a right flap and a flap control system, wherein the flap control system is used to connect the left flap and the right flap and make the left flap and the right flap move synchronously;

[0093] The flap control system is a flap control system as described above.

[0094] The above description is only a preferred embodiment of the utility model, and does not limit the patent protection scope of the utility model. Any equivalent structural transformation made using the contents of the utility model specification and drawings, directly or indirectly used in other related technical fields, is also included in the protection scope of the utility model.

Claims

1. A flap control system, characterized in that: include: A first torque tube, a second torque tube, a flap actuator, a drive rocker arm, and a coupling connector; The coupling connector has a first end, a second end, and a connecting section disposed between the first end and the second end, the first end and the second end being fixed to the first torque tube and the second torque tube respectively; One end of the driving rocker arm is fixed on the connecting section, and the other end of the driving rocker arm is connected to the flap actuator. When the flap actuator is working, it will drive the driving rocker arm to rotate, and at the same time drive the first torque tube and the second torque tube on the coupling connection to rotate synchronously.

2. A flap control system according to claim 1, characterized in that: The flap actuator comprises an actuating body and a telescopic shaft, one end of the telescopic shaft is connected to the actuating body, and the other end is hinged to an end of the driving rocker arm away from the connecting section; The coupling connector is a coupler.

3. A flap control system according to claim 1, characterized in that: The flap control system also includes a first connecting component and a second connecting component, the first torque tube and the second torque tube are respectively sleeved on the first end and the second end of the coupling connector, the first connecting component is used to pass through the first torque tube and the first end of the coupling connector to fix the first torque tube to the first end of the coupling connector, and the second connecting component is used to pass through the second torque tube and the second end of the coupling connector to fix the second torque tube to the second end of the coupling connector.

4. A flap control system according to claim 1, characterized in that: The flap control system also includes an unloading connection device, through which the driving rocker arm is fixed to the connecting section of the coupling connection member. When the first torque tube and / or the second torque tube is subjected to a load exceeding the bearing limit of the unloading connection device, the connection of the unloading connection device fails, allowing the driving rocker arm to rotate relative to the axial direction of the coupling connection member to achieve unloading.

5. A flap control system according to claim 4, characterized in that: A sleeve connection portion is formed at the connection end between the driving rocker arm and the coupling connection piece, and the driving rocker arm is sleeved on the connection section of the coupling connection piece through the sleeve connection portion; The unloading connection device comprises a shear bolt, which is arranged along the radial direction of the sleeve connection part and / or the connection section and passes through the sleeve connection part and the connection section to limit the sleeve connection part of the driving rocker arm from rotating relative to the axial direction of the coupling connection piece; The shear bolt has a thinning groove, and the larger the groove depth of the thinning groove is, the smaller the load that the shear bolt can bear is; The shear bolt forms a shear fracture section at the thinning groove, and the shear fracture section is used to fracture when overloaded to make the connection of the unloading connection device invalid.

6. A flap control system according to claim 5, characterized in that: The thinning grooves include two, and the two thinning grooves respectively form two shear fracture sections, and the two shear fracture sections are respectively arranged corresponding to two sleeve overlapping parts formed when the sleeve connecting part is sleeved on the connecting section.

7. A flap control system according to claim 5, characterized in that: The unloading connection device further comprises a stopper disposed at the end of the shear bolt, and the shear bolt cooperates with the stopper to prevent the shear bolt from falling off from the sleeve connection portion and the connection section.

8. A flap control system according to claim 7, characterized in that: The unloading connection device further comprises a safety connection piece, which is arranged on the driving rocker arm and respectively connected to both ends of the shear bolt. When the shear bolt is broken, the safety connection piece is used to prevent the broken shear bolt and the limit piece on the shear bolt from falling off from the flap control system. The safety connecting piece is a fuse, and the two ends of the shear bolt are respectively formed with safety connecting holes, and the fuse passes through the safety connecting holes at both ends of the shear bolt and is wound around the sleeve connecting part of the driving rocker arm.

9. A flap control system according to claim 1, characterized in that: The flap control system further comprises a first flap rudder surface pull rod and a second flap rudder surface pull rod, one end of the first flap rudder surface pull rod is connected to an end of the first torque tube away from the coupling connector, and the other end of the first flap rudder surface pull rod is used to connect to a flap rudder surface on one side of the first torque tube; One end of the second flap rudder surface pull rod is connected to the end of the second torque tube away from the coupling connector, and the other end of the second flap rudder surface pull rod is used to connect to the flap rudder surface on one side of the second torque tube.

10. An aircraft, characterized in that: It includes a left flap, a right flap and a flap control system, wherein the flap control system is used to connect the left flap and the right flap and make the left flap and the right flap move synchronously; The flap control system is a flap control system as described in any one of claims 1 to 9.

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