Flaperon movement mechanism and assembly compensation method thereof

Abstract

The invention belongs to the technical field of aircraft design, and particularly relates to a flaperon movement mechanism and an assembly compensation method thereof, the complex flaperon movement mechanism can be easily installed through the compensation structure, and additional stress caused by forced assembly can be avoided through adopted compensation measures; meanwhile, the position and the posture of the flaperon can be conveniently adjusted so as to meet the gap order difference requirement between the flaperon and the wing; in addition, the assembly compensation structural form is combined with control over free tolerance at the intersection point, the accumulative error of the mechanism is controlled within a small range, and the control precision of the mechanism is high.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft design, and in particular relates to a flaperon motion mechanism and an assembly compensation method thereof. Background Art

[0002] For short-distance takeoff and landing aircraft, a lift-enhancing device is sometimes used. Its movement mechanism can enable a single wing surface to have both flap and aileron functions. The two functions are independent of each other, and the wing surface has a certain amount of retreat. The flaperon is such a lift-enhancing device.

[0003] The flaperon motion mechanism is a spatial linkage mechanism, involving a large number of rods and complex cross-linking relationships. The motion mechanism rods, flaperon wing surfaces and wing fixed structures will have tolerances during the manufacturing and assembly of parts. These manufacturing tolerances will be exposed when the flaperon is installed on the wing, which is specifically manifested in the gap and step difference between the flaperon wing surface and the wing not meeting the requirements. The conventional assembly compensation structure has many adjustment intersections, and installation coordination and attitude adjustment are difficult, and faces the problem of large cumulative errors in the linkage mechanism. Summary of the invention

[0004] In order to solve the above problems, the present application provides a flaperon motion mechanism, comprising:

[0005] flaperons, which are located on the trailing edge of the wing;

[0006] A backward driving mechanism, comprising a first screw actuator, a second screw actuator, a first rocker arm, and a second rocker arm;

[0007] One end of the first screw actuator and the second screw actuator are respectively fixed to the wing, and the other end is respectively hinged to the first rocker arm and the second rocker arm at the first intersection and the second intersection. The middle parts of the first rocker arm and the second rocker arm are both hinged to the first hinge point and the second hinge point of the first rotating shaft of the wing, and the ends are both hinged to the fourth hinge point and the fifth hinge point of the second rotating shaft of the flaperon.

[0008] A deflection drive mechanism, comprising a hydraulic actuator, a fourth connecting rod, a third connecting rod, a first connecting rod, a second connecting rod and a small tie rod, wherein the hydraulic actuator can be extended and shortened, one end of which is fixedly connected to the wing at a third hinge support, and the other end of which is hinged to one end of the fourth connecting rod at a second connecting hinge, the middle part of the fourth connecting rod and one end of the third connecting rod are both fixedly connected to the wing at a fourth hinge support, the other end of the third connecting rod and one end of the first connecting rod are connected to the third connecting hinge, the middle part of the first connecting rod and one end of the second connecting rod are connected to the fourth connecting hinge, the other end of the second connecting rod and the other end of the fourth connecting rod are connected to the fifth connecting hinge, the other end of the first connecting rod is connected to the sixth connecting hinge with the small tie rod, and the small tie rod is connected to the flaperon at a seventh connecting hinge;

[0009] The Watt connecting rod has one end hinged to the first rotating shaft at the third hinge point, and the other end hinged to the third connecting hinge of the deflection driving mechanism.

[0010] Preferably, the small pull rod is a pull rod with continuously adjustable length.

[0011] Preferably, the hinge axes of the fourth connecting rod, the third connecting rod, the first connecting rod and the second connecting rod are all parallel to the span direction.

[0012] Preferably, the fourth connecting rod, the third connecting rod and the wing are all hinged at the fourth hinge point through a double-ear structure.

[0013] Preferably, the fourth link, the third link and the wing form two mirror-image hinge points at the wing tip side and the wing root side of the binaural structure through two hinge axes respectively.

[0014] A flaperon motion mechanism assembly compensation method, used to compensate for the structural clearance of the flaperon motion mechanism:

[0015] The third hinge point, the fixed hinge point between the first screw actuator and the wing, the fixed hinge point between the second screw actuator and the wing, the second connecting hinge, and the third hinge support point are used to compensate for the tolerance in the span direction through a single sliding bushing.

[0016] Preferably, the fifth hinge point adopts double sliding bushings to compensate for tolerance in the span direction.

[0017] Preferably, the fourth hinge point is compensated for the tolerance in the span direction by adjusting the washer.

[0018] Preferably, the adjusting washer adjustment method comprises:

[0019] The theoretical clearance at the hinge point on the wing root side and the hinge point on the wing tip side at the adjusting washer is δ;

[0020] For the third link, measure the actual deviation Δ3 of the third link 3 in the span direction at the four-hinge pivot point and the third connecting hinge. The deviation at the third connecting hinge relative to the four-hinge pivot point is positive in the direction of the wing root, and negative in the direction of the wing tip;

[0021] For the first link, measure the actual spanwise deviation Δ1 of the first link at the third connection hinge and the fourth connection hinge, which is positive in the direction of the wing root at the fourth connection hinge relative to the third connection hinge, and negative in the direction of the wing tip;

[0022] For the second link, measure the actual spanwise deviation Δ2 of the second link at the fourth connection hinge and the fifth connection hinge, which is positive in the direction of the wing root at the fifth connection hinge relative to the fourth connection hinge, and negative in the direction of the wing tip;

[0023] For the fourth link, measure the actual spanwise deviation Δ4 of the fourth link at the fifth connection hinge and the fourth hinge support point, which is positive in the wing root direction relative to the fifth connection hinge at the fourth hinge support point and negative in the wing tip direction;

[0024] An adjusting washer is formed by arranging and combining washers of a series of thicknesses. The thickness of the adjusting washer on the wing root side is δ-, and the thickness of the adjusting washer on the wing tip side is δ+. The adjusting washers are installed at the reserved gaps.

[0025] Preferably, the adjustment method of the Watt connecting rod is:

[0026] When the small tie rod and Watt's connecting rod are not installed, adjust the offset distance u between the trailing edge of the flaperon wing surface and the trailing edge of the wing fixed structure in the heading direction to meet the appearance requirements. At this time, measure the distance between the third connecting hinge and the third hinge point, adjust the length of the Watt's connecting rod to be equal to this distance, and install the Watt's connecting rod.

[0027] Preferably, the adjustment method of the small pull rod is:

[0028] Measure the step difference v between the trailing edge of the flaperon wing and the trailing edge of the wing. The upward direction is positive. Adjust the length of the small tie rod to l GH +(l HB3 / l B3N )*v, install the small pull rod.

[0029] Preferably, the gasket thickness includes: 2mm, 1mm, 0.5mm, 0.2mm, 0.1mm.

[0030] The advantages of the present application include: the present invention provides an assembly compensation structure for a flaperon motion mechanism with a large number of rods and complex cross-linking relationships, which makes the flaperon motion mechanism simple to install and does not generate additional stress caused by forced assembly; only one intersection point and two tie rods of the entire motion mechanism require manual adjustment, which greatly reduces the difficulty of installation and adjustment of the complex flaperon motion mechanism; the assembly compensation structure is combined with the control of the free tolerance at the intersection to control the cumulative error of the mechanism within a smaller range, and the mechanism control accuracy is higher. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 This is a motion diagram of a flaperon motion mechanism according to a preferred embodiment of the present application;

[0032] Figure 2 This is a schematic diagram of the fourth hinge point A1 of a preferred embodiment of the present application;

[0033] Figure 3 It is a typical schematic diagram of single and double ear articulation;

[0034] Figure 4 is the third connecting hinge E;

[0035] Figure 5 It is a typical structure connecting the Watt link 6 and the flaperon wing surface 8;

[0036] Figure 6 is a structural schematic diagram of the fifth hinge point A2;

[0037] Figure 7 is a structural schematic diagram of the fourth hinge point K;

[0038] Figure 8 It is a schematic diagram of the step difference v and the offset distance u. DETAILED DESCRIPTION

[0039] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0040] like Figure 1-Figure 8 As shown, the present application provides a flaperon motion mechanism, comprising:

[0041] A flaperon 8, arranged at the trailing edge of the wing;

[0042] The backward driving mechanism comprises a first screw actuator 9, a second screw actuator 12, a first rocker arm 7, and a second rocker arm 11;

[0043] One end of the first screw actuator 9 and the second screw actuator 12 are fixed to the wing respectively, and the other end is hinged to the first rocker arm 7 and the second rocker arm 11 at the first intersection C1 and the second intersection C2 respectively. The middle parts of the first rocker arm 7 and the second rocker arm 11 are hinged to the first hinge point B1 and the second hinge point B2 of the first rotating shaft B1B2 of the wing, and the ends are hinged to the fourth hinge point A1 and the fifth hinge point A2 of the second rotating shaft A1A2 of the flaperon 8;

[0044] A deflection drive mechanism, comprising a hydraulic actuator 10, a fourth link 4, a third link 3, a first link 1, a second link 2 and a small tie rod 5, wherein the hydraulic actuator 10 can be extended and shortened, one end of which is fixedly connected to the wing at a third hinge point M, and the other end of which is hinged to one end of the fourth link 4 at a second connecting hinge L, the middle part of the fourth link 4 and one end of the third link 3 are both fixedly connected to the wing at a fourth hinge point K, the other end of the third link 3 and one end of the first link 1 are connected to a third connecting hinge E, the middle part of the first link 1 and one end of the second link 2 are connected to a fourth connecting hinge F, the other end of the second link 2 and the other end of the fourth link 4 are connected to a fifth connecting hinge J, the other end of the first link 1 and the small tie rod 5 are connected to a sixth connecting hinge G, and the small tie rod 5 and the flaperon 8 are connected to a seventh connecting hinge H;

[0045] The Watt link 6 has one end hinged to the first rotating shaft B1B2 at the third hinge point B3, and the other end hinged to the third connecting hinge E of the deflection drive mechanism.

[0046] The movement principle of the above mechanism:

[0047] 1. When the flap moves, the hydraulic actuator 10 is held, and the lead screws 9 and 12 are driven. 10 is held, K is a fixed point, so 4 cannot move; 9 and 12 are driven, 7 and 11 rotate around the A1A2 axis, and the B1B2B3 axis moves. The length of the 6 rod is fixed, so point E moves, so 1, 2, 3, 5, and 8 all move. That is, in this case, 10 and 4 do not move, and the other components all move.

[0048] Second, when the aileron moves, the hydraulic actuator 10 drives, and the lead screws 9 and 12 hold. 9 and 12 hold, 7 and 11 do not move, B1B2B3 axes do not move, K and B3 points do not move, and the lengths of 3 and 6 rods are fixed, so the triangle KEB3 is fixed, and 3 and 6 do not move. That is, in this case, 9, 12, 7, 11, 3, 6 do not move, and the other components are moving.

[0049] 3. During the flap movement, all rods must move in order to realize the aileron function.

[0050] Preferably, the small pull rod 5 is a pull rod with continuously adjustable length.

[0051] Preferably, the hinge axes of the fourth connecting rod 4, the third connecting rod 3, the first connecting rod 1 and the second connecting rod 2 are all parallel to the span direction.

[0052] Preferably, the fourth connecting rod 4, the third connecting rod 3 and the wing are all hinged at the fourth hinge point K through a double-ear structure.

[0053] Preferably, the fourth link 4, the third link 3 and the wing form two mirror-image hinge points at the wing tip side and the wing root side of the binaural structure through two hinge axes respectively.

[0054] A flaperon motion mechanism assembly compensation method, used to compensate for the structural clearance of the flaperon motion mechanism:

[0055] The intersection structure without compensation measures in span direction is as follows:

[0056] Combined with Figure 1 , A1—the intersection of the first rocker arm 7 and the wing fixed structure 13, such as Figure 2 shown.

[0057] B1—the intersection of the first rocker arm 7 and the flaperon wing surface 8, the typical structure is as follows Figure 3 As shown, the first rocker arm 7 is a single-ear piece, and the flaperon wing surface 8 is a double-ear piece.

[0058] B2—intersection point between the second rocker arm 11 and the flaperon wing surface 8, the typical structure is as follows Figure 3 As shown, the second rocker arm 11 is a single-ear piece, and the flaperon wing surface 8 is a double-ear piece.

[0059] C1—the intersection of the first rocker arm 7 and the first screw actuator 9, the typical structure is as follows Figure 3 As shown, the first rocker arm 7 is a single-ear piece, and the first screw actuator 9 is a double-ear piece.

[0060] C2—intersection point between the second rocker arm 11 and the second screw actuator 12, typical structure as Figure 3 As shown, the second rocker arm 11 is a single-ear piece, and the second screw actuator 12 is a double-ear piece.

[0061] E—a composite hinge formed by the first link 1, the third link 3, and the Watt link 6, such as Figure 4 shown.

[0062] F—intersection point between the first link 1 and the second link 2, typical structure is as follows Figure 3 As shown, the second connecting rod 2 is a single-ear piece, and the first connecting rod 1 is a double-ear piece.

[0063] G—intersection point between the first connecting rod 1 and the small pull rod 5, the typical structure is as follows Figure 3 As shown, the small pull rod 5 is a single-ear piece, and the first connecting rod 1 is a double-ear piece.

[0064] H—intersection point between small tie rod 5 and flaperon wing surface 8, typical structure is as follows Figure 3 As shown, the small tie rod 5 is a single-ear piece, and the flaperon wing surface 8 is a double-ear piece.

[0065] J—intersection point of the second connecting rod 2 and the fourth connecting rod 4, the typical structure is as follows Figure 3 As shown, the second connecting rod 2 is a single-ear piece, and the fourth connecting rod 4 is a double-ear piece.

[0066] The intersection structure of spanwise single sliding bushing compensation measure is as follows:

[0067] B3—intersection point between Watt link 6 and flaperon wing surface 8, typical structure is as follows Figure 5 As shown, the flaperon wing surface 8 is a single-ear piece, and the Watt link 6 is a double-ear piece.

[0068] D1—the intersection of the first screw actuator 9 and the wing fixed structure 13, the typical structure is as follows Figure 5 As shown, the first screw actuator 9 is a single-ear piece, and the wing fixing structure 13 is a double-ear piece.

[0069] D2—the intersection of the second screw actuator 12 and the wing fixed structure 13, the typical structure is as follows Figure 5 As shown, the second screw actuator 12 is a single-ear piece, and the wing fixing structure 13 is a double-ear piece.

[0070] L—intersection point of the fourth connecting rod 4 and the hydraulic actuator 10, the typical structure is as follows Figure 5 As shown, the hydraulic actuator 10 is a single-ear piece, and the fourth connecting rod 4 is a double-ear piece.

[0071] M—intersection point of hydraulic actuator 10 and wing fixed structure 13, typical structure is as follows Figure 5 As shown, the hydraulic actuator 10 is a single-ear piece, and the wing fixed structure 13 is a double-ear piece.

[0072] The intersection structure of the spanwise double sliding bushing compensation measure is as follows:

[0073] A2—intersection point between the second rocker arm 11 and the wing fixed structure 13, such as Figure 6 shown.

[0074] The intersection structure of spanwise adjustment washer compensation measures is as follows:

[0075] K—a composite hinge formed by the third link 3, the fourth link 4 and the wing fixed structure 13, such as Figure 7 As shown, Figure 7 The adjusting washers in the tool are a series of washers arranged in combinations, such as 2mm, 1mm, 0.5mm, 0.2mm, 0.1mm, etc., in order to become washers of specific thickness.

[0076] The position and posture adjustment structure is as follows:

[0077] 5—Small pull rod, the length of which can be continuously adjusted.

[0078] 6—Watt connecting rod, a tie rod with continuously adjustable length.

[0079] The intersection structure has no compensation measures in the span direction, and there is a small gap between the single and double ears. The matching size is guaranteed by the manufacturing tolerance of the parts and no manual adjustment is required.

[0080] The intersection structure of the spanwise single sliding bushing compensation measure has no gap between the single and double ears, which facilitates the installation of the first screw actuator 9, the second screw actuator 12, the hydraulic actuator 10, and the Watt connecting rod 6. The spanwise micro-installation tolerances related to these four rods are adjusted by the sliding bushing without manual adjustment.

[0081] The spanwise double sliding bushing compensation measure intersection structure has no gap between the single and double ears and is used to adjust the spanwise difference between the wing fixed structure 13 and the flaperon wing surface 8 due to manufacturing tolerance without manual adjustment.

[0082] The spanwise adjustment washer compensation measure intersection structure is used to adjust the installation tolerance between the first link 1, the second link 2, the third link 3, and the fourth link 4 closed loop and the wing fixed structure 13. There are 17 intersections in the whole set of motion mechanisms, and only the K intersection needs to be manually adjusted according to the actual gap. The adjustment method is as follows:

[0083] like Figure 7 As shown, the theoretical clearance of the adjusting washers on the wing root side and the wing tip side is δ;

[0084] For the third link 3, the actual spanwise deviation Δ3 of the third link 3 at point K and point E is measured, where the deviation at point E relative to point K in the wing root direction is positive, and the deviation at point E relative to point K in the wing tip direction is negative;

[0085] For the first link 1, measure the actual spanwise deviation Δ1 of the first link 1 at point E and point F, where the deviation at point F relative to point E in the wing root direction is positive, and the deviation at point F in the wing tip direction is negative;

[0086] For the second link 2, measure the actual spanwise deviation Δ2 of the second link 2 at points F and J, where the deviation at point J relative to point F in the wing root direction is positive, and the deviation at point J in the wing tip direction is negative;

[0087] For the fourth link 4, the actual spanwise deviation Δ4 of the fourth link 4 at the J point and the K point is measured, the deviation at the K point relative to the J point in the wing root direction is positive, and the deviation at the K point relative to the J point in the wing tip direction is negative;

[0088] An adjusting washer is formed by arranging and combining washers of a series of thicknesses. The thickness of the adjusting washer on the wing root side is δ-Δ1+Δ2+Δ3+Δ4, and the thickness of the adjusting washer on the wing tip side is δ+Δ1+Δ2+Δ3+Δ4. The adjusting washers are installed in the reserved gaps.

[0089] The position and attitude adjustment structure is a small pull rod 5 and a Watt link 6 with continuously adjustable length. In the whole set of motion mechanisms, only these two rods need to be manually adjusted according to the actual situation to meet the gap and step difference requirements between the flaperon wing surface 8 and the wing fixed structure 13, such as Figure 8 The adjustment method is as follows:

[0090] When the small tie rod 5 and the Watt's connecting rod 6 are not installed, adjust the offset distance u between the trailing edge of the flaperon wing surface 8 and the trailing edge of the wing fixed structure in the heading direction so that it meets the shape requirements. At this time, measure the distance between point E and point B3, adjust the length of the Watt's connecting rod 6 to be equal to this distance, and install the Watt's connecting rod 6.

[0091] Measure the step difference v between the trailing edge of the flaperon wing surface 8 and the trailing edge of the wing fixed structure. The upward direction is positive. Adjust the length of the small tie rod 5 to l GH +(l HB3 / l B3N )*v, install the small pull rod 5.

[0092] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A flaperon motion mechanism, characterized in that: include: A flaperon (8) is arranged at the trailing edge of the wing; A backward drive mechanism comprises a first screw actuator (9), a second screw actuator (12), a first rocker arm (7), and a second rocker arm (11); One end of the first screw actuator (9) and the second screw actuator (12) are respectively fixed to the wing, and the other end is respectively hinged to the first rocker arm (7) and the second rocker arm (11) at a first intersection (C1) and a second intersection (C2); the middle parts of the first rocker arm (7) and the second rocker arm (11) are both hinged to the first hinge point (B1) and the second hinge point (B2) of the first rotating shaft (B1B2), and the ends are both hinged to the fourth hinge point (A1) and the fifth hinge point (A2) of the second rotating shaft (A1A2) of the flaperon (8); The deflection drive mechanism comprises a hydraulic actuator (10), a fourth connecting rod (4), a third connecting rod (3), a first connecting rod (1), a second connecting rod (2) and a small pull rod (5); the hydraulic actuator (10) can be extended and shortened, one end of which is fixedly connected to the wing at a third hinge point (M), and the other end is hinged to one end of the fourth connecting rod (4) at a second connecting hinge (L); the middle part of the fourth connecting rod (4) and one end of the third connecting rod (3) are both fixedly connected to the wing at a fourth hinge point (K); The other end of the connecting rod (3) and one end of the first connecting rod (1) are connected to a third connecting hinge (E); the middle part of the first connecting rod (1) and one end of the second connecting rod (2) are connected to a fourth connecting hinge (F); the other end of the second connecting rod (2) and the other end of the fourth connecting rod (4) are connected to a fifth connecting hinge (J); the other end of the first connecting rod (1) and a small tie rod (5) are connected to a sixth connecting hinge (G); and the small tie rod (5) and the flaperon (8) are connected to a seventh connecting hinge (H); A Watt's connecting rod (6) has one end hinged to the first rotating shaft (B1B2) at a third hinge point (B3), and the other end hinged to the third connecting hinge (E) of the deflection drive mechanism.

2. The flaperon motion mechanism according to claim 1, characterized in that: The small pull rod (5) is a pull rod with continuously adjustable length.

3. The flaperon motion mechanism according to claim 2, characterized in that: The hinge axes of the fourth connecting rod (4), the third connecting rod (3), the first connecting rod (1) and the second connecting rod (2) are all parallel to the span direction.

4. The flaperon motion mechanism according to claim 3, characterized in that: The fourth connecting rod (4), the third connecting rod (3) and the wing are all hinged at the fourth hinge support point (K) through a double-ear structure.

5. The flaperon motion mechanism according to claim 3, characterized in that: The fourth connecting rod (4), the third connecting rod (3) and the wing form two mirror-image hinge points on the wing tip side and the wing root side of the double-ear structure through two hinge axes.

6. A flaperon motion mechanism assembly compensation method, used to compensate for the structural clearance of the flaperon motion mechanism according to claim 5, characterized in that: The third hinge point (B3), the first screw actuator (9) and the fixed hinge point (D1) of the wing, the second screw actuator (12) and the fixed hinge point (D2) of the wing, the second connecting hinge (L), and the third hinge point (M) are compensated for the tolerance in the span direction through a single sliding bushing.

7. The flaperon motion mechanism assembly compensation method as claimed in claim 6, characterized in that: The fifth hinge point (A2) uses double sliding bushings to compensate for tolerance in the span direction.

8. The flaperon motion mechanism assembly compensation method as claimed in claim 7, characterized in that: The fourth hinge point (K) is adjusted by a washer to compensate for the tolerance in the span direction.

9. The flaperon motion mechanism assembly compensation method as claimed in claim 7, characterized in that: The adjusting washer adjustment method comprises: The theoretical clearance at the hinge point on the wing root side and the hinge point on the wing tip side at the adjusting washer is δ; For the third link (3), measure the actual spanwise deviation Δ3 of the third link (3) at the four-hinge pivot point (K) and the third connecting hinge (E), wherein the deviation of the third connecting hinge (E) relative to the four-hinge pivot point (K) in the direction of the wing root is positive, and the deviation of the third connecting hinge (E) relative to the wing tip is negative; For the first link (1), measuring the actual spanwise deviation Δ1 of the first link (1) at the third connecting hinge (E) and the fourth connecting hinge (F), wherein the deviation Δ1 at the fourth connecting hinge (F) relative to the third connecting hinge (E) is positive in the direction of the wing root and negative in the direction of the wing tip; For the second link (2), measuring the actual spanwise deviation Δ2 of the second link (2) at the fourth connecting hinge (F) and the fifth connecting hinge (J), wherein the deviation Δ2 at the fifth connecting hinge (J) relative to the fourth connecting hinge (F) is positive in the direction of the wing root and negative in the direction of the wing tip; For the fourth link (4), measuring the actual spanwise deviation Δ4 of the fourth link (4) at the fifth connection hinge (J) and the fourth hinge support (K), which is positive in the direction of the wing root relative to the fifth connection hinge (J) at the fourth hinge support (K) and negative in the direction of the wing tip relative to the fifth connection hinge (J); An adjusting washer is formed by arranging and combining washers of a series of thicknesses. The thickness of the adjusting washer on the wing root side is δ-(Δ1+Δ2+Δ3+Δ4), and the thickness of the adjusting washer on the wing tip side is δ+(Δ1+Δ2+Δ3+Δ4). The adjusting washers are installed at the reserved gaps.

10. The flaperon motion mechanism assembly compensation method according to claim 7, characterized in that: Adjustment method of Watt connecting rod (6): When the small tie rod (5) and the Watt's connecting rod (6) are not installed, the offset distance u between the trailing edge of the flaperon wing surface (8) and the trailing edge of the wing fixed structure is adjusted to meet the shape requirements. At this time, the distance between the third connecting hinge (E) and the third hinge point (B3) is measured, and the length of the Watt's connecting rod (6) is adjusted to be equal to this distance, and the Watt's connecting rod (6) is installed.

11. The flaperon motion mechanism assembly compensation method according to claim 10, characterized in that: Adjustment method of small tie rod (5): Measure the step difference v between the trailing edge of the flaperon wing surface (8) and the trailing edge of the wing. The upward direction is positive. Adjust the length of the small tie rod (5) to l GH +(l HB3 / l B3N )*v, install the small tie rod (5).

12. The flaperon motion mechanism assembly compensation method according to claim 9, characterized in that: Gasket thicknesses include: 2mm, 1mm, 0.5mm, 0.2mm, 0.1mm.

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