Method for testing motion principle of flaperon

Abstract

The invention belongs to the technical field of airplane mechanism design verification, and particularly relates to a flaperon motion principle test method, which comprises the following steps of: S1, mounting all parts and a control system of a flaperon test piece on a test bed; s2, marking a laser measuring point on the flaperon test piece, installing an angular displacement measuring instrument, adjusting the position posture of the flaperon, and zeroing measuring equipment; s3, flap function verification of the flaperon test piece; s4, flap function verification of the flaperon test piece; s5, verifying the coupling function of the flaperon test piece; and S6, when the flap function verification, the flap function verification or the coupling function verification do not meet the design requirements, the mechanism is adjusted, and verification is carried out again. According to the application, the safety risk in the test process of the novel movement mechanism can be avoided, and the test piece is prevented from being damaged too early. By using the method, the test period is short, and any deflection function of the control surface in a corresponding deflection angle range at any position of the flap function can be verified.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft mechanism design verification, and in particular relates to a flaperon motion principle test method. Background Art

[0002] On short takeoff and landing aircraft, a special lift-enhancing device is sometimes used that allows a single wing surface to simultaneously perform the functions of ailerons and Fuller flaps. The aileron function and the flap function are independent of each other.

[0003] The lift-enhancing device is a spatial multi-link mechanism, involving a large number of rods and complex cross-linking relationships. A single rudder is controlled by two independent control systems: one is an extension of the flap mechanical control system, linked to the flap, and the other is an aileron hydraulic control system. The flap function configuration angles are 0°, α2, α3, and α4, respectively. When the flap function angle is 0°≤α<α2, the aileron function deflection angle range is β1~β2; when the flap function angle is α2≤α<α3, the aileron function deflection angle range is β3~β4; when the flap function angle is α3≤α≤α4, the aileron function deflection angle range is β5~β6. At any position of the flap function, the rudder can deflect arbitrarily within the corresponding deflection angle range. All components of the mechanism need to have sufficient transmission efficiency and safety distance. When conducting the mechanism principle verification test, there are safety risks and the test piece may be damaged. Summary of the invention

[0004] In order to solve the above problems, the present application provides a flaperon motion principle test method.

[0005] Used to perform motion principle test on a flaperon test piece, the flaperon test piece is arranged at the trailing edge of the test bench; the flaperon test piece includes:

[0006] The backward drive mechanism comprises a screw actuator: a first screw actuator (9), a second screw actuator (12), a first rocker arm (7), and a second rocker arm (11);

[0007] One end of the first screw actuator (9) and the second screw actuator (12) are respectively fixed to the test bench, and the other ends are 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 hinged to a first hinge point (B1) and a second hinge point (B2) of a first rotating shaft (B1B2) of the test bench, and the ends are hinged to a fourth hinge point (A1) and a fifth hinge point (A2) of the second rotating shaft (A1A2);

[0008] 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 test bench 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 test bench at a fourth hinge point (K); The other end of the third 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); the small tie rod (5) and the flaperon test piece are connected to a seventh connecting hinge (H);

[0009] A Watt connecting rod (6), one end of which is hinged to the first rotating shaft (B1B2) at a third hinge point (B3), and the other end of which is hinged to a third connecting hinge (E) of the deflection drive mechanism;

[0010] The flaperon motion principle test method comprises:

[0011] Step S1: Install the components and control system of the flaperon test piece on the test bench;

[0012] Step S2: marking laser measurement points on the flaperon test piece, installing an angular displacement measuring instrument, adjusting the flaperon position and attitude, and zeroing the measuring equipment;

[0013] Step S3: Verification of flap function of the flaperon test piece: in the flap function angle 0° state, measure the first relevant data, retract and extend the lead screw actuator at a speed slower than the rated speed, measure the second relevant data at each small angle interval, and compare and analyze the first relevant data with the second relevant data;

[0014] Step S4: Verification of flap function of the flaperon test piece: in the flap function angle 0° state, drive the hydraulic actuator at a speed slower than the rated speed, measure the third relevant data at each small angle interval, and in the flap function angle a2, a3, a4 states, drive the hydraulic actuator at a speed slower than the rated speed, measure the fourth relevant data at each small angle interval; compare and analyze the third relevant data with the fourth relevant data;

[0015] Step S5: Verification of the coupling function of the flaperon test piece: retract and extend the screw actuator at a rated speed, perform n3 cycles of retract and extend, and in each cycle, randomly control the rudder surface to deflect up and down 4 to 8 times at a random deflection angle; retract and extend the screw actuator at a rated speed, perform n4 cycles of retract and extend, and in each cycle, randomly control the rudder surface to deflect up and down at a maximum angle 4 to 8 times;

[0016] Step S6: When the flap function verification, flap function verification or coupling function verification does not meet the design requirements, adjust the mechanism and re-verify.

[0017] Preferably, the flap function verification of the flaperon test piece also includes: retracting and extending the lead screw actuator at a rated speed, performing n1 cycles of retraction and extension.

[0018] Preferably, the coupling function verification of the flaperon test piece also includes: at each flap function angle, driving the hydraulic actuator at a rated speed to perform n2 cycles of retraction and extension.

[0019] Preferably, the first screw actuator (9) and the second screw actuator (12) are synchronously and proportionally retracted and extended to realize the flap function of the flaperon wing surface (8); the hydraulic actuator (10) is retracted and extended to realize the aileron function of the flaperon wing surface (8), and the flap function configuration angles are 0°, α2, α3, and α4 respectively. When the flap function angle is 0°≤α<α2, the aileron function deflection angle range is β1 to β2; when the flap function angle is α2≤α<α3, the aileron function deflection angle range is β3 to β4; when the flap function angle is α3≤α≤α4, the aileron function deflection angle range is β5 to β6.

[0020] Preferably, step S2 specifically includes: marking 3 to 4 laser measurement points on the flaperon wing surface (8), pasting an angular displacement measuring instrument on the flaperon wing surface (8), adjusting the length of the small tie rod (5) and the Watt connecting rod (6) so that the gap and step difference between the flaperon wing surface (8) and the test bench (13) meet the requirements, using laser tracking to measure the three-dimensional coordinates of the laser measurement points, recording the values, calibrating the spatial initial position of the flaperon wing surface (8), and zeroing the angular displacement measuring instrument.

[0021] Preferably, the flap function verification of the flaperon test piece specifically includes:

[0022] S31: When the flap function angle is 0°, use a steel ruler or a feeler gauge to measure the spanwise clearance between the flaperon wing surface (8) and the test bench, the structural clearance between the first rocker arm (7) and the first screw actuator (9) at the hinge, the structural clearance between the second rocker arm (11) and the second screw actuator (12) at the hinge, the structural clearance between the third connecting rod (3) and the Watt connecting rod (6) at the hinge, the structural clearance between the first connecting rod (1) and the small tie rod (5) at the hinge, and the structural clearance between the small tie rod (5) and the flaperon wing surface (8).

[0023] S32: The first screw actuator (9) and the second screw actuator (12) are driven at 1 / 4 or 1 / 2 of the rated speed to realize the flap function configuration angle 0°→0°+Δα→…→α2→α2+Δα→…→α3→α3+Δα→…→α4, where Δα is an angle interval less than a preset value. At each flap function angle, the first screw actuator (9) and the second screw actuator (12) are both held, and the structural gap measurement items in S31 are measured with a steel ruler or a feeler gauge. The three-dimensional coordinates of the laser measurement point on the flaperon wing surface (8) are measured with a laser tracker. The deflection angle of the flaperon wing surface (8) relative to the initial position is measured with an angular displacement measuring instrument. During the test, the relative position relationship between the moving components is observed to see if there is a problem of too small gap, collision, or abnormal noise.

[0024] S33: Analyze the measured three-dimensional coordinates, flaperon wing surface (8) deflection angle, and structural clearance, and compare them with theoretical data. If there is no abnormality, proceed to the next step.

[0025] S34: The first screw actuator (9) and the second screw actuator (12) are driven at rated speed to achieve the flap function configuration angle of 0°→α2→α3→α4→α3→α2→0°, and n1 cycles of retraction and extension are performed. The flap function verification is completed without abnormal conditions.

[0026] Preferably, S41: in the flap function angle 0° state, the first screw actuator (9) and the second screw actuator (12) are held without being manipulated. The hydraulic actuator (10) is driven at 1 / 4 or 1 / 2 rated speed to achieve the aileron function angle 0°→0°-Δβ→…→β1→β1+Δβ→…→0°→0°+Δβ→…→β2→β2-Δβ→…→0°, Δβ is an angle interval less than a preset angle, the structural gap measurement item in S41 is measured with a steel ruler or a feeler gauge, the three-dimensional coordinates of the laser measurement point on the flaperon wing surface (8) are measured with a laser tracker, and the deflection angle of the flaperon wing surface (8) relative to the initial position is measured with an angular displacement measuring instrument. In one cycle, only one group of the same aileron function angle data is measured. During the test, the relative position relationship between the moving components is observed to see if there is a problem of too small gap, collision, or abnormal noise.

[0027] S42: The first screw actuator (9) and the second screw actuator (12) are driven at normal speed, and the flap function angles are respectively set to α2, α3, and α4. After reaching the designated position, the first screw actuator (9) and the second screw actuator (12) are held without being manipulated. The hydraulic actuator (10) is driven at 1 / 4 or 1 / 2 of the rated speed, and at each aileron small angle interval, the structural clearance, three-dimensional coordinates, and deflection angle in S41 are measured.

[0028] S43: Analyze the structural gap, three-dimensional coordinates of the laser measurement points, and the deflection angle of the flaperon wing surface (8) measured in S41 and S42, and compare them with theoretical data. If there is no abnormality, proceed to the next step;

[0029] S44: The first screw actuator (9) and the second screw actuator (12) are driven at normal speeds. After the flap function angles are set to 0°, α2, α3, and α4, the first screw actuator (9) and the second screw actuator (12) are held without being manipulated. The hydraulic actuator (10) is driven at rated speeds to achieve aileron function angles deflected within the maximum angle ranges of β1 to β2, β3 to β4, β5 to β6, and β5 to β6. At each flap function angle, the aileron function is cycled and extended n2 times. The aileron function verification is completed without abnormal conditions.

[0030] Preferably, the coupling function verification specifically includes:

[0031] S51: The first screw actuator (9) and the second screw actuator (12) are driven at rated speed, and the flap function angle is 0°→α2→α3→α4→α3→α2→0°, and n3 cycles of retraction and extension are performed. In each cycle, the hydraulic actuator (10) is randomly controlled to control the flaperon to deflect up and down 4 to 8 times. The rated speed is deflected within the maximum deflection range, and the angle is random. If there is no abnormality, proceed to the next step.

[0032] S52: The first screw actuator (9) and the second screw actuator (12) are driven at the rated speed to perform n4 cycles of flap function retraction and extension. In each cycle, the hydraulic actuator (10) is randomly operated to control the flaperon to deflect up and down 4 to 8 times. The rated speed is used for the maximum angle deflection. The coupling function verification is completed without any abnormality.

[0033] 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.

[0034] Preferably, the small pull rod (5) is a pull rod with continuously adjustable length. The adjustment mechanism includes adjustment.

[0035] Preferably, the adjustment mechanism includes adjusting the length of the small pull rod (5).

[0036] Preferably, Δα is 1° to 2°, and Δβ is 1° to 2°.

[0037] The advantages of this application include: avoiding safety risks in the test process of new motion mechanisms and avoiding premature damage to test pieces. The test cycle of this method is short, and the rudder surface can be verified to have any deflection function within the corresponding deflection angle range at any position of the flap function. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1A preferred embodiment of the present application is a schematic diagram of the movement of the flaperon movement mechanism in a preferred embodiment of the present application;

[0039] Figure 2 It is a flow chart of a flaperon motion principle test method according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0040] 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.

[0041] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0042] Figure 1 As shown, a flaperon motion principle test method is used to perform a motion principle test on a flaperon test piece 2, wherein the flaperon test piece 2 is arranged at the trailing edge of a test bench; the flaperon test piece 2 comprises:

[0043] The backward driving mechanism includes a screw actuator: a first screw actuator 9, a second screw actuator 12, a first rocker arm 7, and a second rocker arm 11;

[0044] One end of the first screw actuator 9 and the second screw actuator 12 are respectively fixed to the test bench, and the other ends are respectively hinged to the first rocker arm 7 and the second rocker arm 11 at the first intersection C1 and the second intersection C2. 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 test bench, 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 test piece 2.

[0045] A deflection drive mechanism, comprising 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 tie rod 5, wherein the hydraulic actuator 10 can be extended and shortened, one end of which is fixedly connected to the test bench 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 test bench at a fourth hinge point K, the other end of the third 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 the small tie rod 5 are connected to a sixth connecting hinge G, and the small tie rod 5 and the flaperon test piece 2 are connected to a seventh connecting hinge H;

[0046] A Watt's connecting rod 6, one end of which is hinged to the first rotating shaft B1B2 at a third hinge point B3, and the other end of which is hinged to the third connecting hinge E of the deflection driving mechanism;

[0047] The test method comprises the following steps: Figure 2 shown.

[0048] Step 1: Assemble the moving parts and control system of the test piece Figure 1 As shown, it is installed on a test bench 13, wherein the first rocker arm 7 and the second rocker arm 11 are hinged to the test bench 13 at points A1 and A2, respectively; the first screw actuator 9 and the second screw actuator 12 are hinged to the test bench 13 at points B1 and B2, respectively; the third connecting rod 3 and the fourth connecting rod 4 are hinged to the test bench 13 at point C to form a composite hinge; and the hydraulic actuator 10 is hinged to the test bench 13 at point D. During installation, ensure that the lengths of the first screw actuator 9 and the second screw actuator 12 are zero lengths, and the length of the hydraulic actuator 10 is neutral length. The first screw actuator 9 and the second screw actuator 12 are synchronously and proportionally retracted and extended to realize the flap function of the flaperon wing surface 8; the hydraulic actuator 10 is retracted and extended to realize the aileron function of the flaperon wing surface 8. The flap function configuration angles are 0°, α2, α3, and α4 respectively. When the flap function angle is 0°≤α<α2, the aileron function deflection angle range is β1~β2; when the flap function angle is α2≤α<α3, the aileron function deflection angle range is β3~β4; when the flap function angle is α3≤α≤α4, the aileron function deflection angle range is β5~β6.

[0049] Step 2: Mark about 3 to 4 laser measurement points on the flaperon wing surface 8, and paste the angular displacement measuring instrument on the flaperon wing surface 8. Adjust the length of the small tie rod 5 and the Watt connecting rod 6 so that the gap and step difference between the flaperon wing surface 8 and the test bench 13 meet the requirements. Use a laser tracker or other equipment to measure the three-dimensional coordinates of the laser measurement points, record the values, calibrate the initial spatial position of the flaperon wing surface 8, and zero the angular displacement measuring instrument.

[0050] Step 3: Verify flap function, hydraulic actuator 10 is held without operation.

[0051] (1) When the flap function angle is 0°, use a steel ruler or feeler gauge to measure the spanwise clearance between the flaperon wing surface 8 and the test bench 13, the structural clearance at the hinge between the first rocker arm 7 and the first screw actuator 9, the structural clearance at the hinge between the second rocker arm 11 and the second screw actuator 12, the structural clearance at the hinge between the third connecting rod 3 and the Watt connecting rod 6, the structural clearance at the hinge between the first connecting rod 1 and the small tie rod 5, and the structural clearance between the small tie rod 5 and the flaperon wing surface 8.

[0052] (2) The first screw actuator 9 and the second screw actuator 12 are driven at a slow speed (usually 1 / 4 or 1 / 2 of the normal speed) to realize the flap function configuration angle 0°→0°+Δα→…→α2→α2+Δα→…→α3→α3+Δα→…→α4, where Δα is a small angle interval, usually 1° to 2°. At each flap function angle, the first screw actuator 9 and the second screw actuator 12 are held, and the structural gap measurement items in step 3 (1) are measured with a steel ruler or a feeler gauge, the three-dimensional coordinates of the laser measurement point on the flaperon wing surface 8 are measured with a laser tracker, and the deflection angle of the flaperon wing surface 8 relative to the initial position is measured with an angular displacement measuring instrument. During the test, the relative position relationship between the moving components is observed to see if there are problems such as too small gap, collision, abnormal noise, etc.

[0053] (3) Analyze the measured three-dimensional coordinates, flaperon wing surface 8 deflection angle, and structural clearance, and compare them with theoretical data. If there is no abnormality, proceed to the next step.

[0054] (4) The first screw actuator 9 and the second screw actuator 12 are driven at normal speed to realize the flap functional configuration angle of 0°→α2→α3→α4→α3→α2→0°, and the flap function verification is completed after n1 cycles of retraction and extension are performed without abnormal conditions.

[0055] Step 4: Aileron function verification.

[0056] (1) When the flap function angle is 0°, the first screw actuator 9 and the second screw actuator 12 are not operated. The hydraulic actuator 10 is driven at a slow speed (usually 1 / 4 or 1 / 2 of the normal speed) to achieve the aileron function angle 0°→0°-Δβ→…→β1→β1+Δβ→…→0°→0°+Δβ

[0057] →…→β2→β2-Δβ→…→0°, Δβ is a smaller angle interval, usually 1°~2°, use a steel ruler or feeler gauge to measure the structural gap measurement item in step 3 (1), use a laser tracker to measure the three-dimensional coordinates of the laser measurement point on the flaperon wing surface 8, and use an angular displacement measuring instrument to measure the deflection angle of the flaperon wing surface 8 relative to the initial position. In one cycle, only one set of the same aileron function angle data is measured. During the test, observe the relative position relationship between the moving components to see if there are problems such as too small gap, bumps, and abnormal noises.

[0058] (2) Similar to step 4 (1), the first screw actuator 9 and the second screw actuator 12 are driven at normal speed, and the flap function angles are respectively set to α2, α3, and α4. After reaching the designated position, the first screw actuator 9 and the second screw actuator 12 are held without being manipulated. The hydraulic actuator 10 is driven at a slow speed, and at each aileron small angle interval, the structural clearance, three-dimensional coordinates, and deflection angle in step 4 (1) are measured.

[0059] (3) Analyze the structural gap, three-dimensional coordinates of the laser measurement points, and flaperon wing surface 8 deflection angle measured in steps 4 (1) and (2), and compare them with theoretical data. If there is no abnormality, proceed to the next step.

[0060] (4) The first screw actuator 9 and the second screw actuator 12 are driven at normal speed. After the flap function angles are respectively set to 0°, α2, α3, and α4, the first screw actuator 9 and the second screw actuator 12 are held without being manipulated. The hydraulic actuator 10 is driven at normal speed to achieve the aileron function angle deflection within the maximum angle range of β1-β2, β3-β4, β5-β6, and β5-β6. At each flap function angle, the aileron function cycle is retracted and extended n2 times. If there is no abnormality, the aileron function verification is completed.

[0061] Step 5, coupling function verification. During the use of the flaperon, when the first screw actuator 9 and the second screw actuator 12 are driven, that is, when the flap function switches from one angle to another adjacent angle, the lateral control function of the aileron needs to be realized at the same time, that is, the hydraulic actuator 10 needs to be driven at the same time, and two independent control systems drive one rudder surface at the same time. Step 5 tests and verifies this function. After the above steps 3 and 4, most of the risks of the test have been released.

[0062] (1) The first screw actuator 9 and the second screw actuator 12 are driven at normal speed, and the flap function angle is 0°→α2→α3→α4→α3→α2→0°, and n3 cycles of retraction and extension are performed. In each cycle, the hydraulic actuator 10 is randomly controlled to control the flaperon to deflect up and down 4 to 8 times. The normal speed deflects within the maximum deflection range, and the angle is random. If there is no abnormality, proceed to the next step.

[0063] (2) Similar to step 5 (1), the first screw actuator 9 and the second screw actuator 12 are driven at normal speed to perform n4 cycles of flap function retraction and extension. In each cycle, the hydraulic actuator 10 is randomly controlled to control the flaperon to deflect up and down 4 to 8 times. The maximum angle deflection is performed at normal speed. The coupling function verification is completed without abnormal conditions.

[0064] Step six: disassemble the test piece and check it for bumps, wear, etc., and improve the motion mechanism based on the measured structural clearance, three-dimensional coordinates of the laser measurement points, and rudder surface deflection data.

[0065] 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 principle test method, characterized in that: Used to perform motion principle test on a flaperon test piece, wherein the flaperon test piece is arranged at the trailing edge of the test bench; The flaperon test article includes: The backward drive mechanism comprises a screw actuator: 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 test bench, and the other ends are 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 hinged to the first hinge point (B1) and the second hinge point (B2) of the first rotating shaft (B1B2), 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 test piece; 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 test bench 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 test bench at a fourth hinge point (K); The other end of the third 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); the small tie rod (5) and the flaperon test piece are connected to a seventh connecting hinge (H); A Watt connecting rod (6), one end of which is hinged to the first rotating shaft (B1B2) at a third hinge point (B3), and the other end of which is hinged to a third connecting hinge (E) of the deflection drive mechanism; The flaperon motion principle test method comprises: Step S1: Install the components and control system of the flaperon test piece on the test bench; Step S2: marking laser measurement points on the flaperon test piece, installing an angular displacement measuring instrument, adjusting the flaperon position and attitude, and zeroing the measuring equipment; Step S3: Verification of flap function of the flaperon test piece: in the flap function angle 0° state, measure the first relevant data, retract and extend the lead screw actuator at a speed slower than the rated speed, measure the second relevant data at each small angle interval, and compare and analyze the first relevant data with the second relevant data; Step S4: Verification of flap function of the flaperon test piece: in the flap function angle 0° state, drive the hydraulic actuator at a speed slower than the rated speed, measure the third relevant data at each small angle interval, and in the flap function angle a2, a3, a4 states, drive the hydraulic actuator at a speed slower than the rated speed, measure the fourth relevant data at each small angle interval; compare and analyze the third relevant data with the fourth relevant data; Step S5: Verification of the coupling function of the flaperon test piece: retract and extend the screw actuator at a rated speed, perform n3 cycles of retract and extend, and in each cycle, randomly control the rudder surface to deflect up and down 4 to 8 times at a random deflection angle; retract and extend the screw actuator at a rated speed, perform n4 cycles of retract and extend, and in each cycle, randomly control the rudder surface to deflect up and down at a maximum angle 4 to 8 times; Step S6: When the flap function verification, flap function verification or coupling function verification does not meet the design requirements, adjust the mechanism and re-verify.

2. The flaperon motion principle test method according to claim 1, characterized in that: The flap function verification of the flaperon test piece also includes: retracting and extending the screw actuator at the rated speed, and performing n1 cycles of retraction and extension.

3. The flaperon motion principle test method according to claim 1, characterized in that: The coupling function verification of the flaperon test piece also includes: at each flap functional angle, driving the hydraulic actuator at the rated speed, and performing n2 cycles of retraction and extension.

4. The flaperon motion principle test method according to claim 1, characterized in that: The first screw actuator (9) and the second screw actuator (12) are synchronously and proportionally retracted and extended to realize the flap function of the flaperon wing surface (8); the hydraulic actuator (10) is retracted and extended to realize the aileron function of the flaperon wing surface (8), and the flap function configuration angles are 0°, α2, α3, and α4 respectively. When the flap function angle is 0°≤α<α2, the aileron function deflection angle range is β1 to β2; when the flap function angle is α2≤α<α3, the aileron function deflection angle range is β3 to β4; when the flap function angle is α3≤α≤α4, the aileron function deflection angle range is β5 to β6.

5. The flaperon motion principle test method according to claim 1, characterized in that: Step S2 specifically includes: marking 3 to 4 laser measurement points on the flaperon wing surface (8), pasting an angular displacement measuring instrument on the flaperon wing surface (8), adjusting the length of the small tie rod (5) and the Watt connecting rod (6) so that the gap and step difference between the flaperon wing surface (8) and the test bench (13) meet the requirements, using laser tracking to measure the three-dimensional coordinates of the laser measurement points, recording the values, calibrating the spatial initial position of the flaperon wing surface (8), and zeroing the angular displacement measuring instrument.

6. The flaperon motion principle test method according to claim 1, characterized in that: The flap function verification of the flaperon test piece specifically includes: S31: When the flap function angle is 0°, use a steel ruler or a feeler gauge to measure the spanwise clearance between the flaperon wing surface (8) and the test bench, the structural clearance between the first rocker arm (7) and the first screw actuator (9) at the hinge, the structural clearance between the second rocker arm (11) and the second screw actuator (12) at the hinge, the structural clearance between the third connecting rod (3) and the Watt connecting rod (6) at the hinge, the structural clearance between the first connecting rod (1) and the small tie rod (5) at the hinge, and the structural clearance between the small tie rod (5) and the flaperon wing surface (8). S32: The first screw actuator (9) and the second screw actuator (12) are driven at 1 / 4 or 1 / 2 of the rated speed to realize the flap function configuration angle 0°→0°+Δα→…→α2→α2+Δα→…→α3→α3+Δα→…→α4, where Δα is an angle interval less than a preset value. At each flap function angle, the first screw actuator (9) and the second screw actuator (12) are both held, and the structural gap measurement items in S31 are measured with a steel ruler or a feeler gauge. The three-dimensional coordinates of the laser measurement point on the flaperon wing surface (8) are measured with a laser tracker. The deflection angle of the flaperon wing surface (8) relative to the initial position is measured with an angular displacement measuring instrument. During the test, the relative position relationship between the moving components is observed to see if there is a problem of too small gap, collision, or abnormal noise. S33: Analyze the measured three-dimensional coordinates, flaperon wing surface (8) deflection angle, and structural clearance, and compare them with theoretical data. If there is no abnormality, proceed to the next step. S34: The first screw actuator (9) and the second screw actuator (12) are driven at rated speed to achieve the flap function configuration angle of 0°→α2→α3→α4→α3→α2→0°, and n1 cycles of retraction and extension are performed. The flap function verification is completed without abnormal conditions.

7. The flaperon motion principle test method according to claim 6, characterized in that: S41: When the flap function angle is 0°, the first screw actuator (9) and the second screw actuator (12) are held without being operated. The hydraulic actuator (10) is driven at 1 / 4 or 1 / 2 of the rated speed to achieve the aileron function angle 0°→0°-Δβ→…→β1→β1+Δβ→…→0°→0°+Δβ →…→β2→β2-Δβ→…→0°, Δβ is an angle interval less than a preset angle, a steel ruler or a feeler gauge is used to measure the structural gap measurement item in S41, a laser tracker is used to measure the three-dimensional coordinates of the laser measurement point on the flaperon wing surface (8), and an angular displacement measuring instrument is used to measure the deflection angle of the flaperon wing surface (8) relative to the initial position. In one cycle, only one group of the same aileron function angle data is measured. During the test, the relative position relationship between the moving components is observed to see if there is a problem of too small gap, collision, or abnormal noise. S42: The first screw actuator (9) and the second screw actuator (12) are driven at normal speed, and the flap function angles are respectively set to α2, α3, and α4. After reaching the designated position, the first screw actuator (9) and the second screw actuator (12) are held without being manipulated. The hydraulic actuator (10) is driven at 1 / 4 or 1 / 2 of the rated speed, and at each aileron small angle interval, the structural clearance, three-dimensional coordinates, and deflection angle in S41 are measured. S43: Analyze the structural gap, three-dimensional coordinates of the laser measurement points, and the deflection angle of the flaperon wing surface (8) measured in S41 and S42, and compare them with theoretical data. If there is no abnormality, proceed to the next step; S44: The first screw actuator (9) and the second screw actuator (12) are driven at normal speeds. After the flap function angles are set to 0°, α2, α3, and α4, the first screw actuator (9) and the second screw actuator (12) are held without being manipulated. The hydraulic actuator (10) is driven at rated speeds to achieve aileron function angles deflected within the maximum angle ranges of β1 to β2, β3 to β4, β5 to β6, and β5 to β6. At each flap function angle, the aileron function is cycled and extended n2 times. The aileron function verification is completed without abnormal conditions.

8. The flaperon motion principle test method according to claim 1, characterized in that: The coupling function verification specifically includes: S51: The first screw actuator (9) and the second screw actuator (12) are driven at rated speed, and the flap function angle is 0°→α2→α3→α4→α3→α2→0°, and n3 cycles of retraction and extension are performed. In each cycle, the hydraulic actuator (10) is randomly controlled to control the flaperon to deflect up and down 4 to 8 times. The rated speed is deflected within the maximum deflection range, and the angle is random. If there is no abnormality, proceed to the next step. S52: The first screw actuator (9) and the second screw actuator (12) are driven at the rated speed to perform n4 cycles of flap function retraction and extension. In each cycle, the hydraulic actuator (10) is randomly operated to control the flaperon to deflect up and down 4 to 8 times. The rated speed is used for the maximum angle deflection. The coupling function verification is completed without any abnormality.

9. The flaperon motion principle test method 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.

10. The flaperon motion principle test method according to claim 3, characterized in that: The small pull rod (5) is a pull rod with continuously adjustable length. The adjustment mechanism includes adjustment.

11. The flaperon motion principle test method according to claim 3, characterized in that: The adjustment mechanism includes adjusting the length of the small pull rod (5).

12. The flaperon motion principle test method according to claim 6, characterized in that: Δα is 1°~2°.

13. The flaperon motion principle test method according to claim 7, characterized in that: Δβ is 1°~2°.

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