A sheet-type hinge torque balance structure with built-in bridge correction and correction method

Abstract

A plate-type hinge torque balance structure with built-in bridge correction and a correction method belong to the field of aerospace force measurement test technology. The present invention is to solve the problem of the influence of wing load deformation on the accuracy of the plate-type hinge torque balance. The plate-type hinge torque balance includes a fixed end, a transmission end and a model end. The transmission end and the transition end are located on the same side of the fixed end. The transmission end is connected to the fixed end. One end of the interference elimination measurement beam is connected to the transmission end, and the other end of the interference elimination measurement beam is connected to the transition end. One end of the measuring elastic beam is connected to the end of the transition end away from the fixed end, and the other end of the measuring elastic beam is connected to the model end. The length direction of the measuring elastic beam is parallel to the flap swing axis of the wing. The rudder to be measured is connected to the model end. The interference elimination measurement beam can eliminate the interference of the wing load or the internal stress of the fixed end installation on the balance, so as to achieve accurate measurement of the plate-type hinge torque balance.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace force measurement test, and in particular relates to a sheet-type hinge moment balance structure with built-in bridge correction and a correction method. Background Art

[0002] Hinge moment balance is mainly used to measure the hinge moment acting on the control surface (ailerons, rudder) or all-moving wing surface (horizontal tail, canard) of the aircraft. At present, the demand for hinge moment test for large aspect ratio aircraft types is increasing, and the accuracy requirements are getting higher and higher. The test model of large aspect ratio aircraft has the characteristics of long wings and thin airfoils, and usually has poor rigidity. The design space of the hinge moment balance is insufficient, and it is severely deformed after bearing the test load, which affects the measurement accuracy of the hinge moment balance.

[0003] In view of the multi-component design requirements of the rudder to be tested, a single-component shaft-holding type hinge torque balance cannot be used. The existing technical solutions basically use the structure of a leaf hinge torque balance. However, due to the limitation of the model size, the stiffness of the leaf hinge torque connection end is insufficient and will be affected by the deformation of the wing. The accuracy of the leaf hinge torque balance of the existing technical solutions is very poor.

[0004] At present, researchers have proposed a variety of technical solutions for the thin-wing hinge moment balance. Although these technical solutions have achieved preliminary theoretical results, there are still some drawbacks that have not been solved:

[0005] "Large aspect ratio wing leaf hinge torque balance based on external bridge correction method" discloses a leaf hinge torque balance external bridge signal correction method, which uses external bridge signals to correct the main signals of each component of the leaf hinge torque balance, and substitutes the corrected signals into the balance formula. Although the measurement accuracy of the hinge torque balance is improved, the hinge torque balance has a complex structure and requires a large number of Wheatstone bridges. The deformation of the wing under load will still affect the working formula of the balance, and the correction by the external bridge cannot completely eliminate the influence, and the external bridge cannot completely cover the load transfer path, so the influence cannot be completely simulated or corrected;

[0006] The invention patent with publication number CN113094953A discloses a finite element analysis method for a hinge moment balance with wing deformation, and uses the finite element method to optimize the structure. However, for thin wing surfaces such as large aspect ratio wings, the traditional sheet balance structure is still used. Due to space limitations, the influence of wing load deformation cannot be eliminated.

[0007] The invention patent with publication number CN113092000A discloses a calibration method for a sheet hinge torque balance with an external bridge correction. The calibration of the sheet hinge torque balance with an external bridge correction cannot solve the drawbacks of the sheet hinge torque balance with an external bridge correction.

[0008] The invention patent with publication number CN118504353A discloses a finite element calibration method for a three-component hinge moment balance for a thin rudder surface, in order to solve the problems of calibration loading point arrangement and calibration efficiency, but does not solve the problem of the influence of wing load deformation on the accuracy of the hinge moment balance;

[0009] The invention patent with publication number CN111504596A discloses a hinged moment balance to improve the rigidity of the balance, but does not solve the problem that the deformation of the wing under load affects the accuracy of the balance;

[0010] The invention patent with publication number CN113267317A discloses a hinge torque balance interference elimination structure, which plays a positive role in solving interference stresses such as screw preload and wing load deformation. However, although the interference elimination structure can eliminate part of the interference stress, a certain amount of interference is still transmitted to the balance, affecting the accuracy of the balance. Summary of the invention

[0011] The purpose of the present invention is to provide a plate-type hinge moment balance structure with built-in bridge correction and a correction method to solve the problem of the influence of wing load deformation on the accuracy of the plate-type hinge moment balance. The technical solution adopted by the present invention is as follows:

[0012] A sheet hinge moment balance structure with built-in bridge correction includes a wing, a sheet hinge moment balance and a rudder to be measured, the sheet hinge moment balance includes a fixed end, a transmission end, a disturbance elimination measurement beam, a transition end, a measurement elastic beam and a model end, the fixed end is connected to the wing, the transmission end and the transition end are located on the same side of the fixed end, the transmission end is connected to the fixed end, a gap is provided between the transition end and the fixed end, the disturbance elimination measurement beam is composed of a plurality of sheet beam components arranged at intervals, one end of a plurality of the sheet beam components is connected to the transmission end, and a plurality of the sheet beam components are connected to the transmission end. The other end of the beam is connected to the transition end, the measuring elastic beam is composed of a plurality of column-beam components arranged at intervals, one end of a plurality of the column-beam components is connected to the side of the transition end away from the fixed end, the other ends of a plurality of the column-beam components are connected to the model end, the length direction of the measuring elastic beam is parallel to the flap swing axis of the wing, the rudder surface to be measured is arranged on the side of the model end away from the wing, the rudder surface to be measured is L-shaped, one end of the rudder surface to be measured is a measuring part, the other end of the rudder surface to be measured is a connecting part connected to the model end, and the length direction of the measuring part is parallel to the measuring elastic beam.

[0013] Furthermore, the stiffness of the transition end is greater than the stiffness of the interference elimination measurement beam and the stiffness of the measurement elastic beam.

[0014] Furthermore, the leaf hinge torque balance is integrally formed.

[0015] Furthermore, the leaf hinge moment balance is a steel component.

[0016] The present invention also provides a correction method for a sheet-type hinge torque balance with a built-in bridge correction, which is implemented based on the above-mentioned sheet-type hinge torque balance structure with a built-in bridge correction and includes the following steps:

[0017] Step 1: Paste the first interference elimination strain gauge on the upper end surface of the sheet beam component closest to the fixed end, paste the second interference elimination strain gauge on the lower end surface of the sheet beam component closest to the fixed end, paste the third interference elimination strain gauge on the upper end surface of the sheet beam component farthest from the fixed end, and paste the fourth interference elimination strain gauge on the lower end surface of the sheet beam component farthest from the fixed end. The first interference elimination strain gauge, the second interference elimination strain gauge, the third interference elimination strain gauge and the fourth interference elimination strain gauge constitute a correction bridge and are marked as U 修正 ;

[0018] Step 2: According to the test requirements, a number of measuring strain gauges are attached to the column and beam components to form a number of balance component measuring bridges, which are marked as U1, U2, ..., U n ;

[0019] Step 3: Fix the wing to the calibration equipment, apply the calibration load to the control surface to be tested for the first time according to the calibration load table, and measure U 修正 , U1, U2...U n The strain output is used to obtain the loading data of the wing under unloaded conditions and the working formula of the hinge moment balance, and U1, U2...U n The unloaded output difference is recorded as ΔU i不受载 , where i=1, 2...n, U 修正 The output data is recorded as U 消扰不受载零点 ;

[0020] Step 4: Apply wing load to the wing to simulate the load condition of the wing in the actual wind tunnel test. 修正 After the strain output is generated, the rudder to be tested is loaded with the calibration load for the second time according to the calibration load table, and U 修正 , U1, U2...U i The strain output, and U1, U2...U n The load output difference is recorded as ΔU i受载 , where i=1, 2...n, U 修正 The output data is recorded as U 消扰受载零点 ;

[0021] Step 5: Calculate U1, U2, ..., U respectively n Correction factor K Ui天平 , where i=1, 2, ..., n, K Ui天平 The calculation formula is as follows:

[0022] ;

[0023] Step 6: Correction coefficient K Ui天平 Correct U1, U2, ..., U respectively n The bridge output value;

[0024] Step 7: Add and subtract the bridge output values ​​corrected in step 6 to obtain U1, U2, ..., U n The actual bridge output difference ΔU i风洞 , where i = 1, 2, ... n, and use the working formula obtained in step 2 to calculate the correction data of the aerodynamic load actually applied to the aircraft model in the force measurement wind tunnel test. When the aircraft model is actually subjected to the force measurement wind tunnel test, ΔU i风洞 The difference after balance interference correction is ΔU i风洞修正 , then ΔU i风洞修正 Calculated by the following formula:

[0025] .

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] 1. The present invention proposes a chip hinge moment balance with built-in bridge correction and anti-interference. The interference elimination measuring beam is used as an elastic body, which can eliminate the interference of the wing load or the internal stress of the fixed end installation on the balance, so that the interference stress of the thin wing load deformation is filtered, and the influence of the interference stress on the chip hinge moment balance is reduced, so as to achieve accurate measurement of the chip hinge moment balance and effectively solve the problem of the wing load deformation affecting the accuracy of the chip hinge moment balance.

[0028] 2. By correcting the formula, the residual interference stress transmitted through the transfer end, the interference elimination measuring beam and the transition end can be corrected. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the structure of the present invention;

[0030] Figure 2 It is a structural diagram of a sheet hinge moment balance;

[0031] Figure 3 is a layout diagram of the interference elimination strain gauge of the method of the present invention;

[0032] Figure 4 is the U of the method of the present invention修正 Bridge diagram;

[0033] Figure 5 is a measurement strain gauge arrangement diagram of embodiment 2;

[0034] Figure 6 is the U1 bridge diagram of the second embodiment;

[0035] Figure 7 is the U2 bridge diagram of the second embodiment;

[0036] Figure 8 It is the U3 bridge diagram of the second embodiment;

[0037] Fig. 9 It is the U4 bridge diagram of the second embodiment;

[0038] Fig.10 It is the U5 bridge diagram of the second embodiment.

[0039] In the figure, 1. Wing, 2. Plate hinge moment balance, 21. Fixed end, 22. Transfer end, 23. Interference elimination measuring beam, 24. Transition end, 25. Measuring elastic beam, 26. Model end, 3. Control surface to be measured, 41. Interference elimination first strain gauge, 42. Interference elimination second strain gauge, 43. Interference elimination third strain gauge, 44. Interference elimination fourth strain gauge, 51. Measuring first strain gauge, 52. Measuring second strain gauge, 53. Measuring third strain gauge, 54. Measuring fourth strain gauge, 55. Measuring fifth strain gauge, 56. Measuring sixth strain gauge, 57. Measuring seventh strain gauge, 58. Measuring eighth strain gauge, 59. Measuring ninth strain gauge, 510. Measuring tenth strain gauge, 511. Measuring eleventh strain gauge, 512. Measuring twelfth strain gauge, 513. Measuring thirteenth strain gauge, 514. Measure the fourteenth strain gauge, 515. Measure the fifteenth strain gauge, 516. Measure the sixteenth strain gauge, 517. Measure the seventeenth strain gauge, 518. Measure the eighteenth strain gauge, 519. Measure the nineteenth strain gauge, 520. Measure the twentieth strain gauge, 521. Measure the twenty-first strain gauge, 522. Measure the twenty-second strain gauge, 523. Measure the twenty-third strain gauge, 524. Measure the twenty-fourth strain gauge. DETAILED DESCRIPTION

[0040] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0041] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection is a non-detachable connection including but not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but not limited to conventional detachable methods such as bolt connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can be found in the existing connection methods to achieve the function, and those skilled in the art can choose according to their needs. For example: welding connection is selected for fixed connection, and bolt connection is selected for detachable connection.

[0042] The present invention will be further described in detail below in conjunction with the accompanying drawings. The following embodiments are provided to explain the present invention, but the present invention is not limited to the following embodiments.

[0043] Embodiment 1: Figure 1 , Figure 2 As shown, a plate hinge moment balance structure with built-in bridge correction includes a wing 1, a plate hinge moment balance 2 and a control surface to be measured 3, the plate hinge moment balance 2 includes a fixed end 21, a transmission end 22, a disturbance elimination measurement beam 23, a transition end 24, a measurement elastic beam 25 and a model end 26, the fixed end 21 is connected to the wing 1, the transmission end 22 and the transition end 24 are located on the same side of the fixed end 21, the transmission end 22 is connected to the fixed end 21, and a gap is provided between the transition end 24 and the fixed end 21 to prevent the plate hinge moment balance 2 from contacting the wing 1 after being loaded, and the disturbance elimination measurement beam 23 is composed of a plurality of plate beam components arranged at intervals, and the plurality of said plate beam components are One end is connected to the transfer end 22, and the other ends of the plurality of sheet beam components are connected to the transition end 24. The measuring elastic beam 25 is composed of a plurality of column beam components arranged at intervals, one end of the plurality of column beam components is connected to the side of the transition end 24 away from the fixed end 21, and the other ends of the plurality of column beam components are connected to the model end 26. The length direction of the measuring elastic beam 25 is parallel to the flap swing axis of the wing 1. The rudder surface 3 to be measured is arranged on the side of the model end 26 away from the wing 1. The rudder surface 3 to be measured is L-shaped, one end of the rudder surface 3 to be measured is a measuring part, and the other end of the rudder surface 3 to be measured is a connecting part connected to the model end 26. The length direction of the measuring part is parallel to the measuring elastic beam 25.

[0044] The stiffness of the transition end 24 is greater than the stiffness of the interference elimination measurement beam 23 and the stiffness of the measurement elastic beam 25 , so as to reduce the interference strain transmitted through the interference elimination measurement beam 23 .

[0045] The total cross-sectional area of ​​the plurality of column-beam members is determined based on the test load.

[0046] The total cross-sectional area of ​​the plurality of sheet beam components is determined based on the test load.

[0047] The sheet-type hinge moment balance 2 is integrally formed.

[0048] The leaf hinge moment balance 2 is a steel component.

[0049] Embodiment 2: Figures 1 to 10 As shown, a correction method for a sheet-type hinge torque balance with a built-in bridge correction is implemented based on a sheet-type hinge torque balance structure with a built-in bridge correction described in Example 1, and includes the following steps:

[0050] Step 1: Paste the first interference elimination strain gauge 41 on the upper end surface of the sheet beam component closest to the fixed end 21, paste the second interference elimination strain gauge 42 on the lower end surface of the sheet beam component closest to the fixed end 21, paste the third interference elimination strain gauge 43 on the upper end surface of the sheet beam component farthest from the fixed end 21, and paste the fourth interference elimination strain gauge 44 on the lower end surface of the sheet beam component farthest from the fixed end 21. The first interference elimination strain gauge 41, the second interference elimination strain gauge 42, the third interference elimination strain gauge 43 and the fourth interference elimination strain gauge 44 constitute a correction bridge and are marked as U 修正 ;

[0051] Figure 4 Given U 修正 The wiring diagram of the bridge, R41 represents the resistance of the first interference elimination strain gauge 41, R42 represents the resistance of the second interference elimination strain gauge 42, R43 represents the resistance of the third interference elimination strain gauge 43, and R44 represents the resistance of the fourth interference elimination strain gauge 44;

[0052] Step 2: According to the test requirements, a number of measuring strain gauges are attached to the column and beam components to form a number of balance component measuring bridges, which are marked as U1, U2, ..., U n ;

[0053] Step 3: Fix the wing 1 to the calibration equipment, apply the calibration load to the control surface 3 to be tested for the first time according to the calibration load table, and measure U 修正 , U1, U2...U n The strain output is obtained to obtain the loading data of the wing 1 under unloaded conditions and the working formula of the hinge moment balance 2, and U1, U2...U n The unloaded output difference is recorded as ΔU i不受载 , where i=1, 2...n, U 修正 The output data is recorded as U 消扰不受载零点 ;

[0054] Step 4: Apply wing load to wing 1 to simulate the load condition of wing 1 in actual wind tunnel test. 修正 After the strain output is generated, the calibration load is applied to the rudder surface 3 to be tested for the second time according to the calibration load table, and U 修正 , U1, U2...U i The strain output, and U1, U2...Un The load output difference is recorded as ΔU i受载 , where i=1, 2...n, U 修正 The output data is recorded as U 消扰受载零点 ;

[0055] Step 5: Calculate U1, U2, ..., U respectively n Correction factor K Ui天平 , where i=1, 2, ..., n, K Ui天平 The calculation formula is as follows:

[0056] ;

[0057] Step 6: Correction coefficient K Ui天平 Correct U1, U2, ..., U respectively n The bridge output value;

[0058] Step 7: Add and subtract the bridge output values ​​corrected in step 6 to obtain U1, U2, ..., U n The actual bridge output difference ΔU i风洞 , where i = 1, 2, ... n, and use the working formula obtained in step 2 to calculate the correction data of the aerodynamic load actually applied to the aircraft model in the force measurement wind tunnel test. When the aircraft model is actually subjected to the force measurement wind tunnel test, ΔU i风洞 The difference after balance interference correction is ΔU i风洞修正 , then ΔU i风洞修正 Calculated by the following formula:

[0059] .

[0060] The fixed end 21 is connected to the wing 1 and should not be too large in the span direction. While meeting the strength requirement, the cross-over area with the wing should be minimized.

[0061] A plurality of measuring strain gauges are attached to the measuring elastic beam 25 to form a plurality of Wheatstone bridges, which can realize accurate measurement of three-component or five-component loads. The layout of the strain gauges needs to be determined according to the design load and other conditions. For the convenience of explanation, this embodiment provides a layout of measuring strain gauges. The number of the column beam components is three, and the column beam component close to the transmission end 22 is defined as the first measuring column beam, the middle column beam component is defined as the second measuring column beam, and the column beam components far from the transmission end 22 are three measuring column beams, which are arranged on the left and right sides of the wing 1, and fixed. The fixed end 21 is connected to the trailing edge of the wing 1, the transition end 24 is located on the right side of the fixed end 21, the measuring elastic beam 25 is parallel to the flap swing axis of the wing 1, the first measuring strain gauge 51 and the third measuring strain gauge 53 are attached to the left end of the upper end surface of the No. 2 measuring column beam, and the second measuring strain gauge 52 and the fourth measuring strain gauge 54 are attached to the left end of the lower end surface of the No. 2 measuring column beam. The first measuring strain gauge 51, the second measuring strain gauge 52, the third measuring strain gauge 53 and the fourth measuring strain gauge 54 are connected in sequence to form an electric bridge, which is marked as U1;

[0062] Figure 6 A wiring diagram of the U1 bridge is given, where R51 represents the resistance of the first strain gauge 51, R52 represents the resistance of the second strain gauge 52, R53 represents the resistance of the third strain gauge 53, and R54 represents the resistance of the fourth strain gauge 54;

[0063] The fifth measuring strain gauge 55 and the seventh measuring strain gauge 57 are attached to the right end of the upper end surface of the second measuring column beam, and the sixth measuring strain gauge 56 and the eighth measuring strain gauge 58 are attached to the right end of the lower end surface of the second measuring column beam. The fifth measuring strain gauge 55, the sixth measuring strain gauge 56, the seventh measuring strain gauge 57 and the eighth measuring strain gauge 58 are sequentially connected to form an electric bridge, which is marked as U2;

[0064] Figure 7 A wiring diagram of the U2 bridge is given, where R55 represents the resistance of the fifth strain gauge 55, R56 represents the resistance of the sixth strain gauge 56, R57 represents the resistance of the seventh strain gauge 57, and R58 represents the resistance of the eighth strain gauge 58;

[0065] The ninth measuring strain gauge 59 is pasted on the left end of the upper end surface of the measuring column beam No. 1, the eleventh measuring strain gauge 511 is pasted on the left end of the lower end surface of the measuring column beam No. 1, the twelfth measuring strain gauge 512 is pasted on the right end of the upper end surface of the measuring column beam No. 1, the tenth measuring strain gauge 510 is pasted on the right end of the lower end surface of the measuring column beam No. 1, the sixteenth measuring strain gauge 516 is pasted on the left end of the upper end surface of the measuring column beam No. 3, the fourteenth measuring strain gauge 514 is pasted on the left end of the lower end surface of the measuring column beam No. 3, the thirteenth measuring strain gauge 513 is pasted on the right end of the upper end surface of the measuring column beam No. 3, and the The fifteenth measuring strain gauge 515 is attached to the right end of the lower end surface of the measuring column beam No. 1, the ninth measuring strain gauge 59 and the tenth measuring strain gauge 510 are connected in series to form a first bridge circuit, the eleventh measuring strain gauge 511 and the twelfth measuring strain gauge 512 are connected in series to form a second bridge circuit, the thirteenth measuring strain gauge 513 and the fourteenth measuring strain gauge 514 are connected in series to form a third bridge circuit, the fifteenth measuring strain gauge 515 and the sixteenth measuring strain gauge 516 are connected in series to form a fourth bridge circuit, and the first bridge circuit, the second bridge circuit, the third bridge circuit and the fourth bridge circuit form an electric bridge, which is marked as U3;

[0066] Figure 8 A wiring diagram of the U3 bridge is given, R59 represents the measurement of the resistance of the ninth strain gauge 59, R510 represents the measurement of the resistance of the tenth strain gauge 510, R511 represents the measurement of the resistance of the eleventh strain gauge 511, R512 represents the measurement of the resistance of the twelfth strain gauge 512, R513 represents the measurement of the resistance of the thirteenth strain gauge 513, R514 represents the measurement of the resistance of the fourteenth strain gauge 514, R515 represents the measurement of the resistance of the fifteenth strain gauge 515, and R516 represents the measurement of the resistance of the sixteenth strain gauge 516;

[0067] The seventeenth measuring strain gauge 517 and the eighteenth measuring strain gauge 518 are attached to the left end of the outer side surface of the first measuring column beam, and the nineteenth measuring strain gauge 519 and the twentieth measuring strain gauge 520 are attached to the left end of the outer side surface of the third measuring column beam. The seventeenth measuring strain gauge 517, the eighteenth measuring strain gauge 518, the nineteenth measuring strain gauge 519 and the twentieth measuring strain gauge 520 are sequentially connected to form an electric bridge and marked as U4;

[0068] Fig. 9 A wiring diagram of the U4 bridge is given, where R517 represents the measurement of the resistance of the seventeenth strain gauge 517, R518 represents the measurement of the resistance of the eighteenth strain gauge 518, R519 represents the measurement of the resistance of the nineteenth strain gauge 519, and R520 represents the measurement of the resistance of the twentieth strain gauge 520;

[0069] The 21st measuring strain gauge 521 and the 22nd measuring strain gauge 522 are pasted on the right end of the outer side surface of the measuring column beam No. 1, and the 23rd measuring strain gauge 523 and the 24th measuring strain gauge 524 are pasted on the right end of the outer side surface of the measuring column beam No. 3. The 21st measuring strain gauge 521, the 22nd measuring strain gauge 522, the 23rd measuring strain gauge 523 and the 24th measuring strain gauge 524 are connected in sequence to form an electric bridge, which is marked as U5.

[0070] Fig.10 A wiring diagram of the U5 bridge is given, where R521 represents the measurement of the resistance of the twenty-first strain gauge 521, R522 represents the measurement of the resistance of the twenty-second strain gauge 522, R523 represents the measurement of the resistance of the twenty-third strain gauge 523, and R524 represents the measurement of the resistance of the twenty-fourth strain gauge 524;

[0071] The present invention proposes a leaf hinge torque balance with built-in bridge correction and anti-interference. The interference elimination measurement beam 23 serves as an elastic body, which can eliminate the interference of the wing load or the internal stress of the fixed end installation on the balance, so that the interference stress of the thin wing load deformation is filtered, and the influence of the interference stress on the leaf hinge torque balance is reduced, so as to realize the accurate measurement of the leaf hinge torque balance and effectively solve the problem of the wing load deformation affecting the accuracy of the leaf hinge torque balance.

[0072] By correcting the formula, the residual interference stress transmitted through the transfer end, the interference elimination measuring beam and the transition end can be corrected.

[0073] The above embodiments are merely exemplary descriptions of the present invention and do not limit its protection scope. Those skilled in the art may also make partial changes thereto, which are within the protection scope of the present invention as long as they do not exceed the spirit of the present invention.

Claims

1. A sheet-type hinge torque balance structure with built-in bridge correction, characterized in that: The invention comprises a wing (1), a plate-type hinge moment balance (2) and a control surface to be measured (3), wherein the plate-type hinge moment balance (2) comprises a fixed end (21), a transmission end (22), a disturbance-eliminating measurement beam (23), a transition end (24), a measurement elastic beam (25) and a model end (26), wherein the fixed end (21) is connected to the wing (1), the transmission end (22) and the transition end (24) are located on the same side of the fixed end (21), the transmission end (22) is connected to the fixed end (21), a gap is provided between the transition end (24) and the fixed end (21), and the disturbance-eliminating measurement beam (23) is composed of a plurality of plate-beam components arranged at intervals, one end of a plurality of the plate-beam components is connected to the transmission end (22), and a plurality of the plate-beam components are connected to the transmission end (22). The other end of the component is connected to the transition end (24); the measuring elastic beam (25) is composed of a plurality of column beam components arranged at intervals; one end of the plurality of column beam components is connected to a side of the transition end (24) away from the fixed end (21); the other ends of the plurality of column beam components are connected to the model end (26); the length direction of the measuring elastic beam (25) is parallel to the flap swing axis of the wing (1); the rudder surface (3) to be measured is arranged on a side of the model end (26) away from the wing (1); the rudder surface (3) to be measured is L-shaped; one end of the rudder surface (3) to be measured is a measuring portion; the other end of the rudder surface (3) to be measured is a connecting portion connected to the model end (26); the length direction of the measuring portion is parallel to the measuring elastic beam (25); A first interference elimination strain gauge (41) is affixed to the upper end surface of the sheet beam component closest to the fixed end (21), a second interference elimination strain gauge (42) is affixed to the lower end surface of the sheet beam component closest to the fixed end (21), a third interference elimination strain gauge (43) is affixed to the upper end surface of the sheet beam component farthest from the fixed end (21), and a fourth interference elimination strain gauge (44) is affixed to the lower end surface of the sheet beam component farthest from the fixed end (21). The first interference elimination strain gauge (41), the second interference elimination strain gauge (42), the third interference elimination strain gauge (43) and the fourth interference elimination strain gauge (44) constitute a correction bridge and are marked as .

2. A sheet-type hinge torque balance structure with built-in bridge correction according to claim 1, characterized in that: The stiffness of the transition end (24) is greater than the stiffness of the interference elimination measurement beam (23) and the stiffness of the measurement elastic beam (25).

3. A sheet-type hinge torque balance structure with built-in bridge correction according to claim 1, characterized in that: The sheet-type hinge torque balance (2) is integrally formed.

4. A sheet-type hinge torque balance structure with built-in bridge correction according to claim 1, characterized in that: The leaf hinge moment balance (2) is a steel component.

5. A correction method for a plate-type hinge torque balance with a built-in bridge correction, which is realized by relying on a plate-type hinge torque balance structure with a built-in bridge correction as claimed in any one of claims 1 to 4, characterized in that: The following steps are involved: Step 1: According to the test requirements, a number of measuring strain gauges are attached to the column and beam components to form a number of balance component measuring bridges, which are marked as U1, U2, ..., U n ; Step 2: Fix the wing (1) to the calibration equipment, apply the calibration load to the control surface (3) for the first time according to the calibration load table, and measure , U1, U2...U n The strain output is used to obtain the loading data of the wing (1) under unloaded conditions and the working formula of the hinge moment balance (2), and U1, U2, ... n The unloaded output difference is recorded as ΔU i不受载 , where i=1, 2, ..., n, The output data is recorded as U 消扰不受载零点 ; Step 3: Apply wing load to the wing (1) to simulate the load condition of the wing (1) in the actual wind tunnel test. 修正 After the strain output is generated, the rudder surface to be tested (3) is loaded with the calibration load for the second time according to the calibration load table, and the measurement is performed again. , U1, U2...U i The strain output, and U1, U2...U n The load output difference is recorded as ΔU i受载 , where i=1, 2, ..., n, The output data is recorded as U 消扰受载零点 ; Step 4: Calculate U1, U2, ..., U respectively n Correction factor K Ui天平 , where i=1, 2, ..., n, K Ui天平 The calculation formula is as follows: K Ui天平 =(ΔU i受载 -ΔU i不受载 ) / ΔU i不受载 / (U 消扰受载零点 -U 消扰不受载零点 ) Step 5: Correction coefficient K Ui天平 Correct U1, U2, ..., U respectively n The bridge output value; Step 6: Add and subtract the bridge output values ​​corrected in step 5 to obtain U1, U2, ... U n The actual bridge output difference ΔU i风洞 , where i = 1, 2, ... n, and use the working formula obtained in step 2 to calculate the correction data of the aerodynamic load actually applied to the aircraft model in the force measurement wind tunnel test. When the aircraft model is actually subjected to the force measurement wind tunnel test, ΔU i风洞 The difference after balance interference correction is ΔU i风洞修正 , then ΔU i风洞修正 Calculated by the following formula: ΔU i风洞修正 =ΔU i风洞 / [1+K Ui天平 ×(U 消扰受载零点 -U 消扰不受载零点 )]。

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