Helicopter blade rigidity detection device and detection method

Abstract

The invention discloses a helicopter blade rigidity detection device which comprises a detection table, a flapping rigidity detection mechanism and a torsional rigidity detection mechanism. The driving source I is provided with a power output end I, the power output end I is connected with the limiting piece I, and the power output end I is driven to advance or retreat in the flapping direction of the helicopter blade to be tested; the tension and pressure detection element is used for detecting tension and pressure data between the limiting piece I and the power output end I; the distance detection element is used for detecting forward or backward distance data of the power output end I; the rotor is used for limiting the head part of the helicopter blade to be tested; the driving source II is provided with a power output end II, and the rotor is driven by the power output end II to rotate around a 1 / 4 chord line of the helicopter blade to be tested; the torque detection element is used for detecting torque data of rotor swinging; the angle detection element is used for detecting the swinging angle data of the rotor; the rigidity detection precision of the helicopter blade can be improved.

Description

Technical Field

[0001] The invention relates to the field of helicopter blade stiffness detection, and in particular to a helicopter blade stiffness detection device and a detection method. Background Art

[0002] Current technologies have poor accuracy in detecting the stiffness of helicopter blades;

[0003] The errors in swing stiffness testing include the influence of the self-mass on the measurement results, the influence of the deadweight or friction of the measuring mechanism on the measurement results, and the errors in the installation, use or adjustment of the sensor, all of which have certain influencing factors;

[0004] The errors that exist in torsional stiffness testing include: due to the existence of torsional load, the preset measuring point and the actual measuring point on the blade are not the same point, and the measurement result of the measuring point position is an approximate value, which affects the measurement result. The detection error of this measurement method also includes the measurement error accumulated by multiple sensors, resulting in low measurement accuracy of the entire detection device.

[0005] Therefore, in order to solve the above problems, a helicopter blade stiffness detection device and detection method are needed, which can optimize the detection results of the above-mentioned flapping stiffness detection and torsional stiffness detection, reduce the influence of environmental, operational and detection factors on the measurement results, and improve the stiffness detection accuracy of helicopter blades. Summary of the invention

[0006] In view of this, the purpose of the present invention is to overcome the defects in the prior art and provide a helicopter blade stiffness detection device and detection method, which can optimize the detection results of the above-mentioned flapping stiffness detection and torsional stiffness detection, reduce the influence of environmental, operational and detection factors on the measurement results, and improve the stiffness detection accuracy of helicopter blades.

[0007] The helicopter blade stiffness detection device of the present invention comprises a detection platform, a flapping stiffness detection mechanism and a torsional stiffness detection mechanism;

[0008] The detection table in this solution is in the form of a stand structure, which is used to provide a flat working surface and to install a swing stiffness detection mechanism and a torsional stiffness detection mechanism. The overall detection mechanism has a high degree of integration, high space utilization, and can control costs.

[0009] The flapping stiffness detection mechanism includes a blade root clamping block I, a limiter I, a driving source I, a tension and pressure detection element and a distance detection element;

[0010] The blade root clamping block I is arranged on the test bench, and the blade root clamping block I is used to limit the root of the helicopter blade to be tested; the limiter I is arranged on the test bench through the ball I, and the limiter I is used to limit the head of the helicopter blade to be tested; the setting of the ball I can reduce the friction between the test bench and the limiter I, and the ball I in this scheme is several, which can reduce the friction as much as possible and reduce the influence of external environmental factors on the swing stiffness test results;

[0011] The driving source I is arranged on the testing platform, and the driving source I has a power output terminal I, and the power output terminal I is connected to the limiter I, and the power output terminal I is driven to move forward or backward along the swinging direction of the helicopter blade to be tested; it has the advantages of better stability, stronger operability, higher detection efficiency and detection accuracy;

[0012] The tension and pressure detection element is used to detect the tension and pressure data between the limiter I and the power output terminal I; the distance detection element is used to detect the forward or backward distance data of the power output terminal I.

[0013] In this scheme, the driving source I is a push rod of the prior art, which can preferably realize the push-pull function in the set direction, and will not be repeated here; the pulling and pressure detection element is any pulling and pressure sensor of the prior art, which can preferably obtain the pulling and pressure data of the specified position, and will not be repeated here; the distance detection element is any displacement sensor of the prior art, which can preferably obtain the displacement data of the specified position, and will not be repeated here.

[0014] More specifically, the shell of the push rod serving as the driving source I is limited on the testing platform by an articulated seat, the shell of the push rod and the articulated seat are hingedly arranged, and the articulated axis of the articulated push rod shell is parallel to the extension direction of the helicopter blade to be tested; the tension pressure sensor is arranged between the power output end of the push rod and the limiter I, the tension pressure sensor is fixed to the connecting end of the push rod, the tension pressure sensor is hinged to the connecting end of the limiter I, and the articulated axis of the articulated tension pressure sensor and the limiter I is parallel to the extension direction of the helicopter blade to be tested; the shell of the displacement sensor is fixed on the push rod shell, the front end of the telescopic rod of the displacement sensor is fixed to the power output end of the push rod, and the telescopic rod of the displacement sensor is arranged in parallel with the power output rod of the push rod, so that the detection end of the displacement sensor records data synchronously with the advancement or retreat of the power output end of the push rod; the influence of external factors on the measurement results is reduced, and more accurate detection parameters are obtained.

[0015] The torsional stiffness detection mechanism includes a blade root clamping block II, a limiter II, a driving source II, a torque detection element and an angle detection element;

[0016] The blade root clamping block II is arranged on the testing platform, and the blade root clamping block II is used to limit the root of the helicopter blade to be tested; the limiting member II includes a stator and a rotor, the stator is arranged on the testing platform, the rotor is arranged on the stator, and the rotor is used to limit the head of the helicopter blade to be tested;

[0017] The driving source II is arranged on the testing platform, and the driving source II has a power output terminal II, and the power output terminal II is transmission-connected with the rotor, and the rotor is driven by the power output terminal II to rotate around the 1 / 4 chord of the helicopter blade to be tested; the stability is better, the operability is stronger, and the detection efficiency and detection accuracy are higher;

[0018] The torque detection element is used to detect torque data of the rotor swing; the angle detection element is used to detect angle data of the rotor swing.

[0019] In the present scheme, the driving source II is a driving motor of the prior art, which is preferably capable of outputting a set torque, and will not be described in detail here; the torque detection element is any torque sensor of the prior art, which is preferably capable of obtaining torque data of a specified position, and will not be described in detail here; the angle detection element is any angle sensor of the prior art, which is preferably capable of obtaining angle data of a specified position, and will not be described in detail here.

[0020] More specifically, the housing of the driving motor as the driving source II is limited on the test bench through a fixing seat, and the power output shaft of the driving motor is parallel to the extension direction of the blades of the helicopter to be tested, wherein the present solution further comprises a transmission assembly, the transmission assembly is used to input the power of the driving motor to the rotor, the transmission assembly comprises a driving tooth coaxially fixed with the power output shaft of the driving motor and a driven tooth coaxially fixed with the rotation center of the rotor, the driving tooth and the driven tooth are in transmission cooperation, and the driven tooth is driven to rotate by the driving tooth;

[0021] The active gear is connected to the power output shaft of the drive motor through a connecting shaft, and the connecting shaft equipped with the movable output gear is combined with the power output shaft of the drive motor through any coupling in the prior art to form a whole, wherein the active gear is also limited by a connecting shaft shell fixed to the stator, and the connecting shaft equipped with the movable output gear can be driven to rotate and penetrate through the connecting shaft shell, and the active gear and the power output shaft of the drive motor are arranged on both sides of the connecting shaft shell, so as to further ensure the detection accuracy of the torsional stiffness and reduce the influence of the rotation decline of the long shaft end and the rotational deflection of the long shaft end;

[0022] The torque sensor is arranged between the power output shaft of the driving motor and the connecting shaft equipped with the active gear, and the two ends of the torque sensor are respectively fixed on the power output shaft of the driving motor and the connecting shaft equipped with the active gear;

[0023] The angle sensor is set on the detection table through an auxiliary bracket. The detection end of the angle sensor is provided with a functional gear, which cooperates with the driven gear transmission. The functional gear is driven by the driven gear so that the rotation angle of the rotor is collected by the angle sensor; the influence of external factors on the measurement results is reduced, and more accurate detection parameters are obtained.

[0024] The blade root clamping block I and the blade root clamping block II simulate helicopter rotor blade clamps and are respectively arranged on the test bench. The root of the helicopter blade to be tested is limited in a detachable manner by two bolts arranged in parallel, which is convenient for disassembly and assembly and has high structural strength, thereby ensuring the accuracy of the stiffness test results.

[0025] Furthermore, the torsional stiffness detection mechanism also includes an assembly stand, which is fixed on the detection table, and the stator limits the rotor in a ring sleeve manner, and a ball II is arranged between the stator and the rotor; that is, the connection structure of the stator and the rotor in this scheme is similar to the structure of a bearing, the stator is fixed on the assembly stand, and the rotor is driven to rotate and installed in the stator, and the two are coaxial, which can better specify the rotation angle and rotation accuracy of the rotor; the housing of the drive motor is fixed on the assembly stand through a fixed seat, the angle sensor is fixed on the assembly stand through an auxiliary bracket, the connecting shaft housing is fixed on the assembly stand, the driven tooth is fixed on the rotor, and the rotation center of the driven tooth coincides with the rotation center of the rotor to ensure the accuracy of the detection result, and the driven tooth in this scheme is an arc-shaped rack, which can limit the deflection angle of the rotor and prevent the occurrence of situations such as the breakage of the helicopter blade to be tested caused by overload. The assembly stand of this scheme integrates the various frames of the torsional stiffness detection mechanism into a unified whole, which can improve the transmission accuracy and the detection accuracy.

[0026] Furthermore, it also includes an auxiliary pad, which is driven to support the helicopter blade to be tested on the test bench or release the support for the helicopter blade to be tested. The top of the auxiliary pad has a positioning groove, which is used to limit the deflection of the helicopter blade to be tested. Through the use of the auxiliary pad in this solution, the helicopter blade to be tested can be supported by the test bench even in the unassembled test state, which is more conducive to the installation of the helicopter blade to be tested on the test mechanism. When the helicopter blade to be tested is assembled on the test mechanism, the auxiliary pad no longer forms a support for the helicopter blade to be tested, thereby ensuring the detection accuracy of the required parameters of the helicopter blade to be tested.

[0027] Further, the limiting member I has a limiting cavity I, the inner wall surface of the limiting cavity I is parallel to the blade surface of the helicopter blade to be tested, and after the helicopter blade to be tested is limited by the limiting member I, the inner wall surface of the limiting cavity I is in contact with the limited blade surface of the helicopter blade to be tested;

[0028] The limiting of the helicopter blade to be tested is made more reliable and the detection result is more accurate. The limiting component I of the present scheme includes a driven sliding slide and a limiting strip detachably assembled on the slide. The slide is in an inverted "T" shape as a whole. Its transverse plate is used as a bottom plate to assemble a plurality of ball bearings I to reduce friction. Its vertical plate is used as an assembly plate to assemble the limiting strip. The limiting strip and the assembly plate are combined to form a limiting cavity I that can be controlled to open and close, thereby facilitating the limiting of the helicopter blade to be tested on the limiting component I. The power output end I of the driving source I is arranged on the back of the assembly plate, opposite to the limiting strip, and a reinforcing rib connecting the transverse plate and the assembly plate is arranged on one side of the power output end I of the assembly plate, thereby improving the reliability of the overall structure and facilitating the test of the flapping stiffness of the helicopter blade to be tested.

[0029] The rotor has a limiting cavity II, the inner wall surface of the limiting cavity II is parallel to the blade surface of the helicopter blade to be tested, and after the helicopter blade to be tested is limited by the rotor, the inner wall surface of the limiting cavity II is in contact with the limited blade surface of the helicopter blade to be tested;

[0030] This makes the limiting of the helicopter blade to be tested more reliable and the detection result more accurate. In this scheme, a limit seat is formed at a position close to the rotation center of the rotor. The rotor also includes a limit cover plate that can be detachably assembled on the limit seat. The limit seat and the limit cover plate are combined to form a limit cavity II that can be controlled to open and close, which is conducive to limiting the helicopter blade to be tested on the rotor. The limit cavity II is close to the top surface of the test bench in the height direction, which improves the reliability of the overall structure and is conducive to ensuring the test of the torsional stiffness of the helicopter blade to be tested.

[0031] Furthermore, after the helicopter blade to be tested is limited by the limiter I, the connection point between the power output end I and the limiter I is close to the 1 / 4 chord line of the helicopter blade to be tested in the height direction. The optimal structure of close proximity is overlap, and the overlap of the two is ensured as much as possible during actual assembly and use, so as to further improve the accuracy of the results of the flapping stiffness detection.

[0032] Furthermore, after the helicopter blade to be tested is limited by the rotor, the rotation center of the rotor approximately coincides with the 1 / 4 chord line of the helicopter blade to be tested. The approximate coincidence means that the two theoretically remain coincident, and the approximation includes the influence of factors such as manufacturing and assembly on the actual results, which will not be repeated here, further improving the accuracy of the results of the torsional stiffness detection.

[0033] Furthermore, a limiting portion is connected to the stator, and a limiting end is provided on the rotor, and the limiting end is controlled to be engaged with or disconnected from the limiting portion so that the rotor is positioned at a specified position of the stator or released from the specified position of the stator.

[0034] In this solution, the limiting portion is a functional hole formed on the assembly bench, and the limiting end is a support arm formed on the rotor, which extends radially outward from the rotor. A matching hole is provided on the support arm, and the matching hole can coincide with the functional hole. The torsional stiffness detection mechanism also includes a plug pin, and the functional hole and the matching hole are connected by the plug pin so that the rotor is limited on the assembly bench. In this state, the rotor and the stator form a whole and cannot be driven to rotate, which is used to more conveniently assemble the helicopter blades to be tested on the torsional stiffness detection mechanism. After the helicopter blades to be tested are assembled on the torsional stiffness detection mechanism, the plug pin is removed so that the rotor can be driven to rotate relative to the stator. In this state, the torsional stiffness of the helicopter blades can be detected.

[0035] Furthermore, the stator is provided with an angle limiter, and the angle limiters are two respectively provided at the front and rear sides of the rotation direction of the limit end;

[0036] The rotor is regulated to rotate within a preset angle by the travel limit of the limit end by the two angle limit members.

[0037] In this solution, the angle limiter includes a fixed base and an adjusting rod. The fixed base is fixed on the assembly stand. The adjusting rod is a design structure of a bolt and a nut. A screw hole for the bolt thread to pass through is provided on the fixed base, so that the screw rod can adjust the extension length on the fixed base to limit the rotation angle of the rotor. The angle limiter is two arranged on the front and rear sides of the rotation direction of the support arm, which play a protective function.

[0038] The present solution also discloses a helicopter blade stiffness detection method based on the helicopter blade stiffness detection device, comprising the following detection steps:

[0039] S1. The swing stiffness detection mechanism runs without load to obtain the tension and pressure data of the limiter I in the preset stroke I;

[0040] The torsional stiffness detection mechanism is operated without load to obtain the torque data of the rotor at a preset angle I;

[0041] S2. The helicopter blade to be tested is assembled on the flapping stiffness detection mechanism, the flapping stiffness detection mechanism is started, and the tension and pressure data II of the limiter I in the preset stroke are obtained;

[0042] Alternatively, if the helicopter blade to be tested is assembled on the torsional stiffness detection mechanism, the torsional stiffness detection mechanism is started to obtain torque data II of the rotor at a preset angle;

[0043] S3. Pull and pressure data II - Pull and pressure data I obtain the measured value of the pull and pressure of the helicopter blade to be tested;

[0044] Torque data II-torque data I obtains the actual torque value of the helicopter blade to be tested.

[0045] Among them, step S1 can obtain data uniformly according to actual conditions and send them to the computer for processing. In actual operation, only step S2 needs to be practiced. The obtained data can be directly uploaded to the computer to obtain the measured value, and then the measured value is used to calculate the required data. This can greatly shorten the detection process, and the detection accuracy can be strictly controlled, the structure is more accurate, and it has a higher reference value.

[0046] The beneficial effects of the present invention are as follows: a helicopter blade stiffness detection device and a detection method disclosed in the present invention make the detection integration and efficiency higher through the setting of a flapping stiffness detection mechanism and a torsional stiffness detection mechanism, and the detection data of the helicopter blade to be tested by using the flapping stiffness detection mechanism and the torsional stiffness detection mechanism of the present scheme is more real and accurate, which greatly improves the finished product quality of the helicopter blade to be tested. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] The present invention will be further described below in conjunction with the accompanying drawings and embodiments:

[0048] Figure 1 It is a structural schematic diagram of the present invention;

[0049] Figure 2 It is a schematic diagram of the main structure of the present invention;

[0050] Figure 3 It is a schematic diagram of the top view structure of the present invention;

[0051] Figure 4 It is a side view structural schematic diagram of the present invention;

[0052] Figure 5 For the present invention Figure 3 Schematic diagram of the AA structure. DETAILED DESCRIPTION

[0053] Figure 1 It is a structural schematic diagram of the present invention; Figure 2 It is a schematic diagram of the main structure of the present invention; Figure 3 It is a schematic diagram of the top view structure of the present invention; Figure 4 It is a side view structural schematic diagram of the present invention; Figure 5 For the present invention Figure 3 AA structural schematic diagram, as shown in the figure, the helicopter blade stiffness detection device in this embodiment includes a detection platform 1, a flapping stiffness detection mechanism and a torsional stiffness detection mechanism;

[0054] The testing platform 1 in this solution is a bench-like structure, which is used to provide a flat working surface and to install a swing stiffness testing mechanism and a torsional stiffness testing mechanism. The overall testing mechanism has a high degree of integration, high space utilization, and can control costs.

[0055] The flapping stiffness detection mechanism includes a blade root clamping block Ⅰ2, a limiter Ⅰ3, a driving source Ⅰ4, a tension and pressure detection element 5 and a distance detection element 6;

[0056] The blade root clamping block Ⅰ2 is arranged on the test bench 1, and the blade root clamping block Ⅰ2 is used to limit the root of the helicopter blade to be tested; the limiter Ⅰ3 is arranged on the test bench 1 through the ball Ⅰ7, and the limiter Ⅰ3 is used to limit the head of the helicopter blade to be tested; the setting of the ball Ⅰ7 can reduce the friction between the test bench 1 and the limiter Ⅰ3, and the ball Ⅰ7 in this scheme is several, which can reduce the friction as much as possible and reduce the influence of external environmental factors on the swing stiffness test results;

[0057] The driving source I4 is arranged on the testing platform 1, and has a power output terminal I, and the power output terminal I is connected to the limiter I3, and the power output terminal I is driven to move forward or backward along the swinging direction of the helicopter blade to be tested; it has the advantages of better stability, stronger operability, higher detection efficiency and detection accuracy;

[0058] The tension and pressure detection element 5 is used to detect the tension and pressure data between the limiter Ⅰ3 and the power output terminal Ⅰ; the distance detection element 6 is used to detect the forward or backward distance data of the power output terminal Ⅰ.

[0059] In this solution, the driving source Ⅰ4 is a push rod of the prior art, which can preferably realize the push-pull function in the set direction, and will not be repeated here; the pulling and pressure detection element 5 is any pulling and pressure sensor of the prior art, which can preferably obtain the pulling and pressure data of the specified position, and will not be repeated here; the distance detection element 6 is any displacement sensor of the prior art, which can preferably obtain the displacement data of the specified position, and will not be repeated here.

[0060] More specifically, the shell of the push rod serving as the driving source Ⅰ4 is limited on the test bench 1 by an articulated seat, the shell of the push rod and the articulated seat are hingedly arranged, and the articulated axis of the articulated push rod shell is parallel to the extension direction of the helicopter blade to be tested; the tension pressure sensor is arranged between the power output end of the push rod and the limiter Ⅰ3, the tension pressure sensor is fixed to the connecting end of the push rod, the connecting end of the tension pressure sensor and the limiter Ⅰ3 is hinged, and the articulated axis of the articulated tension pressure sensor and the limiter Ⅰ3 is parallel to the extension direction of the helicopter blade to be tested; the shell of the displacement sensor is fixed on the push rod shell, the front end of the telescopic rod of the displacement sensor is fixed to the power output end of the push rod, and the telescopic rod of the displacement sensor is arranged in parallel with the power output rod of the push rod, so that the detection end of the displacement sensor records data synchronously with the advancement or retreat of the power output end of the push rod; the influence of external factors on the measurement results is reduced, and more accurate detection parameters are obtained.

[0061] The torsional stiffness detection mechanism includes a blade root clamping block II8, a limiter II, a driving source II9, a torque detection element 10 and an angle detection element 11;

[0062] The blade root clamping block II8 is arranged on the test bench 1, and the blade root clamping block II8 is used to limit the root of the helicopter blade to be tested; the limiting member II includes a stator 12 and a rotor 13, the stator 12 is arranged on the test bench 1, and the rotor 13 is arranged on the stator 12, and the rotor 13 is used to limit the head of the helicopter blade to be tested;

[0063] The driving source II 9 is arranged on the testing platform 1, and the driving source II 9 has a power output terminal II, and the power output terminal II is transmission-connected with the rotor 13, and the rotor 13 is driven by the power output terminal II to rotate around the 1 / 4 chord of the helicopter blade to be tested; it has the advantages of better stability, stronger operability, higher detection efficiency and detection accuracy;

[0064] The torque detection element 10 is used to detect torque data of the swing of the rotor 13 ; the angle detection element 11 is used to detect angle data of the swing of the rotor 13 .

[0065] In the present solution, the driving source II9 is ​​a driving motor of the prior art, which is preferably capable of outputting a set torque, and will not be described in detail here; the torque detection element 10 is any torque sensor of the prior art, which is preferably capable of obtaining torque data of a specified position, and will not be described in detail here; the angle detection element 11 is any angle sensor of the prior art, which is preferably capable of obtaining angle data of a specified position, and will not be described in detail here.

[0066] More specifically, the housing of the driving motor as the driving source II9 is ​​limited on the test bench 1 through a fixing seat, and the power output shaft of the driving motor is parallel to the extension direction of the blades of the helicopter to be tested, wherein the present scheme further includes a transmission assembly, the transmission assembly is used to input the power of the driving motor to the rotor 13, the transmission assembly includes a driving tooth 14 fixed coaxially with the power output shaft of the driving motor and a driven tooth 15 fixed coaxially with the rotation center of the rotor 13, the driving tooth 14 and the driven tooth 15 are matched in transmission, and the driven tooth 15 is driven to rotate by the driving tooth 14;

[0067] The active gear 14 is connected to the power output shaft of the drive motor through a connecting shaft, and the connecting shaft equipped with the dynamic output gear is combined with the power output shaft of the drive motor through any coupling in the prior art to form a whole, wherein the active gear 14 is also limited by a connecting shaft shell fixed to the stator 12, and the connecting shaft equipped with the dynamic output gear can be driven to rotate and penetrate through the connecting shaft shell, and the active gear 14 and the power output shaft of the drive motor are arranged on both sides of the connecting shaft shell, so as to further ensure the detection accuracy of the torsional stiffness and reduce the influence of the rotation decline of the long shaft end and the rotation deflection of the long shaft end;

[0068] The torque sensor is arranged between the power output shaft of the driving motor and the connecting shaft on which the driving gear 14 is assembled, and the two ends of the torque sensor are respectively fixed on the power output shaft of the driving motor and the connecting shaft on which the driving gear 14 is assembled;

[0069] The angle sensor is arranged on the detection platform 1 through an auxiliary bracket. A functional gear is arranged at the detection end of the angle sensor. The functional gear cooperates with the driven gear 15 in transmission. Driven by the driven gear 15, the functional gear makes the rotation angle of the rotor 13 collected by the angle sensor, thereby reducing the influence of external factors on the measurement results and obtaining more accurate detection parameters.

[0070] The blade root clamping block Ⅰ2 and the blade root clamping block Ⅱ8 simulate the helicopter rotor blade clamps and are respectively arranged on the test bench 1. The root of the helicopter blade to be tested is limited in a detachable manner by two bolts arranged in parallel, which is convenient for disassembly and assembly and has a high structural strength, thereby ensuring the accuracy of the stiffness test results.

[0071] In this embodiment, the torsional stiffness detection mechanism further includes an assembly stand 16, which is fixed on the detection platform 1, and the stator 12 limits the rotor 13 in a ring-shaped manner, and a ball II is arranged between the stator 12 and the rotor 13; that is, the connection structure of the stator 12 and the rotor 13 is similar to the structure of a bearing in this scheme, the stator 12 is fixed on the assembly stand 16, and the rotor 13 is driven to rotate and installed in the stator 12, and the two are coaxial, which can better regulate the rotation angle and rotation accuracy of the rotor 13; the housing of the drive motor is fixed on the assembly stand 16 through a fixing seat The angle sensor is fixed on the assembly stand 16 through an auxiliary bracket, the connecting shaft housing is fixed on the assembly stand 16, the driven tooth 15 is fixed on the rotor 13, and the rotation center of the driven tooth 15 coincides with the rotation center of the rotor 13 to ensure the accuracy of the detection result. In this scheme, the driven tooth 15 is an arc-shaped rack, which can limit the deflection angle of the rotor 13 and prevent the occurrence of blade breakage of the helicopter to be tested caused by overload. The assembly stand 16 of this scheme integrates the various frames of the torsional stiffness detection mechanism into a unified whole, which can improve the transmission accuracy and the detection accuracy.

[0072] In this embodiment, an auxiliary pad 17 is also included, and the auxiliary pad 17 is driven to support the helicopter blade to be tested on the test bench 1 or release the support for the helicopter blade to be tested. The top of the auxiliary pad 17 has a positioning groove, and the positioning groove is used to limit the deflection of the helicopter blade to be tested. Through the use of the auxiliary pad 17 in this solution, the helicopter blade to be tested can also be supported by the test bench 1 in the unassembled test state, which is more conducive to the installation of the helicopter blade to be tested on the test mechanism. When the helicopter blade to be tested is assembled on the test mechanism, the auxiliary pad 17 no longer forms a support for the helicopter blade to be tested, thereby ensuring the detection accuracy of the required parameters of the helicopter blade to be tested.

[0073] In this embodiment, the limiting member I3 has a limiting cavity I, and the inner wall surface of the limiting cavity I is parallel to the blade surface of the helicopter blade to be tested. After the helicopter blade to be tested is limited by the limiting member I3, the inner wall surface of the limiting cavity I is in contact with the limited blade surface of the helicopter blade to be tested;

[0074] In order to make the limiting of the helicopter blade to be tested more reliable and the detection result more accurate, the limiting part Ⅰ3 of the present scheme includes a sliding seat driven to slide and a limiting strip detachably assembled on the sliding seat, the sliding seat is in an inverted "T" shape as a whole, and its transverse plate is used as a bottom plate to assemble a plurality of balls Ⅰ7 to reduce friction, and its vertical plate is used as an assembly plate to assemble the limiting strip, and the limiting strip and the assembly plate are enclosed to form a limiting cavity Ⅰ that can be controlled to open and close, so as to facilitate limiting the helicopter blade to be tested on the limiting part Ⅰ3, wherein the power output end Ⅰ of the driving source Ⅰ4 is arranged on the back of the assembly plate, opposite to the limiting strip, and a reinforcing rib connecting the transverse plate and the assembly plate is arranged on one side of the power output end Ⅰ of the assembly plate, so as to improve the reliability of the overall structure and facilitate the test of the flapping stiffness of the helicopter blade to be tested.

[0075] The rotor 13 has a limiting cavity II, the inner wall surface of the limiting cavity II is parallel to the blade surface of the helicopter blade to be tested, and after the helicopter blade to be tested is limited by the rotor 13, the inner wall surface of the limiting cavity II is in contact with the limited blade surface of the helicopter blade to be tested;

[0076] In order to make the limiting of the helicopter blade to be tested more reliable and the detection result more accurate, a limiting seat is formed near the rotation center of the rotor 13 in this scheme, and the rotor 13 also includes a limiting cover plate that can be detachably assembled on the limiting seat. The limiting seat and the limiting cover plate are surrounded to form a limiting cavity II that can be controlled to open and close, so as to facilitate limiting the helicopter blade to be tested on the rotor 13. The limiting cavity II is close to the top surface of the test bench 1 in the height direction, which improves the reliability of the overall structure and is conducive to ensuring the test of the torsional stiffness of the helicopter blade to be tested.

[0077] In this embodiment, after the helicopter blade to be tested is limited by the limiter I3, the connection point between the power output end I and the limiter I is close to the 1 / 4 chord line of the helicopter blade to be tested in the height direction. The optimal structure of close proximity is overlap. In actual assembly and use, the overlap of the two is ensured as much as possible to further improve the accuracy of the results of detecting the flapping stiffness.

[0078] In this embodiment, after the helicopter blade to be tested is limited by the rotor 13, the rotation center of the rotor approximately coincides with the 1 / 4 chord line of the helicopter blade to be tested. The approximate coincidence means that the two theoretically remain coincident, and the approximation includes the influence of factors such as manufacturing and assembly on the actual results, which will not be repeated here, further improving the accuracy of the results of detecting torsional stiffness.

[0079] In this embodiment, a limiting portion is connected to the stator 12, and a limiting end 18 is provided on the rotor 13. The limiting end 18 is controlled to be engaged with or disconnected from the limiting portion so that the rotor 13 is positioned at a specified position of the stator 12 or released from the specified position of the stator 12.

[0080] In this solution, the limiting portion is a functional hole formed on the assembly stand 16, and the limiting end 18 is a support arm formed on the rotor 13, which extends radially outward from the rotor 13. A matching hole is provided on the support arm, and the matching hole can coincide with the functional hole. The torsional stiffness detection mechanism also includes a plug pin 19, and the functional hole and the matching hole are connected by the plug pin 19 so that the rotor 13 is limited on the assembly stand 16. In this state, the rotor 13 and the stator 12 form a whole and cannot be driven to rotate, which is used to more conveniently assemble the helicopter blades to be tested on the torsional stiffness detection mechanism. After the helicopter blades to be tested are assembled on the torsional stiffness detection mechanism, the plug pin 19 is removed so that the rotor 13 can be driven to rotate relative to the stator 12. In this state, the torsional stiffness of the helicopter blades can be detected.

[0081] In this embodiment, the stator 12 is provided with an angle limiter 20, and the angle limiters 20 are two respectively provided at the front and rear sides of the limit end 18 in the rotation direction;

[0082] The rotor 13 is regulated to rotate within a preset angle by the travel limit of the limit end 18 by the two angle limit members 20 .

[0083] In this solution, the angle limiter 20 includes a fixed base and an adjusting rod. The fixed base is fixed on the assembly stand 16. The adjusting rod is a design structure of a bolt and a nut. A screw hole for the bolt thread to pass through is provided on the fixed base, so that the screw rod can adjust the extension length on the fixed base to limit the rotation angle of the rotor 13. The angle limiter 20 is two arranged on the front and rear sides of the rotation direction of the support arm, which play a protective function.

[0084] The present solution also discloses a helicopter blade stiffness detection method based on the helicopter blade stiffness detection device, comprising the following detection steps:

[0085] S1. The swing stiffness detection mechanism is operated without load to obtain the tension and pressure data of the limiter Ⅰ3 in the preset stroke Ⅰ;

[0086] The torsional stiffness detection mechanism operates at no load to obtain torque data I of the rotor 13 at a preset angle;

[0087] S2. The helicopter blade to be tested is assembled on the flapping stiffness detection mechanism, the flapping stiffness detection mechanism is started, and the tension and pressure data of the limiter Ⅰ3 in the preset stroke Ⅱ is obtained; more specifically, the driving source Ⅰ4, the tension and pressure detection element 5 and the distance detection element 6 are started to obtain the corresponding data;

[0088] Alternatively, if the helicopter blade to be tested is assembled on the torsional stiffness detection mechanism, the torsional stiffness detection mechanism is started to obtain the torque data II of the rotor 13 at the preset angle; more specifically, the driving source II 9, the torque detection element 10 and the angle detection element 11 are started to obtain the corresponding data;

[0089] S3. Pull and pressure data II - Pull and pressure data I obtain the measured value of the pull and pressure of the helicopter blade to be tested;

[0090] Torque data II-torque data I obtains the actual torque value of the helicopter blade to be tested.

[0091] Among them, step S1 can obtain data uniformly according to actual conditions and send them to the computer for processing. In actual operation, only step S2 needs to be practiced. The obtained data can be directly uploaded to the computer to obtain the measured value, and then the measured value is used to calculate the required data. This can greatly shorten the detection process, and the detection accuracy can be strictly controlled, the structure is more accurate, and it has a higher reference value.

[0092] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the purpose and scope of the technical solution of the present invention, which should be included in the scope of the claims of the present invention.

Claims

1. A helicopter blade stiffness detection device, characterized in that: It includes a testing platform, a swing stiffness testing mechanism and a torsional stiffness testing mechanism; The flapping stiffness detection mechanism includes a blade root clamping block I, a limiter I, a driving source I, a tension and pressure detection element and a distance detection element; The blade root clamping block I is arranged on the testing platform, and the blade root clamping block I is used to limit the root of the helicopter blade to be tested; The limiting member I is arranged on the testing platform through the ball I, and the limiting member I is used to limit the front part of the helicopter blade to be tested; The driving source I is arranged on the testing platform, and the driving source I has a power output terminal I, and the power output terminal I is connected to the limiter I, and the power output terminal I is driven to move forward or backward along the swinging direction of the helicopter blade to be tested; The tension and pressure detection element is used to detect the tension and pressure data between the limiter I and the power output terminal I; the distance detection element is used to detect the forward or backward distance data of the power output terminal I; The torsional stiffness detection mechanism includes a blade root clamping block II, a limiter II, a driving source II, a torque detection element and an angle detection element; The blade root clamping block II is arranged on the testing platform, and the blade root clamping block II is used to limit the root of the helicopter blade to be tested; the limiting member II includes a stator and a rotor, the stator is arranged on the testing platform, the rotor is arranged on the stator, and the rotor is used to limit the head of the helicopter blade to be tested; The torque detection element is used to detect torque data of the rotor swing; the angle detection element is used to detect angle data of the rotor swing.

2. The helicopter blade stiffness detection device according to claim 1, characterized in that: The device also includes an auxiliary pad, which is driven to support the helicopter blade to be tested on the testing platform or to release the support for the helicopter blade to be tested.

3. The helicopter blade stiffness detection device according to claim 1, characterized in that: The limiting member I has a limiting cavity I, the inner wall surface of the limiting cavity I is parallel to the blade surface of the helicopter blade to be tested, and after the helicopter blade to be tested is limited by the limiting member I, the inner wall surface of the limiting cavity I is in contact with the limited blade surface of the helicopter blade to be tested; The rotor has a limiting cavity II, the inner wall surface of the limiting cavity II is parallel to the blade surface of the helicopter blade to be tested, and after the helicopter blade to be tested is limited by the rotor, the inner wall surface of the limiting cavity II fits with the limited blade surface of the helicopter blade to be tested.

4. The helicopter blade stiffness detection device according to claim 1, characterized in that: After the helicopter blade to be tested is limited by the limiting member I, the connection point between the power output end I and the limiting member I is close to the 1 / 4 chord line of the helicopter blade to be tested in the height direction.

5. The helicopter blade stiffness detection device according to claim 1, characterized in that: After the helicopter blade to be tested is limited by the rotor, the rotation center of the rotor approximately coincides with the 1 / 4 chord line of the helicopter blade to be tested.

6. The helicopter blade stiffness detection device according to claim 1, characterized in that: The stator limits the rotor in a ring-shaped manner, and a ball II is arranged between the stator and the rotor.

7. The helicopter blade stiffness detection device according to claim 6, characterized in that: The stator is connected with a limiting portion, and the rotor is provided with a limiting end, and the limiting end is controlled to be combined with or disconnected from the limiting portion.

8. The helicopter blade stiffness detection device according to claim 7, characterized in that: The stator is provided with an angle limiter, and the angle limiters are two respectively provided at the front side and the rear side of the rotation direction of the limit end; The rotor is regulated to rotate within a preset angle by the travel limit of the limit end by the two angle limit members.

9. A method for detecting helicopter blade stiffness based on the helicopter blade stiffness detection device according to any one of claims 1 to 8, characterized in that: The following detection steps are included: S1. The swing stiffness detection mechanism runs without load to obtain the tension and pressure data of the limiter I in the preset stroke I; The torsional stiffness detection mechanism is operated without load to obtain the torque data of the rotor at a preset angle I; S2. The helicopter blade to be tested is assembled on the flapping stiffness detection mechanism, the flapping stiffness detection mechanism is started, and the tension and pressure data II of the limiter I in the preset stroke are obtained; Alternatively, if the helicopter blade to be tested is assembled on the torsional stiffness detection mechanism, the torsional stiffness detection mechanism is started to obtain torque data II of the rotor at a preset angle; S3. Pull and pressure data II - Pull and pressure data I obtain the measured value of the pull and pressure of the helicopter blade to be tested; Torque data II-torque data I obtains the actual torque value of the helicopter blade to be tested.

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