CN120756668A - A test device and method for tiltrotor transmission - Google Patents
A test device and method for tiltrotor transmissionInfo
- Publication number
- CN120756668A CN120756668A CN202511201286.4A CN202511201286A CN120756668A CN 120756668 A CN120756668 A CN 120756668A CN 202511201286 A CN202511201286 A CN 202511201286A CN 120756668 A CN120756668 A CN 120756668A
- Authority
- CN
- China
- Prior art keywords
- transmission
- bevel gear
- load
- gear
- torque
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a test device and a test method for transmission of a tiltrotor aircraft, wherein the test device comprises a test platform, a turnover driving mechanism and a rotation driving mechanism are respectively arranged on the test platform, the turnover driving mechanism is connected with the rotation driving mechanism through a synchronizing mechanism, the rotation driving mechanism is used for synchronously driving two tiltrotor simulation systems to rotate, the two tiltrotor simulation systems are respectively arranged on two synchronous tilting bases, the turnover driving mechanism is in transmission connection with the two synchronous tilting bases, the turnover driving mechanism is used for driving the two bases to synchronously tilt, and the synchronizing mechanism is connected with the tiltrotor simulation systems, the rotation driving mechanism and the turnover driving mechanism in series, so that the tilting driving mechanism drives the bases to rotate synchronously while the tilting rotor simulation systems and the rotation driving mechanism rotate synchronously. The method comprises the steps S1-S11. The invention can carry out transmission test and experiment of various flight attitudes, can realize quantitative and qualitative evaluation of transmission performance under dynamic random working conditions, and effectively improves the accuracy and rationality of the transmission test and experiment of the rotor wing.
Description
Technical Field
The invention relates to the field of rotor wing transmission test, in particular to a test device and a test method for transmission of a tiltrotor aircraft.
Background
As a more efficient aircraft, tiltrotor aircraft can greatly reduce the take-off and landing distance and increase the cruising speed relative to fixed wing aircraft and helicopters. However, when the tilting rotorcraft changes the flight mode in the flight process, the rotor is tilted at an angle, and the overall transmission performance requirement is higher, so that the transmission system of the tilting rotorcraft needs to be subjected to complex design and test to ensure that the transmission system can keep the stability and transmission performance of the overall structure when the tilting rotorcraft is switched between the take-off and landing state and the cruising state, and the problems of severe vibration, uneven stress and the like of the transmission system are avoided. The existing rotor wing test device can only realize the rotation test of a rotor wing of a helicopter, cannot realize the test of the transmission of a tilting rotorcraft, and cannot realize the transmission test of the rotation and tilting linkage of the rotor wing. Therefore, it is desirable to provide a testing device and method for tiltrotor aircraft transmission.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a testing device and a method for transmission of a tiltrotor aircraft, which can simulate the working states of a transmission system of the tiltrotor aircraft in different flight states and different environments and evaluate the transmission performance.
In order to achieve the aim of the invention, the invention adopts the following technical scheme:
the utility model provides a tilting gyroplane driven test device, it includes test platform, be provided with tilting drive mechanism and rotation drive mechanism on the test platform respectively, be connected through synchro between tilting drive mechanism and the rotation drive mechanism, rotation drive mechanism is used for two tilting gyroplane simulation systems of synchronous drive to rotate, two tilting gyroplane simulation systems are installed respectively on two bases that incline in step, tilting drive mechanism is connected with the base transmission that two synchronous tilts, tilting drive mechanism is used for driving two bases and inclines in step, tilting gyroplane simulation system is established ties to synchro, rotation drive mechanism and tilting drive mechanism, tilting gyroplane simulation system and rotation drive mechanism synchronous rotation when making tilting drive mechanism drive base upset.
Further, the rotation driving mechanism comprises a T-shaped transmission box, two first driving motors are respectively arranged on two sides of the T-shaped transmission box, a first rotation speed torque sensor is arranged between the two first driving motors and the T-shaped transmission box, two ends of the first rotation speed torque sensor are respectively connected with a first input end, a second input end and two first driving motors on two sides of the T-shaped transmission box through a coupler, and an output end of the T-shaped transmission box is respectively connected with load motors on the two bases through a rotor wing transmission mechanism in a transmission mode.
Further, a first bevel gear is arranged in the T-shaped transmission box, the first bevel gear is arranged on a first input shaft, one end of the first input shaft is used as a first input end of the T-shaped transmission box, a second bevel gear is arranged on the other end of the first input shaft, two sides of the second bevel gear are meshed with two middle bevel gears, a third bevel gear is meshed between the two middle bevel gears, the second bevel gear, the two middle bevel gears and the third bevel gear are enclosed to form a mouth shape, the two middle bevel gears are symmetrically arranged on the first bevel gear through L-shaped shafts to form circle centers, the third bevel gear is arranged on a second input shaft, the second input shaft is used as a second input end of the T-shaped transmission box, the first bevel gear is meshed with a fourth bevel gear in the T-shaped transmission box, and the fourth bevel gear is arranged on an output end of the T-shaped transmission box.
Further, the rotor transmission mechanism comprises a fifth bevel gear arranged at the output end of the T-shaped transmission box, the fifth bevel gear is meshed with a sixth bevel gear arranged on the first transmission shaft, the first transmission shaft is perpendicular to the output end of the T-shaped transmission box, seventh bevel gears are arranged at two ends of the first transmission shaft, the seventh bevel gears at two ends are respectively arranged at one end of two second transmission shafts, the second transmission shafts are perpendicular to the first transmission shaft, eighth bevel gears are respectively arranged at the other ends of the two second transmission shafts, the eighth bevel gears on the two second transmission shafts are respectively meshed with a ninth bevel gear arranged at one end of the two third transmission shafts, the other ends of the two third transmission shafts are respectively connected with two tilting rotor simulation systems through a synchronous mechanism, and the first transmission shaft, the second transmission shafts and the third transmission shafts are arranged on the test platform through bearing seats.
Further, the tilting rotor simulation system comprises a load motor arranged on the base, the output end of the load motor is in transmission connection with a second rotating speed torque sensor, and the second rotating speed torque sensor is connected with the synchronous mechanism through a coupler;
The synchronous mechanism comprises a swinging box, a tenth bevel gear and an eleventh bevel gear, the tenth bevel gear is connected with the second rotating speed torque sensor through a coupler, the tenth bevel gear is meshed with the eleventh bevel gear arranged at the other end of the third transmission shaft, the eleventh bevel gear and the tenth bevel gear are arranged in the swinging box, and the third transmission shaft stretches into the swinging box and coaxially rotates relative to the third transmission shaft.
Further, the overturning driving mechanism comprises an overturning driving motor, a third rotating speed torque sensor and a reduction gearbox which are sequentially connected with the overturning driving motor in a transmission way, the output end of the reduction gearbox is connected with a fourth transmission shaft, the end part of the fourth transmission shaft is sequentially provided with a bevel gear A and a bevel gear B, a gap for accommodating a bevel gear C and a bevel gear D which are distributed on two sides of the fourth transmission shaft is arranged between the bevel gear A and the bevel gear B, and the bevel gear C and the bevel gear D are meshed with the bevel gear A;
Bevel gear C and bevel gear D set up the one end at the coaxial fifth transmission shaft in both sides respectively, and the other end of both sides fifth transmission shaft is provided with first gear and second gear respectively, and first gear passes through intermediate gear transmission with the third gear and is connected, second gear and fourth gear engagement, bevel gear B and the bevel gear E meshing that sets up in the middle part of the sixth transmission shaft, and the sixth transmission shaft is coaxial with two third transmission shafts, and the both ends of the sixth transmission shaft are connected with the hangers that the swing case both sides set up.
Further, the base comprises a base plate, swing rods are respectively arranged on two sides of the base plate, the swing rods on two sides are respectively distributed on two sides of the swing box, the end part of one swing rod is arranged on an extension section of the swing bearing support through a shaft sleeve, the extension section is of a hollow structure and is rotationally connected with the shaft sleeve, a semicircular lantern ring is arranged at the end part of the other swing rod, the lantern ring is coaxially arranged with the third gear and the fourth gear, and the lantern ring is synchronously rotated with the third gear and the fourth gear through bolt connection;
The two sides of the suspension loops are rotationally connected to the two sides of the swing bearing support, the suspension loops are rotationally connected with bearings on the swing bearing support, the end part of the sixth transmission shaft penetrates through the swing bearing support on one side of the suspension loops to be fixedly connected with the suspension loops on one side of the suspension loops, and the third gear and the fourth gear are respectively rotationally connected to the extension section of the swing bearing support on one side through bearings.
Further, the fourth transmission shaft is installed on the test platform through two bearing frames, an overturning limiting mechanism is arranged on the fourth transmission shaft between the two bearing frames and comprises a limiting rotary table, two spaced limiting pins are arranged on the side face of the limiting rotary table, one limiting pin is fixed, the other limiting pin is inserted into a limiting pin hole formed in the limiting rotary table, at least two limiting pins are arranged in parallel in the limiting pin hole, limiting shafts for blocking the limiting pins are arranged on the bearing frames, the limiting shafts are matched with the limiting pins to limit the tilting angle of the base, and the other limiting pins are respectively inserted into different limiting pin holes to adjust the tilting angle range of the base.
The test method of the test device for the transmission of the tiltrotor aircraft comprises the following steps:
s1, starting a first driving motor or a second driving motor to output set torque And rotational speedThe first rotational speed torque sensor collects the actual torque output by the first drive motor or the second drive motor under the zero load conditionAnd rotational speed;
S2, a second rotating speed and torque sensor collects torque under the zero load conditionAnd rotational speedCalculating a transmission torque errorAnd transmission speed error;
S3, constructing a wind speed power spectrum model under random fluctuation of wind load turbulence;
;
wherein f is the frequency, As frequency fluctuation coefficient, frequency coefficientTaking outA random number between the two random numbers,Taking 50-100 m for low-altitude flight and V as the target wind speed (m/s) of the test for the turbulence length,To be based on the variance of the longitudinal wind speed of the turbulence intensity,For the tested turbulent wind speed power, T is the load period, and N is the number of times of applying load in the load period;
s4, setting fixed turbulence wind speed power, and calculating fluctuation wind speed values at different moments T in a load period T according to a wind speed power spectrum model And based on fluctuating wind speed valuesCalculating the load forces at different moments in the load period T;
;
Wherein, the For air density, c is the experimentally set chord length of the rotor, r is the rotor radius,The resistance generated by the rotor wing is U, which is the rotation speed of the rotor wing;
s5, according to the load force Calculating the load torque of the rotor at different moments in the load period T;
;
Wherein, the The length of the load unit of the rotor wing;
S6, starting the load motor to load dynamic load, so that the torque data acquired by the second rotating speed torque sensor meets the load torque And obtain real-time rotation speed;
S7, driving the swinging box and the base to swing reciprocally at a fixed speed by the overturning driving motor;
s8, collecting the load torque by a first rotational speed torque sensor Real-time torque under conditionsAnd real-time rotational speedAnd according to the transmission torque errorAnd transmission speed errorCalculating torque ripple values under different load conditionsAnd a rotational speed fluctuation value;
;
S9, according to the torque fluctuation valueAnd a rotational speed fluctuation valueUniformly taking m sampling points in a load period T, and obtaining torque fluctuation value data corresponding to each sampling pointAnd rotational speed fluctuation value data,The torque fluctuation value corresponding to the mth sampling point,The rotation speed fluctuation value corresponding to the mth sampling point is t m, and the time corresponding to the mth sampling point is t m;
S10, setting the allowable value of torque fluctuation And allowable value of rotational speed fluctuationCalculating a transmission performance coefficient f of the rotor transmission mechanism in a test period T;
;
where k is the number of the sampling point, For the torque ripple value corresponding to the kth sampling point,The rotation speed fluctuation value corresponding to the kth sampling point is t k, the time corresponding to the kth sampling point is t k,The weight coefficients of torque fluctuation and rotation speed fluctuation on rotor transmission performance are respectively taken as general;
S11, setting a threshold value of a transmission performance coefficientIf (if)The transmission performance of the rotor transmission mechanism meets the requirements, otherwise, the requirements are not met.
The invention has the beneficial effects that the load motor is arranged to provide the working load for the constructed tested rotor transmission mechanism to simulate the real working environment, and the load motor outputs real-time random dynamic load to further realize the simulation and test of the real working environment. The overturning driving motor is used as an overturning swinging power source, realizes the synchronization of overturning and rotation of the rotor wing through the serial connection of the synchronous mechanisms, can carry out transmission test and test of various flight attitudes, can realize quantitative and qualitative evaluation of transmission performance under dynamic random working conditions, and effectively improves the accuracy and rationality of the transmission test and test of the rotor wing.
Drawings
Fig. 1 is a perspective view of a test setup for tiltrotor aircraft transmission.
Fig. 2 is a block diagram of a tiltrotor simulation system in series with a tiltrotor drive mechanism.
Fig. 3 is a structural view of the turnover limiting mechanism.
Fig. 4 is a connection structure diagram of the sixth transmission shaft and the swing case.
The device comprises a first driving motor, 2, a first rotating speed torque sensor, 3, a T-shaped transmission case, 4, a first bevel gear, 5, an intermediate bevel gear, 6, a fourth bevel gear, 7, a fifth bevel gear, 8, a first transmission shaft, 9, a seventh bevel gear, 10, a second transmission shaft, 11, a third transmission shaft, 12, a ninth bevel gear, 13, a swinging case, 14, a second rotating speed torque sensor, 15, a load motor, 16, a reduction gearbox, 17, a third rotating speed torque sensor, 18, a turnover driving motor, 19, a fourth transmission shaft, 20, a fifth transmission shaft, 21, a sixth transmission shaft, 22, a base plate, 23, a swinging rod, 24, a shaft sleeve, 25, a bevel gear B,26, a bevel gear A,27, a limit turntable, 28, a lantern ring, 29, a bearing seat, 30, a limit pin shaft, 31, a third gear, 32, a limit shaft, 33, an eleventh bevel gear, 34, an extension section, 35, a bolt, 36, a swinging bearing support, 37 and a hanging lug.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and all the inventions which make use of the inventive concept are protected by the spirit and scope of the present invention as defined and defined in the appended claims to those skilled in the art.
As shown in fig. 1-4, a test device for driving a tiltrotor comprises a test platform, wherein a turnover driving mechanism and a rotation driving mechanism are respectively arranged on the test platform, the turnover driving mechanism is connected with the rotation driving mechanism through a synchronizing mechanism, the rotation driving mechanism is used for synchronously driving two tiltrotor simulation systems to rotate, the two tiltrotor simulation systems are respectively arranged on two synchronous tilting bases, the turnover driving mechanism is in transmission connection with the two synchronous tilting bases, the turnover driving mechanism is used for driving the two bases to synchronously tilt, and the synchronizing mechanism is used for connecting the tiltrotor simulation systems, the rotation driving mechanism and the turnover driving mechanism in series, so that the tilting driving mechanism drives the bases to turn and simultaneously rotates synchronously with the rotation driving mechanism.
In the embodiment, the rotation driving mechanism comprises a T-shaped transmission case 3, two first driving motors 1 are respectively arranged on two sides of the T-shaped transmission case 3, a first rotation speed torque sensor 2 is arranged between the two first driving motors 1 and the T-shaped transmission case 3, two ends of the first rotation speed torque sensor 2 are respectively connected with a first input end, a second input end and two first driving motors 1 on two sides of the T-shaped transmission case 3 through a coupler, and output ends of the T-shaped transmission case 3 are respectively connected with load motors 15 on two bases through a rotor transmission mechanism in a transmission mode.
The two first driving motors 1 can be used as power devices of the rotor wing transmission mechanism, one of the first driving motors 1 is used as a main driving motor, the other first driving motor is used as a redundant driving motor, and when the main driving motor fails, the transmission mechanism is powered normally.
In the embodiment, a first bevel gear 4 is arranged in a T-shaped transmission box 3, the first bevel gear 4 is arranged on a first input shaft, one end of the first input shaft is used as a first input end of the T-shaped transmission box 3, a second bevel gear is arranged on the other end of the first input shaft, two sides of the second bevel gear are meshed with two middle bevel gears 5, a third bevel gear is meshed between the two middle bevel gears 5, the second bevel gear, the two middle bevel gears 5 and the third bevel gear are surrounded to form a mouth shape, the two middle bevel gears 5 are symmetrically arranged on the first bevel gear 4 through an L-shaped shaft to form a circle center, the third bevel gear is arranged on a second input shaft which is used as a second input end of the T-shaped transmission box 3, the first bevel gear 4 is meshed with a fourth bevel gear 6 in the T-shaped transmission box 3, and the fourth bevel gear 6 is arranged on an output end of the T-shaped transmission box 3. By the design of the T-shaped transmission case 3, the two first driving motors 1 can output power at the same time, and differential power output is realized.
In this embodiment, the rotor transmission mechanism includes a fifth bevel gear 7 mounted at the output end of the T-shaped transmission case 3, the fifth bevel gear 7 is meshed with a sixth bevel gear on the first transmission shaft 8, the first transmission shaft 8 is perpendicular to the output end of the T-shaped transmission case 3, both ends of the first transmission shaft 8 are respectively provided with a seventh bevel gear 9, both ends of the seventh bevel gear 9 are respectively provided with one end of two second transmission shafts 10, the second transmission shaft 10 is perpendicular to the first transmission shaft 8, the other ends of the two second transmission shafts 10 are respectively provided with an eighth bevel gear, the eighth bevel gears on the two second transmission shafts 10 are respectively meshed with a ninth bevel gear 12 provided at one ends of two third transmission shafts 11, the other ends of the two third transmission shafts 11 are respectively connected with two tiltrotor simulation systems through a synchronization mechanism, and the first transmission shaft 8, the second transmission shaft 10 and the third transmission shafts 11 are mounted on the test platform through bearing seats 29. The first transmission shaft 8, the second transmission shaft 10 and the third transmission shaft 11 form an equivalent rotor transmission mechanism by related bevel gears, so that the transmission process of the real rotor transmission mechanism can be effectively simulated.
In this embodiment, the tiltrotor simulation system includes a load motor 15 mounted on a base, and an output end of the load motor 15 is in transmission connection with a second rotational speed torque sensor 14, where the second rotational speed torque sensor 14 is connected with a synchronization mechanism through a coupling. The load motor 15 outputs the load borne by the rotor during flight to simulate the transmission under load conditions.
The synchronizing mechanism includes a swinging box 13, a tenth bevel gear and an eleventh bevel gear 33, the tenth bevel gear is connected with the second rotational speed torque sensor 14 through a coupling, the tenth bevel gear is meshed with the eleventh bevel gear 33 arranged at the other end of the third transmission shaft 11, the eleventh bevel gear 33 and the tenth bevel gear are arranged in the swinging box 13, and the third transmission shaft 11 extends into the swinging box 13 and rotates coaxially and relatively to the third transmission shaft 11.
In the embodiment, the overturning driving mechanism comprises an overturning driving motor 18, a third rotating speed torque sensor 17 and a reduction gearbox 16 which are sequentially connected with the overturning driving motor 18 in a transmission way, a fourth transmission shaft 19 is connected to the output end of the reduction gearbox 16, a bevel gear A26 and a bevel gear B25 are sequentially arranged at the end part of the fourth transmission shaft 19, a gap for accommodating bevel gears C and D distributed on two sides of the fourth transmission shaft 19 is arranged between the bevel gear A26 and the bevel gear B25, and the bevel gears C and D are meshed with the bevel gear A26;
Bevel gear C and bevel gear D set up the one end of the coaxial fifth transmission shaft 20 in both sides respectively, the other end of the both sides fifth transmission shaft 20 is provided with first gear and second gear respectively, the first gear is connected through the intermediate gear transmission with third gear 31, the second gear is meshed with fourth gear, bevel gear B25 is meshed with bevel gear E that the middle part of the sixth transmission shaft 21 set up, and the sixth transmission shaft 21 is coaxial with two third transmission shafts 11, the both ends of the sixth transmission shaft 21 are connected with hangers 37 that the both sides of swinging box 13 set up.
In this embodiment, the base includes a base plate 22, swing rods 23 are respectively disposed on two sides of the base plate 22, the swing rods 23 on two sides are respectively distributed on two sides of the swing box 13, an end portion of the swing rod 23 on one side is disposed on an extension section 34 of a swing bearing support 36 through a shaft sleeve 24, the extension section 34 is of a hollow structure, the extension section 34 is rotationally connected with the shaft sleeve 24, a semicircular collar 28 is disposed on an end portion of the swing rod 23 on the other side, the collar 28 is coaxially disposed with a third gear 31 and a fourth gear, and the collar 28 is connected with the third gear 31 and the fourth gear through bolts 35 for synchronous rotation.
The two side lugs 37 are rotatably connected to the two side swing bearing supports 36, the lugs 37 are rotatably connected with bearings on the swing bearing supports 36, the end of the sixth transmission shaft 21 penetrates through one side of the swing bearing supports 36 to be fixedly connected with one side of the lugs 37, and the third gear 31 and the fourth gear are respectively rotatably connected to the extension section 34 of one side of the swing bearing supports 36 through bearings.
The bevel gear C and the bevel gear D are meshed with the bevel gear A26 to cause the opposite steering directions of the fifth transmission shafts 20 on the two sides, so that an intermediate gear is arranged between the first gear and the third gear 31 to change the steering directions of the third gear 31, the third gear 31 and the fourth gear are guaranteed to have the same steering directions, and simultaneously, the hanging lugs of the swinging box 13 are rotationally connected with the swinging bearing support 36 to play a supporting role. The moment synchronization of the load motor 15 and the tilting process of the swinging box 13 is ensured, and the overturning driving motor 18 provides stable power for the tilting process of the swinging box 13 and the substrate 22. The function of the intermediate gear is to change the rotation direction of the driven gear so that the direction is uniform and the speed is uniform when the left and right base plates 22 are lifted and rotated.
In this embodiment, the fourth transmission shaft 19 is installed on the test platform through two bearing seats 29, a turnover limiting mechanism is arranged on the fourth transmission shaft 19 between the two bearing seats 29, the turnover limiting mechanism comprises a limiting turntable 27, two spaced limiting pins 30 are arranged on the side surface of the limiting turntable 27, one limiting pin 30 is fixed, the other limiting pin 30 is inserted into a limiting pin hole formed in the limiting turntable 27, at least two limiting pins are arranged in parallel in the limiting pin hole, a limiting shaft 32 for blocking the limiting pin 30 is arranged on the bearing seat 29, the limiting shaft 32 is matched with the limiting pin 30 to limit the tilting angle of the base, and the other limiting pin 30 is respectively inserted into different limiting pin holes to adjust the tilting angle range of the base.
The test method of the test device for the transmission of the tiltrotor aircraft comprises the following steps:
S1, starting the first drive motor 1 or the second drive motor to output set torque And rotational speedThe first rotational speed torque sensor 2 collects the actual torque output from the first drive motor 1 or the second drive motor under the zero load conditionAnd rotational speed;
S2, the second rotating speed and torque sensor 14 collects the torque under the zero load conditionAnd rotational speedCalculating a transmission torque errorAnd transmission speed error;
S3, constructing a wind speed power spectrum model under random fluctuation of wind load turbulence;
;
wherein f is the frequency, As frequency fluctuation coefficient, frequency coefficientTaking outA random number between the two random numbers,Taking 50-100 m for low-altitude flight and V as the target wind speed (m/s) of the test for the turbulence length,To be based on the variance of the longitudinal wind speed of the turbulence intensity,In the invention, when wind load power is loaded, a sine function is introduced to randomize frequency, and wind load under random frequency is calculated so as to achieve the purpose of simulating random wind load.
S4, setting fixed turbulence wind speed power, and calculating fluctuation wind speed values at different moments T in a load period T according to a wind speed power spectrum modelAnd based on fluctuating wind speed valuesCalculating the load forces at different moments in the load period T;
;
Wherein, the For air density, c is the experimentally set chord length of the rotor, r is the rotor radius,The resistance generated by the rotor wing is U, which is the rotation speed of the rotor wing;
s5, according to the load force Calculating the load torque of the rotor at different moments in the load period T;
;
Wherein, the The length of the load unit of the rotor wing;
S6, starting the load motor 15 to load dynamic load, so that the torque data acquired by the second rotating speed torque sensor 14 meets the load torque And obtain real-time rotation speed;
S7, a turnover driving motor 18 drives the swinging box 13 and the base to swing reciprocally at a fixed speed;
S8, the first rotational speed torque sensor 2 collects the load torque Real-time torque under conditionsAnd real-time rotational speedAnd according to the transmission torque errorAnd transmission speed errorCalculating torque ripple values under different load conditionsAnd a rotational speed fluctuation value;
;
S9, according to the torque fluctuation valueAnd a rotational speed fluctuation valueUniformly taking m sampling points in a load period T, and obtaining torque fluctuation value data corresponding to each sampling pointAnd rotational speed fluctuation value data,The torque fluctuation value corresponding to the mth sampling point,The rotation speed fluctuation value corresponding to the mth sampling point is t m, and the time corresponding to the mth sampling point is t m;
S10, setting the allowable value of torque fluctuation And allowable value of rotational speed fluctuationCalculating a transmission performance coefficient f of the rotor transmission mechanism in a test period T;
;
where k is the number of the sampling point, For the torque ripple value corresponding to the kth sampling point,The rotation speed fluctuation value corresponding to the kth sampling point is t k, the time corresponding to the kth sampling point is t k,The weight coefficients of torque fluctuation and rotation speed fluctuation on rotor transmission performance are respectively taken as general;
S11, setting a threshold value of a transmission performance coefficientIf (if)The transmission performance of the rotor transmission mechanism meets the requirements, otherwise, the requirements are not met.
The load motor 15 is arranged to provide a working load for the constructed rotor transmission mechanism to be tested so as to simulate the real working environment, and the real working environment is further simulated and tested by outputting a real-time random dynamic load through the load motor 15. The overturning driving motor 18 is used as a power source for overturning and swinging, realizes the synchronization of overturning and rotation of the rotor wing through the serial connection of the synchronous mechanisms, can carry out transmission test and experiment of various flight postures, can realize quantitative and qualitative evaluation of transmission performance under dynamic random working conditions, and effectively improves the accuracy and rationality of the transmission test and experiment of the rotor wing.
Claims (9)
1. The utility model provides a tilting gyroplane driven test device, its characterized in that, includes test platform, be provided with tilting drive mechanism and rotation drive mechanism on the test platform respectively, be connected through synchro between tilting drive mechanism and the rotation drive mechanism, rotation drive mechanism is used for synchronous drive two tilting gyroplane simulation systems to rotate, two tilting gyroplane simulation systems install respectively on two synchronous tilting's bases, tilting drive mechanism is connected with two synchronous tilting's base transmission, tilting drive mechanism is used for driving two bases and tilts in step, synchro series tilting gyroplane simulation system, rotation drive mechanism and tilting drive mechanism make tilting gyroplane simulation system and rotation drive mechanism synchronous rotation when tilting drive mechanism drive base upset.
2. The test device for the transmission of the tiltrotor aircraft according to claim 1, wherein the rotation driving mechanism comprises a T-shaped transmission box, two first driving motors are respectively arranged on two sides of the T-shaped transmission box, a first rotation speed torque sensor is arranged between the two first driving motors and the T-shaped transmission box, two ends of the first rotation speed torque sensor are respectively connected with a first input end, a second input end and two first driving motors on two sides of the T-shaped transmission box through a coupler, and an output end of the T-shaped transmission box is respectively connected with load motors on two bases through the rotor transmission mechanism in a transmission mode.
3. The tiltrotor aircraft transmission test device according to claim 2, wherein a first bevel gear is arranged in the T-shaped transmission box, the first bevel gear is arranged on a first input shaft, one end of the first input shaft serves as a first input end of the T-shaped transmission box, a second bevel gear is arranged on the other end of the first input shaft, two sides of the second bevel gear are meshed with two middle bevel gears, a third bevel gear is meshed between the two middle bevel gears, the second bevel gear, the two middle bevel gears and the third bevel gear are surrounded to form a mouth shape, the two middle bevel gears are symmetrically arranged on the first bevel gear through L-shaped shafts in circle centers, the third bevel gear is arranged on a second input shaft serving as a second input end of the T-shaped transmission box, the first bevel gear is meshed with a fourth bevel gear in the T-shaped transmission box, and the fourth bevel gear is arranged on an output end of the T-shaped transmission box.
4. The tiltrotor aircraft transmission test device according to claim 3, wherein the rotor transmission mechanism comprises a fifth bevel gear arranged at the output end of the T-shaped transmission box, the fifth bevel gear is meshed with a sixth bevel gear arranged on a first transmission shaft, the first transmission shaft is perpendicular to the output end of the T-shaped transmission box, seventh bevel gears are arranged at two ends of the first transmission shaft, the seventh bevel gears at two ends are respectively arranged at one ends of two second transmission shafts, the second transmission shaft is perpendicular to the first transmission shaft, eighth bevel gears are respectively arranged at the other ends of the two second transmission shafts, the eighth bevel gears on the two second transmission shafts are respectively meshed with a ninth bevel gear arranged at one ends of two third transmission shafts, the other ends of the two third transmission shafts are respectively connected with the two tiltrotor simulation systems through a synchronizing mechanism, and the first transmission shaft, the second transmission shafts and the third transmission shafts are respectively arranged on the test platform through bearing seats.
5. The tiltrotor aircraft transmission test apparatus of claim 4, wherein the tiltrotor simulation system comprises a load motor mounted on a base, an output of the load motor in driving connection with a second rotational speed torque sensor, the second rotational speed torque sensor in driving connection with a synchronization mechanism through a coupling;
The synchronous mechanism comprises a swinging box, a tenth bevel gear and an eleventh bevel gear, the tenth bevel gear is connected with the second rotating speed torque sensor through a coupler, the tenth bevel gear is meshed with the eleventh bevel gear arranged at the other end of the third transmission shaft, the eleventh bevel gear and the tenth bevel gear are arranged in the swinging box, and the third transmission shaft stretches into the swinging box and coaxially rotates relative to the third transmission shaft.
6. The tiltrotor aircraft transmission test device according to claim 5, wherein the turnover driving mechanism comprises a turnover driving motor, a third rotating speed torque sensor and a reduction gearbox which are sequentially connected with the turnover driving motor in a transmission manner, the output end of the reduction gearbox is connected with a fourth transmission shaft, the end part of the fourth transmission shaft is sequentially provided with a bevel gear A and a bevel gear B, a gap for accommodating bevel gears C and D distributed on two sides of the fourth transmission shaft is arranged between the bevel gears A and B, and the bevel gears C and D are meshed with the bevel gears A;
the bevel gears C and D are respectively arranged at one end of a fifth transmission shaft with the same shafts at two sides, a first gear and a second gear are respectively arranged at the other end of the fifth transmission shaft at two sides, the first gear and the third gear are connected through an intermediate gear transmission, the second gear is meshed with a fourth gear, the bevel gears B are meshed with bevel gears E arranged in the middle of a sixth transmission shaft, the sixth transmission shaft is coaxial with the two third transmission shafts, and two ends of the sixth transmission shaft are connected with hanging lugs arranged at two sides of the swinging box.
7. The tiltrotor aircraft transmission test device according to claim 6, wherein the base comprises a base plate, swing rods are respectively arranged on two sides of the base plate, the swing rods on two sides are respectively distributed on two sides of a swing box, the end part of one swing rod is arranged on an extension section of a swing bearing support through a shaft sleeve, the extension section is of a hollow structure, the extension section is rotationally connected with the shaft sleeve, a semicircular lantern ring is arranged on the end part of the other swing rod, the lantern ring is coaxially arranged with a third gear and a fourth gear, and the lantern ring is synchronously rotated with the third gear and the fourth gear through bolt connection;
the two sides are rotationally connected to the two side swing bearing supports, the hangers are rotationally connected with bearings on the swing bearing supports, the end part of the sixth transmission shaft penetrates through the swing bearing support on one side to be fixedly connected with the hangers on the other side, and the third gear and the fourth gear are respectively rotationally connected to the extension section of the swing bearing support on one side through bearings.
8. The tiltrotor aircraft transmission test device according to claim 7, wherein the fourth transmission shaft is mounted on the test platform through two bearing blocks, a turnover limiting mechanism is arranged on the fourth transmission shaft between the two bearing blocks, the turnover limiting mechanism comprises a limiting rotary table, two spaced limiting pins are arranged on the side face of the limiting rotary table, one limiting pin is fixed, the other limiting pin is inserted into a limiting pin hole formed in the limiting rotary table, at least two limiting pins are arranged in parallel in the limiting pin hole, a limiting shaft for blocking the limiting pin is arranged on the bearing block, and the limiting shaft is matched with the limiting pin to limit the tilting angle of the base, and the other limiting pin is respectively inserted into different limiting pin holes to adjust the tilting angle range of the base.
9. A method of testing a tiltrotor aircraft transmission test apparatus according to claim 8, comprising the steps of:
s1, starting a first driving motor or a second driving motor to output set torque And rotational speedThe first rotational speed torque sensor collects the actual torque output by the first drive motor or the second drive motor under the zero load conditionAnd rotational speed;
S2, a second rotating speed and torque sensor collects torque under the zero load conditionAnd rotational speedCalculating a transmission torque errorAnd transmission speed error;
S3, constructing a wind speed power spectrum model under random fluctuation of wind load turbulence;
;
wherein f is the frequency, As frequency fluctuation coefficient, frequency coefficientTaking outA random number between the two random numbers,For turbulence length, V is the target wind speed for the test,To be based on the variance of the longitudinal wind speed of the turbulence intensity,For the tested turbulent wind speed power, T is the load period, and N is the number of times of applying load in the load period;
s4, setting fixed turbulence wind speed power, and calculating fluctuation wind speed values at different moments T in a load period T according to a wind speed power spectrum model And based on fluctuating wind speed valuesCalculating the load forces at different moments in the load period T;
;
Wherein, the For air density, c is the experimentally set chord length of the rotor, r is the rotor radius,The resistance generated by the rotor wing is U, which is the rotation speed of the rotor wing;
s5, according to the load force Calculating the load torque of the rotor at different moments in the load period T;
;
Wherein, the The length of the load unit of the rotor wing;
S6, starting the load motor to load dynamic load, so that the torque data acquired by the second rotating speed torque sensor meets the load torque And obtain real-time rotation speed;
S7, driving the swinging box and the base to swing reciprocally at a fixed speed by the overturning driving motor;
s8, collecting the load torque by a first rotational speed torque sensor Real-time torque under conditionsAnd real-time rotational speedAnd according to the transmission torque errorAnd transmission speed errorCalculating torque ripple values under different load conditionsAnd a rotational speed fluctuation value;
;
S9, according to the torque fluctuation valueAnd a rotational speed fluctuation valueUniformly taking m sampling points in a load period T, and obtaining torque fluctuation value data corresponding to each sampling pointAnd rotational speed fluctuation value data,The torque fluctuation value corresponding to the mth sampling point,The rotation speed fluctuation value corresponding to the mth sampling point is t m, and the time corresponding to the mth sampling point is t m;
S10, setting the allowable value of torque fluctuation And allowable value of rotational speed fluctuationCalculating a transmission performance coefficient f of the rotor transmission mechanism in a test period T;
;
where k is the number of the sampling point, For the torque ripple value corresponding to the kth sampling point,The rotation speed fluctuation value corresponding to the kth sampling point is t k, the time corresponding to the kth sampling point is t k,The weight coefficients of torque fluctuation and rotation speed fluctuation on rotor transmission performance are respectively;
S11, setting a threshold value of a transmission performance coefficient If (if)The transmission performance of the rotor transmission mechanism meets the requirements, otherwise, the requirements are not met.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202511201286.4A CN120756668A (en) | 2025-08-26 | 2025-08-26 | A test device and method for tiltrotor transmission |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202511201286.4A CN120756668A (en) | 2025-08-26 | 2025-08-26 | A test device and method for tiltrotor transmission |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN120756668A true CN120756668A (en) | 2025-10-10 |
Family
ID=97249663
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202511201286.4A Pending CN120756668A (en) | 2025-08-26 | 2025-08-26 | A test device and method for tiltrotor transmission |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN120756668A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| US20160159471A1 (en) * | 2014-12-04 | 2016-06-09 | Elwha Llc | System and method for operation and management of reconfigurable unmanned aircraft |
| CN108146629A (en) * | 2018-02-07 | 2018-06-12 | 深圳市旗客智能技术有限公司 | Tilting rotor wing unmanned aerial vehicle |
| US20190023410A1 (en) * | 2017-07-23 | 2019-01-24 | Bell Helicopter Textron Inc. | Clutch with Synchronizer and Locking Mechanism |
| DE202022100818U1 (en) * | 2022-02-14 | 2022-05-03 | Georgiy Volodymyrovych Beylin | multicopter |
| CN115892463A (en) * | 2022-11-22 | 2023-04-04 | 中国人民解放军总参谋部第六十研究所 | Tilt rotor power transmission mechanism |
| CN117993090A (en) * | 2022-10-27 | 2024-05-07 | 中国科学院沈阳自动化研究所 | A method for analyzing test information of tilt-rotor UAV |
-
2025
- 2025-08-26 CN CN202511201286.4A patent/CN120756668A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160159471A1 (en) * | 2014-12-04 | 2016-06-09 | Elwha Llc | System and method for operation and management of reconfigurable unmanned aircraft |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| US20190023410A1 (en) * | 2017-07-23 | 2019-01-24 | Bell Helicopter Textron Inc. | Clutch with Synchronizer and Locking Mechanism |
| CN108146629A (en) * | 2018-02-07 | 2018-06-12 | 深圳市旗客智能技术有限公司 | Tilting rotor wing unmanned aerial vehicle |
| DE202022100818U1 (en) * | 2022-02-14 | 2022-05-03 | Georgiy Volodymyrovych Beylin | multicopter |
| CN117993090A (en) * | 2022-10-27 | 2024-05-07 | 中国科学院沈阳自动化研究所 | A method for analyzing test information of tilt-rotor UAV |
| CN115892463A (en) * | 2022-11-22 | 2023-04-04 | 中国人民解放军总参谋部第六十研究所 | Tilt rotor power transmission mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109612681B (en) | Aerodynamic interference measurement method of coaxial rigid rotor model of helicopter | |
| CN113670561B (en) | Wind tunnel test simulation method for obtaining aerodynamic interference characteristic of helicopter tail rotor | |
| CN102774509B (en) | Performance test bench for reaction torque device of helicopter | |
| CN111596571A (en) | Composite UAV semi-physical simulation system | |
| CN103381885A (en) | Multi-rotor wing aircraft | |
| CN205642791U (en) | Wind -tunnel is with toper motion simulation device of rotatory guided missile | |
| CN114166496B (en) | A tilt-rotor test device | |
| CN108275287B (en) | Multi-rotor aircraft aerodynamic interference and ground effect comprehensive test device and method | |
| CN113753261B (en) | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter | |
| CN115465472B (en) | A flapping-wing aircraft testing device | |
| CN104843177B (en) | Aircraft | |
| CN116588351A (en) | An electric multi-rotor configuration attitude parameter adjustment test bench | |
| CN204895843U (en) | Multiaxis aircraft | |
| CN205593740U (en) | Owner rotor shaft loading device goes straight up to based on equivalence blade | |
| CN202605730U (en) | Multi-rotor aircraft | |
| CN116625692A (en) | A gear-type coaxial counter-rotating dual-rotor system simulation test bench | |
| CN111516866B (en) | Single-drive tilting dual-rotor aircraft | |
| RU59251U1 (en) | STAND FOR TESTING THE SYSTEM OF THE DRIVE SYSTEM OF THE COXIAL CARRYING SCREWS OF THE HELICOPTER | |
| CN120756668A (en) | A test device and method for tiltrotor transmission | |
| CN218317402U (en) | Tilt rotor UAV iron bird test bed | |
| CN204623834U (en) | Aircraft | |
| CN112520026B (en) | A new type of transformable aircraft | |
| CN220164184U (en) | Electric multi-rotor wing configuration posture parameter adjusting test bed | |
| CN217864830U (en) | Tilt rotor power experimental device | |
| CN217146408U (en) | Attitude balance parameter adjusting test bed for multi-rotor unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |