CN110940480B - Pitching yawing forced vibration dynamic derivative test device used under high attack angle of high-speed flying wing model - Google Patents
Pitching yawing forced vibration dynamic derivative test device used under high attack angle of high-speed flying wing model Download PDFInfo
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- CN110940480B CN110940480B CN201911108080.1A CN201911108080A CN110940480B CN 110940480 B CN110940480 B CN 110940480B CN 201911108080 A CN201911108080 A CN 201911108080A CN 110940480 B CN110940480 B CN 110940480B
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
A pitching yawing forced vibration dynamic derivative test device used under a high attack angle of a high-speed flying wing model comprises: the device comprises a motor driving device, a rigid supporting device, a simple harmonic motion conversion device, a motion transmission device and a signal measuring device; the motor driving device is a torque output part of the whole dynamic derivative testing device; the rigid supporting device is used for installing the whole testing device in the wind tunnel and supporting the motor driving device, the simple harmonic motion conversion device and the signal measuring device; the simple harmonic motion conversion device converts the continuous rotary motion output by the motor driving device into simple harmonic motion required by the test and transmits the simple harmonic motion to the motion transmission device; the motion transmission device is directly connected to the middle part of the signal measurement device and drives the signal measurement device to do simple harmonic motion in a specified form; the signal measuring device measures force, moment and angular displacement signals in the whole movement process.
Description
Technical Field
The invention relates to a wind tunnel test device for measuring a pitching/yawing direction dynamic derivative of a high-speed flying wing model at a large attack angle by a small-amplitude forced vibration method.
Background
Both the aerodynamic design of an aircraft and the design of a control system require the provision of derivative data for the dynamic stability of the aircraft under its flight conditions. When the aircraft performs attitude change actions or is disturbed by air flow, pitching, yawing or rolling vibration deviating from the balanced attitude can occur. The purpose of the dynamic stability study is to predict the damping trends and laws of these vibrations. For the aircraft with passive damping control, the dynamic flight quality and reliability requirements of the aircraft place extremely high requirements on the prediction of the dynamic stability of the aircraft. Too low dynamic stability tends to cause divergence of the angular movements of the aircraft, which, in this way, will seriously affect the attitude of the aircraft. Therefore, accurate prediction of the dynamic derivative is important.
The dynamic derivative, also known as the dynamic stability derivative, is used to describe the aerodynamic characteristics of the aircraft in a maneuver and in a disturbance. Are the essential aerodynamic parameters in the design of the aerodynamic performance of the aircraft, the control system and the overall design. The derivatives of dynamic stability are important to aircraft designers because they provide the natural stability, control surface efficiency and maneuverability of the aircraft, and they also make the geometry of the aircraft of particular importance in the initial design process.
The flying wing layout aircraft is an aircraft with a medium aspect ratio aerodynamic profile, which is only composed of a fused wing body and a triangular/diamond/lambda wing surface with a sweepback angle of 50-60 degrees, and the whole aircraft has no plane tails, vertical tails, canard wings and other stabilizing surfaces and has no fuselage in the traditional sense. Sufficient inner space is provided for the overall arrangement of the airplane by reasonably setting the spanwise direction and the chordwise thickness distribution, the geometrical characteristics of smooth transition and high fusion are embodied in the appearance, and the aerodynamic force of the fusion flying wing layout aircraft presents a strong coupling characteristic. Under the constraint of high stealth and high maneuverability, flying wing layout aircrafts have gradually become the development direction of future aircrafts, such as European neuron unmanned fighter aircraft, American X-45C and X-47B aircraft, Chinese Risk aircraft, and American Grumann flying wing layout sensor aircrafts.
The flying wing layout aircraft has simple structure, high dynamic lift, good super maneuverability and excellent stealth performance. However, the flying wing layout aircraft has obvious disadvantages in the aspects of dynamic stability and control, for example, due to the lack of vertical tails and control surfaces and the need of satisfying stealth performance constraints, the flying wing layout aircraft lacks in lateral and heading stability and is insufficient in control efficiency, and generally, when flying in a stable boundary edge region, uncontrollable instability occurs in the process of over-maneuver. The defects and shortcomings of dynamic stability and control seriously restrict the wide application of the flying wing layout aircraft in future aircrafts.
The wind tunnel dynamic test technology is an important research means for researching the dynamic stability problems of the transverse and course unsteady aerodynamic force, aerodynamic coupling, cross coupling and the like of the flying wing layout aircraft, so that the dynamic derivative data of the flying wing layout aircraft with the small aspect ratio is obtained through the wind tunnel test, and important support is provided for researching the dynamic stability characteristics of the flying wing layout aircraft.
The conventional methods for wind tunnel dynamic stability derivative tests are a free vibration test method and a forced vibration test method, and the dynamic stability derivative is obtained by measuring aerodynamic force and moment acting on a model and measuring the motion parameters of the model. Because the free vibration test method is only suitable for measuring direct damping derivatives, can not measure cross and cross coupling derivatives, and can only measure positive damping derivatives, a forced vibration test method is mostly adopted for comprehensively obtaining the dynamic stability derivatives of the aircraft, particularly the cross and cross coupling derivatives.
The forced vibration test method is that a vibration exciter is used for driving a model to make simple harmonic vibration with fixed frequency and fixed amplitude under a certain degree of freedom, the response of the model generated in different degrees of freedom is measured through a strain balance, and the dynamic stability derivative is further obtained through data processing. The forced vibration test device mainly comprises an excitation device, a dynamic balance, a displacement sensor, a support rod and the like, and has the functions of providing the model to move in a wind tunnel test section according to a certain required rule and measuring the vibration amplitude, the vibration frequency, the force and the moment acting on the model.
Due to the appearance characteristics of the flying wing layout aircraft, aerodynamic load is large when Ma is 0.6-1.5 under a large attack angle (15-30 degrees), and the maximum normal force load of a 1.2-meter-level sub-span supersonic wind tunnel test model is 10000N, so that higher requirements are provided for a dynamic derivative test device, particularly a motor driving device, a rigid supporting device, a simple harmonic motion conversion device, a motion transmission device and a signal measurement device. In order to accurately measure the dynamic derivative data of the flying wing layout aircraft, a dynamic derivative test device aiming at the aircraft is urgently needed to be developed.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the device overcomes the defects of the prior art and provides a pitching yawing forced vibration dynamic derivative test device for a high-speed flying wing model under a large attack angle.
The technical solution of the invention is as follows: a pitching yawing forced vibration dynamic derivative test device used under a high attack angle of a high-speed flying wing model comprises: the device comprises a motor driving device, a rigid supporting device, a simple harmonic motion conversion device, a motion transmission device and a signal measuring device;
the motor driving device is a torque output part of the whole dynamic derivative testing device; the rigid supporting device is used for installing the whole testing device in the wind tunnel and supporting the motor driving device, the simple harmonic motion conversion device and the signal measuring device; the simple harmonic motion conversion device converts the continuous rotary motion output by the motor driving device into simple harmonic motion required by the test and transmits the simple harmonic motion to the motion transmission device; the motion transmission device is directly connected to the middle part of the signal measurement device and drives the signal measurement device to do simple harmonic motion in a specified form; the signal measuring device measures force, moment and angular displacement signals in the whole movement process.
Preferably, the signal measuring device is of an integrated structure, and a flying wing model is installed at the front end of the signal measuring device; the signal measuring device comprises a model connecting cone, a right rolling thin beam, a right rolling compensation thin beam, a pitching beam, a left rolling compensation thin beam, a left rolling thin beam, a yawing beam, a motion transfer device matching surface, an angle measuring beam, an angle moving beam and a rigid supporting device connecting cone; the front ends of the ten beams are connected with the rear end of a model connecting cone, and the rear ends of the ten beams are connected with the front end of a motion transfer device matching surface; the yaw beam and the angle measuring beam are distributed in a bilateral symmetry mode, and a pair of yaw beams and an angle measuring beam are respectively distributed; the front ends of the two yaw beams are connected to the rear end of the model connecting cone, and the rear ends of the two yaw beams are connected to the front end of the matching surface of the motion transmission device; the angle movement beam is positioned between the angle measurement beams, the front ends of the angle movement beam and the angle measurement beams are connected to the rear end of the matching surface of the movement transfer device, and the rear end of the angle movement beam and the rear end of the matching surface of the movement transfer device are connected to the front end of the connecting cone of the rigid supporting device; the two angle measuring beams play a supporting role, and the angle moving beam enables the matching surface of the motion transmission device and the front end part thereof to move around the center of the angle measuring beams.
Preferably, the thickness of the thin beam rolled on the right side and the thickness of the thin beam rolled on the left side are 0.5 mm-1.0 mm.
Preferably, the thickness of the right side rolling compensation thin beam and the thickness of the left side rolling compensation thin beam are 0.5 mm-1.0 mm.
Preferably, the thickness of the pitching beam is 8 mm-10 mm.
Preferably, the thickness of the yaw beam is 3 mm-5 mm.
Preferably, the thickness of the yaw beam is 3 mm-5 mm.
Preferably, the range of the gap a between the right rolling thin beam and the right rolling compensation thin beam is 0.8-1.2 mm.
Preferably, the range of the gap b between the thin rolling compensation beam and the pitching beam on the right side is 0.8-1.2 mm.
Preferably, the lengths of the right rolling thin beam, the right rolling compensation thin beam, the pitching beam, the left rolling compensation thin beam, the left rolling thin beam and the yawing beam are consistent, and the range is 35 mm-45 mm.
Preferably, the mating surface of the motion transfer device has a cross-sectional dimension of not less than 22mmx22mm and a length of not less than 28 mm.
Preferably, the angle moving beam comprises a front part, a middle part and a rear part, and the middle part is a straight beam with the thickness consistent with that of the angle measuring beam; the included angle d between the front part and the middle part is consistent with that between the front part and the middle part.
Preferably, the angle measuring beam has a thickness of 6.0mm to 8.0mm and a length of 27.5mm to 32.5 mm.
Preferably, the included angle d ranges from 40 ° to 50 °.
Preferably, the range of the gap c between the angle measuring beam and the angle moving beam is 0.8 mm-1.2 mm.
Preferably, the model connecting cone is connected with the model in a cone and screw matching mode, and the rigid supporting device connecting cone is connected with the rigid supporting device in a cone and wedge matching mode.
Preferably, the motion transmission device comprises a fixing ring, a moment beam connecting taper pin, a main moment beam (5), a secondary moment beam, a reinforcing beam fixing screw, a reinforcing beam and a moment beam fixing screw; the main moment beam and the secondary moment beam are fixed together through a pair of moment beam fixing screws, and the moment beams are connected with the matching surface in the signal measuring device through a fixing ring, two moment beam connecting taper pins and four screws;
preferably, the stiffening beam is of an integrated structure and comprises a right fulcrum, a right thin beam, a middle section, a left thin beam and a left fulcrum; the middle section is connected with the moment beam through a fixing screw, and a right side fulcrum and a left side fulcrum are fixed on the rigid supporting device; the right side thin beam and the left side thin beam are symmetrically distributed, the thicknesses of the right side thin beam and the left side thin beam are consistent, and the thickness range is 0.5 mm-2.0 mm.
Preferably, the simple harmonic motion conversion device comprises a shaft sleeve, a front needle bearing, an eccentric shaft, a middle needle bearing and a rear angle contact bearing; the eccentric shaft is fixed in the inner cavity of the rigid supporting device through the front needle bearing, the middle needle bearing and the rear angle contact bearing, the shaft sleeve is arranged at the front end of the eccentric shaft, and the rear end of the eccentric shaft is connected with the motor driving device.
Preferably, the shaft sleeve is made of tin bronze, and the thickness of the shaft sleeve is 0.8 mm-1.5 mm.
Preferably, the rigid supporting device comprises a support rod, a middle shaft and a 10-degree turning head; the front end of the supporting rod is fixed with a signal measuring device, the interior of the signal measuring device is hollow, and a simple harmonic motion conversion device is supported; the support rod is matched with the middle shaft through a cone and is connected with the middle shaft through a wedge key; the motor driving system is arranged at the tail part of the middle shaft; the middle shaft is connected with a 10-degree turning head, and the 10-degree turning head is directly arranged on the wind tunnel curved knife.
Preferably, the size of the matching surface of the central axis and the 10-degree elbow is not less than 200mmx100mm, the number of the fixing pins is not less than 4, and the number of the fixing screws is not less than 4.
Compared with the prior art, the invention has the advantages that:
the high-speed flying wing aircraft flies in a speed-crossing domain, aerodynamic load changes violently, transverse and lateral loads are not matched with longitudinal loads, and the conventional forced vibration test device cannot meet the requirement of accurate measurement of dynamic derivatives of the high-speed flying wing aircraft. The appearance characteristics of the high-speed flying wing aircraft limit the size of the internal space of a test model of the high-speed flying wing aircraft, the development of a dynamic derivative test device of the high-speed flying wing model is completed in the limited space, and the high requirements on signal measurement, motion transmission and motion conversion are higher. Aiming at the difficulties of the high-speed flying wing model, the invention carries out optimization design in the aspects of motion transmission, motion conversion and signal measurement, develops a small-size and high-bearing integrated dynamic signal measuring device and a controllable small-gap and tight-fit motion transmission device, is applied to a dynamic derivative wind tunnel test of a certain high-speed flying wing model, and obtains the pitching/yawing dynamic derivative parameters with high precision.
The small-size high-bearing integrated dynamic signal measuring device developed by the invention can be integrally arranged in the inner cavity of the model, the influence of the connection clearance of the force and moment measuring part and the angle measuring part is avoided, and meanwhile, the force and moment measuring part is closer to the movement center, so that the dynamic variation of the force and moment signals can be measured more accurately. The force and moment measuring units in the signal measuring device adopt a multi-piece beam structure, and the interference of each unit is reduced as much as possible on the premise of ensuring the rigidity and the strength by specifically and optimally designing the form of the beam structure, so that the measuring sensitivity of each unit is improved. In addition, parameters such as thickness parameters, gap parameters and angles in the beam structure are designed through a large amount of optimization design and research, and the measurement accuracy of dynamic weak signals in a dynamic derivative test is further improved.
According to the controllable small-gap and tight-fit motion transfer device, the moment beam and the integrated dynamic signal measuring device are connected in a fixing ring, taper pin and screw mode, and mechanism deformation and motion gaps caused in the force transfer process can be reduced. The stiffening beam is additionally arranged between the moment beam and the supporting rod through the optimized design, so that the testing mechanism can bear larger moment load, the integral deformation of the moment beam and the integrated dynamic signal measuring device is reduced, and the effect of transmitting simple harmonic signals accurately is achieved. According to the invention, parameters such as the diameter, the length, the matching surface of the connecting part and the like of the stiffening beam are designed in the design process of the stiffening beam, so that the rigidity and the strength of the motion transfer part are further improved, and the improvement of the coincidence degree of the designed simple harmonic motion signal and the actual simple harmonic motion signal is realized.
The rigid supporting device developed by the invention adopts an optimized design, and can meet the load of the maximum 10000N normal force under the condition of ensuring that the diameter of the front section of the supporting rod is less than 36 mm.
Drawings
FIG. 1 is an assembly schematic according to an embodiment of the invention;
FIG. 2 is a schematic diagram of a signal measurement device according to an embodiment of the present invention;
FIG. 3 is a schematic view of a retaining ring according to an embodiment of the present invention;
FIG. 4 is a schematic view of a primary moment beam according to an embodiment of the present invention;
FIG. 5 is a schematic view of a secondary moment beam according to an embodiment of the present invention;
FIG. 6 is a schematic view of a reinforced moment beam according to an embodiment of the present invention;
FIG. 7 is a schematic view of a strut according to an embodiment of the present invention;
FIG. 8 is a schematic view of a bushing in accordance with an embodiment of the invention;
FIG. 9 is a schematic view of an eccentric shaft according to an embodiment of the present invention;
FIG. 10 is a schematic bottom view of a bottom bracket according to an embodiment of the present invention;
FIG. 11 is a schematic view of a 10 ° elbow according to an embodiment of the invention;
FIG. 12 is a graph of collected pitch moment signals and pitch angle displacement signals, according to an embodiment of the present invention;
FIG. 13 is a collected yaw moment signal and yaw angular displacement signal according to an embodiment of the present invention.
Detailed Description
Embodiments of the present invention are described in detail below with reference to fig. 1-13.
As shown in FIG. 1, the device for testing the dynamic derivative of the pitching yawing forced vibration under the high attack angle of the high-speed flying wing model comprises: the device comprises a signal measuring device 2, a fixing ring 3, a moment beam connecting taper pin 4, a main moment beam 5, a secondary moment beam 6, a signal measuring device connecting wedge 7, a signal measuring device positioning key 8, a reinforcing beam connecting screw 9, a reinforcing beam 10, a moment beam connecting screw 11, a support rod 12, a shaft sleeve 13, a front needle bearing 14, an eccentric shaft 15, a middle needle bearing 16, a middle shaft 17, a support rod connecting wedge 18, a support rod connecting positioning key 19, a rear angle contact bearing 20, a connecting pin 21, a connecting screw 22, a 10-degree turning head 23, a motor driving device 24 and a motor cover 25.
As shown in fig. 2, the signal measuring device 2 is an integrated structure, and a flying wing model 1 is installed at the front end of the signal measuring device; the signal measuring device 2 comprises a model connecting cone 31, a right rolling thin beam 32, a right rolling compensation thin beam 33, a pitch beam 34, a left rolling compensation thin beam 35, a left rolling thin beam 36, a yaw beam 37, a motion transmission device matching surface 38, an angle measuring beam 39, an angle motion beam 40 and a rigid support device connecting cone 41; the right rolling thin beam 32, the right rolling compensation thin beam 33, the pitching beam 34, the left rolling compensation thin beam 35 and the left rolling thin beam 36 are distributed in a vertically symmetrical manner, and are respectively in a pair, wherein the front ends of the ten beams are connected to the rear end of the model connecting cone 31, and the rear ends of the ten beams are connected to the front end of the motion transmission device matching surface 38; the yaw beam 37 and the angle measuring beam 39 are distributed in bilateral symmetry, and are respectively in a pair; the front ends of the two yaw beams 37 are connected to the rear ends of the model connecting cones 31, and the rear ends are connected to the front ends of the motion transfer device matching surfaces 38; the angle movement beam 40 is positioned between the angle measurement beams 39, the front ends of the angle movement beams are connected with the rear end of the motion transfer device matching surface 38, and the rear end of the angle movement beams is connected with the front end of the rigid supporting device connecting cone 41; two angle measuring cross beams 39 support and an angle movement beam 40 moves the motion transfer means mating surface 38 and its front part around its centre.
The right side rolling thin beam 32 and the left side rolling thin beam 36 are 0.8mm thick; the thickness of the right side rolling compensation thin beam 33 and the left side rolling compensation thin beam 35 is 0.8 mm; the pitch beam 34 is 9mm thick; the thickness of the yaw beam 37 is 4 mm; the gap a between the right rolling thin beam 32 and the right rolling compensation thin beam 33 is 1.0 mm; the gap b between the right roll compensating thin beam 33 and the pitch beam 34 is 1.0 mm. The lengths of the right rolling thin beam 32, the right rolling compensation thin beam 33, the pitch beam 34, the left rolling compensation thin beam 35, the left rolling thin beam 36 and the yaw beam 37 are all 40 mm; the motion transfer device mating surface 38 has a cross-sectional dimension of 24mmx24mm and a length of 30 mm;
the angle moving beam 40 includes three portions, front, middle, and rear, and the middle portion is a straight beam having a thickness identical to that of the angle measuring beam 39; the included angles d between the front part and the middle part and between the front part and the middle part are both 45 degrees; the thickness of the angle measuring beam 39 is 7.5mm, and the length is 30 mm; the gap c between the angle measuring beam 39 and the angle moving beam 40 is 1.0 mm.
The model connecting cone 31 is connected with the model through a cone and screw matching mode, and the rigid supporting device connecting cone 41 is connected with the rigid supporting device through a cone and wedge matching mode.
The motion transfer device comprises a fixing ring 3 (figure 3), a moment beam connecting taper pin 4, a main moment beam 5 (figure 4), a secondary moment beam 6 (figure 5), a reinforcing beam fixing screw 9, a reinforcing beam 10 and a moment beam fixing screw 11; the main moment beam 5 and the secondary moment beam 6 are fixed together through a pair of moment beam fixing screws 11, and the moment beams are connected with the matching surface in the signal measuring device 2 through a fixing ring 3, two moment beam connecting taper pins 4 and four screws;
as shown in fig. 6, the reinforcing beam 10 is an integrated structure, and includes a right fulcrum 46, a right thin beam 42, a middle section 43, a left thin beam 44, and a left fulcrum 45; the middle section 43 is connected with the moment beam through a fixing screw 9, and a right fulcrum 46 and a left fulcrum 45 are fixed on the rigid supporting device; the right side thin beam 42 and the left side thin beam 44 are symmetrically distributed, have consistent thickness and are 1.5mm in thickness.
The simple harmonic motion conversion device comprises a shaft sleeve 13 (figure 8), a front needle bearing 14, an eccentric shaft 15 (figure 9), a middle needle bearing 16 and a rear angle contact bearing 20; the eccentric shaft 15 is fixed in the inner cavity of the rigid supporting device through a front needle bearing 14, a middle needle bearing 16 and a rear angle contact bearing 20, the shaft sleeve 13 is installed at the front end of the eccentric shaft 15, and the rear end of the eccentric shaft 15 is connected with a motor driving device. The shaft sleeve 13 is made of tin bronze and is 1.0mm thick.
The rigid supporting device comprises a support rod 12 (figure 7), a middle shaft 17 (figure 10) and a 10-degree elbow 23 (figure 11); the front end of the strut 12 is fixed with a signal measuring device, the interior of the signal measuring device is hollow, and a simple harmonic motion conversion device is supported; the support rod 12 is matched with the middle shaft 17 through a cone and is connected with the middle shaft through a wedge key; the motor driving system is arranged at the tail part of the middle shaft 17; the middle shaft 17 is connected with a 10-degree turning head 23, and the 10-degree turning head 23 is directly arranged on the wind tunnel curved blade. The size of the matching surface of the central shaft 17 and the 10-degree elbow 23 is not less than 200mmx100mm, the number of the fixing pins is not less than 4, and the number of the fixing screws is not less than 4.
Examples
When the pitching yawing forced vibration dynamic derivative test device for the high-speed flying wing model under the large attack angle is used for testing, a 10-degree turning head of the device is installed on a wind tunnel bent knife, the front end of a signal measurement device is connected with the flying wing model, the theoretical mass center of the test model is superposed with the rotation center of the signal measurement device, a motor control system controls a motor driving device to rotate at a specified frequency, the amplitude is adjusted through an eccentric shaft 15, so that the model performs simple harmonic motion at the specified frequency and the specified amplitude, and the switching between pitching vibration and yawing vibration can be realized through rotating a supporting rod 12 by 90 degrees. During testing, force, moment signals and angular displacement signals of the signal measuring device are synchronously measured, and corresponding dynamic stability derivatives can be obtained by correspondingly processing the two paths of signals.
The overall size of the whole set of test mechanism is about 1600mm, the diameter of the front end of the support rod 12 is 35mm, the maximum outer diameter of the motor driving device is 130mm, the whole set of test mechanism can realize the pitching/yawing vibration angle +/-1 degree, and the maximum vibration frequency which can be achieved is 16Hz by adjusting the rotating speed of the motor driving device. As shown in fig. 12, the angular displacement signal is-0.8 to 0.8 degrees, the vibration frequency is 10Hz, and the variation range of the pitching moment is-5.5 n.m to 5.5n.m under the working condition of a test mach number of 0.9 and an attack angle of 30 degrees and the original signal and the filtered signal collected during pitching forced vibration. As shown in fig. 13, the angular displacement signal is-0.8 ° -0.8 °, the vibration frequency is 10Hz, and the yaw moment variation range is-5.2 n.m, which are the original signal and the filtered signal collected during yaw forced vibration under the working condition of a mach number of 1.5 and an attack angle of 30 °.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (16)
1. A pitching yawing forced vibration dynamic derivative test device used under a high attack angle of a high-speed flying wing model comprises: the device comprises a motor driving device, a rigid supporting device, a simple harmonic motion conversion device, a motion transmission device and an integrated dynamic signal measuring device; the front end of the integrated dynamic signal measuring device is provided with a flying wing model;
the motor driving device is a torque output part of the whole dynamic derivative testing device; the rigid supporting device is used for installing the whole testing device in the wind tunnel and supporting the motor driving device, the simple harmonic motion conversion device and the integrated dynamic signal measuring device; the simple harmonic motion conversion device converts the continuous rotary motion output by the motor driving device into simple harmonic motion required by the test and transmits the simple harmonic motion to the motion transmission device; the motion transmission device is directly connected to the middle part of the integrated dynamic signal measuring device and drives the integrated dynamic signal measuring device to do simple harmonic motion in a specified form; the integrated dynamic signal measuring device measures force, moment and angular displacement signals in the whole movement process;
the integrated dynamic signal measuring device comprises a model connecting cone (31), a right rolling thin beam (32), a right rolling compensation thin beam (33), a pitching beam (34), a left rolling compensation thin beam (35), a left rolling thin beam (36), a yawing beam (37), a motion transmission device matching surface (38), an angle measuring beam (39), an angle moving beam (40) and a rigid supporting device connecting cone (41); the right rolling thin beam (32), the right rolling compensation thin beam (33), the pitching beam (34), the left rolling compensation thin beam (35) and the left rolling thin beam (36) are distributed in an up-down symmetrical mode, and are respectively in a pair, the front ends of the ten beams are connected to the rear end of the model connecting cone (31), and the rear ends of the ten beams are connected to the front end of the motion transfer device matching surface (38); the yawing beams (37) and the angle measuring cross beams (39) are distributed in a left-right symmetrical mode and are respectively in a pair; the front ends of the two yawing beams (37) are connected to the rear ends of the model connecting cones (31), and the rear ends of the two yawing beams are connected to the front ends of the motion transfer device matching surfaces (38); the angle moving beam (40) is positioned between the angle measuring beams (39), the front ends of the angle moving beam and the angle measuring beams are connected to the rear end of the motion transfer device matching surface (38), and the rear end of the angle moving beam and the angle measuring beams is connected to the front end of the rigid supporting device connecting cone (41); two angle measuring cross beams (39) support and an angle movement beam (40) moves the motion transfer device mating surface (38) and its front part around its center.
2. The test device of claim 1, wherein: the thickness of the right side rolling thin beam (32) and the left side rolling thin beam (36) is 0.5 mm-1.0 mm; the thicknesses of the right side rolling compensation thin beam (33) and the left side rolling compensation thin beam (35) are 0.5-1.0 mm; the thickness of the pitching beam (34) is 8 mm-10 mm; the thickness of the yaw beam (37) is 3 mm-5 mm.
3. The test device according to claim 1 or 2, wherein: the range of a gap a between the right rolling thin beam (32) and the right rolling compensation thin beam (33) is 0.8-1.2 mm; the range of the gap b between the right rolling compensation thin beam (33) and the pitch beam (34) is 0.8-1.2 mm.
4. The test device according to claim 1 or 2, wherein: the lengths of the right rolling thin beam (32), the right rolling compensation thin beam (33), the pitching beam (34), the left rolling compensation thin beam (35), the left rolling thin beam (36) and the yawing beam (37) are consistent, and the range is 35-45 mm.
5. The test device of claim 1, wherein: the motion transfer device mating surface (38) has a cross-sectional dimension of no less than 22mmx22mm and a length of no less than 28 mm.
6. The test device of claim 1, wherein: the angle moving beam (40) comprises a front part, a middle part and a rear part, and the middle part is a straight beam with the thickness consistent with that of the angle measuring beam (39); the included angle d between the front part and the middle part is consistent with that between the front part and the middle part.
7. The test device of claim 6, wherein: the thickness of the angle measuring beam (39) is 6.0 mm-8.0 mm, and the length is 27.5 mm-32.5 mm.
8. The test device of claim 6, wherein: the included angle d ranges from 40 degrees to 50 degrees.
9. The test device according to claim 1 or 6, wherein: the range of a gap c between the angle measuring beam (39) and the angle moving beam (40) is 0.8 mm-1.2 mm.
10. The test device of claim 1, wherein: the motion transmission device comprises a fixing ring (3), a moment beam connecting taper pin (4), a main moment beam (5), a secondary moment beam (6), a reinforcing beam fixing screw (9), a reinforcing beam (10) and a moment beam fixing screw (11);
the main moment beam (5) and the secondary moment beam (6) are fixed together through a pair of moment beam fixing screws (11) to form a moment beam; the moment beam is connected with the motion transmission device matching surface (38) through a fixing ring (3), two moment beam connecting taper pins (4) and four screws.
11. The test device of claim 10, wherein: the reinforcing beam (10) is of an integrated structure and comprises supporting points at two sides and a middle section; the supporting points at the two sides are connected with the middle section through a left thin beam and a right thin beam respectively; the fulcrums at the two sides are fixed on the rigid supporting device, and the middle section (43) is connected with the moment beam through a reinforcing beam fixing screw (9).
12. The testing device of claim 11, wherein: the right side thin beam (42) and the left side thin beam (44) are symmetrically distributed, the thicknesses of the right side thin beam and the left side thin beam are consistent, and the thickness range is 0.5 mm-2.0 mm.
13. The test device of claim 1, wherein: the simple harmonic motion conversion device comprises a shaft sleeve (13), a front needle bearing (14), an eccentric shaft (15), a middle needle bearing (16) and a rear angle contact bearing (20);
the eccentric shaft (15) is fixed in the inner cavity of the rigid supporting device through a front needle bearing (14), a middle needle bearing (16) and a rear angle contact bearing (20), the shaft sleeve (13) is installed at the front end of the eccentric shaft (15), and the rear end of the eccentric shaft (15) is connected with a motor driving device.
14. The test device of claim 13, wherein: the shaft sleeve (13) is made of tin bronze and has the thickness of 0.8-1.5 mm.
15. The test device of claim 1, wherein: the rigid supporting device comprises a supporting rod (12), a middle shaft (17) and a crank head (23);
the front end of the supporting rod (12) is fixedly provided with an integrated dynamic signal measuring device, the interior of the integrated dynamic signal measuring device is hollow, and a simple harmonic motion conversion device is supported; the support rod (12) is matched with the middle shaft (17) through a cone and is connected with the middle shaft through a wedge key; the motor driving device is arranged at the tail part of the middle shaft (17); the middle shaft (17) is connected with a turning head (23), and the turning head (23) is directly arranged on the wind tunnel curved knife.
16. The test device according to claim 15, characterized in that: the size of the matching surface of the central shaft (17) and the crank head (23) is not less than 200mmx100mm, the number of the fixing pins is not less than 4, and the number of the fixing screws is not less than 4.
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| RU2736347C1 (en) * | 2020-05-27 | 2020-11-16 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Electromechanical bench |
| CN112525476B (en) * | 2020-12-07 | 2022-04-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Model supporting and coupling rolling driving device for unsteady force measurement wind tunnel test |
| CN112577696B (en) * | 2020-12-24 | 2022-10-11 | 中国航天空气动力技术研究院 | High-speed wind tunnel washing flow time difference derivative test device |
| CN113753261B (en) * | 2021-11-09 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
| CN114486151B (en) * | 2022-04-14 | 2022-06-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Add oil pipe wind-tunnel flight test device |
| CN115508038A (en) * | 2022-08-30 | 2022-12-23 | 中国航天空气动力技术研究院 | Test device for high-speed wind tunnel ultra-large attack angle pitching and rolling double-freedom-degree motion |
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