Amplitude and inertia variable aircraft reciprocating motion test device and method

Abstract

The invention discloses an amplitude and inertia variable aircraft reciprocating motion test device and method, and belongs to the field of wind tunnel tests. The device comprises an amplitude adjusting assembly, an inertia adjusting assembly, a driving assembly and an executing assembly, the driving assembly is connected with the executing assembly through the amplitude adjusting assembly and the inertia adjusting assembly in sequence, a supporting rod is installed on the executing assembly, the supporting rod stretches into a wind tunnel, and an aircraft is installed on the supporting rod. The invention aims to solve the problems that a hydraulic cylinder direct-drive mechanism in an existing linear oscillation motion wind tunnel test device is poor in sealing performance, easy to damage and leak oil, long in preparation time, low in test efficiency and difficult to realize stable control of high-frequency oscillation. And an electric cylinder direct drive mechanism has the problems of small output, low movement speed, unsuitability for high-speed reciprocating linear oscillation movement of a large-mass model and relatively large abrasion in rotation.

Description

Technical Field

[0001] The invention relates to an aircraft reciprocating motion test device and method with variable amplitude and inertia, belonging to the field of wind tunnel testing. Background Art

[0002] The dynamic derivative is the derivative of the aerodynamic coefficient of the aircraft with respect to the time rate of change of the aircraft attitude parameters, and is an essential aerodynamic parameter in the aircraft development process. Linear oscillation motion is a key research content of dynamic derivatives, which is used for aircraft stability analysis and control law design. At present, the main means of obtaining the dynamic derivatives of the linear oscillation motion of aircraft include numerical simulation and wind tunnel testing. The calculation time required for numerical simulation is relatively long, which is not suitable for the acquisition of large amounts of data, and the accuracy of the calculation method and the calculation results need further study. Wind tunnel testing is the most reliable means of obtaining the dynamic derivatives of the linear oscillation motion of aircraft at this stage.

[0003] At present, the linear oscillation motion wind tunnel test devices mainly include hydraulic cylinder direct drive mechanisms and electric cylinder direct drive mechanisms. The hydraulic cylinder direct drive mechanism has the advantage of high output and can realize the linear oscillation motion of large-mass models. However, the hydraulic cylinder direct drive mechanism has sealing problems during high-speed linear oscillation motion. When the rod chamber of the hydraulic cylinder performs multiple rapid reciprocating motions in the rodless chamber, the seals are highly destructive. After a period of use, the seals are very easy to be damaged, causing oil leakage in the hydraulic cylinder. In addition, before the test, the system oil circuit needs to be flushed and circulated for a long time to ensure the cleanliness requirements of the servo valve, resulting in long preparation time, low test efficiency, and the hydraulic system is difficult to implement.

[0004] The electric cylinder direct drive mechanism has the advantages of precise control and no oil leakage, but the electric cylinder direct drive mechanism has low output and low movement speed, which is not suitable for high-speed reciprocating oscillation movement of large mass models. At the same time, the internal components of the electric cylinder are greatly worn during high-speed movement, resulting in reduced operation accuracy of the electric cylinder after a period of use.

[0005] Therefore, it is urgent to propose an aircraft reciprocating motion test device and method with variable amplitude and inertia to solve the above technical problems. Summary of the invention

[0006] The purpose of the research and development of the present invention is to solve the problems of poor sealing, easy damage and oil leakage, long preparation time, low test efficiency, and difficulty in achieving smooth control of high-frequency oscillation in the hydraulic cylinder direct drive mechanism in the existing linear oscillation motion wind tunnel test device, as well as the problems of low output, low movement speed, unsuitability for high-speed reciprocating linear oscillation motion of large mass models, and large wear in the rotation of the electric cylinder direct drive mechanism. A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to identify the key or important parts of the present invention, nor is it intended to limit the scope of the present invention.

[0007] The technical solution of the present invention:

[0008] Scheme 1: A reciprocating motion test device for an aircraft with variable amplitude and inertia, including an amplitude adjustment component, an inertia adjustment component, a drive component and an execution component. The drive component is connected to the execution component through the amplitude adjustment component and the inertia adjustment component in sequence. A support rod is installed on the execution component, the support rod is extended into a wind tunnel, and an aircraft is installed on the support rod.

[0009] Preferably: the driving assembly comprises a driving motor, a motor bracket, a gear shaft, a main gear, a base, a spline shaft, a double-row angular contact ball bearing and a spherical roller bearing; the base is fixedly mounted on one side of the wind tunnel; the driving motor is fixedly mounted on the base through the motor bracket; a gear shaft is mounted on the output end of the driving motor; the gear shaft is rotatably mounted on the base through a bearing assembly; a main gear is mounted on the gear shaft; the spline shaft is fixed in the inner hole of the main gear through a spline connection; the double-row angular contact ball bearing and the spherical roller bearing are respectively mounted on the front and rear ends of the spline shaft, so that the front and rear ends of the spline shaft are rotatably mounted on the base through the double-row angular contact ball bearing and the spherical roller bearing respectively.

[0010] Preferably: the bearing assembly includes an eccentric bushing, a double-row cylindrical roller bearing, a bearing inner baffle, a bearing outer baffle and a locking nut. The gear shaft is fixed inside the eccentric bushing through two sets of double-row cylindrical roller bearings. The inner and outer diameter axes of the eccentric bushing installed in the base are not coaxially arranged. The bearing inner baffle and the bearing outer baffle axially position the double-row cylindrical roller bearing, and the outer side of the bearing inner baffle is locked by a locking nut.

[0011] Preferably, the front and rear ends of the double-row angular contact ball bearing are positioned respectively by the front of the outer retaining ring and the front of the inner retaining ring, and the front and rear ends of the spherical roller bearing are positioned respectively by the rear of the inner retaining ring, the bearing locking retaining ring and the rear of the outer retaining ring.

[0012] Preferably: the inertia adjustment component includes an inertia adjustment reduction motor, an inertia adjustment reduction motor mounting seat, an inertia adjustment long shaft, an angular contact ball bearing, an inertia adjustment slider, an inertia adjustment guide rail, an inertia adjustment small bevel gear, a deep groove ball bearing, an inertia adjustment screw, a seat bearing, an inertia flywheel, an inertia adjustment mass block, an inertia adjustment large bevel gear, an inertia adjustment large bevel gear shaft and a small round nut, the inertia adjustment long shaft is installed in the inner hole of the spline shaft through a pair of angular contact ball bearings, the inertia adjustment reduction motor mounting seat is installed on the rear of the outer retaining ring, the inertia adjustment reduction motor is fixed to the inertia adjustment reduction motor mounting seat through a flange, and the output end of the inertia adjustment reduction motor is connected to the inertia adjustment long shaft through a key; the inertia adjustment long shaft transmits torque to the inertia adjustment large bevel gear shaft through a key, and the inertia adjustment large bevel gear shaft is connected to the inertia adjustment long shaft through a set of The deep groove ball bearing is fixed in the inner hole of the inertia flywheel, and the rear end of the deep groove ball bearing is axially positioned by a small round nut; an inertia adjustment large bevel gear is installed on the outer side of the inertia adjustment large bevel gear shaft, and the inertia adjustment large bevel gear is meshed with four groups of inertia adjustment small bevel gears installed on the front end of the inertia adjustment screw; four groups of inertia adjustment guide rails are installed on the inner wall of the inertia flywheel connected to the spline shaft, and an inertia adjustment slider is installed on the inertia adjustment guide rail. The inertia adjustment slider is sleeved on the inertia adjustment screw, and the inertia adjustment screw is fixed on the inner wall of the inertia flywheel through two groups of seat bearings, and an inertia adjustment mass block is installed on the outer side of the inertia adjustment slider; when the inertia adjustment large bevel gear rotates, the four groups of identical inertia adjustment small bevel gears are driven to rotate synchronously through gear meshing transmission, thereby driving the inertia adjustment mass block on the inertia adjustment screw to move forward and backward along the inertia adjustment guide rail.

[0013] Preferably: the amplitude adjustment assembly comprises an auxiliary cross slide, a main cross slide, a cross slide cross plate, a roller shaft, a rolling body cover plate, an amplitude adjustment block, a roller box body, a needle bearing, a clamping nut, an amplitude adjustment rod, an amplitude guide baffle, a locking side nail, a locking pressure plate and an amplitude guide; the amplitude guide is fixed to the inertia flywheel by screws arranged symmetrically on the left and right, and the two amplitude guide baffles are respectively fixed on the upper and lower sides of the amplitude guide; the amplitude adjustment rod is installed in the inner hole of the amplitude guide baffle, and the amplitude adjustment block is threadedly mounted on the amplitude adjustment rod, and when the amplitude adjustment rod is rotated, the amplitude adjustment block is driven to move up and down along the inner side of the amplitude guide; the end of the amplitude adjustment block The end is installed in the square groove of the locking pressure plate through a boss structure. The locking pressure plate and the amplitude guide are meshed with mouse-shaped teeth. The position of the amplitude adjustment block is locked by tightening the clamping nut. At the same time, two locking side nails arranged on the left and right pass through the long holes of the amplitude guide and are screwed into the left and right threaded holes of the amplitude adjustment block. The position of the amplitude adjustment block is locked again by relying on the friction force generated by the nail heads of the locking side nails. The roller box body is mounted on the front end of the amplitude adjustment block and axially positioned by rolling the box body cover. Four sets of roller shafts are installed inside the roller box body, and needle bearings are installed on the roller shafts. During the movement, the needle bearings on both sides of the roller box body are popped out to contact the auxiliary cross slide or the main cross slide.

[0014] Preferably: the actuator assembly includes a load-bearing square tube, a guide rail mounting seat, a linear guide rail assembly and a support, the main cross slide and the auxiliary cross slide are connected as a whole through a cross slide cross plate, and are connected to the end of the load-bearing square tube through the front end stop of the main cross slide, the front end of the load-bearing square tube and the support rod are connected with a cone, the outer side of the load-bearing square tube is installed on the inner side of two sets of guide rail mounting seats symmetrically arranged along the linear motion axis through a linear guide rail assembly, and the guide rail mounting seat is fixed on the support.

[0015] Solution 2: A method for testing reciprocating motion of an aircraft with variable amplitude and inertia, which is implemented based on the reciprocating motion test device for an aircraft with variable amplitude and inertia described in Solution 1, comprises the following steps:

[0016] Step a, installing the variable amplitude and inertia aircraft reciprocating motion test device controlled by the control system in the wind tunnel, and connecting the data line of the control system and the balance to the wind tunnel control and acquisition system;

[0017] Step b, according to the oscillation frequency of the aircraft during the test, the rotation speed of the inertia flywheel is calculated, and then the speed of the drive motor is calculated by the gear reduction ratio, as shown in the following formula:

[0018]

[0019] Where w is the motor speed, f is the aircraft oscillation frequency, z 1 The number of teeth on the main gear, z 2 is the number of teeth on the gear shaft;

[0020] Step c, according to the amplitude of the aircraft, adjust the distance between the amplitude adjustment component and the rotation axis of the inertia flywheel, and calculate the moment of inertia under the amplitude, as shown in the following formula:

[0021] I=I 固 +I 振 =I 固 +m 振 ×A 2

[0022] Where A is the amplitude corresponding to the aircraft oscillation frequency f, I 固 is the inertia around the rotation axis excluding the amplitude adjustment component, I 振 is the inertia of the amplitude adjustment component around the rotation axis, m 振 The mass of the component is adjusted for amplitude;

[0023] Step d, starting the wind tunnel, and after the wind speed of the wind tunnel reaches the target value, driving the aircraft to perform an oscillating motion at a given frequency f and amplitude A;

[0024] Step e, calculating the equivalent moment of inertia required by the inertia adjustment component;

[0025]

[0026] In the formula, I F is the equivalent moment of inertia required by the lower inertia adjustment component corresponding to the aircraft oscillation frequency f, ΔW max is the maximum surplus or loss work corresponding to the aircraft oscillation frequency f, w F is the angular velocity of the inertia flywheel at the aircraft oscillation frequency f, w Fmax is the upper limit of the angular velocity fluctuation of the inertia flywheel at the aircraft oscillation frequency f, w Fmin is the lower limit of the angular velocity fluctuation of the inertia flywheel corresponding to the aircraft oscillation frequency f, and δ is the velocity non-uniformity coefficient;

[0027] Step f, calculating the center distance L between the inertia adjustment mass block and the rotating shaft of the rotational installation of the inertia flywheel according to the equivalent rotational inertia;

[0028]

[0029] Where L is the center distance of the inertia adjustment mass block from the rotating axis corresponding to the aircraft oscillation frequency f, m 质 is the mass of the inertia adjustment mass block, I F0 The inertia of the inertia adjustment components relative to the rotating shaft except the inertia adjustment mass block;

[0030] Step g, controlling the amplitude adjustment reduction motor to rotate according to the distance L between the inertia adjustment mass block and the center of the rotating shaft, and adjusting the inertia adjustment mass block to a specified position;

[0031] Step h, starting the wind tunnel data acquisition system to collect and record test values;

[0032] Step i, stop the wind tunnel operation and reduce the wind speed to 0;

[0033] Step j, repeat steps b and i to complete the test under different frequency and amplitude combinations.

[0034] The present invention has the following beneficial effects:

[0035] 1. The present invention can carry out the dynamic derivative test of aircraft linear motion in the wind tunnel to obtain the dynamic derivative characteristics of the aircraft linear model. Through the ingenious structural design, the uniform rotational motion of the input end is converted into the reciprocating linear oscillation motion of the output end, and the amplitude and oscillation frequency can be adjusted according to the test requirements;

[0036] 2. The present invention can adjust the system inertia in real time according to the test load, ensuring that the driving motor is minimally affected by the impact of the variable load, and the mechanism operates more stably, thereby achieving higher accuracy and better repeatability of the test data;

[0037] 3. Compared with the traditional hydraulic cylinder direct drive mechanism, the present invention has no problems of oil leakage, long preparation time before the test and difficult high-frequency oscillation control;

[0038] 4. Compared with the traditional electric cylinder direct drive mechanism, the present invention does not have the problems of low output, low movement speed and reduced accuracy of the electric cylinder after a period of use;

[0039] 5. The present invention has a compact structure, a high degree of automation, and strong versatility. It can meet the needs of manufacturing wind tunnel dynamic derivative test devices for aircraft models of different sizes and masses, and is suitable for popularization and use. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 It is a three-dimensional diagram of a test device for the reciprocating motion of an aircraft with variable amplitude and inertia;

[0041] Figure 2 It is a front view of a test device for the reciprocating motion of an aircraft with variable amplitude and inertia;

[0042] Figure 3 It is a top view of a test device for the reciprocating motion of an aircraft with variable amplitude and inertia;

[0043] Figure 4 It is a coordination and installation diagram of a reciprocating motion test device for an aircraft with variable amplitude and inertia;

[0044] Figure 5 It is a stereogram of the execution assembly;

[0045] Figure 6 This is the coordination installation diagram of the main cross slide and the auxiliary cross slide;

[0046] Figure 7 is a stereogram of the inertia adjustment assembly;

[0047] Figure 8 It is an exploded view of the inertia adjustment assembly;

[0048] Fig. 9 It is a three-dimensional diagram of the inertia flywheel;

[0049] Fig.10 This is the coordination installation diagram of the amplitude adjustment component;

[0050] Fig.11 It is the matching installation drawing of the spline shaft;

[0051] Fig.12 This is the matching installation drawing of the gear shaft;

[0052] Fig.13 is a cross-sectional view of the eccentric bushing of the drive assembly;

[0053] Fig.14 It is the motion principle of a reciprocating motion test device for an aircraft with variable amplitude and inertia;

[0054] Fig.15 It is a flow chart of a method for testing reciprocating motion of an aircraft with variable amplitude and inertia;

[0055] In the figure, 101-amplitude adjustment component, 102-inertia adjustment component, 103-drive component, 104-actuator component, 1-wind tunnel, 2-aircraft, 3-support rod, 4-support, 5-linear guide rail component, 6-guide rail mounting seat, 7-load-bearing square tube, 8-cross slide cross plate, 9-main cross slide, 10-auxiliary cross slide, 11-roller shaft, 12-roller cover plate, 13-amplitude adjustment block, 14-roller box body, 15-needle bearing, 16-pressing nut, 17-amplitude adjustment rod, 18-amplitude guide rail baffle, 19-locking side nail, 20-locking pressure plate, 21-amplitude guide rail, 22-inertia flywheel, 23-seat bearing, 24-inertia adjustment screw, 25-deep groove ball bearing, 26-inertia adjustment small bevel gear, 27-inertia adjustment Section guide rail, 28-inertia adjustment slider, 29-inertia adjustment mass block, 30-inertia adjustment large bevel gear, 31-inertia adjustment large bevel gear shaft, 32-inertia adjustment long shaft, 33-small round nut, 34-spline shaft, 35-angular contact ball bearing, 36-front of outer retaining ring, 37-double-row angular contact ball bearing, 38-front of inner retaining ring, 39-main gear, 40-behind inner retaining ring, 41-spherical roller bearing, 42-bearing locking retaining ring, 43-inertia adjustment reduction motor, 44-inertia adjustment reduction motor mounting seat, 45-behind outer retaining ring, 46-base, 47-eccentric bushing, 48-bearing outer baffle plate, 49-gear shaft, 50-bearing inner baffle plate, 51-double-row cylindrical roller bearing, 52-spare nut, 53-drive motor, 54-motor bracket. DETAILED DESCRIPTION

[0056] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0057] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection is a non-detachable connection including but not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but not limited to conventional detachable methods such as threaded connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can always be found in the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example: a fixed connection is selected as a welding connection, and a detachable connection is selected as a hinge connection.

[0058] Specific implementation method 1: Combination Figure 1-Figure 14 The present embodiment is described. A variable amplitude and inertia aircraft reciprocating motion test device of the present embodiment includes an amplitude adjustment component 101, an inertia adjustment component 102, a drive component 103 and an actuator component 104. The drive component 103 is connected to the actuator component 104 via the amplitude adjustment component 101 and the inertia adjustment component 102 in sequence. A support rod 3 is installed on the actuator component 104. The support rod 3 extends into the wind tunnel 2 and is installed with the aircraft 2.

[0059] The driving assembly 103 includes a driving motor 53, a motor bracket 54, a gear shaft 49, a main gear 39, a base 46, a spline shaft 34, a double-row angular contact ball bearing 37 and a spherical roller bearing 41. The base 46 is fixedly installed on one side of the wind tunnel 2. The driving motor 53 is fixedly installed on the base 46 through the motor bracket 54. The output end of the driving motor 53 is installed with a gear shaft 49, and the gear shaft 49 is rotatably installed on the base 46 through a bearing assembly. The main gear 39 is installed on the gear shaft 49. The spline shaft 34 is fixed in the inner hole of the main gear 39 through a spline connection. The double-row angular contact ball bearing 37 and the spherical roller bearing 41 are respectively installed at the front and rear ends of the spline shaft 34. This arrangement can withstand the impact load in the gear meshing transmission process and ensure the concentricity of the transmission system. The front and rear ends of the spline shaft 34 are rotatably installed on the base 46 through the double-row angular contact ball bearing 37 and the spherical roller bearing 41 respectively.

[0060] The bearing assembly includes an eccentric bushing 47, a double-row cylindrical roller bearing 51, a bearing inner baffle 50, a bearing outer baffle 48 and a backup nut 52. The gear shaft 49 is fixed inside the eccentric bushing 47 through two sets of double-row cylindrical roller bearings 51. The inner and outer diameter axes of the eccentric bushing 47 installed in the base 46 are not coaxially arranged, so that the gear shaft 49 and the main gear 39 fit more closely and the transmission noise can be reduced at the same time. The bearing inner baffle 50 and the bearing outer baffle 48 axially position the double-row cylindrical roller bearing 51, and the outer side of the bearing inner baffle 50 is locked by the backup nut 52.

[0061] The front and rear ends of the double row angular contact ball bearing 37 are positioned respectively by the front outer retaining ring 36 and the front inner retaining ring 38, and the front and rear ends of the spherical roller bearing 41 are positioned respectively by the rear inner retaining ring 40, the bearing locking retaining ring 42 and the rear outer retaining ring 45.

[0062] The inertia adjustment component 102 includes an inertia adjustment reduction motor 43, an inertia adjustment reduction motor mounting seat 44, an inertia adjustment long shaft 32, an angular contact ball bearing 35, an inertia adjustment slider 28, an inertia adjustment guide rail 27, an inertia adjustment small bevel gear 26, a deep groove ball bearing 25, an inertia adjustment screw 24, a seat bearing 23, an inertia flywheel 22, an inertia adjustment mass block 29, an inertia adjustment large bevel gear 30, an inertia adjustment large bevel gear shaft 31 and a small round nut 33. The inertia adjustment long shaft 32 is connected to a pair of angular contact ball bearings. The ball bearing 35 is installed in the inner hole of the spline shaft 34, the inertia adjustment reduction motor mounting seat 44 is installed on the outer retaining ring 45, the inertia adjustment reduction motor 43 is fixed on the inertia adjustment reduction motor mounting seat 44 through a flange, and the output end of the inertia adjustment reduction motor 43 is connected to the inertia adjustment long shaft 32 through a key. This "nested" structure utilizes the working principle of a large shaft sleeve and a small shaft, and effectively saves the structural space of the device; the inertia adjustment long shaft 32 transmits torque to the inertia adjustment large bevel gear shaft 31 through a key, and the inertia adjustment long shaft 32 transmits torque to the inertia adjustment large bevel gear shaft 31 through a key. The inertia adjustment large bevel gear shaft 31 is fixed in the inner hole of the inertia flywheel 22 through a group of deep groove ball bearings 25, and the rear end of the deep groove ball bearing 25 is axially positioned by a small round nut 33; the inertia adjustment large bevel gear 30 is installed on the outer side of the inertia adjustment large bevel gear shaft 31, and the inertia adjustment large bevel gear 30 is meshed with four groups of inertia adjustment small bevel gears 26 installed at the front end of the inertia adjustment screw 24; four groups of inertia adjustment guide rails 27 are installed on the inner wall of the inertia flywheel 22 connected to the spline shaft 34, and the inertia adjustment slide is installed on the inertia adjustment guide rail 27 The inertia adjustment slider 28 is mounted on the inertia adjustment screw 24. The inertia adjustment screw 24 is fixed to the inner wall of the inertia flywheel 22 through two sets of seat bearings 23. An inertia adjustment mass block 29 is installed on the outer side of the inertia adjustment slider 28. When the inertia adjustment large bevel gear 30 rotates, the four sets of identical inertia adjustment small bevel gears 26 are driven to rotate synchronously through the gear meshing transmission, thereby driving the inertia adjustment mass block 29 on the inertia adjustment screw 24 to move forward and backward along the inertia adjustment guide rail 27, thereby realizing inertia adjustment.

[0063] The amplitude adjustment assembly 101 includes an auxiliary cross slide 10, a main cross slide 9, a cross slide cross plate 8, a roller shaft 11, a rolling body cover plate 12, an amplitude adjustment block 13, a roller box body 14, a needle bearing 15, a clamping nut 16, an amplitude adjustment rod 17, an amplitude guide baffle 18, a locking side nail 19, a locking pressure plate 20 and an amplitude guide 21. The amplitude guide 21 is fixed on the inertia flywheel 22 by screws arranged symmetrically on the left and right. , two amplitude guide rail baffles 18 are respectively fixed on the upper and lower sides of the amplitude guide rail 21; the amplitude adjustment rod 17 is installed in the inner hole of the amplitude guide rail baffle 18, and the amplitude adjustment block 13 is sleeved on the amplitude adjustment rod 17 through a threaded form. When the amplitude adjustment rod 17 is rotated, the amplitude adjustment block 13 is driven to move up and down along the inner side of the amplitude guide rail 21; the end of the amplitude adjustment block 13 is installed in the square groove of the locking pressure plate 20 through a boss structure, and the locking pressure plate 2 0 is meshed with the amplitude guide rail 21 in a mouse-shaped tooth, and the position of the amplitude adjustment block 13 is locked by pressing the clamping nut 16. At the same time, the two locking side nails 19 arranged on the left and right pass through the long strip hole of the amplitude guide rail 21 and are screwed into the left and right threaded holes of the amplitude adjustment block 13. The position of the amplitude adjustment block 13 is locked again by relying on the friction force generated by the nail heads of the locking side nails 19; the roller box body 14 is sleeved on the front end of the amplitude adjustment block 13, and axial positioning is performed by rolling the box body cover plate 12. Four groups of roller shafts 11 are installed inside the roller box body 14, and needle bearings 15 are installed on the roller shafts 11. During the movement, the needle bearings 15 on both sides of the pop-up roller box body 14 contact the auxiliary cross slide 10 or the main cross slide 9. This structural form can avoid direct friction between the roller box body 14 and the inner slideways of the main cross slide 9 and the auxiliary cross slide 10 during high-frequency reciprocating motion, making the system run more smoothly.

[0064] The actuator assembly 104 includes a load-bearing square tube 7, a guide rail mounting seat 6, a linear guide rail assembly 5 and a support 4. The main cross slide 9 and the auxiliary cross slide 10 are connected as a whole through the cross slide cross plate 8, and are connected to the end of the load-bearing square tube 7 through the front end stop of the main cross slide 9. The front end of the load-bearing square tube 7 is connected to the support rod 3 by a cone. The outer side of the load-bearing square tube 7 is installed on the inner side of two groups of guide rail mounting seats 6 symmetrically arranged along the axis of linear motion through the linear guide rail assembly 5, and the guide rail mounting seats 6 are fixed on the support 4.

[0065] The driving motor 53 drives the gear shaft 49, driving the driving main gear 39 and the inertia flywheel 22 to rotate, and the amplitude adjustment block 13 connected to the inertia flywheel 22 swings in a circle to drive the main cross slide 9 to reciprocate, thereby achieving the effect of linear oscillation of the aircraft 2. Its motion transmission route is: driving motor 53→gear shaft 49→main gear 39→spline shaft 34→inertia flywheel 22→amplitude adjustment block 13→main cross slide 9→load-bearing square tube 7→support rod 3→aircraft 2.

[0066] The amplitude adjustment block 13 is installed at the center of the roller box 14 in the amplitude adjustment component 101, and four groups of roller shafts 11 are installed around the roller box 14. Two groups of needle bearings 15 that can withstand large radial loads and occupy a small installation space are installed on each group of roller shafts 11. During the movement, the needle bearings 15 contact the cross slide. The rolling body cover plate 12 is installed on the outside of the roller box 14 by screws. This structural form can avoid direct friction between the roller box 14 and the inner slides of the main cross slide 9 and the auxiliary cross slide 10 during high-frequency reciprocating motion, making the system run more smoothly.

[0067] The main cross slide 9 and the auxiliary cross slide 10 in the amplitude adjustment component 101 are connected to form a closed loop body through two sets of identical cross slide cross plates 8, and the roller box 14 reciprocates inside the closed loop body. In order to reduce the weight of the linear motion components, reduce the system driving torque, and ensure that the motion components have sufficient rigidity, the main cross slide 9 and the auxiliary cross slide 10 are subjected to structural grid weight reduction optimization during the design process.

[0068] Four groups of inertia adjustment mass blocks 29 are symmetrically mounted on the inner wall of the inertia flywheel 22 in the inertia adjustment assembly 102 along the cross axis thereof, and the displacement from the rotation axis of the inertia flywheel 22 can be adjusted. The inertia adjustment mass blocks 29 are connected to the inertia adjustment slider 28, and are installed on the shaft diameter of the inertia adjustment screw 24 through a threaded form. When the inertia adjustment large bevel gear 30 rotates, the four groups of identical inertia adjustment small bevel gears 26 are driven to rotate synchronously through gear meshing transmission, thereby driving the inertia adjustment mass blocks 29 on the inertia adjustment screw 24 to move forward and backward along the inertia adjustment guide rail 27, thereby realizing the inertia adjustment of the test device.

[0069] The inertia adjustment long shaft 32 in the inertia adjustment component 102 is nested inside the spline shaft 34 through a pair of angular contact ball bearings 35. The front end of the inertia adjustment long shaft 32 is connected to the inertia adjustment large bevel gear shaft 31, and the rear end is connected to the inertia adjustment reduction motor 43. When the system rotational inertia needs to be adjusted, the inertia adjustment reduction motor 43 drives the inertia adjustment large bevel gear shaft 31 to rotate through the inertia adjustment long shaft 32, thereby driving the inertia adjustment large bevel gear 30 to rotate. This "nested" structure utilizes the working principle of a large shaft sleeve and a small shaft, effectively saves the structural space of the device, and can perform real-time inertia adjustment of the system to ensure stable operation of the equipment.

[0070] The inertia of the inertia adjustment component 102 around the axis can be adjusted in real time to ensure that the periodic speed fluctuation of the system is minimized. When the wind load and the inertia load do excess work on the system, the inertia adjustment mass block 29 moves away from the rotation axis, reducing the amplitude of the system speed increase; when the wind load and the inertia load do insufficient work on the system, the inertia adjustment mass block 29 moves closer to the rotation axis, reducing the amplitude of the system speed decrease. This variable inertia high-frequency reciprocating motion test device for an aircraft 2 can ensure that the drive motor 53 is minimally affected by the impact of variable loads, and the mechanism operates stably, thereby ensuring high accuracy and good repeatability of the test data.

[0071] The eccentric bushing 47 in the driving assembly 103 is installed in the base 46, and the gear shaft 49 is fixed by two sets of double-row cylindrical roller bearings 51. The driving motor 53 drives the gear shaft 49 to mesh with the main gear 39 for transmission. The structural form of the eccentric bushing 47 can effectively improve the fit degree of gear meshing transmission and reduce transmission noise. The front end of the spline shaft 34 adopts a double-row angular contact ball bearing 37 and the rear end adopts a self-aligning roller bearing 41 to be installed in the base 46. This arrangement can not only withstand the large impact during the gear meshing transmission process, but also ensure the concentricity of the transmission system.

[0072] Specific implementation method 2: Combination Figure 1-Figure 15 This embodiment describes a method for testing the reciprocating motion of an aircraft with variable amplitude and inertia, which is implemented based on a device for testing the reciprocating motion of an aircraft with variable amplitude and inertia described in the first embodiment, and includes the following steps:

[0073] Step a, equipment installation and control system connection: install the variable amplitude and inertia aircraft reciprocating motion test device controlled by the control system in the wind tunnel 1, and connect the data line of the control system and the balance to the wind tunnel control and acquisition system;

[0074] Step b, calculating the inertia flywheel speed and the motor speed: according to the oscillation frequency of the aircraft 2 during the test, the rotation speed of the inertia flywheel 22 is solved, and then the speed of the drive motor is calculated by the gear reduction ratio, as shown in the following formula:

[0075]

[0076] Where w is the speed of the motor, f is the oscillation frequency of the aircraft 2, and z 1 The number of teeth on the main gear, z 2 is the number of teeth on the gear shaft;

[0077] Step c, amplitude adjustment and moment of inertia calculation: according to the amplitude of the aircraft 2, the distance between the amplitude adjustment component 101 and the rotation axis of the inertia flywheel 22 is adjusted, and the moment of inertia under the amplitude is calculated as follows:

[0078] I=I固 +I 振 =I 固 +m 振 ×A 2

[0079] Where A is the amplitude corresponding to the oscillation frequency f of the aircraft 2, I 固 is the inertia around the rotation axis excluding the amplitude adjustment component 101, I 振 is the inertia of the amplitude adjustment component 101 around the rotation axis, m 振 The mass of the amplitude adjustment component 101;

[0080] Step d, starting the wind tunnel to perform an oscillating motion at a given frequency f and an amplitude A: starting the wind tunnel 1, and after the wind speed of the wind tunnel 1 reaches a target value, driving the aircraft 2 to perform an oscillating motion at a given frequency f and an amplitude A;

[0081] Step e, calculating the equivalent moment of inertia required by the inertia adjustment component 102;

[0082]

[0083] In the formula, I F is the equivalent moment of inertia required by the lower inertia adjustment component 102 corresponding to the oscillation frequency f of the aircraft 2, ΔW max is the maximum surplus or loss work corresponding to the oscillation frequency f of aircraft 2, w F is the angular velocity of the inertia flywheel 22 at the oscillation frequency f of the aircraft 2, w Fmax is the upper limit of the angular velocity fluctuation of the inertia flywheel 22 corresponding to the oscillation frequency f of the aircraft 2, w Fmin is the lower limit of the angular velocity fluctuation of the inertia flywheel corresponding to the oscillation frequency f of the aircraft 2, and δ is the velocity non-uniformity coefficient;

[0084] Step f, calculating the center distance between the inertia adjustment mass block and the rotating shaft: calculating the center distance L between the inertia adjustment mass block 29 and the rotating shaft on which the inertia flywheel 22 is rotatably mounted according to the equivalent rotational inertia;

[0085]

[0086] Where, L is the center distance of the lower inertia adjustment mass block 29 from the rotating shaft corresponding to the oscillation frequency f of the aircraft 2, m 质 is the mass of the inertia adjustment mass block 29, I F0 is the inertia of the inertia adjustment assembly 102 relative to the rotating shaft except the inertia adjustment mass block 29;

[0087] Step g, controlling the amplitude adjustment reduction motor to adjust the inertia adjustment mass block to a specified position: controlling the amplitude adjustment reduction motor to rotate according to the distance L between the inertia adjustment mass block 29 and the center of the rotating shaft to adjust the inertia adjustment mass block 29 to a specified position;

[0088] Step h, starting the wind tunnel data acquisition system to collect and record test values;

[0089] Step i, stopping the operation of wind tunnel 1 and reducing the wind speed to 0;

[0090] Step j, repeat steps b and i to complete the test under different frequency and amplitude combinations.

[0091] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be arranged and combined, and those skilled in the art can exhaust all possibilities based on the mathematical knowledge of arrangement and combination. Therefore, the present invention will no longer describe the technical solutions after arrangement and combination one by one, but it should be understood that the technical solutions after arrangement and combination have been disclosed by the present invention.

[0092] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A reciprocating motion test device for an aircraft with variable amplitude and inertia, characterized in that: The invention comprises an amplitude adjustment component (101), an inertia adjustment component (102), a driving component (103) and an execution component (104); the driving component (103) is connected to the execution component (104) via the amplitude adjustment component (101) and the inertia adjustment component (102) in sequence; a support rod (3) is installed on the execution component (104); the support rod (3) is inserted into a wind tunnel (2) and is installed with an aircraft (2).

2. The aircraft reciprocating motion test device with variable amplitude and inertia according to claim 1, characterized in that: The driving assembly (103) comprises a driving motor (53), a motor bracket (54), a gear shaft (49), a main gear (39), a base (46), a spline shaft (34), a double-row angular contact ball bearing (37) and a spherical roller bearing (41); the base (46) is fixedly mounted on one side of the wind tunnel (2); the driving motor (53) is fixedly mounted on the base (46) via the motor bracket (54); the output end of the driving motor (53) is equipped with a gear shaft (49); the gear The shaft (49) is rotatably mounted on the base (46) through a bearing assembly, a main gear (39) is mounted on the gear shaft (49), a spline shaft (34) is fixed in an inner hole of the main gear (39) through a spline connection, a double-row angular contact ball bearing (37) and a spherical roller bearing (41) are respectively mounted on the front and rear ends of the spline shaft (34), so that the front and rear ends of the spline shaft (34) are rotatably mounted on the base (46) through the double-row angular contact ball bearing (37) and the spherical roller bearing (41).

3. The aircraft reciprocating motion test device with variable amplitude and inertia according to claim 2, characterized in that: The bearing assembly comprises an eccentric bushing (47), a double-row cylindrical roller bearing (51), a bearing inner baffle (50), a bearing outer baffle (48) and a retaining nut (52); the gear shaft (49) is fixed inside the eccentric bushing (47) through two sets of double-row cylindrical roller bearings (51); the inner and outer diameter axes of the eccentric bushing (47) installed in the base (46) are not coaxially arranged; the bearing inner baffle (50) and the bearing outer baffle (48) axially position the double-row cylindrical roller bearing (51); and the outer side of the bearing inner baffle (50) is locked by the retaining nut (52).

4. The aircraft reciprocating motion test device with variable amplitude and inertia according to claim 3, characterized in that: The front and rear ends of the double-row angular contact ball bearing (37) are positioned respectively by the front of the outer retaining ring (36) and the front of the inner retaining ring (38), and the front and rear ends of the spherical roller bearing (41) are positioned respectively by the rear of the inner retaining ring (40), the bearing locking retaining ring (42) and the rear of the outer retaining ring (45).

5. The aircraft reciprocating motion test device with variable amplitude and inertia according to claim 4, characterized in that: The inertia adjustment component (102) comprises an inertia adjustment reduction motor (43), an inertia adjustment reduction motor mounting seat (44), an inertia adjustment long shaft (32), an angular contact ball bearing (35), an inertia adjustment slider (28), an inertia adjustment guide rail (27), an inertia adjustment small bevel gear (26), a deep groove ball bearing (25), an inertia adjustment screw (24), a seat bearing (23), an inertia flywheel (22), an inertia adjustment mass block (29), an inertia adjustment large bevel gear (30), an inertia adjustment large bevel gear shaft (31) and a small round nut (33 ), the inertia adjustment long shaft (32) is installed in the inner hole of the spline shaft (34) through a pair of angular contact ball bearings (35), the inertia adjustment reduction motor mounting seat (44) is installed on the outer retaining ring (45), the inertia adjustment reduction motor (43) is fixed on the inertia adjustment reduction motor mounting seat (44) through a flange, and the output end of the inertia adjustment reduction motor (43) is connected to the inertia adjustment long shaft (32) through a key; the inertia adjustment long shaft (32) transmits torque to the inertia adjustment large bevel gear shaft (31) through a key, and the inertia adjustment large bevel gear shaft (31) is connected to the inertia adjustment large bevel gear shaft (31) through a flange. A group of deep groove ball bearings (25) are fixed in the inner hole of the inertia flywheel (22), and the rear end of the deep groove ball bearing (25) is axially positioned by a small round nut (33); an inertia adjustment large bevel gear (30) is installed on the outer side of the inertia adjustment large bevel gear shaft (31), and the inertia adjustment large bevel gear (30) is meshed with four groups of inertia adjustment small bevel gears (26) installed at the front end of the inertia adjustment screw (24); four groups of inertia adjustment guide rails (27) are installed on the inner wall of the inertia flywheel (22) connected to the spline shaft (34), and an inertia adjustment slider is installed on the inertia adjustment guide rail (27) (28), the inertia adjustment slider (28) is sleeved on the inertia adjustment screw (24), the inertia adjustment screw (24) is fixed on the inner wall of the inertia flywheel (22) through two groups of seat bearings (23), and an inertia adjustment mass block (29) is installed on the outer side of the inertia adjustment slider (28); when the inertia adjustment large bevel gear (30) rotates, the four groups of identical inertia adjustment small bevel gears (26) are driven to rotate synchronously through gear meshing transmission, thereby driving the inertia adjustment mass block (29) on the inertia adjustment screw (24) to move forward and backward along the inertia adjustment guide rail (27).

6. The aircraft reciprocating motion test device with variable amplitude and inertia according to claim 5, characterized in that: The amplitude adjustment component (101) comprises an auxiliary cross slide (10), a main cross slide (9), a cross slide cross plate (8), a roller shaft (11), a rolling body cover plate (12), an amplitude adjustment block (13), a roller box body (14), a needle bearing (15), a clamping nut (16), an amplitude adjustment rod (17), an amplitude guide baffle (18), a locking side nail (19), a locking pressure plate (20) and an amplitude guide (21), wherein the amplitude guide (21 ) is fixed on the inertia flywheel (22) by screws arranged symmetrically on the left and right, and two amplitude guide rail baffles (18) are respectively fixed on the upper and lower sides of the amplitude guide rail (21); the amplitude adjustment rod (17) is installed in the inner hole of the amplitude guide rail baffle (18), and the amplitude adjustment block (13) is sleeved on the amplitude adjustment rod (17) by threading. When the amplitude adjustment rod (17) is rotated, the amplitude adjustment block (13) is driven to move up and down along the inner side of the amplitude guide rail (21); The end of the amplitude adjustment block (13) is installed in the square groove of the locking pressure plate (20) through a boss structure. The locking pressure plate (20) and the amplitude guide rail (21) are meshed with mouse-shaped teeth. The position of the amplitude adjustment block (13) is locked by pressing the clamping nut (16). At the same time, two locking side nails (19) arranged on the left and right are passed through the long holes of the amplitude guide rail (21) and screwed into the left and right threaded holes of the amplitude adjustment block (13). The locking side nails (19) are used to generate a locking force. The friction force realizes the re-locking of the position of the amplitude adjustment block (13); the roller box body (14) is sleeved on the front end of the amplitude adjustment block (13) and is axially positioned by rolling the box body cover plate (12); four groups of roller shafts (11) are installed inside the roller box body (14); needle bearings (15) are installed on the roller shafts (11); during the movement, the needle bearings (15) on both sides of the pop-up roller box body (14) contact the auxiliary cross slide (10) or the main cross slide (9).

7. The aircraft reciprocating motion test device with variable amplitude and inertia according to claim 6, characterized in that: The actuator assembly (104) comprises a load-bearing square tube (7), a guide rail mounting seat (6), a linear guide rail assembly (5) and a support seat (4); a main cross slide (9) and an auxiliary cross slide (10) are connected as a whole via a cross slide cross plate (8), and are connected to the end of the load-bearing square tube (7) via a front end stop of the main cross slide (9); the front end of the load-bearing square tube (7) and the support rod (3) are connected by a cone; the outer side of the load-bearing square tube (7) is mounted on the inner side of two groups of guide rail mounting seats (6) symmetrically arranged along the linear motion axis via a linear guide rail assembly (5); and the guide rail mounting seats (6) are fixed on the support seat (4).

8. A method for testing reciprocating motion of an aircraft with variable amplitude and inertia, which is realized by relying on the reciprocating motion testing device of an aircraft with variable amplitude and inertia as claimed in claim 7, characterized in that: The following steps are involved: Step a, installing the variable amplitude and inertia aircraft reciprocating motion test device controlled by the control system in the wind tunnel (1), and connecting the data line of the control system and the balance to the wind tunnel control and acquisition system; Step b, according to the oscillation frequency of the aircraft (2) during the test, the rotation speed of the inertia flywheel (22) is calculated, and then the rotation speed of the drive motor is calculated by the gear reduction ratio, as shown in the following formula: In the formula, w is the speed of the motor, f is the oscillation frequency of the aircraft (2), z1 is the number of teeth on the main gear, and z2 is the number of teeth on the gear shaft; Step c, according to the amplitude of the aircraft (2), adjusting the distance between the amplitude adjustment component (101) and the rotation axis of the inertia flywheel (22), and calculating the moment of inertia under the amplitude, as shown in the following formula: I=I 固 +I 振 =I 固 +m 振 ×A 2 Where A is the amplitude of the aircraft (2) at the oscillation frequency f, I 固 is the inertia around the rotation axis excluding the amplitude adjustment component (101), I 振 is the inertia of the amplitude adjustment component (101) around the rotation axis, m 振 is the mass of the amplitude adjustment component (101); Step d, starting the wind tunnel (1), and after the wind speed of the wind tunnel (1) reaches a target value, driving the aircraft (2) to perform an oscillating motion at a given frequency f and amplitude A; Step e, calculating the equivalent moment of inertia required by the inertia adjustment component (102); In the formula, I F is the equivalent moment of inertia required by the lower inertia adjustment component (102) corresponding to the oscillation frequency f of the aircraft (2), ΔW max is the maximum surplus or loss work corresponding to the oscillation frequency f of the aircraft (2), w F is the angular velocity of the inertia flywheel (22) at the oscillation frequency f of the aircraft (2), w Fmax is the upper limit of the angular velocity fluctuation of the inertia flywheel (22) corresponding to the oscillation frequency f of the aircraft (2), w Fmin is the lower limit of the angular velocity fluctuation of the inertia flywheel corresponding to the oscillation frequency f of the aircraft (2), and δ is the velocity non-uniformity coefficient; Step f, calculating the center distance L between the inertia adjustment mass block (29) and the rotation axis of the rotational installation of the inertia flywheel (22) according to the equivalent rotational inertia; Where L is the center distance of the lower inertia adjustment mass block (29) from the rotation axis corresponding to the oscillation frequency f of the aircraft (2), m 质 is the mass of the inertia adjustment mass block (29), I F0 The inertia of the inertia adjustment component (102) excluding the inertia adjustment mass block (29) relative to the rotating shaft; Step g, controlling the rotation of the amplitude-adjusting reduction motor according to the distance L between the inertia-adjusting mass block (29) and the center of the rotating shaft, and adjusting the inertia-adjusting mass block (29) to a specified position; Step h, starting the wind tunnel data acquisition system to collect and record test values; Step i, stopping the operation of the wind tunnel (1) and reducing the wind speed to 0; Step j, repeat steps b and i to complete the test under different frequency and amplitude combinations.

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