Loading test device of flight motor
By designing bending moment loading mechanism and axial loading mechanism, and combining spline structure and tapered roller bearing, the problem of simultaneous loading of lift and bending moment in the existing technology was solved, and accurate and stable comprehensive load testing of flight motor was achieved.
Patent Information
- Application Number
- CN202520313812.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-25
- Publication Date
- 2026-02-13
- Estimated Expiration
- 2035-02-25
AI Technical Summary
Existing flight motor loading test equipment cannot simultaneously ensure the synchronous loading of lift and bending moment, and cannot simulate dynamic alternating loads, resulting in test results that do not match actual flight conditions.
A flight motor loading test device was designed. Through a bending moment loading mechanism and an axial loading mechanism, the flight motor can withstand the real bending moment at a specific angle and release the unexpected bending moment at other angles. Combined with a spline structure and tapered roller bearings, the lift and torque can be dynamically loaded synchronously.
It achieves accurate and stable simulation of the comprehensive load of the flight motor under conditions of no propeller and no airflow, ensuring the synchronous loading of lift, bending moment and torque, and the test results are closer to the actual flight conditions.
Smart Images
Figure CN223911020U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to aircraft testing technical field, concretely relates to loading test device of flight motor. BACKGROUND
[0002] The motor of the aircraft rotates at high speed to output torque to drive the propeller to work in the actual flight process, and the motor bears the load generated by the rotation of the propeller under the combined action of the propeller and the air flow, including the lift and the bending moment. Therefore, in the design and testing process of the motor, it is necessary to test the torque, the lift and the bending moment to verify the reliability.
[0003] In the actual flight, the bending moment of the motor is dynamic and alternating. In theory, as shown in the figure, Figure 6 When the radial direction of the propeller is perpendicular to the flow, the two pieces of propeller generate the maximum lift difference and input the maximum bending moment load to the motor; when the radial direction of the propeller is parallel to the flow, the lift of the two pieces of propeller remains consistent, and at this time, the bending moment input to the motor is the smallest.
[0004] In the related technology, the loading test device of the flight motor includes a loading mechanism and a load dynamometer, the lower end of the loading mechanism is connected with the motor, and the upper end is connected with the load dynamometer, the loading mechanism includes a loading disc, an extension shaft and an axial loading cylinder, the axial loading cylinder is connected with the loading disc, the extension shaft rotatable is arranged in the loading disc, the output shaft of the motor is connected with one end of the extension shaft, the other end of the extension shaft is connected with the load dynamometer, and the loading disc is used to replace the real propeller. Since the loading disc cannot rotate, the axial loading cylinder cannot realize the synchronous rotation with the rotor state of the motor. The loading device has the following problems: it is impossible to simultaneously ensure the lift and the bending moment, for example, if the lift is given priority to, only two axial loading cylinder values can be fixed at a time, resulting in that the bending moment borne by the flight motor is a continuous constant value, which is inconsistent with the actual situation; if the bending moment is given priority to, the dynamic phase and the loading force of the axial loading cylinder are required to have a super-high frequency dynamic response, and the stability of the lift load cannot be ensured. UTILITY MODEL CONTENTS
[0005] Therefore, the utility model provides a loading test device of a flight motor to solve the problem that the loading mechanism cannot simultaneously ensure the lift and the bending moment.
[0006] The utility model provides a loading test device of a flight motor, which comprises a support for mounting a flight motor to be tested, a loading assembly including a loading disc, a connecting shaft, an axial loading mechanism and a bending moment loading mechanism, an installation cavity is arranged on the loading disc, the connecting shaft is installed in the installation cavity, one end of the connecting shaft is connected with the output shaft of the flight motor through the bending moment loading mechanism, the axis of the connecting shaft coincides with the axis of the output shaft, the axial loading mechanism is arranged on the support, and the output end of the axial loading mechanism is connected with the loading disc.
[0007] Beneficial effects: the output shaft of the flight motor to be tested and the connecting shaft are connected through the bending moment loading mechanism, the axial loading mechanism sets the lift and bending moment values according to the real load, when the flight motor to be tested rotates to 90° or 180°, the flight motor bears the real bending moment, when the flight motor rotates to a position other than 90° or 180°, the unexpected bending moment will be released due to the setting of the bending moment loading mechanism, the bending moment of the flight motor becomes 0, thereby realizing the pulse input of the bending moment, and the lift loading and torque output can be ensured at the same time, the synchronous dynamic loading of the lift and pulse bending moment of the flight motor is realized, the input of various loads is closer to the real load, and the comprehensive load loading test of the flight torque, lift and bending moment is accurately and stably realized without loading the propeller and without air flow.
[0008] In an alternative embodiment, the bending moment loading mechanism comprises: a first fixing member fixed to one end of the connecting shaft; a second fixing member fixed to the output shaft; and a loading shaft rotatably arranged between the first fixing member and the second fixing member, and the axis of the loading shaft is perpendicular to the axis of the connecting shaft.
[0009] Beneficial effects: by arranging the loading shaft with the circumferential freedom between the output shaft and the connecting shaft, the unexpected bending moment is released, thereby realizing the pulse input of the bending moment, and the lift loading and torque output can be ensured at the same time. The bending moment loading mechanism has a simple structure and is easy to realize.
[0010] In an alternative embodiment, the first fixing member is a fixed shaft sleeve arranged on the loading shaft, and the second fixing member is two fixed shaft seats matched with both ends of the loading shaft.
[0011] Beneficial effects: the fixed shaft sleeve and the fixed shaft seat can facilitate the installation of the loading shaft and the connection with the output shaft and the connecting shaft, the fixed shaft sleeve has the advantages of simplified installation and maintenance, low cost, good shock absorption performance and the like, and the fixed shaft seat has the advantages of enhanced structural stability and facilitated assembly.
[0012] In an alternative embodiment, a spline structure is arranged between the fixed shaft sleeve and the loading shaft, a bearing is arranged between the fixed shaft seat and the loading shaft, or a bearing is arranged between the fixed shaft sleeve and the loading shaft, and a spline structure is arranged between the fixed shaft seat and the loading shaft.
[0013] Beneficial effects: the spline structure increases the freedom of the loading shaft in the axial direction, reduces the influence of the additional load while ensuring the lossless transmission of the bending moment.
[0014] In an alternative embodiment, the spline structure comprises an outer spline and an inner spline in engagement, and the outer spline is arranged on the loading shaft.
[0015] In an alternative embodiment, the spline structure further comprises a ball arranged between the outer spline and the inner spline.
[0016] Beneficial effects: the spline structure utilizes ball rolling instead of sliding contact, greatly reduces friction, improves energy transmission efficiency, and reduces wear rate.
[0017] In an alternative embodiment, the bearing is a tapered roller bearing.
[0018] Beneficial effects: the tapered roller bearing has the advantages of simple structure, convenient use, and low cost.
[0019] In an alternative embodiment, the axial loading mechanism includes two axial loading pieces, which are symmetrically arranged on the loading disc along the axis of the loading disc.
[0020] Beneficial effects: the two axial loading pieces provide a force parallel to the axis of the loading disc, and the loading disc transmits the force to the connecting shaft and the output shaft, simulating the axial force and bending moment received by the output shaft.
[0021] In an alternative embodiment, the axial loading piece is a loading cylinder.
[0022] Beneficial effects: the loading cylinder has the advantages of simple structure, low cost, accurate control, and smooth movement.
[0023] In an alternative embodiment, the loading test device further includes a dynamometer and a transmission shaft, the dynamometer is arranged on the support, and the dynamometer is connected to the other end of the connecting shaft through the transmission shaft.
[0024] Beneficial effects: the dynamometer is used to detect the power of the output shaft, and the power of the flight motor is tested. BRIEF DESCRIPTION OF DRAWINGS
[0025] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings needed in the specific embodiments or prior art description. Obviously, the drawings described below are some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative labor.
[0026] Figure 1 It is a perspective view of a loading test device for a flight motor according to an embodiment of the present application;
[0027] Figure 2 It is a perspective view of a loading test device for a flight motor according to an embodiment of the present application; Figure 1 It is a partial structure schematic view of the loading test device shown in the figure;
[0028] Figure 3 It is a side view of a bending moment loading mechanism shown in the figure; Figure 2 It is a side view of a bending moment loading mechanism shown in the figure;
[0029] Figure 4For Figure 1 a cross-sectional view of the bending moment loading mechanism shown in FIG.
[0030] Figure 5 For Figure 1 a bending moment loading change process schematic diagram of the loading test device shown in FIG.
[0031] Figure 6 For the flight electric motor in the related art, a bending moment alternate process schematic diagram is shown.
[0032] Mark explanation:
[0033] 1, loading disc;
[0034] 2, connecting shaft;
[0035] 3, axial loading mechanism; 301, axial loading piece;
[0036] 4, bending moment loading mechanism; 401, first fixed piece; 4011, outer connecting sleeve; 4012, end cover; 4013, spline sleeve; 402, second fixed piece; 403, loading shaft; 404, bearing;
[0037] 5, to be tested flight electric motor;
[0038] 6, mounting frame. DETAILED DESCRIPTION
[0039] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be described clearly and completely below in combination with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the protection scope of the utility model.
[0040] The embodiments of the utility model will be described below in combination with Figures 1 to 5 .
[0041] According to the embodiments of the utility model, a kind of loading test device of flight electric motor is provided, comprising: support and loading assembly, support is used to install the flight electric motor to be tested;Loading assembly includes loading disc 1, connecting shaft 2, axial loading mechanism 3 and bending moment loading mechanism 4, loading disc 1 is equipped with installation cavity, connecting shaft 2 is installed in installation cavity, one end of connecting shaft 2 is connected with the output shaft of flight electric motor by bending moment loading mechanism 4, the axis of connecting shaft 2 coincides with the axis of output shaft, axial loading mechanism 3 is arranged in support, and the output end of axial loading mechanism 3 is connected with loading disc 1.
[0042] The loading test device of the flight motor of the embodiment is used to connect the output shaft of the flight motor 5 to be tested and the connecting shaft 2 through the bending moment loading mechanism 4, and the axial loading mechanism 3 sets the lift and bending moment values according to the real load. When the flight motor 5 to be tested rotates to 90° or 180°, the flight motor bears the real bending moment. When the flight motor rotates to a position other than 90° or 180°, the bending moment loading mechanism 4 is set, and the unexpected bending moment is released at this time. The bending moment of the flight motor becomes 0 (as shown in Figure 5 Thus, the pulse input of the bending moment is realized, and the lift loading and torque output can be ensured at the same time. The synchronous dynamic loading of the lift and pulse bending moment of the flight motor is realized, the input of each load is closer to the real load, and the comprehensive load loading test of the flight torque, lift and bending moment is accurately and stably realized without loading the propeller and without air flow.
[0043] In one embodiment, the bending moment loading mechanism 4 includes a first fixing member 401, a second fixing member 402 and a loading shaft 403. The first fixing member 401 is fixed to one end of the connecting shaft 2. The second fixing member 402 is fixed to the output shaft. The loading shaft 403 is rotatably arranged between the first fixing member 401 and the second fixing member 402, and the axis of the loading shaft 403 is perpendicular to the axis of the connecting shaft 2. By arranging the loading shaft 403 with the circumferential freedom between the output shaft and the connecting shaft 2, the unexpected bending moment is released, and the pulse input of the bending moment is realized, and the lift loading and torque output can be ensured at the same time. The structure of the bending moment loading mechanism 4 is simple and easy to realize.
[0044] In one embodiment, the first fixing member 401 is a fixed shaft sleeve arranged on the loading shaft 403, and the second fixing member 402 is two fixed shaft seats matched with the two ends of the loading shaft 403. The fixed shaft sleeve and the fixed shaft seat can facilitate the installation of the loading shaft 403 and the connection with the output shaft and the connecting shaft 2. The fixed shaft sleeve has the advantages of simplified installation and maintenance, low cost and good damping performance. The fixed shaft seat has the advantages of enhanced structural stability and convenient assembly.
[0045] In one embodiment, a spline structure is arranged between the fixed shaft sleeve and the loading shaft 403, and a bearing 404 is arranged between the fixed shaft seat and the loading shaft 403. The two ends of the loading shaft 403 adopt the bearing 404, which can realize the circumferential freedom of the output shaft and ensure the axial positioning of the loading shaft 403. The spline structure increases the freedom of the loading shaft 403 in the axial direction, reduces the influence of the additional load while ensuring the lossless transmission of the bending moment.
[0046] Further, the spline structure includes an outer spline and an inner spline which are engaged. The outer spline is arranged on the loading shaft 403, and the inner spline is arranged on the fixed shaft sleeve.
[0047] Specifically, as Figure 4As shown, the fixed bushing includes an outer connecting sleeve 4011, two end caps 4012, and a spline sleeve 4013. The outer connecting sleeve 4011 is connected to the connecting shaft 2. The two end caps 4012 are disposed at both ends of the outer connecting sleeve 4011. The spline sleeve 4013 is sleeved on the loading shaft 403 and located between the two end caps 4012. The two end caps 4012 limit the position of the spline sleeve 4013, ensuring that the spline sleeve 4013 is correctly fixed in the axial and circumferential directions, thereby achieving a precise positioning function.
[0048] It is understood that in another embodiment, a bearing 404 is provided between the fixed bushing and the loading shaft 403, and a spline structure is provided between the fixed bearing seat and the loading shaft 403. In this case, a spline structure is provided between the two ends of the loading shaft 403 and the fixed bearing seat, and a bearing 404 is provided between the middle of the loading shaft 403 and the fixed bushing. The bearing 404 can be a back-to-back tapered roller bearing or other thrust bearing 404. In this case, the internal spline is provided on the fixed bearing seat.
[0049] In one embodiment, the spline structure further includes balls disposed between the external and internal splines; in this case, the spline structure can be called a ball spline. The spline structure utilizes rolling rather than sliding contact of the balls, greatly reducing friction, improving energy transfer efficiency, and lowering wear rate.
[0050] In one embodiment, bearing 404 is a tapered roller bearing. Tapered roller bearings have advantages such as simple structure, ease of use, and low cost. By employing a design combining ball splines and tapered roller bearings, the circumferential degree of freedom of the loading shaft 403 is decoupled, thereby achieving synchronous dynamic loading of the lift pulse bending moment of the flight motor.
[0051] It is understood that in another embodiment, bearing 404 is a thrust bearing or the like.
[0052] In one embodiment, the axial loading mechanism 3 includes two axial loading members 301, which are symmetrically arranged on the loading disk 1 about the axis of the loading disk 1. The two axial loading members 301 provide an axial force parallel to the loading disk 1 to the loading disk 1, and the loading disk 1 then transmits the force to the connecting shaft 2 and the output shaft, simulating the axial force and bending moment experienced by the output shaft.
[0053] In one embodiment, the axial loading member 301 is a loading cylinder. The lift and bending moment of the flight motor are applied by setting the axial tension of the two loading cylinders. If the force values of the two loading cylinders are set identically, the lift is the sum of the tension values of the two loading cylinders, and the bending moment is 0; if the force values of the two loading cylinders are set differently, the lift is still the sum of the tension values of the two loading cylinders, and the bending moment is M. z=F1×L-F2×L, wherein, L is the force arm of the loading cylinder to the axis of the connecting shaft 2, F1 is the force value of one loading cylinder, and F2 is the force value of the other loading cylinder. The loading cylinder has simple structure, low cost, accurate control and stable movement.
[0054] Further, the upper end of the loading cylinder is arranged on the support through the hinge seat, the piston rod of the loading cylinder is arranged on the loading disc 1 through the hinge seat, the force sensor is arranged on the piston rod, and the acting force of the loading cylinder is detected through the force sensor.
[0055] In an embodiment, the loading test device further comprises a dynamometer and a transmission shaft, the dynamometer is arranged on the support, and the dynamometer is connected to the other end of the connecting shaft 2 through the transmission shaft. The power of the output shaft is detected through the dynamometer, and the power test of the flight motor is realized.
[0056] Further, the transmission shaft is a coupling or the like. The bearing is arranged between the connecting shaft 2 and the loading disc 1, and the bearing preferably adopts a thrust bearing.
[0057] Further, the support comprises a frame and a mounting rack 6, the flight motor 5 to be tested is arranged on the mounting rack 6, and the dynamometer and the axial loading piece 301 are arranged on the frame.
[0058] It should be noted that, Figure 3 and Figure 4 The abscissa of the two figures is the rotation angle of the output shaft of the flight motor, the ordinate is the bending moment, the gray part is the propeller, and the arrow above the propeller is the direction of the flow.
[0059] Although the embodiments of the utility model are described in combination with the drawings, various modifications and changes can be made by those skilled in the art without departing from the spirit and scope of the utility model, and such modifications and changes all fall within the scope defined by the appended claims.
Claims
1. A loading test device for a flight motor, characterized by comprising: The utility model relates to a loading test device for flight motor, comprising: a bracket for mounting the flight motor to be tested; a loading assembly comprising a loading disc (1), a connecting shaft (2), an axial loading mechanism (3) and a bending moment loading mechanism (4), the loading disc (1) is provided with a mounting cavity, the connecting shaft (2) is mounted in the mounting cavity, one end of the connecting shaft (2) is connected with the output shaft of the flight motor through the bending moment loading mechanism (4), the axis of the connecting shaft (2) coincides with the axis of the output shaft, the axial loading mechanism (3) is arranged on the bracket, and the output end of the axial loading mechanism (3) is connected with the loading disc (1).
2. The loading test device according to claim 1, characterized in that, The bending moment loading mechanism (4) comprises: a first fixing part (401) fixed to one end of the connecting shaft (2); a second fixing part (402) fixed to the output shaft; a loading shaft (403) rotatably arranged between the first fixing part (401) and the second fixing part (402), and the axis of the loading shaft (403) is perpendicular to the axis of the connecting shaft (2).
3. The loading test device of claim 2, wherein The first fixing part (401) is a fixed shaft sleeve sleeved on the loading shaft (403), and the second fixing part (402) is two fixed shaft seats matched with both ends of the loading shaft (403).
4. The loading test device of claim 3, wherein Spline structure is arranged between the fixed shaft sleeve and the loading shaft (403), bearings (404) are arranged between the fixed shaft seat and the loading shaft (403), or bearings (404) are arranged between the fixed shaft sleeve and the loading shaft (403), and spline structure is arranged between the fixed shaft seat and the loading shaft (403).
5. The loading test device of claim 4, wherein The spline structure comprises engaged external spline and internal spline, and the external spline is arranged on the loading shaft (403).
6. The loading test device of claim 5, wherein The spline structure further comprises balls, and the balls are arranged between the external spline and the internal spline.
7. The loading test device of claim 4, wherein The bearing (404) is a tapered roller bearing.
8. The loading test device according to any one of claims 1 to 7, characterized in that, The axial loading mechanism (3) comprises two axial loading parts (301), and the two axial loading parts (301) are symmetrically arranged on the loading disc (1) along the axis of the loading disc (1).
9. The loading test device of claim 8, wherein, The axial loading part (301) is a loading cylinder.
10. The loading test device according to any one of claims 1 to 7, characterized by The loading test device further comprises a dynamometer and a transmission shaft, the dynamometer is arranged on the bracket, and the other end of the connecting shaft (2) is connected with the dynamometer through the transmission shaft.