A multi-load UAV engine dynamometer and operation method

Abstract

The present invention discloses a multi-load UAV engine dynamometer and an operation method, belonging to the field of UAV engine test equipment. A multi-load UAV engine dynamometer includes a frame, a detection unit is installed on the top of the frame, an engine body is arranged on one side of the detection unit, the detection unit and the engine body are connected and installed together through a transmission shaft, and a support seat is installed on the transmission shaft through a bearing; the present invention uses the kinetic energy generated by the rotation of the transmission shaft to generate airflow through the heat dissipation structure, and dissipates the heat generated by the detection unit and the outer wall of the transmission shaft, and can adjust the heat dissipation intensity according to the extreme working conditions. In the heat dissipation process, the heat of the transmission shaft center is assisted by heat pipes for conduction and heat dissipation, thereby improving the heat dissipation effect, avoiding interference caused by vibration, and cooperating with PTFE sliders and copper meshes to realize energy conversion and recycling.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle engine testing equipment, and in particular to a multi-load unmanned aerial vehicle engine dynamometer and an operating method thereof. Background Art

[0002] In the power system of UAV, the engine is one of the core components. Its performance and reliability have a vital impact on the flight performance and safety of the UAV. In order to ensure the performance and reliability of the UAV engine, it needs to be fully tested and evaluated; Among them, the commonly used detection equipment dynamometer can monitor parameters such as torque and power of UAV engines. During the detection, the output end of the engine to be tested is usually connected to the input end of the detection unit through a transmission shaft. However, during the test, due to the long-term operation of the engine or the high outdoor temperature, the heat generated during operation is transmitted to the detection area through the transmission shaft, causing the sensor installed for the detection to drift, and the high temperature of the transmission shaft causes deformation and wear, which in turn affects the detection accuracy of the device. For this reason, we proposed a multi-load UAV engine dynamometer and operation method to solve the above-mentioned problems. Summary of the invention

[0003] The purpose of the present invention is to solve the problem in the prior art that due to long-term operation of the engine or excessively high outdoor temperature, the heat generated during operation is transferred to the detection area through the transmission shaft, causing the drift of the sensor installed for detection, and the high temperature of the transmission shaft causes deformation and wear, and a multi-load UAV engine dynamometer and operation method are proposed.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions: A multi-load UAV engine dynamometer comprises a frame, a detection unit is installed on the top of the frame, an engine body is arranged on one side of the detection unit, the detection unit and the engine body are connected and installed together through a transmission shaft, a support seat is installed on the transmission shaft through a bearing, and blades with adjustable attack angles are distributed in a ring shape around the transmission shaft; a heat pipe with an inclined angle is arranged on one side of the detection unit, and one end of the heat pipe is embedded and installed on the transmission shaft; wherein the heat pipe comprises an evaporation section, a heat dissipation section and a condensation section, and the heat dissipation section of a plurality of the heat pipes is located in the airflow output area at one end of the blade; a PTFE slider and a copper mesh are sleeved on the outside of the transmission shaft, and heat is transferred through the transmission shaft when the detection unit is working, and airflow is generated by the axial rotation of the plurality of blades around the transmission shaft to dissipate heat from the outer wall of the transmission shaft and the detection unit, and heat is conducted and dissipated from the center of the transmission shaft by the heat pipe, and energy is recovered by frictional power generation during the heat dissipation process.

[0005] Preferably, a mounting sleeve is fixedly mounted on the surface of the transmission shaft, the blades are fixedly mounted on the mounting sleeve, and the bottom of one end of a plurality of the blades is rotatably connected to a connecting block via a pin shaft, and one end of the connecting block is fixed to the outer wall of the mounting sleeve.

[0006] Preferably, the other ends of the plurality of blades are fixedly connected to a limiting slider, the limiting slider is slidably connected in a limiting slot, the limiting slot is provided on the surface of the mounting sleeve, an arc-shaped heat conducting plate is fixedly connected in the limiting slot, a memory alloy spring is fixedly connected to the top of the arc-shaped heat conducting plate, one end of the memory alloy spring is fixedly connected to the limiting slider, an outer sleeve of the memory alloy spring is provided with a heat insulating sleeve, and an end of the heat insulating sleeve is fixedly connected to the limiting slider and the arc-shaped heat conducting plate.

[0007] Preferably, a card slot is provided on the inner wall of one side of the limiting slide slot, grooves are provided on both side surfaces of the limiting slide block, a return spring is fixed inside the groove, the end of the return spring is fixedly connected to the limiting block, the limiting block is slidably connected in the groove, a protrusion is fixed at one end of the limiting block, and the protrusion is adapted to the card slot.

[0008] Preferably, an open groove is provided on the outer wall surface of the transmission shaft, and one end of the heat pipe is inserted in the open groove, wherein the evaporation section includes a capillary adsorption area located at one end of the heat pipe close to the transmission shaft, and multi-layer copper powder sintering is adopted, and the copper powder particle size increases gradually from the inner layer μm to the outer layer μm, and the porosity is %, and a medium is arranged below the capillary adsorption area.

[0009] Preferably, the heat dissipation section includes a groove arranged in the middle of the heat pipe, and the groove is surrounded by a porous nickel mesh transition layer filled in the heat pipe with a pore size of μm. The condensation section includes heat dissipation fins arranged on the outer wall of the other end of the heat pipe, and the inclination angle of the multiple heat dissipation fins is degrees. The inner wall of the other end of the heat pipe is provided with a hydrophobic coating.

[0010] Preferably, one end of the blade is fixedly connected to a guide cover, the surface of the guide cover is provided with an air inlet, the inner wall of the guide cover is provided with a T-shaped groove, the interior of the T-shaped groove is slidably connected with a T-shaped block, one side of the T-shaped block is fixedly connected to a tension spring, the tension spring is fixedly connected in the T-shaped groove, one end of the T-block is fixed with an extrusion spring, and the end of the extrusion spring is fixedly connected to the PTFE slider.

[0011] Preferably, one side of the PTFE slider is fitted with a copper mesh, the copper mesh is arranged in a shroud, the copper mesh and the shroud are fixedly connected via a support block, a micro rectifier is arranged on the inner wall of the shroud, and a supercapacitor is installed on one side of the micro rectifier on the shroud.

[0012] Preferably, a wireless transmission coil is provided on the outer wall of the air deflector, a storage battery is installed on the top of the frame below the wireless transmission coil, a mounting frame is fixed on one side of the frame, and the detection unit is fixedly mounted on the mounting frame.

[0013] A method for operating a multi-load UAV engine dynamometer mainly includes the following steps: Step A: When in use, the engine body to be tested is placed on the frame and fixed in advance, and the engine body and the detection unit are connected by a transmission shaft. When testing, the engine body is started, and the torque and power of the engine body when working can be tested by the detection unit; Step B: When in extreme working conditions, the heat generated by the long-term operation of the engine body is transferred to the detection unit through the transmission shaft. By arranging annular blades on the surface of the transmission shaft, as the transmission shaft rotates synchronously at high speed, the generated airflow is blown to the detection unit and the outer surface of the transmission shaft. The heat transferred from the axis of the transmission shaft can be conducted through the heat pipe, and the passing airflow then blows the PTFE slider to rub back and forth on the copper mesh, converting wind energy into electrical energy.

[0014] Compared with the prior art, the present invention provides a multi-load UAV engine dynamometer, which has the following beneficial effects: 1. This multi-load UAV engine dynamometer has a heat dissipation structure arranged on the surface of the transmission shaft between the detection unit and the engine body. The transmission shaft is rotated to generate airflow, which is blown to the outer surface of the engine body and the transmission shaft, thereby dissipating and cooling the heat transferred from the detection unit during long-term operation, reducing the interference caused by heat transfer, and maintaining the heat dissipation efficiency of the device without attenuation under extreme working conditions. The change in the angle of attack changes the aerodynamic torque of the heat dissipation structure, automatically compensating for the engine torque fluctuation.

[0015] 2. This multi-load UAV engine dynamometer is equipped with a ring-shaped heat pipe at one end of the heat dissipation structure, and the other end is embedded and installed on the transmission shaft, so as to conduct and dissipate the heat transferred from the axis of the transmission shaft. Different from the prior art, it uses the centrifugal pressure difference generated by high-speed rotation to drive the phase change cycle of the working fluid, realizes pump-free self-driven heat dissipation, reduces the generation of mechanical vibration, reduces the driving source, and reduces the production cost.

[0016] 3. This multi-load UAV engine dynamometer uses the airflow driven by the heat dissipation structure to generate electricity through friction between the PTFE slider and the copper mesh, so that they cooperate with each other. In the process of heat dissipation, energy conversion and recycling are realized. After the electric energy is stored, low-power devices such as temperature control valves and pressure sensors are driven, effectively saving the energy consumption generated by the operation of the device.

[0017] The parts not involved in the device are the same as the prior art or can be implemented by the prior art. The present invention uses the kinetic energy generated by the rotation of the transmission shaft to generate airflow through the heat dissipation structure, and dissipates the heat generated by the detection unit and the outer wall of the transmission shaft. At the same time, the heat dissipation intensity can be adjusted according to the extreme working conditions. During the heat dissipation process, heat pipes are set to assist in conduction and heat dissipation of the heat of the transmission shaft axis, thereby improving the heat dissipation effect and avoiding interference caused by vibration. In addition, the PTFE slider and the copper mesh are used to realize energy conversion and recycling. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the overall structure of a multi-load UAV engine dynamometer proposed by the present invention; Figure 2 This is a schematic diagram of a top view of a multi-load UAV engine dynamometer proposed by the present invention; Figure 3 A schematic diagram of the side cross-sectional structure of a multi-load UAV engine dynamometer proposed by the present invention; Figure 4 The present invention proposes Figure 3 The enlarged structural diagram at A in the middle; Figure 5 This is a schematic diagram of a partial cross-sectional structure of a blade in a multi-load UAV engine dynamometer proposed by the present invention; Figure 6 The present invention proposes Figure 5 The enlarged structural diagram at B in the middle; Figure 7 This is a schematic diagram of the overall distribution and installation structure of blades in a multi-load UAV engine dynamometer proposed by the present invention; Figure 8 This is a schematic diagram of the heat pipe structure in a multi-load UAV engine dynamometer proposed by the present invention; Fig. 9 This is a schematic diagram of the structure of a shroud in a multi-load UAV engine dynamometer proposed by the present invention; Fig.10 This is a schematic diagram of the partial cross-sectional structure of a shroud in a multi-load UAV engine dynamometer proposed by the present invention.

[0019] In the figure: 1, frame; 2, detection unit; 3, engine body; 31, transmission shaft; 32, support seat; 33, mounting frame; 4, mounting sleeve; 41, blade; 42, connecting block; 43, limit slider; 45, limit slide groove; 46, memory alloy spring; 461, arc-shaped heat conducting plate; 47, heat insulation sleeve; 48, slot; 49, groove; 491, reset spring; 492, limit block; 493, raised point; 5, heat pipe ; 51. Open slot; 52. Medium; 53. Capillary adsorption area; 54. Groove; 55. Heat dissipation fin; 56. Hydrophobic coating; 6. Air guide cover; 61. Air inlet; 62. T-shaped slide; 63. T-block; 64. Tension spring; 65. Extrusion spring; 66. PTFE slider; 661. Copper mesh; 67. Support block; 68. Micro rectifier; 69. Supercapacitor; 691. Wireless transmission coil; 7. Storage battery. DETAILED DESCRIPTION

[0020] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0021] In the description of the present invention, the term "multiple" refers to two or more. Unless otherwise clearly defined, the orientation or positional relationship indicated by the terms "upper", "lower", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation of the present invention. The terms "connection", "installation", "fixation", etc. should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected or indirectly connected through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first", "second", etc. can explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, the meaning of "multiple" is two or more.

[0022] In the description of this specification, the description of the terms "one embodiment", "some implementations", "specific embodiments", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0023] Reference Figure 1-Figure 10 A multi-load UAV engine dynamometer comprises a frame 1, a detection unit 2 is installed on the top of the frame 1, an engine body 3 is arranged on one side of the detection unit 2, the detection unit 2 and the engine body 3 are connected and installed together through a transmission shaft 31, a support seat 32 is installed on the transmission shaft 31 through a bearing, and blades 41 with adjustable attack angles are distributed in a ring shape around the transmission shaft 31; a heat pipe 5 with an inclined angle is arranged on one side of the detection unit 2, and one end of the heat pipe 5 is embedded and installed on the transmission shaft 31; wherein the heat pipe 5 includes an evaporation section, a heat dissipation section and a condensation section, and the heat dissipation section of multiple heat pipes 5 is located at the airflow output area at one end of the blade 41; a PTFE slider 66 and a copper mesh 661 are sleeved on the outside of the transmission shaft 31, and when the detection unit 2 is working, heat is transferred through the transmission shaft 31, and multiple blades 41 are used to rotate around the axial direction of the transmission shaft 31 to generate airflow, and the heat of the outer wall of the transmission shaft 31 and the detection unit 2 is dissipated, and the heat of the axis of the transmission shaft 31 is conducted and dissipated by the heat pipe 5, and energy is recovered by friction power generation during the heat dissipation process.

[0024] In the present invention, when in use, the engine body 3 to be tested is placed on the frame 1 in advance and fixed, and the engine body 3 and the detection unit 2 are connected by transmission through the transmission shaft 31, wherein the detection unit 2 includes a torque sensor and a speed acquisition module for real-time monitoring of the engine output parameters, and the measured data signal is transmitted to the computer host for analysis and comparison, thereby realizing the test operation of the engine body 2. The working principle of the dynamometer test in the prior art can be referred to, and it will not be repeated in this scheme. During the test process, when it is in extreme working conditions, the heat generated by the long-term operation of the engine body 3 is transmitted to the detection unit 2 through the transmission shaft 31, and the surface of the transmission shaft 31 is provided with annularly distributed blades 41, and the transmission shaft 31 rotates synchronously with the high-speed rotation, thereby generating airflow, and the generated airflow is then blown to the outer surface of the detection unit 2 and the transmission shaft 31, thereby achieving heat dissipation and cooling, and ensuring the stability of the detection unit 2 during the detection process. Avoid the occurrence of drift failure caused by high temperature to the sensor detected at the detection unit 2. At the same time, the heat dissipation structure can adaptively adjust the angle of attack of the blade 41 according to the extremely high temperature state, thereby enhancing the airflow, so that the shaft temperature can still maintain the heat dissipation efficiency without attenuation under extreme working conditions, and at the same time compensate for the engine torque fluctuation, further improving the accuracy of the device detection. During the rotation of the transmission shaft 31, multiple heat pipes 5 are driven to rotate synchronously, and the heat pipe 5 is installed on the side of the air outlet end of the heat dissipation structure. The heat transferred from the axis of the transmission shaft 31 can be conducted through the heat pipe 5. In conjunction with the airflow generated by the heat dissipation structure, the centrifugal pressure difference generated by high-speed rotation is used to drive the phase change cycle of the working medium, thereby realizing pump-free self-driven heat dissipation, reducing the generation of mechanical vibration, reducing the driving source, and reducing production costs. The passing airflow then blows the PTFE slider 66 to rub back and forth on the copper mesh 661, realizing energy conversion and recycling, and effectively saving the energy consumption generated by the operation of the device.

[0025] In a preferred embodiment, referring to Figure 5 Figure 6 and Figure 7The surface of the transmission shaft 31 is fixedly mounted with a mounting sleeve 4, and the blades 41 are fixedly mounted on the mounting sleeve 4. The bottom of one end of the plurality of blades 41 is rotatably connected with a connecting block 42 through a pin shaft, and one end of the connecting block 42 is fixed to the outer wall of the mounting sleeve 4. The other ends of the plurality of blades 41 are fixedly connected with a limiting slider 43, and the limiting slider 43 is slidably connected in a limiting slide groove 45. The limiting slide groove 45 is provided on the surface of the mounting sleeve 4, and an arc-shaped heat conducting plate 461 is fixedly connected in the limiting slide groove 45. The top of the arc-shaped heat conducting plate 461 is fixedly connected with a memory alloy spring 46, and the memory alloy spring 4 6 is fixedly connected to the limit slider 43, the outer sleeve of the memory alloy spring 46 is provided with a heat insulating sleeve 47, the end of the heat insulating sleeve 47 is fixedly connected to the limit slider 43 and the arc-shaped heat conducting plate 461, the inner wall of one side of the limit slide 45 is provided with a card slot 48, both sides of the limit slider 43 are provided with a groove 49, the inner part of the groove 49 is fixed with a return spring 491, the end of the return spring 491 is fixedly connected to the limit block 492, the limit block 492 is slidably connected in the groove 49, and one end of the limit block 492 is fixed with a protruding point 493, and the protruding point 493 is adapted to the card slot 48.

[0026] The above scheme is adopted, wherein the mounting sleeve 4 is mounted on the surface of the transmission shaft 31, and a plurality of blades 41 are distributed around the mounting sleeve 4. When the transmission shaft 31 rotates, an airflow is formed by the plurality of blades 41, and then the airflow can be guided to the detection unit 2 and the outer surface of the transmission shaft 31 near one end of the detection unit 2, achieving a good heat dissipation and temperature reduction effect; The memory alloy spring 46 is made of Nitinol alloy material and is fixedly connected to the arc-shaped heat conducting plate 461. When the heat at the transmission shaft 31 is transferred to the memory alloy spring 46 through the arc-shaped heat conducting plate 461, the memory alloy spring 46 is converted into up and down linear displacement through thermal induction, thereby pulling the limit slider 43 to slide in the limit slide groove 45. The limit slider 43 is connected to the blade 41, and the attack angle of the blade 41 can be adjusted, thereby changing the air intake of the heat dissipation structure, so that the transmission shaft 31 can adaptively improve the heat dissipation effect under extremely high temperature conditions, and the change in the attack angle changes the aerodynamic torque of the heat dissipation structure, automatically compensating for the engine torque fluctuation, and the torque measurement under extremely high temperature conditions is more accurate; It should be noted that the blade 41 is in a twisted shape. The limiting slider 43 slides in the limiting slot 45, which can limit the moving blade 41 and maintain the stability of the structure. Two side surfaces of the limiting slider 43 are located in the axial direction of the mounting sleeve 4, and a certain gap is set with the inner wall of the limiting slot 45, so as not to affect the lifting and lowering operation of one end of the blade 41. During the adjustment process, since the elasticity of the reset spring 491 is less than that of the memory alloy spring 46, after the memory alloy spring 46 is thermally induced and deformed, it is squeezed and stuck in the slot 48 through the protruding point 493, so as to limit the position of the limiting slider 43 after deformation. At the same time, it does not affect the subsequent adaptive adjustment of the blade 41. The limiting slider 43 is in a cross shape, and the limiting slot 45 is a T-shaped structure, which has a double limiting effect, improves the stability of the structure, and the angle of attack adjustment is set within 12°.

[0027] In a preferred embodiment, referring to Figure 8 An open groove 51 is provided on the outer wall surface of the transmission shaft 31, and one end of the heat pipe 5 is inserted into the open groove 51, wherein the evaporation section includes a capillary adsorption area 53 located at one end of the heat pipe 5 close to the transmission shaft 31, and multi-layer copper powder sintering is adopted, and the copper powder particle size increases gradually from 50 μm in the inner layer to 150 μm in the outer layer, and the porosity is 60%. A medium 52 is arranged below the capillary adsorption area 53, and the heat dissipation section includes a groove 54 arranged in the middle of the heat pipe 5, and the groove 54 is surrounded by a porous nickel mesh transition layer filled in the heat pipe 5, and the pore size is 10 μm. The condensation section includes a heat dissipation fin 55 arranged on the outer wall of the other end of the heat pipe 5, and the inclination angle of the multiple heat dissipation fins 55 is 45 degrees. The inner wall of the other end of the heat pipe 5 is provided with a hydrophobic coating 56.

[0028] The above scheme is adopted, wherein one end of the heat pipe 5 is inserted into the open groove 51, and is closely fitted with the transmission shaft 31, so as to better conduct the heat at the axis of the transmission shaft 31, and avoid the heat being transferred to the detection unit 2, which affects the detection unit 2 being detected. The medium 52 can be made of acetone, and the heat pipe 5 is made of copper tube. When the medium 52 absorbs heat at high temperature, it is vaporized and transported to the heat dissipation section. Since the heat dissipation section is located in the air supply area of ​​the heat dissipation structure, the temperature is blown away by the contact of the air flow to dissipate the heat, and then it is condensed to form liquid in the condensation section. Due to the design of the capillary adsorption area 53 and the groove 54, the heat dissipation section 53 is formed by the heat dissipation section 54. Through centrifugal force and capillary action at the capillary adsorption area 53, the liquid is accelerated to flow back through the groove 54 to form a circulation of the medium 52. Through this design, compared with traditional heat dissipation methods such as fan blades, no additional power source is required, which saves costs and effectively reduces the vibration impact caused by power drive, further improving the accuracy of device testing. The hydrophobic coating 56 adopts a polytetrafluoroethylene super-slip coating, which can inhibit liquid film retention. The heat dissipation fins 55 can assist in the heat conduction of heat in the heat pipe 5, and at the same time cause vortexes to the passing airflow to enhance the condensation effect.

[0029] In a preferred embodiment, referring to Figure 4 , Fig. 9 and Fig.10 One end of the blade 41 is fixedly connected to a guide cover 6, an air inlet 61 is provided on the surface of the guide cover 6, a T-shaped slot 62 is provided on the inner wall of the guide cover 6, a T-shaped block 63 is slidably connected inside the T-shaped slot 62, a tension spring 64 is fixedly connected to one side of the T-shaped block 63, the tension spring 64 is fixedly connected in the T-shaped slot 62, an extrusion spring 65 is fixedly connected to one end of the T-shaped block 63, an end of the extrusion spring 65 is fixedly connected to a PTFE slider 66, and one side of the PTFE slider 66 is connected to the copper mesh 66 1, the copper mesh 661 is arranged in the air deflector 6, the copper mesh 661 and the air deflector 6 are fixedly connected by a support block 67, a micro rectifier 68 is arranged on the inner wall of the air deflector 6, a super capacitor 69 is installed on one side of the micro rectifier 68, a wireless transmission coil 691 is arranged on the outer wall of the air deflector 6, a storage battery 7 is installed on the top of the frame 1 below the wireless transmission coil 691, a mounting frame 33 is fixed on one side of the frame 1, and the detection unit 2 is fixedly installed on the mounting frame 33.

[0030] By adopting the above scheme, the air flow enters the interior of the air guide cover 6 through the air inlet 61, blowing the PTFE slider 66 so that the PTFE slider 66 slides back and forth on the surface of the copper mesh 661 to generate friction electricity. The copper mesh 661 is electrically connected to the micro rectifier 68, and is converted into direct current by the micro rectifier 68, and then input into the super capacitor 69. The super capacitor 69 is electrically connected to the wireless transmission coil 691. The wireless transmission coil 691 cooperates with the receiver provided on the storage battery 7, that is, the receiving coil. The receiving coil is installed on the storage battery 7, and the electrical energy is stored in the storage battery 7 through magnetic resonance coupling transmission, which is convenient for powering the sensors and other components on the device. By combining the above structure with the heat dissipation structure, the device can make full use of kinetic energy in the process of heat dissipation and perform energy conversion and recycling.

[0031] It should be noted that the PTFE slider 66 adopts a NACA0012 airfoil cross-section style shape. When the airflow blows toward the PTFE slider 66, the airflow is converted into a periodic exciting force through the characteristics of the structure, so that the PTFE slider 66 rubs back and forth on the surface of the copper mesh 661. The tension spring 64 adopts a nonlinear conical silicone spring. When the PTFE slider 66 is displaced by the airflow and the airflow is weak, the tension spring 64 elastically pulls back to make the PTFE slider 66 reciprocate.

[0032] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A multi-load UAV engine dynamometer, comprising a frame (1), a detection unit (2) is mounted on the top of the frame (1), an engine body (3) is arranged on one side of the detection unit (2), the detection unit (2) and the engine body (3) are connected and mounted together via a transmission shaft (31), a support seat (32) is mounted on the transmission shaft (31) via a bearing, and the characteristics are as follows: Blades (41) with adjustable attack angles are distributed in a ring shape around the transmission shaft (31); A heat pipe (5) with an inclined angle is arranged on one side of the detection unit (2), and one end of the heat pipe is embedded and mounted on the transmission shaft (31); The heat pipe (5) comprises an evaporation section, a heat dissipation section and a condensation section, and the heat dissipation sections of the plurality of heat pipes (5) are located in the airflow output area at one end of the blade (41); The PTFE slider (66) and the copper mesh (661) are sleeved on the outside of the transmission shaft (31). When the detection unit (2) is working, heat is transferred through the transmission shaft (31). The plurality of blades (41) rotate axially around the transmission shaft (31) to generate airflow to dissipate heat from the outer wall of the transmission shaft (31) and the detection unit (2). At the same time, the heat pipe (5) is used to conduct heat from the center of the transmission shaft (31) to dissipate heat, and frictional power generation is used to recover energy during the heat dissipation process.

2. A multi-load UAV engine dynamometer according to claim 1, characterized in that: A mounting sleeve (4) is fixedly mounted on the surface of the transmission shaft (31), the blades (41) are fixedly mounted on the mounting sleeve (4), the bottoms of one end of a plurality of blades (41) are rotatably connected to a connecting block (42) via a pin, and one end of the connecting block (42) is fixed to the outer wall of the mounting sleeve (4).

3. A multi-load UAV engine dynamometer according to claim 2, characterized in that: The other ends of the plurality of blades (41) are fixedly connected to a limit slider (43), the limit slider (43) is slidably connected in a limit slide groove (45), the limit slide groove (45) is provided on the surface of the mounting sleeve (4), an arc-shaped heat conducting plate (461) is fixedly connected in the limit slide groove (45), a memory alloy spring (46) is fixedly connected to the top of the arc-shaped heat conducting plate (461), one end of the memory alloy spring (46) is fixedly connected to the limit slider (43), an outer sleeve of the memory alloy spring (46) is provided with a heat insulating sleeve (47), and an end of the heat insulating sleeve (47) is fixedly connected to the limit slider (43) and the arc-shaped heat conducting plate (461).

4. A multi-load UAV engine dynamometer according to claim 3, characterized in that: A clamping groove (48) is provided on the inner wall of one side of the limiting sliding groove (45), and grooves (49) are provided on both side surfaces of the limiting sliding block (43). A return spring (491) is fixed inside the groove (49), and the end of the return spring (491) is fixedly connected to a limiting block (492). The limiting block (492) is slidably connected in the groove (49), and a protruding point (493) is fixed on one end of the limiting block (492), and the protruding point (493) is adapted to the clamping groove (48).

5. The multi-load UAV engine dynamometer according to claim 1, characterized in that: An open groove (51) is provided on the outer wall surface of the transmission shaft (31), and one end of the heat pipe (5) is inserted into the open groove (51), wherein the evaporation section comprises a capillary adsorption area (53) located at one end of the heat pipe (5) close to the transmission shaft (31), and is sintered using multiple layers of copper powder, wherein the copper powder particle size increases gradually from 50 μm in the inner layer to 150 μm in the outer layer, and the porosity is 60%, and a medium (52) is provided below the capillary adsorption area (53).

6. The multi-load UAV engine dynamometer according to claim 1, characterized in that: The heat dissipation section comprises a groove (54) arranged in the middle of the heat pipe (5), and the groove (54) is surrounded by a porous nickel mesh transition layer located in the heat pipe (5) and filled with a porous nickel mesh transition layer, the pore size of which is 10 μm. The condensation section comprises heat dissipation fins (55) arranged on the outer wall of the other end of the heat pipe (5), and the inclination angle of the plurality of heat dissipation fins (55) is 45 degrees. The inner wall of the other end of the heat pipe (5) is provided with a hydrophobic coating (56).

7. The multi-load UAV engine dynamometer according to claim 1, characterized in that: One end of the blade (41) is fixedly connected to a guide cover (6), a surface of the guide cover (6) is provided with an air inlet (61), an inner wall of the guide cover (6) is provided with a T-shaped groove (62), the interior of the T-shaped groove (62) is slidably connected to a T-shaped block (63), a side surface of the T-shaped block (63) is fixedly connected to a tension spring (64), the tension spring (64) is fixedly connected in the T-shaped groove (62), an end of the T-shaped block (63) is fixedly connected to an extrusion spring (65), and an end of the extrusion spring (65) is fixedly connected to a PTFE slider (66).

8. The multi-load UAV engine dynamometer according to claim 1, characterized in that: One side of the PTFE slider (66) is in contact with the copper mesh (661); the copper mesh (661) is arranged in the air guide cover (6); the copper mesh (661) and the air guide cover (6) are fixedly connected via a support block (67); a micro rectifier (68) is arranged on the inner wall of the air guide cover (6); and a super capacitor (69) is installed on one side of the micro rectifier (68) located on the air guide cover (6).

9. The multi-load UAV engine dynamometer according to claim 7, characterized in that: The outer wall of the air guide cover (6) is provided with a wireless transmission coil (691), a storage battery (7) is installed below the wireless transmission coil (691) and located on the top of the frame (1), a mounting frame (33) is fixed to one side of the frame (1), and the detection unit (2) is fixedly mounted on the mounting frame (33).

10. A method for operating a multi-load UAV engine dynamometer, according to the multi-load UAV engine dynamometer of claim 1, characterized in that: The main steps include: Step A: When in use, the engine body (3) to be tested is placed on the frame (1) and fixed in place in advance, and the engine body (3) and the detection unit (2) are connected by transmission through the transmission shaft (31). When testing, the engine body (3) is started, and the torque and power of the engine body (3) when working can be tested through the detection unit (2); Step B: When in extreme working conditions, the heat generated by the engine body (3) working for a long time is transferred to the detection unit (2) through the transmission shaft (31). By arranging annularly distributed blades (41) on the surface of the transmission shaft (31), as the transmission shaft (31) rotates synchronously at a high speed, the generated airflow is blown toward the detection unit (2) and the outer surface of the transmission shaft (31). The heat transferred from the axis of the transmission shaft (31) can be conducted through the heat pipe (5), and the passing airflow then blows the PTFE slider (66) to rub back and forth on the copper mesh (661), thereby converting wind energy into electrical energy.

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