WO2019227639A1 - 风沙环境下旋翼无人机复合材料桨叶可靠性试验装备 - Google Patents

风沙环境下旋翼无人机复合材料桨叶可靠性试验装备 Download PDF

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WO2019227639A1
WO2019227639A1 PCT/CN2018/096959 CN2018096959W WO2019227639A1 WO 2019227639 A1 WO2019227639 A1 WO 2019227639A1 CN 2018096959 W CN2018096959 W CN 2018096959W WO 2019227639 A1 WO2019227639 A1 WO 2019227639A1
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composite material
sand
blade
laser
reflector
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PCT/CN2018/096959
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English (en)
French (fr)
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李晖
陈延炜
陈曦
陈达
刘宏浩
李朝峰
姚红良
闻邦椿
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东北大学
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Publication of WO2019227639A1 publication Critical patent/WO2019227639A1/zh

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00—Testing of machine parts

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  • the invention belongs to the technical field of vibration and reliability testing of rotor blade composite material blades, and particularly relates to reliability test equipment for rotor blade composite material blades in a wind and sand environment.
  • Multi-rotor UAVs are simple in technology, low in cost, and flexible in design and use. They are widely used in various industries. With the gradual progress of research and development, rotor blades, as an important part of multi-rotor drones, have stricter requirements on their weight and load capacity. Combining composite materials and their structures with high specific strength, high specific modulus, material designability, good thermal stability, but also the advantages of large bearing capacity and light weight, the application of composite materials to rotor blades is inevitable trend. Considering the complicated working environment of the drone, especially the wind and sand environment has a greater impact on the UAV composite rotor blades, which is likely to cause wear and damage, affect flight safety, and even cause safety accidents in severe cases. Therefore, it is of great engineering significance to study the vibration characteristics and reliability of composite rotor blades in wind and sand environment.
  • Chinese patent CN105092191A introduces a system and method for implementing blade fatigue test by forced resonance; CN102507275A has invented a helicopter suitable for the formation of helicopter composite blade fatigue test pieces. Method for forming composite material blade fatigue test piece.
  • CN105447316B relates to a method for predicting the fatigue life of a composite blade structure with initial defects. Taken together, there is no composite blade test research device and method for simulating the actual service environment. The experimental research on composite rotor blades in complex environments is still in its infancy. It is necessary to develop related vibration and Reliability test equipment.
  • Rotor drone composite material blade reliability test equipment under wind and sand environment including equipment body, wind direction adjusting device, sand guiding device, laser vibration measuring device and sand circulating device, said device is provided with a laser vibration measuring device in the middle of the internal cavity of the equipment
  • the bottom of the bottom plate of the equipment body is provided with a sand circulation device located at the left end of the laser vibration measuring device, a Doppler laser vibration meter is provided on the top of the equipment body, and a Doppler laser vibration meter is provided on the top of the equipment body
  • a sand guiding device located at the left end of the wind direction adjusting device is provided on the top of the equipment body
  • the left side wall of the equipment body is provided with a wind direction adjusting device
  • the right side wall of the equipment body is provided with an air outlet.
  • the laser vibration measuring device includes a support frame, a servo motor is installed at the bottom of the top plate of the support frame, a light control turntable is set on the top of the support frame top plate, and a slip ring electric attractor is set in the middle of the inner cavity of the light control turntable, and The middle part of the slip ring initiator is connected with the output shaft of the servo motor.
  • the top of the slip ring initiator is provided with a first reflector, the mirror surface of the first reflector is 45 ° from the horizontal plane, and the middle and lower side walls of the first reflector are provided.
  • a composite paddle penetrating the top of the light control turntable is provided on the top of the first reflector, and a strain gauge is provided on the top of the composite paddle.
  • a slip ring initiator and a strain gauge constitute a strain measurement module.
  • a laser guide tube is provided in the middle of the top end of the composite material paddle, and a Doppler laser vibrometer is provided on the top of the laser guide tube.
  • the Doppler laser vibration measurement Instrument, laser guide tube, first reflecting mirror and reflecting mirror fine-tuning device constitute a laser vibration measuring module.
  • the reflector fine-tuning device includes a rotating stage, and an oval thin-walled reflecting mirror is symmetrically mounted on the top of the rotating stage.
  • a bracket is provided at the middle of the top of the rotating stage, and a rotating table driving motor is provided at the middle of the bottom of the bracket.
  • a second reflector is mounted on the top of the bracket.
  • the sand circulation device includes a driving motor and an excitation rod, and a thick connecting rod and a thin connecting rod are installed between the two excitation rods.
  • a composite excitation surface is provided on the top of the thick connecting rod and the excitation rod.
  • a long thin link is provided at the right end of the excitation rod, and a torsion spring is provided on the outer wall of the extended end of the long thin link.
  • a first mounting seat is provided on the outer wall of the extended end of the long thin link, and the torsion spring is embedded in the first
  • a pendulum is mounted on the outer wall of the output shaft of the driving motor in a through hole of a mounting seat, and a second mounting seat is mounted on the output shaft of the driving motor of the two outer walls of the pendulum.
  • the wind direction adjusting device includes a fan blade, a stepping motor and an air inlet.
  • Fan blades are evenly installed between the inner wall of the air inlet, a stepper motor is installed on the outer wall of the air inlet, and the axis of the stepper motor and the fan blade are installed. It is horizontally arranged, and the top of the air inlet is provided with a flow valve directly above the stepping motor.
  • the sand guiding device includes a sand inlet, and a double-layer grille plate is provided at the bottom of the sand inlet.
  • the equipment body bottom plate is composed of a horizontal portion and an inclined portion.
  • the test method for the reliability test of composite blades of rotor UAV under wind and sand environment adopts the reliability test equipment of composite blades of rotor UAV under wind and sand environment, including the following steps,
  • Step 1 Install the composite material paddle on the top of the first reflector, and turn on the power to ensure the normal operation of the composite material paddle, check whether each part shows normal, and perform debugging and correction;
  • Step 2 Perform a pre-test, start the servo motor, and perform a composite material blade idling test for 30 minutes to eliminate the influence of the thermal error of the servo motor on the test;
  • Step 3 accurately attach the strain gauge to the composite material paddle, and lead the wire out through the slip ring electrical conductor
  • Step 4 Adjust the Doppler laser vibrometer so that the laser beam emitted by the Doppler laser vibrometer is perpendicularly directed to the first reflector through the laser conductive tube, and the laser light on the mirror surface of the first reflector is made using the principle of light reflection.
  • the beam is horizontally directed to the second reflector. Since the second reflector is located at the spatial focal position of the oval thin-walled mirror, the laser beam emitted through one focus, that is, the laser beam located on the mirror surface of the second reflector passes through the oval thin
  • the wall reflector reflects the position of the composite blade at the second focal point;
  • Step 5 Start the rotary table drive motor and rotate the elliptical thin-walled reflector to scan a measuring point; then adjust the overall position of the rotary table along the radial position of the composite material blade to achieve global scanning of the composite material blade, Global scanning of composite blade measuring points;
  • Step 6 place the sand, start the driving motor and supply wind at the same time to realize the wind and sand environment simulation;
  • Step 7 Start the servo motor of the composite material blade again for the formal test
  • Step 8 Change the position of the measuring point of the composite material blade, and repeat steps 4-6 to realize the test of multiple vibration points on the composite material blade.
  • the present invention emits a laser beam through a Doppler laser vibrometer on the top of the device body.
  • the laser beam is directed to a first reflector through a laser guide tube, and the laser beam located on the mirror surface of the first reflector is horizontally directed using the principle of light reflection.
  • the second reflector since the second reflector is located at the spatial focal position of the oval thin-walled mirror, the laser beam located on the mirror surface of the second reflector is reflected again by the oval thin-walled reflector toward the composite material located at the second focus.
  • the global scanning of the composite material blades can be achieved.
  • the rotation speed of the driving motor on the sand circulation device to control the excitation frequency
  • the sand circulation flow is controlled, and the air flow is controlled by the flow valve on the wind direction adjustment device.
  • the direction of the airflow is controlled by the fan blades, so that the device of the present invention can measure multiple blades of composite materials in a wind and sand environment. Measurement and observation, to obtain composite blades meet the working environment in the sand, composite blades to avoid damage, damage resulting multi-rotor UAV does not work, or even lead to accidents.
  • FIG. 1 is a schematic structural diagram of a rotor blade UAV composite material blade reliability test equipment in a wind and sand environment according to the present invention
  • FIG. 2 is a schematic diagram of the internal structure of a rotorcraft UAV composite material blade reliability test equipment in a windy sand environment according to the present invention
  • FIG. 3 is a top view of the structure of a rotor blade UAV composite material blade reliability test equipment in the wind and sand environment of the present invention
  • FIG. 4 is a schematic structural diagram of a laser vibration measuring device according to the present invention.
  • FIG. 5 is a schematic structural diagram of a mirror fine-tuning device according to the present invention.
  • FIG. 6 is a schematic structural diagram of a sand circulation device according to the present invention.
  • FIG. 7 is a schematic structural diagram of a wind direction adjusting device according to the present invention.
  • 1-equipment body 2-laser vibration measuring device, 3-sand circulation device, 4-Doppler laser vibration measuring device, 5-wind direction adjusting device, 6-sand guiding device, 7-air outlet, 8-support frame, 9-servo motor, 10-light control turntable, 11-slip ring initiator, 12-first reflector, 13-mounting plate, 14-mirror trimmer, 15-composite paddle, 16-strain gauge, 17 -Laser guide tube, 18-rotary stage, 19-ellipse thin-walled reflector, 20-stand, 21-rotary stage drive motor, 22-second reflector, 23-drive motor, 24-excitation rod, 25- Thick link, 26-fine link, 27-composite excitation surface, 28-long thin link, 29-torsion spring, 30-first mount, 31-pendulum, 32-second mount, 33- Fan blade, 34-stepper motor, 35-air inlet, 36-flow valve, 37-sand inlet, 38-double-layer grille plate.
  • the rotor blade UAV composite material blade reliability test equipment under wind and sand environment includes equipment body 1, wind direction adjusting device 5, sand guiding device 6, laser vibration measuring device 2 and sand circulating device 3,
  • a laser vibration measuring device 2 is provided in the middle of the inner cavity of the equipment body 1
  • a sand circulation device 3 at the left end of the laser vibration measuring device 2 is provided at the bottom of the equipment body 1
  • a Doppler laser is provided on the top of the equipment body 1.
  • a vibrometer 4, a wind direction adjusting device 5 at the left end of the Doppler laser vibrometer 4 is provided on the top of the equipment body 1
  • a sand guiding device 6 is provided at the left end of the wind direction adjusting device 5 on the top of the equipment body 1.
  • the left side wall of the equipment body 1 is provided with a wind direction adjusting device 5, and the right side wall of the equipment body 1 is provided with an air outlet 7.
  • the laser vibration measuring device 2 includes a support frame 8, a servo motor 9 is installed at the bottom of the top plate of the support frame 8, and a light control turntable 10 is provided on the top of the top plate of the support frame 8.
  • a slip ring induction device 11 is provided in the middle of the inner cavity of the turntable 10, and a middle portion of the slip ring induction device 11 is connected to the output shaft of the servo motor 9, and a first reflector 12 is provided on the top of the slip ring induction device 11.
  • the composite material blade 15 on the top of the light control turntable 10 is provided with a strain gauge 16 on the top of the composite material blade 15.
  • the slip ring inductor 11 and the strain gauge 16 form a strain measurement module, and the top of the composite material blade 15
  • a laser guide tube 17 is provided in the middle, and a Doppler laser vibrometer 4 is provided on the top of the laser guide tube 17, the Doppler laser vibrometer 4, laser guide tube 17, first reflector 12 and reflector Fine-tuning device 14 constitutes a laser vibration measuring module .
  • the mirror fine-tuning device 14 includes a rotating stage 18, and an oval thin-walled reflecting mirror 19 is symmetrically mounted on the top of the rotating stage 18.
  • a bracket 20 is provided in the middle of the top of the rotating stage 18.
  • a rotary table driving motor 21 is provided in the middle of the bottom end of the 20, and a second reflector 22 is mounted on the top end of the bracket 20.
  • the sand circulation device 3 includes a driving motor 23 and an excitation rod 24.
  • a thick link 25 and a thin link 26 are installed between the two excitation rods 24.
  • a composite excitation surface 27 is provided on the top of the excitation rod 24, and the composite excitation surface 27 is provided as a surface with an elastic body, which is conducive to the lifting of the sand.
  • a long thin link 28 is provided at the right end of the excitation rod 24.
  • a torsion spring 29 is provided on the outer wall of the extended end of the elongated connecting rod 28, and a first mounting base 30 is provided on the outer wall of the extended end of the elongated connecting rod 28, and the torsion spring 29 is embedded in the through hole of the first mounting base 30.
  • a pendulum 31 is installed on the outer wall of the output shaft of the driving motor 23, and a second mounting seat 32 is installed on the output shaft of the two side drive motors 23 of the pendulum 31.
  • the wind direction adjusting device 5 includes a fan blade 33, a stepping motor 34, and an air inlet 35.
  • the fan blade 33 is evenly installed between the inner walls of the air inlet 35, and is controlled by the reciprocating swing of the fan blade 33.
  • a stepping motor 34 is installed on the outer side wall of the air inlet 35, and the axis of the stepping motor 34 is horizontally arranged with the fan blade 33.
  • a flow valve 36 directly above the stepping motor 34 is provided on the top of the air inlet 35 The flow valve 36 is used to control the size of the input airflow, and the wind direction simulation of the multi-angle and multi-direction is realized by the wind direction adjusting device 5.
  • the sand guiding device 6 includes a sand inlet 37, and a double-layer grille plate 38 is provided at the bottom of the sand inlet 37.
  • a double-layer grille plate 38 By adjusting the position of the double-layer grille plate 38, the sand is released at a certain flow rate in cooperation with the wind direction adjusting device. 5 to simulate the wind and sand environment.
  • the bottom plate of the equipment body 1 is composed of a horizontal portion and an inclined portion, and the sand that is favorable for release along the inclined portion returns to the top of the composite excitation surface 27 for recycling.
  • the test method for the reliability test of composite blades of rotor UAV under wind and sand environment adopts the reliability test equipment of composite blades of rotor UAV under wind and sand environment, including the following steps,
  • Step 1 Install the composite material blade 15 on the top of the first reflector 12 and turn on the power to ensure that the composite material blade 15 operates normally, check whether each component is normal, and perform debugging and correction;
  • Step 2 Perform a pre-test, start the servo motor 9, and perform a composite material blade 15 idling test for 30 minutes to eliminate the effect of the thermal error of the servo motor 9 on the test;
  • Step 3 accurately attach the strain gauge 16 to the composite material paddle 15 and lead the wire out through the slip ring electric conductor 11;
  • Step 4 Adjust the Doppler laser vibrometer 4 so that the laser beam emitted by the Doppler laser vibrometer 4 is directed to the first reflecting mirror 12 via the laser guide tube 17, and the light reflecting principle is used to locate the first reflecting mirror 12.
  • the laser beam on the 12 mirror surface is horizontally directed toward the second reflector 22. Since the second reflector 22 is located at the spatial focal position of the elliptical thin-walled reflector 19, the laser beam emitted through one focus is located at the second reflector 22 The laser beam on the mirror surface is reflected by the elliptical thin-wall reflector 19 to the measurement position of the composite blade 15 at the second focus;
  • Step 5 Start the rotary table driving motor 21 and rotate the elliptical thin-walled reflector 19 to scan one measuring point. Then adjust the rotary table 18 as a whole along the radial position of the composite material blade 15 to achieve the composite material blade 15 Global scanning to achieve global scanning of corresponding points of composite blade 15;
  • step 6 the sand is placed, the driving motor 23 is started, and the wind power is supplied to realize the simulation of the wind and sand environment.
  • Step 7 Start the servo motor 9 of the composite material blade 15 again for a formal test
  • Step 8 Change the measuring point position of the composite material blade 15 and repeat steps 4-6 to realize the test of multiple vibration points on the composite material blade 15.

Abstract

一种风沙环境下旋翼无人机复合材料浆叶可靠性试验装备，包括装备本体（1），风向调节装置（5），沙子导向装置（6），激光测振装置（2）和沙子循环装置（3），通过多普勒激光测振仪（4）发射激光束，经由激光导向管（17）射向第一反光镜（12），利用光的反射原理水平射向第二反光镜（22），第二反光镜（22）的激光束经由椭圆状薄壁反光镜（19）反射射向复合材料桨叶（15）测点位置，通过旋转椭圆状薄壁反光镜（19）实现对复合材料桨叶（15）测点的全局扫描，通过驱动电机（23）控制激振频率进而控制沙子的流量及流量阀（36）和扇叶（33）控制气流大小和方向，实现在风沙环境下对复合材料桨叶（15）多个测点的测量，获取满足在风沙环境下工作的复合材料桨叶（15），避免因复合材料桨叶（15）破坏、损坏导致多旋翼无人机无法正常工作，甚至酿成安全事故。

Description

风沙环境下旋翼无人机复合材料桨叶可靠性试验装备 技术领域
本发明属于旋翼无人机复合材料桨叶振动及可靠性测试技术领域，具体涉及风沙环境下旋翼无人机复合材料桨叶可靠性试验装备。
背景技术
多旋翼无人机具有技术简单、成本低廉、设计与使用灵活性强等特点，在各行业中的运用都最为广泛。随着研究发展的逐步进行，旋翼桨叶，作为多旋翼无人机的重要组成部分，对于其重量以及负载能力有着更为严格的要求。结合复合材料及其结构的比强度高、比模量高、材料具有可设计性、热稳定性好，而且还具有承载力大、重量轻等优点，将复合材料应用于旋翼桨叶已是必然趋势。考虑无人机工作的复杂工作环境，特别是风沙环境对无人机复合旋翼桨叶的影响较大，易造成磨损、损坏，影响飞行安全，严重时甚至酿成安全事故。因此，研究风沙环境下复合材料旋翼桨叶的振动特性和可靠性问题有着重要的工程意义。
目前针对符合材料桨叶的试验研究有一些技术方案，中国专利CN105092191A介绍一种强迫共振实现桨叶疲劳试验的系统以及方法；CN102507275A发明了一种适用于直升机复合材料桨叶疲劳试验件成型的直升机复合材料桨叶疲劳试验件成型工艺方法。CN105447316B涉及一种预测含初始缺陷复合材料桨叶结构疲劳寿命的方法。综合来看，还没有一种用于模拟实际服役环境的复合材料桨叶试验研究装置及方法，对于复合材料旋翼桨叶在复杂环境下的实验研究尚处于起步状态，有必要研发相关的振动及可靠性试验装备。
发明内容
为了实现上述目的，本发明采用如下技术方案：
风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，包括装备本体，风向调节装置，沙子导向装置、激光测振装置和沙子循环装置，所述装备本体内腔中部设置有激光测振装置，所述装备本体底板底部设置有位于激光测振装置左端的沙子循环装置，所述装备本体顶部设置有多普勒激光测振仪，所述装备本体顶部设置有位于多普勒激光测振仪左端的风向调节装置，所述装备本体顶部设置有位于风向调节装置左端的沙子导向装置，所述装备本体左端侧壁设置有风向调节装置，所述装备本体右端侧壁设置有出风口。
所述激光测振装置包括支撑架，所述支撑架的顶板底部安装有伺服电机，所述支撑架顶板顶部设置有光线控制转台，所述光线控制转台内腔中部设置有滑环引电器，且滑环引电器中部与伺服电机输出轴相连，所述滑环引电器顶部设置有第一反光镜，所述第一反光镜镜面与水平面呈45°，所述第一反光镜中下部侧壁设置有安装板，所述安装板末端设置有反光镜 微调装置，所述第一反光镜顶部设置有贯穿光线控制转台顶部的复合材料桨叶，所述复合材料桨叶顶部设置有应变片，所述滑环引电器和应变片组成应变测量模块，所述复合材料桨叶顶端中部设置有激光导向管，所述激光导向管顶部设置有多普勒激光测振仪，所述多普勒激光测振仪、激光导向管、第一反光镜和反光镜微调装置构成激光测振模块。
所述反光镜微调装置包括旋转台，所述旋转台顶部对称安装有椭圆状薄壁反光镜，所述旋转台顶端中部设置有支架，所述支架底端中部设置有旋转台驱动电机，所述支架顶端的安装有第二反光镜。
所述沙子循环装置包括驱动电机和激振杆，两所述激振杆之间安装有粗连杆和细连杆，所述粗连杆和激振杆顶部设置有复合激振面，所述激振杆中右端设置有长细连杆，且长细连杆伸出端外壁设置有扭簧，所述长细连杆伸出端外壁设置有第一安装座，且扭簧内嵌在第一安装座通孔内，所述驱动电机输出轴外壁安装有摆锤，两所述摆锤外侧壁驱动电机输出轴上安装有第二安装座。
所述风向调节装置包括扇叶、步进电机和进风口，所述进风口内侧壁之间均匀安装有扇叶，所述进风口外侧壁安装有步进电机，且步进电机轴线与扇叶水平设置，所述进风口顶部设置有位于步进电机正上方的流量阀。
所述沙子导向装置包括进沙口，所述进沙口底部设置有双层格栅板。
所述装备本体底板由水平部分和倾斜部分组成。
风沙环境下旋翼无人机复合材料桨叶可靠性试验的试验方法，采用风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，包括以下步骤，
步骤1，将复合材料桨叶安装在第一反光镜顶端，接通电源，确保复合材料桨叶正常运转，检测各部件是否显示正常，进行调试和校正；
步骤2，进行预试验，启动伺服电机，进行复合材料桨叶空转试验30分钟，以消除伺服电机热误差对试验的影响；
步骤3，将应变片准确贴于复合材料桨叶上，并通过滑环引电器将导线引出；
步骤4，调整多普勒激光测振仪，使多普勒激光测振仪发射的激光束经由激光导电管垂直射向第一反光镜，利用光反射原理使位于第一反光镜镜面上的激光束水平射向第二反光镜，由于第二反光镜位于椭圆状薄壁反光镜的空间焦点位置，由于经由一个焦点射出的激光束，即位于第二反光镜镜面上的激光束经由椭圆状薄壁反光镜反射射向位于第二焦点的复合材料桨叶测点位置；
步骤5，启动旋转台驱动电机，旋转椭圆状薄壁反光镜，实现一个测点的扫描；再通过 调整旋转台整体沿复合材料桨叶径向位置，实现复合材料桨叶的全局扫描，实现对复合材料桨叶测点的全局扫描；
步骤6，放置好沙子，同时启动驱动电机以及进行风力的供给，实现风沙环境模拟；
步骤7，再次启动复合材料桨叶的伺服电机，进行正式试验；
步骤8，改变复合材料桨叶的测点位置，重复步骤4-6，实现复合材料桨叶上多个振点的测试。
本发明有益效果：
本发明通过装置本体顶部的多普勒激光测振仪发射激光束，激光束经由激光导向管射向第一反光镜，利用光的反射原理使位于第一反光镜镜面上的激光束水平射向第二反光镜，由于第二反光镜位于椭圆状薄壁反光镜的空间焦点位置，位于第二反光镜镜面上的激光束再次经由椭圆状薄壁反光镜反射射向位于第二焦点的复合材料桨叶测点位置，并且通过旋转台驱动电机的作用，旋转椭圆状薄壁反光镜，实现一个测点的扫描；再通过调整旋转台整体沿复合材料桨叶径向位置，实现复合材料桨叶的全局扫描，实现对复合材料桨叶测点的全局扫描；通过控制沙子循环装置上的驱动电机的转速控制激振频率，进而控制沙子循环的流量，通过风向调节装置上的流量阀控制气流大小，通过扇叶控制气流的方向，实现本发明装置在风沙环境下，对复合材料桨叶多个测点的测量与观察，获取满足在风沙环境下工作的复合材料桨叶，避免因复合材料桨叶破坏、损坏致使多旋翼无人机无法正常工作，甚至酿成安全事故。
附图说明
图1本发明风沙环境下旋翼无人机复合材料桨叶可靠性试验装备结构示意图；
图2为本发明风沙环境下旋翼无人机复合材料桨叶可靠性试验装备内部结构示意图；
图3为本发明风沙环境下旋翼无人机复合材料桨叶可靠性试验装备结构俯视图；
图4为本发明激光测振装置结构示意图；
图5为本发明反光镜微调装置结构示意图；
图6为本发明沙子循环装置结构示意图；
图7为本发明风向调节装置结构示意图；
1-装备本体，2-激光测振装置，3-沙子循环装置，4-多普勒激光测振仪，5-风向调节装置，6-沙子导向装置，7-出风口，8-支撑架，9-伺服电机，10-光线控制转台，11-滑环引电器，12-第一反光镜，13-安装板，14-反光镜微调装置，15-复合材料桨叶，16-应变片，17-激光导向管，18-旋转台，19-椭圆状薄壁反光镜，20-支架，21-旋转台驱动电机，22-第二反 光镜，23-驱动电机，24-激振杆，25-粗连杆，26-细连杆，27-复合激振面，28-长细连杆，29-扭簧，30-第一安装座，31-摆锤，32-第二安装座，33-扇叶，34-步进电机，35-进风口，36-流量阀，37-进沙口，38-双层格栅板。
具体实施方式
下面结合附图和实施例对本发明作进一步的详细说明。
如图1-3所示，风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，包括装备本体1，风向调节装置5，沙子导向装置6、激光测振装置2和沙子循环装置3，所述装备本体1内腔中部设置有激光测振装置2，所述装备本体1底板底部设置有位于激光测振装置2左端的沙子循环装置3，所述装备本体1顶部设置有多普勒激光测振仪4，所述装备本体1顶部设置有位于多普勒激光测振仪4左端的风向调节装置5，所述装备本体1顶部设置有位于风向调节装置5左端的沙子导向装置6，所述装备本体1左端侧壁设置有风向调节装置5，所述装备本体1右端侧壁设置有出风口7。
如图4所示，所述激光测振装置2包括支撑架8，所述支撑架8的顶板底部安装有伺服电机9，所述支撑架8顶板顶部设置有光线控制转台10，所述光线控制转台10内腔中部设置有滑环引电器11，且滑环引电器11中部与伺服电机9输出轴相连，所述滑环引电器11顶部设置有第一反光镜12，所述第一反光镜12镜面与水平面呈45°，所述第一反光镜12中下部侧壁设置有安装板13，所述安装板13末端设置有反光镜微调装置14，所述第一反光镜12顶部设置有贯穿光线控制转台10顶部的复合材料桨叶15，所述复合材料桨叶15顶部设置有应变片16，所述滑环引电器11和应变片16组成应变测量模块，所述复合材料桨叶15顶端中部设置有激光导向管17，所述激光导向管17顶部设置有多普勒激光测振仪4，所述多普勒激光测振仪4、激光导向管17、第一反光镜12和反光镜微调装置14构成激光测振模块。
如图5所示，所述反光镜微调装置14包括旋转台18，所述旋转台18顶部对称安装有椭圆状薄壁反光镜19，所述旋转台18顶端中部设置有支架20，所述支架20底端中部设置有旋转台驱动电机21，所述支架20顶端的安装有第二反光镜22。
如图6所示，所述沙子循环装置3包括驱动电机23和激振杆24，两所述激振杆24之间安装有粗连杆25和细连杆26，所述粗连杆25和激振杆24顶部设置有复合激振面27，复合激震面27设置为具有弹性体的表面，有利于沙子的扬起，所述激振杆24中右端设置有长细连杆28，所述长细连杆28伸出端外壁设置有扭簧29，所述长细连杆28伸出端外壁设置有第一安装座30，且扭簧29内嵌在第一安装座30通孔内，所述驱动电机23输出轴外壁安装有摆锤31，两所述摆锤31外侧壁驱动电机23输出轴上安装有第二安装座32，当释放的沙子沿 斜面滚回复合激振面27上时，沙子受到激振杆24和复合激振面27的激励，使得沙子扬起，并在风的作用下继续作用于复合材料桨叶15，实现了沙子的循环供应。同时，可以通过控制驱动电机23的转速来控制激振频率，来最终控制沙子循环的流量。
如图7所示，所述风向调节装置5包括扇叶33、步进电机34和进风口35，所述进风口35内侧壁之间均匀安装有扇叶33，通过扇叶33的往复摆动控制气流的方向，所述进风口35外侧壁安装有步进电机34，且步进电机34轴线与扇叶33水平设置，所述进风口35顶部设置有位于步进电机34正上方的流量阀36，流量阀36用于控制输入气流的大小，通过风向调节装置5实现多角度多方位的风向模拟。
所述沙子导向装置6包括进沙口37，所述进沙口37底部设置有双层格栅板38，通过调整双层格栅板38的位置，使沙子按一定流量释放，配合风向调节装置5实现风沙环境的模拟。
所述装备本体1底板由水平部分和倾斜部分组成，有利于释放的沙子沿着倾斜部分回到复合激振面27顶部，以便循环使用。
风沙环境下旋翼无人机复合材料桨叶可靠性试验的试验方法，采用风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，包括以下步骤，
步骤1，将复合材料桨叶15安装在第一反光镜12顶端，接通电源，确保复合材料桨叶15正常运转，检测各部件是否显示正常，进行调试和校正；
步骤2，进行预试验，启动伺服电机9，进行复合材料桨叶15空转试验30分钟，以消除伺服电机9热误差对试验的影响；
步骤3，将应变片16准确贴于复合材料桨叶15上，并通过滑环引电器11将导线引出；
步骤4，调整多普勒激光测振仪4，使多普勒激光测振仪4发射的激光束经由激光导向管17垂直射向第一反光镜12，利用光反射原理使位于第一反光镜12镜面上的激光束水平射向第二反光镜22，由于第二反光镜22位于椭圆状薄壁反光镜19的空间焦点位置，由于经由一个焦点射出的激光束，即位于第二反光镜22镜面上的激光束经由椭圆状薄壁反光镜19反射射向位于第二焦点的复合材料桨叶15测点位置；
步骤5，启动旋转台驱动电机21，旋转椭圆状薄壁反光镜19，实现一个测点的扫描；再通过调整旋转台18整体沿复合材料桨叶15径向位置，实现复合材料桨叶15的全局扫描，实现复合材料桨叶15相应点的全局扫描；
步骤6，放置好沙子，同时启动驱动电机23以及进行风力的供给，实现风沙环境模拟。
步骤7，再次启动复合材料桨叶15的伺服电机9，进行正式试验；
步骤8，改变复合材料桨叶15的测点位置，重复步骤4-6，实现复合材料桨叶15上多个 振点的测试。

Claims (8)

  1. 风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，其特征在于，包括装备本体，风向调节装置，沙子导向装置、激光测振装置和沙子循环装置，所述装备本体内腔中部设置有激光测振装置，所述装备本体底板底部设置有位于激光测振装置左端的沙子循环装置，所述装备本体顶部设置有多普勒激光测振仪，所述装备本体顶部设置有位于多普勒激光测振仪左端的风向调节装置，所述装备本体顶部设置有位于风向调节装置左端的沙子导向装置，所述装备本体左端侧壁设置有风向调节装置，所述装备本体右端侧壁设置有出风口。
  2. 根据权利要求1所述的风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，其特征在于：所述激光测振装置包括支撑架，所述支撑架的顶板底部安装有伺服电机，所述支撑架顶板顶部设置有光线控制转台，所述光线控制转台内腔中部设置有滑环引电器，且滑环引电器中部与伺服电机输出轴相连，所述滑环引电器顶部设置有第一反光镜，所述第一反光镜镜面与水平面呈45°，所述第一反光镜中下部侧壁设置有安装板，所述安装板末端设置有反光镜微调装置，所述第一反光镜顶部设置有贯穿光线控制转台顶部的复合材料桨叶，所述复合材料桨叶顶部设置有应变片，所述滑环引电器和应变片组成应变测量模块，所述复合材料桨叶顶端中部设置有激光导向管，所述激光导向管顶部设置有多普勒激光测振仪，所述多普勒激光测振仪、激光导向管、第一反光镜和反光镜微调装置构成激光测振模块。
  3. 根据权利要求2所述的风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，其特征在于：所述反光镜微调装置包括基座，所述基座顶部对称安装有椭圆状薄壁反光镜，所述基座顶端中部设置有旋转台支架，所述旋转台支架底端中部设置有旋转台驱动电机，所述旋转台支架顶端的安装有第二反光镜。
  4. 根据权利要求1所述的风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，其特征在于：所述沙子循环装置包括驱动电机和激振杆，两所述激振杆之间安装有粗连杆和细连杆，所述粗连杆和激振杆顶部设置有复合激振面，所述激振杆中右端设置有长细连杆，且长细连杆伸出端外壁设置有扭簧，所述长细连杆伸出端外壁设置有第一安装座，且扭簧内嵌在第一安装座通孔内，所述驱动电机输出轴外壁安装有摆锤，两所述摆锤外侧壁驱动电机输出轴上安装有第二安装座。
  5. 根据权利要求1所述的风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，其特征在于：所述风向调节装置包括扇叶、步进电机和进风口，所述进风口内侧壁之间均匀安装有扇叶，所述进风口外侧壁安装有步进电机，且步进电机轴线与扇叶水平设置，所述进风口顶部设置有位于步进电机正上方的流量阀。
  6. 根据权利要求1所述的风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，其特征 在于：所述沙子导向装置包括进沙口，所述进沙口底部设置有双层格栅板。
  7. 根据权利要求1所述的风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，其特征在于：所述装备本体底板由水平部分和倾斜部分组成。
  8. 风沙环境下旋翼无人机复合材料桨叶可靠性试验的试验方法，采用权利要求1所述的风沙环境下旋翼无人机复合材料桨叶可靠性试验装备，其特征在于：包括以下步骤，
    步骤1，将复合材料桨叶安装在第一反光镜顶端，接通电源，确保复合材料桨叶正常运转，检测各部件是否显示正常，进行调试和校正；
    步骤2，进行预试验，启动伺服电机，进行复合材料桨叶空转试验30分钟，以消除伺服电机热误差对试验的影响；
    步骤3，将应变片准确贴于复合材料桨叶上，并通过滑环引电器将导线引出；
    步骤4，调整多普勒激光测振仪，使多普勒激光测振仪发射的激光束经由激光导电管垂直射向第一反光镜，利用光反射原理使位于第一反光镜镜面上的激光束水平射向第二反光镜，由于第二反光镜位于椭圆状薄壁反光镜的空间焦点位置，由于经由一个焦点射出的激光束，即位于第二反光镜镜面上的激光束经由椭圆状薄壁反光镜反射射向位于第二焦点的复合材料桨叶测点位置；
    步骤5，启动旋转台驱动电机，旋转椭圆状薄壁反光镜，实现一个测点的扫描；再通过调整旋转台整体沿复合材料桨叶径向位置，实现复合材料桨叶的全局扫描，实现对复合材料桨叶测点的全局扫描；
    步骤6，放置好沙子，同时启动驱动电机以及进行风力的供给，实现风沙环境模拟；
    步骤7，再次启动复合材料桨叶的伺服电机，进行正式试验；
    步骤8，改变复合材料桨叶的测点位置，重复步骤4-6，实现复合材料桨叶上多个振点的测试。
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