Testing device for hovering characteristics of pendulum type rotor system of Mars unmanned aerial vehicle
A characteristic test and aircraft rotor technology, applied in the direction of measuring device, aircraft component test, machine/structural component test, etc., can solve problems such as difficult to simulate accurate test of rotor performance, achieve novel measurement methods, scientific and reasonable structural design, and test The effect of stable performance indicators
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[0036] Specific implementation mode 1: see figure 1 This embodiment will be described. The pendulum type Mars UAV rotor system hovering characteristic test device described in this embodiment includes a Mars atmospheric environment simulation device 1, a support frame 2, a rotor system 3 and a swing angle detection device 4;
[0037] The support frame 2 is placed in the Martian atmospheric environment simulation device 1, and the rotor system 3 and the swing angle detection device 4 are fixed on the support frame 2;
[0038] The rotor system 3 is used to generate the rotor lift in the horizontal direction;
[0039] The swing angle detection device 4 is used to detect the swing angle value of the rotor link 3-1 on the rotor system 3 under different rotor lift forces.
[0040] In this embodiment, the support frame 2 , the rotor system 3 and the swing angle detection device 4 are placed in the Martian atmospheric environment simulation device 1 to accurately test the rotor perfo...
Example Embodiment
[0041] Specific implementation two: see Figure 1 to Figure 6 Describing this embodiment, the difference between this embodiment and the pendulum-type Mars UAV rotor system hovering characteristic testing device described in the first embodiment is that the rotor system 3 includes a rotor connecting rod 3-1, a counterweight Block 3-2, connecting rod seat 3-3, photoelectric encoder 3-4, motor 3-5 and rotor blade 3-6;
[0042] The head end of the rotor connecting rod 3-1 is fixed with a counterweight 3-2, the tail end is fixed with a connecting rod seat 3-3, and the rotor connecting rod 3-1 is fixed on the support frame 2;
[0043] The photoelectric encoder 3-4 and the motor 3-5 are fixed on the connecting rod base 3-3. The photoelectric encoder 3-4 is used to detect the rotation speed of the motor 3-5. The output shaft of the motor 3-5 is fixed with a rotor propeller. Leaves 3-6.
[0044] In this embodiment, the rotor connecting rod 3-1 and the connecting rod seat 3-3 can be ...
Example Embodiment
[0045] Specific implementation mode three: see Figure 1 to Figure 6 Describing this embodiment, the difference between this embodiment and the pendulum-type Mars UAV rotor system hovering characteristic testing device described in the second embodiment is that the swing angle detection device 4 includes an inclinometer 4-1, two A knife edge bracket 4-2 and a knife edge connecting rod 4-3;
[0046] The front and rear two support rods of the upper end face of the support frame 2 are provided with a knife-edge groove 2-1, and a knife-edge bracket 4-2 is respectively provided in the two knife-edge grooves 2-1. The blade of the knife-edge bracket 4-2 The tip is in line contact with the knife edge groove 2-1;
[0047] Two knife-edge brackets 4-2 are respectively fixed on both ends of the knife-edge connecting rod 4-3, and the knife-edge connecting rod 4-3 is vertically fixed on the rotor connecting rod 3-1,
[0048] The inclinometer 4-1 is fixed on the knife-edge connecting rod 4-3...
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