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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

Active Publication Date: 2018-06-29
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention is to solve the problem that it is difficult to simulate the accurate test of the rotor performance in the Martian environment for the rotor hovering test device on the ground. The present invention provides a pendulum-type Mars UAV rotor system hover characteristic test device

Method used

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  • Testing device for hovering characteristics of pendulum type rotor system of Mars unmanned aerial vehicle
  • Testing device for hovering characteristics of pendulum type rotor system of Mars unmanned aerial vehicle
  • Testing device for hovering characteristics of pendulum type rotor system of Mars unmanned aerial vehicle

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specific Embodiment approach 1

[0036] Specific implementation mode one: see figure 1 Describe this embodiment, a kind of pendulum-type Mars unmanned aerial vehicle rotor system hovering characteristic testing device described in this embodiment, it comprises Mars atmospheric environment simulation device 1, support frame 2, rotor system 3 and swing angle detection device 4;

[0037] The support frame 2 is placed in the Mars 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 rotor lift in the horizontal direction;

[0039] The swing angle detection device 4 is used to detect the swing angle value of the rotor connecting rod 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 Mars atmospheric environment simulation device 1, and the rotor p...

specific Embodiment approach 2

[0041] Specific implementation mode two: see Figure 1 to Figure 6 Describe this embodiment, the difference between this embodiment and the pendulum-type Mars UAV rotor system hovering characteristic test 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, and 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 all fixed on the connecting rod seat 3-3, the photoelectric encoder 3-4 is used to detect the rotating speed of the motor 3-5, and the output shaft of the motor 3-5 is fixed with a rotor blade Leaves 3-6.

[0044] In this embodiment, the rotor connecting rod 3-1 and the connecting rod base 3-3 ...

specific Embodiment approach 3

[0045] Specific implementation mode three: see Figure 1 to Figure 6 Describe this embodiment, the difference between this embodiment and a pendulum-type Mars unmanned aerial vehicle rotor system hovering characteristic test device described in the second embodiment is that the pendulum angle detection device 4 includes an inclinometer 4-1, two A knife-edge support 4-2 and a knife-edge connecting rod 4-3;

[0046] The front and rear two support rods of the upper end surface of the support frame 2 are all provided with a knife-edge groove 2-1, and a knife-edge support 4-2 is respectively arranged in the two knife-edge grooves 2-1, and the blade of the knife-edge support 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 the two 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...

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Abstract

The invention relates to a testing device for hovering characteristics of a pendulum type rotor system of a Mars unmanned aerial vehicle, and relates to the hovering characteristics testing field of the rotor system of the unmanned aerial vehicle. The device solves the problem that it is difficult to simulate accurate tests of rotor performance in the Martian environment through rotor hovering test devices on the ground. The device includes a Martian atmospheric environment simulator, a support frame, a rotor system and a pendulum angle detection device; the support frame is placed in the Martian atmospheric environment simulator, and the rotor system and the pendulum angle detection device are fixed on the support frame; the rotor system is used for generating rotor lift in the horizontaldirection; the pendulum angle detection device is used for detecting the pendulum angle value of a rotor connecting rod under different rotor lift in a rotor system. The device is mainly used for testing the rotor system of the unmanned aerial vehicle in the Martian environment.

Description

technical field [0001] The invention relates to the field of testing the hovering characteristics of an unmanned aerial vehicle rotor system. Background technique [0002] With the continuous development of deep space exploration technology, the exploration of extraterrestrial planets has gradually become a new direction of scientific researchers' attention, and it is of great significance for human beings to explore extraterrestrial life and explore the origin of life. Mars is adjacent to the Earth in the solar system and has a similar size and diurnal change to that of the Earth. In addition, Mars was found to have a thin atmosphere and is considered to be one of the exoplanets that humans can live in in the future. In order to further accelerate the exploration of Mars, a concept of an aircraft for Mars exploration has been proposed and continuously promoted. Its main forms include: fixed wing, floating air balloon, flapping wing and rotary wing. Among them, it is diffic...

Claims

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Application Information

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IPC IPC(8): B64G7/00B64F5/60G01M99/00
CPCB64G7/00B64G2007/005B64F5/60G01M99/00
Inventor 全齐全陈水添赵鹏越柏德恩李贺邓宗全
Owner HARBIN INST OF TECH
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