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A hovering characteristic test simulation device and method of a lever-type Mars UAV rotor system

A simulation device and characteristic testing technology, which is applied to the simulation device of space navigation conditions, aircraft component testing, transportation and packaging, etc. It can solve the problems of large measurement error, poor applicability, and inability to simulate the Mars environment, and achieve measurement accuracy Improvement, the use process is safe and reliable, and the effect of novel measurement methods

Active Publication Date: 2020-12-25
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 aims to solve the problem that the existing hovering characteristic testing device can only be used for the evaluation of the hovering performance of the rotor system of the earth UAV, and cannot realize the simulation of the Martian environment, poor applicability and large measurement error

Method used

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  • A hovering characteristic test simulation device and method of a lever-type Mars UAV rotor system
  • A hovering characteristic test simulation device and method of a lever-type Mars UAV rotor system
  • A hovering characteristic test simulation device and method of a lever-type Mars UAV rotor system

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specific Embodiment approach 1

[0036] Specific implementation mode one: refer to Figure 1 to Figure 3 Specifically illustrate the present embodiment, a kind of hover characteristic test simulation device of the lever type Mars unmanned aerial vehicle rotor system described in the present embodiment, it comprises Mars atmospheric environment simulation device 1 and hovering experimental device 2,

[0037] The Mars atmospheric environment simulation device 1 is an airtight device, and the hovering experimental device 2 is located on the inner bottom surface of the Mars atmospheric environment simulation device 1.

[0038] The Mars atmospheric environment simulator 1 is used to simulate a low-vacuum carbon dioxide gas environment and maintain the pressure on the environment;

[0039] The hovering experimental device 2 includes an electromagnetic force dial indicator seat 2-1, a load cell 2-2, a weight plate 2-3, a base 2-4, a balance plate 2-5, a torque sensor 2-6, and a rotor system 2 -7 and weights 2-8,

...

specific Embodiment approach 2

[0042] Specific implementation mode two: refer to Figure 4 , Figure 6 to Figure 8 This embodiment is described in detail. This embodiment is a further description of the hovering characteristic test device of a lever type Mars unmanned aerial vehicle rotor system described in the first embodiment. In this embodiment, the Mars atmospheric environment simulation device 1 includes Vacuum chamber 1-1, first set of vacuum gauges 1-3, second set of vacuum gauges 1-5, fourth set of vacuum gauges 1-6, third set of vacuum gauges 1-8, vent valve 1-10, proportional valve 1-14, pipeline 1-15, carbon dioxide bottle 1-16, Roots pump 1-17, vane pump 1-18, bellows 1-19 and butterfly valve 1-20,

[0043] The vane pump 1-18 is used for preliminary vacuumizing the vacuum chamber 1-1,

[0044] The Roots pump 1-17 is used to further evacuate the vacuum chamber 1-1 to create a low vacuum environment. When the low vacuum environment is reached in the vacuum chamber 1-1, the Roots pump 1-17 is turn...

specific Embodiment approach 3

[0054] Specific implementation mode three: refer to Figure 4 Describe this embodiment in detail, this embodiment is to further illustrate the hover characteristic testing device of a kind of lever type Mars unmanned aerial vehicle rotor system described in specific embodiment two, in this embodiment, Mars atmospheric environment simulation device 1 also Including vacuum gauge shell 1-2, monitoring window 1-7, clamp 1-4, hatch door 1-11, first set of aviation insertion flange 1-9, second set of aviation insertion flange 1-12 and temperature control Flange 1-13,

[0055] Close the hatch 1-11 to form a closed space in the Mars atmospheric environment simulation device 1,

[0056] The outside of the first group of vacuum gauges 1-3, the second group of vacuum gauges 1-5, the third group of vacuum gauges 1-8 and the fourth group of vacuum gauges 1-6 are all covered with vacuum gauge shells 1-2 for sealing The first set of vacuum gauges 1-3, the second set of vacuum gauges 1-5, t...

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Abstract

The invention provides a lever type hovering characteristic test simulating device and method of a Mars unmanned aerial vehicle rotor wing system, and relates to the field of hovering characteristic test of unmanned aerial vehicle rotor wing systems. The lever type hovering characteristic test simulating device aims to solve the problems that an existing hovering characteristic test device can only be used for evaluating the hovering performance of an Earth unmanned aerial vehicle rotor wing system, simulation of the Mars environment cannot be achieved, the applicability is poor, and the measuring errors are large. A hovering experiment device is located on the inner bottom face of a Mars atmosphere environment simulating device, and the Mars atmosphere environment simulating device is used for simulating a low-vacuum carbon dioxide gas environment. A base serves as the fulcrum of a balancing plate, a rotor wing of the rotor wing system is mounted reversely, so that the lifting force direction goes downwards vertically, a torque sensor is used for measuring a torque generated in the rotating process of the rotor wing of the rotor wing system, a weight is placed in a weight disk soas to balance the weights of the two ends of the balancing plate, thus the balancing plate can be in a balanced state, and a force cell is used for measuring the lifting force generated in the rotating process of the rotor wing of the rotor wing system. The lever type hovering characteristic test simulating device is used for testing the hovering characteristic of the Mars unmanned aerial vehiclerotor wing system.

Description

technical field [0001] The invention relates to a hovering characteristic test simulation device and method of a lever type Mars unmanned aerial vehicle rotor system. It belongs to the field of testing the hovering characteristics of the UAV rotor system. Background technique [0002] Mars is adjacent to the earth in the solar system and has a physical volume and topography similar to the earth. It has completely recorded the birth and evolution of planets in the solar system for 5 billion years. Therefore, Mars exploration is very important for expanding the living space of human beings and exploring the origin of life. is of great significance. Exploring and developing new extraterrestrial deep space probes with high reliability, high efficiency and low risk has become an important topic. There is a thin atmosphere on Mars, which makes it possible to develop a rotary-wing Mars drone to assist the Mars rover in the Martian atmosphere. Compared with the traditional Mars r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G7/00B64F5/60
CPCB64G7/00B64G2007/005B64F5/60
Inventor 全齐全赵鹏越邓宗全陈水添柏德恩
Owner HARBIN INST OF TECH
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