Rotary-wing Mars UAV single-rotor system aerodynamic characteristics test device and torque test method and lift test method

A technology for aerodynamic characteristics and testing devices, which is used in measurement devices, aircraft component testing, and mechanical component testing. and other problems, to achieve the effect of high scope of application and flexibility, scientific and reasonable structural design

Active Publication Date: 2021-05-07
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problems that the existing rotor system aerodynamic characteristic test device is difficult to realize the small lift and low torque index requirements of the Mars UAV rotor system, poor applicability, and large measurement error, and provides a rotor type Mars unmanned Aerodynamic characteristic test device, torque test method and lift test method of aircraft single rotor system

Method used

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  • Rotary-wing Mars UAV single-rotor system aerodynamic characteristics test device and torque test method and lift test method
  • Rotary-wing Mars UAV single-rotor system aerodynamic characteristics test device and torque test method and lift test method
  • Rotary-wing Mars UAV single-rotor system aerodynamic characteristics test device and torque test method and lift test method

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specific Embodiment approach 1

[0036] Specific implementation mode one: the following combination figure 1 and figure 2 Describe this embodiment, the aerodynamic characteristic testing device of the single-rotor system of the rotor-type Mars UAV described in this embodiment, it includes motion module 1, torque measurement module 2 and lift force measurement module 3;

[0037] The lower end surface of the motion module 1 is connected to the upper end of the torque measurement module 2, and the motion module 1 and the torque measurement module 2 are placed on the upper end surface of one end of the balance bar of the lift measurement module 3;

[0038] The motion module 1 is used to generate rotational motion, thereby generating torque and lift;

[0039] The torque measurement module 2 is used to measure the torque generated by the motion module 1;

[0040] The lift measuring module 3 is used to measure the lift generated by the motion module 1 .

specific Embodiment approach 2

[0041] Specific implementation mode two: the following combination image 3 Describe this embodiment. This embodiment will further explain Embodiment 1. The motion module 1 includes a test rotor 1-1, an external high-speed brushless motor 1-2, a Hall element 1-3 and a No. 1 adapter rod 1-4. ;

[0042] The output shaft of the external high-speed brushless motor 1-2 drives the test rotor 1-1 to rotate. The shell of the external high-speed brushless motor 1-2 is connected to the upper end of the No. 1 adapter rod 1-4 through the bottom flange, and the Hall element 1-3 is connected to the bottom flange of the external high-speed brushless motor 1-2, the Hall element 1-3 is adjacent to and not in contact with the external high-speed brushless motor 1-2, and the Hall element 1-3 is used for external The speed of the high-speed brushless motor 1-2 is closed-loop controlled.

[0043] In this embodiment, the external high-speed brushless motor 1-2 is directly connected to the test ro...

specific Embodiment approach 3

[0044] Specific implementation mode three: the following combination Figure 4 and Figure 5 Describe this embodiment, this embodiment will further illustrate Embodiment 2, the torque measurement module 2 includes two sets of ball bearings 2-1, a laser transmitter 2-2, an upper grating ruler 2-3, a lower grating ruler 2-4, Laser receiver 2-5, No. 2 adapter rod 2-6, shell top cover 2-7, shell 2-8, lower grating seat 2-9 and shell bottom cover 2-10;

[0045]No. 2 transfer rod 2-6 is "T" shape, the upper end of No. 2 transfer rod 2-6 is connected with the lower end of No. 1 transfer rod 1-4, and the lower end of No. 2 transfer rod 2-6 is connected with the upper grating The ruler 2-3 is connected, the shell top cover 2-7, the shell 2-8 and the shell bottom cover 2-10 are connected in turn by screws, the lower grating ruler 2-4, the lower grating seat 2-9 and the shell bottom cover 2-10 in turn connected, and the lower grating seat 2-9 is located at the center of the shell botto...

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Abstract

The aerodynamic characteristic test device, torque test method and lift test method of the single-rotor system of the rotor-type Mars unmanned aerial vehicle belong to the technical field of the single-rotor unmanned aerial vehicle. The small lift and low torque index requirements of the rotor system, poor applicability, and large measurement errors. The present invention comprises a movement module, a torque measurement module and a lift measurement module; the lower end surface of the movement module is connected to the upper end of the torque measurement module, and the movement module and the torque measurement module are placed on the upper end surface of one end of the balance bar of the lift measurement module; the movement module is used to generate rotational movement , and then generate torque and lift; the torque measurement module is used to measure the torque generated by the motion module; the lift measurement module is used to measure the lift generated by the motion module. The invention is an unmanned aerial vehicle single-rotor system used for Mars exploration.

Description

technical field [0001] The invention relates to an aerodynamic characteristic testing device for a single-rotor system of a Mars unmanned aerial vehicle, belonging to the technical field of single-rotor unmanned aerial vehicles. Background technique [0002] Exploring the evolution of near-Earth planets, the origin of life, and the existence of water sources has always been one of the concerns of scientists at home and abroad in deep space exploration. Mars and the Earth have similar physical volumes, the same thin atmosphere, the same four seasons and day and night changes, and a more suitable temperature. Therefore, Mars exploration has become an important goal of deep space exploration missions. At present, the main means of Mars exploration include launching satellites and Mars rovers, etc. However, these means are limited by the detection accuracy and efficiency. The development of a Mars drone used to assist Mars rovers to complete the Mars exploration mission has bec...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01L5/00G01M13/00B64F5/60
CPCB64F5/60G01L5/00G01M13/00
Inventor 全齐全赵鹏越陈水添柏德恩唐德威邓宗全
Owner HARBIN INST OF TECH
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