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Aerodynamic characteristic measuring device capable of automatically adjusting distance between upper and lower rotors of Mars aircraft

A technology of aerodynamic characteristics and measurement device, which is applied in the simulation device of space navigation conditions, space shuttle, transportation and packaging, etc., can solve the problems such as the inability to realize the measurement of lift-drag characteristics of the dual-rotor system, and achieves reasonable design size coordination and structural design. Scientific and reasonable, novel structure effect

Active Publication Date: 2020-05-08
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problem that the lift-drag characteristic measurement device of the split Mars spacecraft rotor system in the prior art cannot realize the measurement of the lift-drag characteristic of the dual-rotor system under the earth’s atmospheric environment and the Martian atmospheric environment, the present invention further provides the upper and lower rotors of the Mars spacecraft. Pneumatic characteristic measuring device with automatic adjustable spacing

Method used

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  • Aerodynamic characteristic measuring device capable of automatically adjusting distance between upper and lower rotors of Mars aircraft
  • Aerodynamic characteristic measuring device capable of automatically adjusting distance between upper and lower rotors of Mars aircraft
  • Aerodynamic characteristic measuring device capable of automatically adjusting distance between upper and lower rotors of Mars aircraft

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specific Embodiment approach 1

[0030] Specific implementation mode one: combine Figure 1 to Figure 3Describe this embodiment, the aerodynamic characteristic measuring device that the distance between the upper and lower rotors of the Mars spacecraft is automatically adjustable, the device includes a frame 1, an up and down lifting slide mechanism, an upper rotor mechanism and a lower rotor mechanism;

[0031] The up and down lifting slide mechanism is installed inside the frame 1, the lower rotor mechanism is installed on the up and down lifting slide mechanism, and the upper rotor mechanism is installed on the frame 1 top, and the upper rotor mechanism and the lower rotor mechanism are relatively arranged.

[0032] In this embodiment, the frame 1 is located at the outermost layer, which reduces the influence of the rotor boundary layer effect, has a simple structure and high rigidity, and realizes the basic positioning of the lift-drag characteristic measuring device of the rotor system of the split Mars a...

specific Embodiment approach 2

[0033] Specific implementation mode two: combination Figure 1 to Figure 3 Describe this embodiment. This embodiment is to further limit the up and down lifting slide mechanism described in the first specific embodiment. In this embodiment, the up and down lifting slide mechanism includes a movable bracket 4, a lifting module 7, two Guide rail 2 and two slider assemblies 3, each guide rail 2 is fixed on the side wall of the frame 1, each guide rail 2 is provided with a slider assembly 3, and each slider assembly 3 slides with a guide rail 2 Connection, one end of the movable support 4 is fixedly connected with the two slider assemblies 3, and the other end of the movable support 4 is rotatably connected with the lifting module 7. Other compositions and connection methods are the same as those in the second embodiment.

[0034] In this embodiment, the guide rail 2, the slider assembly 3, and the movable bracket 4 constitute a sliding workbench with the function of moving up an...

specific Embodiment approach 3

[0035] Specific implementation mode three: combination Figure 5 Describe this embodiment. This embodiment is to further limit the movable support 4 described in the second specific embodiment. In this embodiment, the movable support 4 includes a slide table 4-1 and a lower rotor housing 4-2. , the lower rotor housing 4-2 is fixed on the upper surface of the slide table 4-1 by bolts, one end of the slide table 4-1 is fixedly connected with the two slide block assemblies 3, and the other end of the slide table 4-1 is connected with the lift Module 7 is connected by rotation. Other compositions and connection methods are the same as those in the second embodiment.

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Abstract

The invention discloses an aerodynamic characteristic measuring device capable of automatically adjusting the distance between upper and lower rotors of a Mars aircraft. The invention belongs to the field of Mars aircraft research and development. The invention mainly aims to solve the problem that a split-type Mars aircraft rotor system lift-drag characteristic measuring device in the prior art cannot measure the lift-drag characteristic of a double-rotor system in the earth atmospheric environment and the Mars atmospheric environment. The invention provides an aerodynamic characteristic measuring device capable of automatically adjusting the distance between an upper rotor and a lower rotor of a Mars aircraft. The device comprises a rack, an up-down lifting sliding table mechanism, an upper rotor mechanism and a lower rotor mechanism, wherein the up-down lifting sliding table mechanism is installed in the rack, the lower rotor wing mechanism is installed on the up-down lifting sliding table mechanism, the upper rotor wing mechanism is installed on the upper portion of the rack, and the upper rotor wing mechanism and the lower rotor wing mechanism are oppositely arranged. The device is used for experiments in two modes of the earth environment and the vacuum environment, and provides important test data for further research of Mars aircrafts.

Description

technical field [0001] The invention belongs to the field of research and development of Mars spacecraft, and in particular relates to an aerodynamic characteristic measuring device with automatically adjustable distance between the upper and lower rotors of the Mars spacecraft. Background technique [0002] The detection and research of life and water sources on extraterrestrial planets has always been an important part of the human deep space exploration plan. Since Mars is adjacent to the earth in the solar system and has a similar size to the earth, and the seasons alternate, life and water sources on Mars The detection of has become the focus of attention of scientists from all over the world. Since the complex terrain structure on the surface of Mars greatly limits the range of activities of the Mars rover, and the multi-point transfer of the Mars rover through the Mars spacecraft can largely solve this problem, so the research and development of the Mars spacecraft is...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G7/00B64G1/14
CPCB64G7/00B64G1/14
Inventor 全齐全朱凯杰沈文清赵鹏越唐德威吕艺轩邓宗全
Owner HARBIN INST OF TECH
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