阅读说明：本技术 一种直立式火星飞行器单旋翼系统升阻特性测量装置 (Lift-drag characteristic measuring device for single rotor system of vertical Mars aircraft ) 是由 全齐全 赵鹏越 陈水添 唐德威 邓宗全 朱凯杰 吕艺轩 于 2019-09-24 设计创作，主要内容包括：一种直立式火星飞行器单旋翼系统升阻特性测量装置,本发明涉及一种测量装置,本发明的目的是提供一种直立式火星飞行器单旋翼系统升阻特性测量装置,以解决常规地球单旋翼系统升阻特性测量装置难以提供充足的飞行转速高精度测量升阻特性的问题。它包括旋翼模块、动力模块和测量模块；旋翼模块、动力模块和测量模块沿旋翼系统旋转轴方向由上至下依次固定连接。本发明用于飞行器单旋翼系统升阻特性测量领域。(The invention discloses a lift-drag characteristic measuring device of a single-rotor system of a vertical Mars aircraft, relates to a measuring device, and aims to provide the lift-drag characteristic measuring device of the single-rotor system of the vertical Mars aircraft so as to solve the problem that the conventional lift-drag characteristic measuring device of the single-rotor system of the Earth is difficult to provide sufficient flight rotating speed to measure the lift-drag characteristic with high precision. The device comprises a rotor wing module, a power module and a measuring module; rotor module, power module and measurement module are along rotor system rotation axis direction fixed connection from top to bottom in proper order. The method is used for the field of lift-drag characteristic measurement of a single rotor system of an aircraft.)

1. The utility model provides a single rotor system of vertical type mars aircraft lifts and hinders characteristic measurement device which characterized in that: the device comprises a rotor wing module (1), a power module (2) and a measuring module (3); rotor module (1), power module (2) and measuring module (3) are along rotor system rotation axis direction fixed connection from top to bottom in proper order.

2. The device of claim 1, wherein the device is adapted to measure lift-drag characteristics of a single-rotor system of an upright Mars aircraft: the rotor wing module (1) comprises a propeller clamp (1-2), two rotor wing blades (1-1), two fixing screw rods (1-3), two pairs of double nuts (1-5) and two locking bolts (1-4), wherein two ends of the propeller clamp (1-2) are respectively processed with a blade mounting groove, one rotor wing blade (1-1) is respectively arranged in each blade mounting groove, one end of each rotor wing blade (1-1) is mounted on one blade mounting groove through one fixing screw rod (1-3), each pair of double nuts (1-5) are in threaded connection with each other and mounted on the threaded end of the fixing screw rods (1-3), the two rotor wing blades (1-1) are oppositely arranged, the end face of the connecting end of one rotor wing blade (1-1) and the propeller clamp (1-2) and the end face of the connecting end of the other rotor wing blade (1-1) and the propeller clamp (1-2) are mutually perpendicularly arranged The two locking bolts (1-4) are arranged on the paddle clamp (1-2), and the paddle clamp (1-2) is fixedly arranged on the top end of the power module (2) through the two locking bolts (1-4).

3. The device of claim 1, wherein the device is adapted to measure lift-drag characteristics of a single-rotor system of an upright Mars aircraft: the power module (2) comprises a bearing end cover (2-2), a first deep groove ball bearing (2-3), a main shaft (2-4), an upper end shell (2-6), a second deep groove ball bearing (2-7), a coupler (2-10), a high-speed motor (2-13) and a lower end shell (2-14); a bearing end cover (2-2) is fixedly arranged at the top end of an upper end shell (2-6), a first deep groove ball bearing (2-3), a second deep groove ball bearing (2-7) and a coupler (2-10) are arranged in the upper end shell (2-6) from top to bottom, a main shaft (2-4) penetrates through the bearing end cover (2-2), an inner ring of the first deep groove ball bearing (2-3) and an inner ring of the second deep groove ball bearing (2-7) from top to bottom and is fixedly inserted on the top end of the coupler (2-10), a high-speed motor (2-13) is arranged on a lower end shell (2-14), a lower end shell (2-14) is fixedly arranged on the bottom end of the upper end shell (2-6), the output end of a rotating shaft of the high-speed motor (2-13) is fixedly inserted on the bottom end of the coupler (2-10), the bottom ends of the lower end shells (2-14) are fixedly arranged on the measuring module (3).

4. The device of claim 3, wherein the device is adapted to measure lift-drag characteristics of a single-rotor system of an upright Mars aircraft: the power module (2) further comprises a first retainer ring (2-5), a second retainer ring (2-8), a locking double nut (2-9), a plurality of end cover fixing screws (2-1), a plurality of shell connecting bolts (2-11) and a plurality of motor fixing screws (2-12), the bearing end cover (2-2) is fixedly arranged on the top end of the upper end shell (2-6) through the plurality of end cover fixing screws (2-1), the top end of the outer ring of the first deep groove ball bearing (2-3) is propped against the bottom end face of the bearing end cover (2-2), the first retainer ring (2-5) is arranged between the outer ring of the first deep groove ball bearing (2-3) and the outer ring of the second deep groove ball bearing (2-7), the bottom end of the outer ring of the second deep groove ball bearing (2-7) is clamped on the inner side wall of the upper end shell (2-6), the shoulder of the main shaft (2-4) is clamped between the bearing end cover (2-2) and the inner ring of the first retainer ring (2-5), the bottom end of the second retainer ring (2-8) close to the second deep groove ball bearing (2-7) is sleeved on the main shaft (2-4), the lower end face of the locking double nut (2-9) close to the second retainer ring (2-8) is in threaded connection with the main shaft (2-4), the shell of the high-speed motor (2-13) is installed on the top end of the lower end shell (2-14) through a plurality of motor fixing screws (2-12), the bottom end of the upper end shell (2-6) is fixedly installed on the top end of the lower end shell (2-14) through a plurality of shell connecting bolts (2-11), the bottom end of the lower end shell (2-14) is provided with a plurality of shell connecting bolts (2-11), the axial line of the rotating shaft of the high-speed motor (2-13) is superposed with the axial line of the main shaft (2-4).

5. The device of claim 1, wherein the device is adapted to measure lift-drag characteristics of a single-rotor system of an upright Mars aircraft: the measuring module (3) comprises a sensor tool (3-1), a six-dimensional force sensor (3-2), a bottom plate (3-5), a plurality of sensor tool connecting screws (3-3) and a plurality of bottom plate connecting screws (3-4); the top end of the six-dimensional force sensor (3-2) is fixedly connected with the sensor tool (3-1) through a plurality of sensor tool connecting screws (3-3), and the bottom end of the six-dimensional force sensor (3-2) is fixedly connected with the bottom plate (3-5) through a plurality of bottom plate connecting screws (3-4).

6. The device for measuring lift-drag characteristics of a single-rotor system of an upright mars aircraft according to claims 1, 2, 3, 4, or 5, wherein: the top end of the main shaft (2-4) is inserted into a center hole of the paddle clamp (1-2), two locking bolts (1-4) on the paddle clamp (1-2) are fixedly connected with the connecting end of the main shaft (2-4), and the bottom end of the lower end shell (2-14) is fixedly connected with the sensor tool (3-1) through a plurality of shell connecting bolts (2-11).

Technical Field

the invention relates to a measuring device, in particular to a device for measuring lift-drag characteristics of a single rotor system of a vertical Mars aircraft.

Background

The thin atmospheric environment on the surface of the mars can provide flight conditions for the low-altitude atmospheric flight of the mars, however, the physical characteristics of the mars atmospheric environment are complex and changeable, and the flight performance evaluation of the mars aircraft still needs to be further researched. The existing aircraft capable of being used for Mars surface flight mainly comprises a rotary wing aircraft, a fixed wing aircraft, a flapping wing aircraft, a floating balloon and the like, wherein the rotary wing aircraft can vertically take off and land for a plurality of times aiming at rugged and complex terrains on the Mars surface, hover flight is realized at a certain flying height, terrain and landform beliefs on the Mars surface are collected and information interaction is carried out with a Mars rover, the Mars rover is assisted to realize path planning on the Mars surface, and high-risk areas such as an annular mountain are avoided. Because mars surface atmosphere is thin and surface temperature is lower, thereby the rotor system of rotor formula aircraft need possess the flight that the high rotation rate produced sufficient flight lift and supported mars aircraft, however traditional rotor lift hinders characteristic measurement device structure complicacy, be difficult to provide sufficient flight rotational speed for mars rotor system, and be difficult to low lift to mars rotor system, low moment of torsion characteristic carries out high accuracy and measures, can't satisfy the actual engineering demand, the parameter characteristic measurement of little lift, the experimental apparatus who is applicable to mars rotor formula aircraft rotor system lift and hinders the characteristic research still has a large amount of blanks. Therefore, the device for measuring the lift-drag characteristic of the single rotor system of the Mars rotor type aircraft with a compact structure has important theoretical and engineering significance for the development of the aircraft.

Disclosure of Invention

The invention aims to provide a lift-drag characteristic measuring device of a single-rotor system of a vertical Mars aircraft, which solves the problem that the conventional lift-drag characteristic measuring device of the single-rotor system of the earth is difficult to provide sufficient flight rotating speed to measure the lift-drag characteristic with high precision.

The technical scheme adopted by the invention for solving the problems is as follows:

The device comprises a rotor wing module, a power module and a measuring module; rotor module, power module and measurement module are along rotor system rotation axis direction fixed connection from top to bottom in proper order.

The invention has the beneficial effects that:

1. The rotor blade of the rotor module is arranged on two sides of the paddle clamp and is used as a whole to perform dynamic balance adjustment before measurement, so that the requirement of the lift-drag characteristic measuring device on the motion stability of a rotor system is met. The rotor module and the main shaft lug connection of power module, the rotor blade of rotor module can carry out quick replacement to satisfy and rise and hinder characteristic measuring device to the multiple measurement of different rotor systems. The whole vertical connection of the power module ensures that the measuring device has compact structure and high and stable motion process. The measuring module is directly connected with the bottom of the power module, so that the lift-drag characteristic of the rotor system can be directly measured, and the measuring precision requirement of the measuring device is met.

2. The rotor blade and the rotor clamp of the rotor module can be replaced quickly, the structure and the installation angle of the rotor system blade can be adjusted respectively, and the mode is simple and efficient.

3. The invention adopts a mode of direct connection of the high-speed motor, the coupler and the main shaft, and can ensure the stability of the motion transmission process.

4. The measuring module of the invention adopts the six-dimensional force sensor to directly measure, can realize the decoupling measurement of the lift force and the torque in each direction, and ensures the correctness and the accuracy of the measuring result.

5. According to multiple tests, the rotating speed adjusting range of the lift-drag characteristic measuring device of the single rotor system is 0-4000 r/min, the rotating speed error is +/-10 r/min, the adjusting range of the diameter of the rotor system blade is 0.5-1.0 m, and the rotor system can adjust the installation angle and replace the rotor blade.

6. According to multiple tests, the rotor wing system has stable overall performance in a 640Pa carbon dioxide environment working process at 4000r/min and a wingspan of 1.0 m.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention.

Fig. 2 is a front view of the present invention.

Fig. 3 is a top view of the present invention.

Detailed Description