阅读说明：本技术 一种直立式火星飞行器共轴旋翼系统升阻特性测量装置 (lift-drag characteristic measuring device for vertical Mars aircraft coaxial rotor system ) 是由 唐德威 赵鹏越 陈水添 全齐全 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共轴旋翼系统升阻特性测量装置,它涉及一种测量装置。本发明解决了现有的旋翼系统升阻特性测试装置没有针对火星飞行器系统提供充足的转速并精确获取旋翼系统工作时产生的升力与扭矩,难以满足实际的工程需求的问题。内轴的下端依次穿过外轴上齿轮、第一挡圈、内轴下齿轮、第二挡圈、第一深沟球轴承和第三挡圈,内轴的下端通过双螺母锁紧,外轴上齿轮通过一对第一深沟球轴承安装在内轴上且二者同轴连接,内轴上齿轮与内轴下齿轮相互啮合,外轴下齿轮与外轴上齿轮的下部外沿相互啮合,轴承外壳的下端安装在上支架的中心处,外轴上齿轮通过两个第二深沟球轴承安装在轴承外壳内。本发明用于火星飞行器共轴旋翼系统升阻特性测量。(A lift-drag characteristic measuring device for a coaxial rotor system of a vertical Mars aircraft relates to a measuring device. The invention solves the problems that the existing rotor system lift-drag characteristic testing device does not provide sufficient rotating speed for a Mars aircraft system, accurately obtains the lift force and the torque generated by the rotor system during working and is difficult to meet the actual engineering requirement. The lower end of the inner shaft sequentially penetrates through the outer shaft upper gear, the first retaining ring, the inner shaft lower gear, the second retaining ring, the first deep groove ball bearings and the third retaining ring, the lower end of the inner shaft is locked through the double nuts, the outer shaft upper gear is mounted on the inner shaft through the pair of first deep groove ball bearings and is coaxially connected with the inner shaft upper gear and the inner shaft lower gear, the outer shaft lower gear is meshed with the outer edge of the lower portion of the outer shaft upper gear, the lower end of the bearing shell is mounted at the center of the upper support, and the outer shaft upper gear is mounted in the bearing shell through the two second deep groove ball bearings. The method is used for measuring the lift-drag characteristic of the coaxial rotor system of the Mars aircraft.)

1. A lift-drag characteristic measuring device of a vertical Mars aircraft coaxial rotor system comprises a rotor module (1), a driving module (2) and a measuring module (3), wherein the rotor module (1), the driving module (2) and the measuring module (3) are sequentially connected in the vertical direction of a rotating shaft of the rotor system; the method is characterized in that:

the rotor wing module (1) comprises an upper propeller clamp (1-1), an inner shaft (1-4), an upper rotor wing mounting seat (1-5), a lower propeller clamp (1-8) and a plurality of rotor wing blades (1-9); the upper propeller clamp (1-8) is detachably mounted on a lower propeller tool (2-1) of the driving module (2), and the lower propeller clamp (1-8) is detachably mounted on two rotor blades (1-9);

the driving module (2) comprises a lower rotor wing tool (2-1), bearing end covers (2-4), an outer shaft upper gear (2-5), an upper bracket (2-9), an outer shaft lower gear (2-10), a lower bracket (2-12), an inner shaft lower gear (2-16), bearing lower end covers (2-21), two high-speed motors (2-24), bearing outer shells (2-26) and inner shaft upper gears (2-27); the lower rotor wing tool (2-1) is installed in the middle of an inner shaft (1-4), the lower end of the inner shaft (1-4) sequentially penetrates through an outer shaft upper gear (2-5), a first retainer ring (2-17), an inner shaft lower gear (2-16), a second retainer ring (2-25), a first deep groove ball bearing (2-19) and a third retainer ring (2-25), the lower end of the inner shaft (1-4) is locked through a double nut (2-23), the outer shaft upper gear (2-5) is installed on the inner shaft (1-4) through a pair of first deep groove ball bearings (2-2) and coaxially connected with the inner shaft (1-4), two high-speed motors (2-24) are correspondingly installed on the upper end face of a base (3-2) of a measuring module (3) from left to right, the upper portions of the two high-speed motors (2-24) are detachably connected with a lower support (2-12, an inner shaft upper gear (2-27) is arranged on an output shaft of a left high-speed motor (2-24), the inner shaft upper gear (2-27) is meshed with an inner shaft lower gear (2-16), an outer shaft lower gear (2-10) is arranged on an output shaft of a right high-speed motor (2-24), the lower edge of the outer shaft lower gear (2-10) is meshed with the outer edge of the lower part of an outer shaft upper gear (2-5), an upper bracket (2-9) is detachably arranged on the upper end face of a lower bracket (2-12), the lower end of a bearing shell (2-26) is arranged at the center of the upper bracket (2-9), the outer shaft upper gear (2-5) is arranged in the bearing shell (2-26) through two second deep groove ball bearings (2-7), a bearing end cover (2-4) is detachably arranged on the upper end face of the bearing shell (2-26), the lower end of the inner shaft (1-4) is mounted on the lower support (2-12) through a third deep groove ball bearing (2-19), and a bearing lower end cover (2-21) is detachably connected to the middle of the lower support (2-12);

the measuring module (3) comprises a base (3-2) and a plurality of pressure sensors (3-1), wherein the pressure sensors (3-1) are uniformly arranged between the base (3-2) and the lower support (2-12) along the circumferential direction.

2. The device of claim 1, wherein the device is configured to measure lift-drag characteristics of a coaxial rotor system of an upright mars aircraft: two rotor blades (1-9) are arranged on the upper paddle clamp (1-1), two rotor blades (1-9) are arranged on the lower paddle clamp (1-8), and the rotating directions of the two rotor blades (1-9) on the upper paddle clamp (1-1) and the two rotor blades (1-9) on the lower paddle clamp (1-8) are opposite.

3. an upright mars aircraft coaxial rotor system lift-drag characteristic measurement device of claim 1 or 2, wherein: the upper propeller clamp (1-1) is detachably connected with the rotor blade (1-9) through two bolt nuts, the lower propeller clamp (1-8) is detachably connected with the rotor blade (1-9) through two bolt nuts, and the bolt nuts are locked through two nuts.

4. The device of claim 3, wherein the device is configured to measure lift-drag characteristics of a coaxial rotor system of an upright Mars aircraft: the inner shaft (1-4) is used for driving the rotor blades (1-9) on the upper paddle clamp (1-1) to rotate at a high speed, the outer shaft upper gear (2-5) is used for driving the rotor blades (1-9) on the lower paddle clamp (1-8) to rotate at a high speed, the rotating motions of the inner shaft (1-4) and the outer shaft upper gear (2-5) are mutually independent, and the rotating directions of the inner shaft (1-4) and the outer shaft upper gear (2-5) are opposite.

5. The device of claim 1, 2 or 4 for measuring lift-drag characteristics of a coaxial rotor system of an upright mars aircraft, wherein: the pressure sensors (3-1) are S-shaped pressure sensors, the number of the pressure sensors (3-1) is three, and the circumferentially arranged pressure sensors (3-1) can directly measure the lifting force generated by the rotor module (1) in each direction.

6. The device of claim 5, wherein the device is configured to measure lift-drag characteristics of a coaxial rotor system of an upright Mars aircraft: the gear (2-5) on the outer shaft consists of a sleeve section and a gear, and the lower end of the sleeve section and the gear are coaxially and fixedly installed into a whole.

7. An upright mars aircraft coaxial rotor system lift-drag characteristic measurement device of claim 1, 2, 4, or 6, wherein: the lower part of the inner shaft (1-4) is driven by a high-speed motor (2-24) positioned on the left side, the gear of the gear (2-5) on the outer shaft is driven by a high-speed motor (2-24) positioned on the right side, and the high-speed motor (2-24) is detachably connected with the lower bracket (2-12).

8. the device of claim 7, wherein said device is configured to measure lift-drag characteristics of a coaxial rotor system of an upright mars aircraft: the coaxial rotor system is in a vertical structure.

9. An upright mars aircraft coaxial rotor system lift-drag characteristic measurement device according to claim 1, 2, 4, 6, or 8, wherein: the ratio of the rotation speed of the internal shaft upper gears (2-27) to the rotation speed of the internal shaft lower gears (2-16) is 1.

10. The device of claim 9, wherein the device is configured to measure lift-drag characteristics of a coaxial rotor system of an upright mars aircraft: the rotating speed ratio of the outer shaft lower gears (2-10) to the outer shaft upper gears (2-5) is 1.

Technical Field

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

Background

The mars as a red planet ball adjacent to the earth completely records the evolution process of the solar system planets, and has important significance for exploring the surface of the mars to research the geological structure of the planets, explore the origin of life and expand the second family of human beings. At present, a Mars rover is mainly adopted for the detection mode of the Mars surface, and the surface detection of the Mars rover has great challenges due to a large number of dangerous areas such as sand pits and the like with complex and coexisting Mars in the surface topography and landform of the Mars. Research shows that a thin atmospheric environment exists on the surface of the Mars, and the possibility is provided for developing an aircraft for assisting a Mars rover to realize a Mars detection task. According to the flight principle, the aircraft mainly comprises three types, namely a fixed wing type aircraft, a flapping wing type aircraft and a rotary wing type aircraft, wherein the fixed wing type aircraft needs to run slowly for realizing the take-off and landing of the aircraft, the aircraft is difficult to adapt to the rugged and changeable terrain features of the Mars surface, the flight lift force of the flapping wing type aircraft is low, the flapping wing type aircraft is difficult to carry large detection equipment such as a high-resolution camera and the like, the aircraft is difficult to be used for assisting the detection of the Mars rover, the rotary wing type aircraft can realize stable take-off and landing on the Mars surface and can hover at a certain flight height to detect and plan the motion track of the Mars rover, and the aircraft has important significance for the implementation of a Mars detection. Therefore, the development of the coaxial rotor system suitable for the Mars atmospheric environment has important theoretical and engineering significance for realizing the function of the Mars aircraft.

the existing rotor system lift-drag characteristic testing device does not provide sufficient rotating speed for a mars aircraft system and accurately obtains lift force and torque generated when the rotor system works, and actual engineering requirements are difficult to meet.

Disclosure of Invention

The invention provides a lift-drag characteristic measuring device of a coaxial rotor system of a vertical mars aircraft, aiming at solving the problems that the existing lift-drag characteristic measuring device of the rotor system does not provide sufficient rotating speed for a mars aircraft system, accurately obtains lift force and torque generated by the rotor system during working and is difficult to meet the actual engineering requirement.

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

The lift-drag characteristic measuring device of the vertical Mars aircraft coaxial rotor system comprises a rotor module 1, a driving module 2 and a measuring module 3, wherein the rotor module 1, the driving module 2 and the measuring module 3 are sequentially connected in the vertical direction of a rotating shaft of the rotor system;

The rotor wing module 1 comprises an upper paddle clamp 1-1, an inner shaft 1-4, an upper rotor wing mounting seat 1-5, a lower paddle clamp 1-8 and a plurality of rotor wing blades 1-9; the upper rotor wing mounting seat 1-5 is detachably mounted at the upper end of the inner shaft 1-4, the upper propeller clamp 1-1 is detachably mounted on the upper rotor wing mounting seat 1-5, the upper propeller clamp 1-1 is detachably mounted with two rotor wing blades 1-9, the lower propeller clamp 1-8 is detachably mounted on the lower rotor wing tool 2-1 of the driving module 2, and the lower propeller clamp 1-8 is detachably mounted with two rotor wing blades 1-9;

the driving module 2 comprises a lower rotor wing tool 2-1, bearing end covers 2-4, outer shaft upper gears 2-5, upper brackets 2-9, outer shaft lower gears 2-10, lower brackets 2-12, inner shaft lower gears 2-16, bearing lower end covers 2-21, two high-speed motors 2-24, bearing outer shells 2-26 and inner shaft upper gears 2-27; the lower rotor wing tool 2-1 is arranged in the middle of an inner shaft 1-4, the lower end of the inner shaft 1-4 sequentially penetrates through an outer shaft upper gear 2-5, a first retainer ring 2-17, an inner shaft lower gear 2-16, a second retainer ring 2-25, a first deep groove ball bearing 2-19 and a third retainer ring 2-25, the lower end of the inner shaft 1-4 is locked through a double nut 2-23, an outer shaft upper gear 2-5 is arranged on the inner shaft 1-4 through a pair of first deep groove ball bearings 2-2 and coaxially connected with the inner shaft 1-4, the two high-speed motors 2-24 are correspondingly arranged on the upper end face of a base 3-2 of a measuring module 3 from left to right, the upper parts of the two high-speed motors 2-24 are detachably connected with a lower support 2-12, an upper gear 2-27 is arranged on an output shaft of a, the inner shaft upper gear 2-27 and the inner shaft lower gear 2-16 are meshed with each other, the outer shaft lower gear 2-10 is installed on an output shaft of a high-speed motor 2-24 on the right side, the outer shaft lower gear 2-10 and the lower outer edge of the outer shaft upper gear 2-5 are meshed with each other, an upper support 2-9 is detachably installed on the upper end face of a lower support 2-12, the lower end of a bearing outer shell 2-26 is installed at the center of the upper support 2-9, the outer shaft upper gear 2-5 is installed in the bearing outer shell 2-26 through two second deep groove ball bearings 2-7, a bearing end cover 2-4 is detachably installed on the upper end face of the bearing outer shell 2-26, the lower end of an inner shaft 1-4 is installed on the lower support 2-12 through a third deep groove ball bearing 2-19, and a bearing lower end cover 2-21 is detachably connected to;

the measuring module 3 comprises a base 3-2 and a plurality of pressure sensors 3-1, wherein the pressure sensors 3-1 are uniformly arranged between the base 3-2 and the lower support 2-12 along the circumferential direction.

In one embodiment, two rotor blades 1-9 are mounted on the upper paddle clamp 1-1, two rotor blades 1-9 are mounted on the lower paddle clamp 1-8, and the two rotor blades 1-9 on the upper paddle clamp 1-1 rotate in opposite directions to the two rotor blades 1-9 on the lower paddle clamp 1-8.

In one embodiment, the upper paddle clamp 1-1 is detachably connected to the rotor blade 1-9 by two bolts and nuts, and the lower paddle clamp 1-8 is detachably connected to the rotor blade 1-9 by two bolts and nuts, which are locked by two nuts.

In one embodiment, inner shaft 1-4 is used to drive rotor blades 1-9 on upper paddle clamp 1-1 to rotate at high speed, outer shaft gear 2-5 is used to drive rotor blades 1-9 on lower paddle clamp 1-8 to rotate at high speed, inner shaft 1-4 and outer shaft gear 2-5 rotate independently of each other, and inner shaft 1-4 and outer shaft gear 2-5 rotate in opposite directions.

In one embodiment, the pressure sensors 3-1 are S-shaped pressure sensors, the number of the pressure sensors 3-1 is three, and the circumferentially arranged pressure sensors 3-1 can directly measure the lift force generated by the rotor module 1 in all directions.

In one embodiment, the gears 2-5 on the outer shaft are formed by a sleeve section and a gear wheel, the lower end of the sleeve section being fixed coaxially with the gear wheel.

In one embodiment, the lower part of the inner shaft 1-4 is driven by a high speed motor 2-24 located on the left side, the gear of the gear 2-5 on the outer shaft is driven by a high speed motor 2-24 located on the right side, and the high speed motor 2-24 is detachably connected to the lower rack 2-12.

In one embodiment, the coaxial rotor system is configured in the form of a vertical mast.

compared with the prior art, the invention has the following beneficial effects:

the device for measuring the lift-drag characteristic of the vertical Mars aircraft coaxial rotor system is scientific and reasonable in structural design, the high-speed motors are arranged on two sides of the rotating shaft and are respectively matched with a group of gears, the rotating directions of the high-speed motors are opposite in the working process, and the upper rotor blades and the lower rotor blades are reversely arranged, so that the opposite rotating motions of the upper rotor and the lower rotor are realized, and the torque generated by the upper rotor and the lower rotor is offset; the coaxiality of the gears on the inner shaft and the outer shaft in the motion process is realized through a pair of deep groove ball bearings respectively, and the coaxiality of the gears on the inner shaft and the outer shaft in the motion process of the rotor system is finally ensured; the rotor module is connected with the driving module, the whole structure of the device is compact, the stability is high, the measuring module is arranged at the bottom of the device, and the lift-drag characteristic of the coaxial rotor system is directly obtained through the pressure sensor, so that the measuring precision requirement of the measuring device can be met;

the rotor wing can be integrally installed and disassembled, the rotor wing installation angle can be adjusted by replacing the propeller clamps, different blade forms can be adjusted by replacing the rotor wing blades, the rotor wing system can be simply and quickly replaced, the dynamic balance experiment can be performed on the whole rotor wing module before the experiment, and the motion stability of the rotor wing module in the working process is ensured;

The transmission of the rotary motion of the rotary shaft in opposite directions is realized by adopting the gear, so that the interference of the assembly of the two high-speed motors is avoided;

The high-speed motor and the S-shaped pressure sensor are arranged on the same plane, so that the compact structure of the testing device is ensured;

The measuring module of the invention adopts the S-shaped pressure sensor to directly measure, can realize the measurement of the lifting force in the vertical direction and ensure the correctness and the accuracy of the measuring result;

According to multiple tests, the rotating speed adjusting range of the lift-drag characteristic measuring device of the single-rotor system is 0-3000 r/min, the rotating speed error is +/-10 r/min, the adjusting range of the diameter of the blade of the rotor system is 0.5-1.5 m, the blade of the rotor system can be quickly replaced, the size of the installation angle can be adjusted, and the assembly is simple and efficient.

According to the invention, multiple tests show that the rotor system has good coaxiality and motion stability in the high-speed motion process of the inner shaft and the outer shaft at 3000 r/min.

According to multiple tests, the rotor wing system has stable overall performance in a 640Pa carbon dioxide environment working process at 3000r/min and a wingspan of 1.0 m.

drawings

FIG. 1 is a perspective view of a lift-drag characteristic measurement device of a coaxial rotor system of an upright Mars aircraft according to the present invention;

FIG. 2 is a front cross-sectional view of the lift-drag characteristic measurement device of the coaxial rotor system of the upright Mars aircraft of the present invention;

FIG. 3 is a front view of the lift-drag characteristic measurement device of the coaxial rotor system of the upright Mars aircraft of the present invention;

3 fig. 3 4 3 is 3 a 3 sectional 3 view 3 a 3- 3 a 3 of 3 fig. 3 2 3. 3

Detailed Description