阅读说明：本技术 用于测试火星飞行器单轴旋翼系统的悬停特性测试装置 (Hovering characteristic testing device for testing single-shaft rotor system of Mars aircraft ) 是由 唐德威 朱凯杰 沈文清 全齐全 赵鹏越 邓宗全 于 2019-09-24 设计创作，主要内容包括：用于测试火星飞行器单轴旋翼系统的悬停特性测试装置,涉及航空航天域。现有的单轴旋翼飞行器中的旋翼无法实现火星环境的飞行及定点着陆,适用性差且飞行效率极低。本装置包括单轴旋翼模块、动力模块和测量模块,动力模块中的交流伺服电机通过挠性联轴器带动传动轴旋转,传动轴带动浆叶旋转,电机编码器对交流伺服电机的转速进行检测,通过自反馈调节电源电压并修正交流伺服电机的转速,保证浆叶运动转速与工作人员要求的转速值一致,拉力传感器用于测量旋翼的升力,扭矩传感器用于测量旋翼的扭矩。本发明主要用于优选出最适合火星的旋翼。(a characteristic testing arrangement that hovers for testing mars aircraft single-axis rotor system relates to the aerospace domain. The rotor among the current unipolar rotor craft can't realize the flight and the fixed point landing of mars environment, and the suitability is poor and flight efficiency is extremely low. This device includes the unipolar rotor module, power module and measurement module, it is rotatory that the alternating current servo motor among the power module passes through flexible coupling and drives the transmission shaft, the transmission shaft drives the paddle and rotates, motor encoder detects alternating current servo motor's rotational speed, through the rotational speed of self-feedback regulation mains voltage and correction alternating current servo motor, it is unanimous with the rotational speed value that the staff required to guarantee paddle motion rotational speed, force transducer is used for measuring the lift of rotor, torque sensor is used for measuring the moment of torsion of rotor. The invention is mainly used for preferably selecting the rotor wing most suitable for mars.)

1. A characteristic testing arrangement that hovers for testing mars aircraft single-axis rotor system, its characterized in that: the single-shaft rotor wing measuring system comprises a single-shaft rotor wing module (1), a power module (2) and a measuring module (3);

The single-shaft rotor module (1) comprises a transmission shaft (1-1), a carbon fiber blade clamp (1-2) and two blades (1-3), wherein the carbon fiber blade clamp (1-2) is fixedly arranged at the top end of the transmission shaft (1-1), and one blade (1-3) is fixedly arranged on each of two sides of the carbon fiber blade clamp (1-2);

The power module (2) comprises an upper bearing end cover (2-1), a bearing seat (2-2), two first angular contact ball bearings (2-3), a flexible coupling (2-6), an alternating current servo motor (2-8) and a servo motor support (2-9), wherein the upper bearing end cover (2-1) is fixedly arranged at the upper port of the bearing seat (2-2), the two first angular contact ball bearings (2-3) which are arranged side by side up and down are clamped in the bearing seat (2-2), the two first angular contact ball bearings (2-3) are sleeved outside the transmission shaft (1-1), a driving shaft of the alternating current servo motor (2-8) is fixedly connected with the bottom end of the transmission shaft (1-1) through the flexible coupling (2-6), the alternating current servo motor (2-8) is fixedly arranged on the servo motor support (2-9), the lower end of the bearing seat (2-2) is fixedly connected with the upper end of the servo motor support (2-9);

the measuring module (3) comprises a tension sensor lower mounting seat (3-2), a torque sensor (3-7), a torque sensor mounting seat (3-4), a second angular contact ball bearing (3-5), a lower bearing end cover (3-3), a second flat key (3-8) and three tension sensors (3-1), the three tension sensors (3-1) are uniformly arranged between a servo motor support (2-9) and the tension sensor lower mounting seat (3-2) in the circumferential direction, the torque sensor (3-7) is arranged in the torque sensor mounting seat (3-4), the upper end of the torque sensor mounting seat (3-4) extends into a lower port of the tension sensor lower mounting seat (3-2), the torque sensor (3-7) is fixedly connected with the tension sensor lower mounting seat (3-2) through the second flat key (3-8), the second angular contact ball bearing (3-5) is sleeved on the outer surface of the torque sensor mounting seat (3-4), the lower bearing end cover (3-3) is fixedly arranged on the lower port of the tension sensor lower mounting seat (3-2), and the second angular contact ball bearing (3-5) is clamped at the lower port of the tension sensor lower mounting seat (3-2) by the lower bearing end cover (3-3).

2. the hover characteristic testing device of claim 1, wherein: the power module (2) further comprises a motor encoder (2-10), and the motor encoder (2-10) is arranged below the rotor of the alternating current servo motor (2-8).

3. the hover characteristic testing device of claim 1, wherein: the longitudinal section of the bearing seat (2-2) is convex, the two first angular contact ball bearings (2-3) are arranged in the upper convex opening of the bearing seat (2-2), and the flexible coupling (2-6) is arranged in the lower convex opening of the bearing seat (2-2).

4. the hover characteristic testing device of claim 1, wherein: the alternating current servo motors (2-8) are fixedly connected with the bottom ends of the flexible couplings (2-6) through first flat keys (2-7).

5. The hover characteristic testing device of claim 1, wherein: a baffle ring (2-4) is arranged between the two first angular contact ball bearings (2-3), the upper surface of the baffle ring (2-4) is in contact with the lower surface of the inner ring of the first angular contact ball bearing (2-3) positioned above, and the lower surface of the baffle ring (2-4) is in contact with the upper surface of the inner ring of the first angular contact ball bearing (2-3) positioned below.

6. The hover characteristic testing device of any of claims 1-5, wherein: the power module (2) further comprises a first shaft elastic retainer ring (2-5), the first shaft elastic retainer ring (2-5) is sleeved on the transmission shaft (1-1), and the upper surface of the first shaft elastic retainer ring (2-5) is in contact with the upper surface of the inner ring of the first angular contact ball bearing (2-3) below the first shaft elastic retainer ring.

7. the hover characteristic testing device of claim 1, wherein: the measuring module (3) further comprises a second shaft elastic check ring (3-6), the second shaft elastic check ring (3-6) is sleeved on the outer surface of the torque sensor mounting seat (3-4), and the lower surface of the second shaft elastic check ring (3-6) is in contact with the upper surface of the inner ring of the second angular contact ball bearing (3-5).

Technical Field

The invention relates to the aerospace field, in particular to a hovering characteristic testing device for testing a single-shaft rotor system of a Mars aircraft.

background

Mars are located adjacent to the Earth in the solar system and have a physical environment very similar to the Earth. A large number of researches show that a large amount of liquid water and other substances necessary for life exist in Mars, so that the Mars detection task can expand the living space of human beings and explore the origin of life, and the scientific research process of the human beings is greatly promoted. At present, the detection of mars is still in the detection stage of the mars rover. The Mars aircraft can fly at a certain height on the surface of the Mars to obtain images with higher resolution, and meanwhile, a far visual field is provided for the Mars vehicle so as to navigate the Mars vehicle. The safety of the Mars vehicle in a complex Mars terrain environment is guaranteed, and the Mars detection task has higher efficiency.

The existing single-shaft rotor craft suitable for the earth environment has the advantages of fixed-point take-off and landing, and aiming at the characteristic of fixed-point landing, the single-shaft rotor craft can carry out in-situ sampling on earth surface soil and then return to carry out soil sample analysis, if the function is applied to the sparks, the device has important practical value for detecting the sparks by human beings, the thin and cold atmosphere of mars causes the rotor (blade) surfaces in a rotary wing aircraft to be in a low reynolds number and high mach number regime, this puts higher demands on the aerodynamic performance of the rotor (blade), the rotor (blade) in the existing single-shaft rotor craft can not realize the flying and fixed-point landing in the Mars environment, the applicability is poor and the flying efficiency is extremely low, a further need exists for a testing apparatus to optimize a single-axis rotor deployment system that is best suited for Mars low reynolds number environments.

Disclosure of Invention

The technical problems to be solved by the invention are as follows: the rotor (blade) in the existing single-shaft rotor aircraft can not realize the flying and fixed-point landing of a spark environment, the applicability is poor and the flying efficiency is extremely low; and further provides a hovering characteristic testing device for testing a single-shaft rotor system of a mars aircraft.

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

The hovering characteristic testing device comprises a single-shaft rotor module 1, a power module 2 and a measuring module 3;

the single-shaft rotor module 1 comprises a transmission shaft 1-1, a carbon fiber blade clamp 1-2 and two blades 1-3, wherein the carbon fiber blade clamp 1-2 is fixedly arranged at the top end of the transmission shaft 1-1, and one blade 1-3 is fixedly arranged on each of two sides of the carbon fiber blade clamp 1-2;

The power module 2 comprises an upper bearing end cover 2-1, a bearing seat 2-2, two first angular contact ball bearings 2-3, a flexible coupling 2-6, an alternating current servo motor 2-8 and a servo motor support 2-9, the upper bearing end cover 2-1 is fixedly arranged at the upper port of the bearing seat 2-2, two first angular contact ball bearings 2-3 which are arranged up and down side by side are clamped in the bearing seats 2-2, two first angular contact ball bearings 2-3 are sleeved outside the transmission shaft 1-1, a driving shaft of an alternating current servo motor 2-8 is fixedly connected with the bottom end of the transmission shaft 1-1 through a flexible coupling 2-6, the alternating current servo motor 2-8 is fixedly arranged on a servo motor support 2-9, and the lower end of the bearing seat 2-2 is fixedly connected with the upper end of the servo motor support 2-9;

The measuring module 3 comprises a tension sensor lower mounting seat 3-2, a torque sensor 3-7, a torque sensor mounting seat 3-4, a second angular contact ball bearing 3-5, a lower bearing end cover 3-3, a second flat key 3-8 and three tension sensors 3-1, wherein the three tension sensors 3-1 are uniformly arranged between a servo motor support 2-9 and the tension sensor lower mounting seat 3-2 in the circumferential direction, the torque sensors 3-7 are arranged in the torque sensor mounting seat 3-4, the upper ends of the torque sensor mounting seats 3-4 extend into the lower port of the tension sensor lower mounting seat 3-2, the torque sensors 3-7 are fixedly connected with the tension sensor lower mounting seat 3-2 through the second flat key 3-8, and the second angular contact ball bearings 3-5 are sleeved on the outer surface of the torque sensor mounting seat 3-4, the lower bearing end cover 3-3 is fixedly arranged on the lower port of the lower mounting seat 3-2 of the tension sensor, and the second angular contact ball bearing 3-5 is clamped at the lower port of the lower mounting seat 3-2 of the tension sensor by the lower bearing end cover 3-3.

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

1. The device is placed in a vacuum state or is tested in an environment with a carbon dioxide (Mars simulation) working environment, the lift force or the thrust force of a single-shaft rotor wing in the rotating process is measured through a tension sensor, the torque generated by a single-shaft rotor wing system is measured through a torque sensor, an alternating current servo motor adopts a motor encoder to measure the rotating speed of the single-shaft rotor wing, and the aircraft needs to bear certain load in the process of flying the Mars aircraft on the surface of the Mars, so that the single-shaft rotor wing system needs to generate certain lift force and torque to meet the requirements of the aircraft in the flying process;

2. The device has scientific and reasonable structural design, wherein a power module of the single-shaft rotor wing is driven by an alternating current servo motor, a motor shaft transmits motion power to a rotor wing transmission shaft through a flexible coupling, the transmission shaft drives the blades to rotate through the blades, and the power module adopts the flexible coupling, so that the power of a single-shaft rotor wing system is directly transmitted, the efficiency loss and the mechanical vibration in the transmission process are reduced, and the rigidity of the hovering characteristic testing device of the single-shaft rotor wing measurement system is also improved;

3. According to the single-shaft rotor module, blades with different installation angles and geometric characteristics are installed by replacing different carbon fiber blade clamps, so that the rotor blades can be quickly replaced, and the hovering characteristic experiment of the blades with different parameters is facilitated.

Drawings

FIG. 1 is an isometric view of the present device;

FIG. 2 is a side view of the present device;

3 fig. 3 3 3 is 3 a 3 cross 3- 3 sectional 3 view 3 taken 3 at 3 a 3- 3 a 3 in 3 fig. 3 2 3. 3

Detailed Description

The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings: