阅读说明：本技术 四自由度的飞行器调参平台及其工作方法 (Four-degree-of-freedom aircraft parameter adjusting platform and working method thereof ) 是由 刘佳 朱清华 张广林 王昊 吴远航 于 2020-06-05 设计创作，主要内容包括：本发明提供了一种四自由度的飞行器调参平台及其工作方法,该平台包括模块化设计的主框架、球铰转动轴、中央板,中央球铰柱和安装底板,所述的中央板四周设置有若干第二球铰外壳,中央球铰柱固定在中央板上,中央球铰柱顶端与安装顶板连接；所述的主框架包括若干支架,所述的球铰转动轴包括若干杆轴,每个杆轴两端分别与主框架的支架以及中央板连接。本发明具有多个自由度,可以更真实地模拟飞行器偏航-俯仰-横滚的姿态,进而可以对多种旋翼式飞行器进行实验性调参和飞行,并且结构简洁,可快速拆装,使用简单,适合飞行器的初步调参,应用前景广阔。(The invention provides a four-degree-of-freedom aircraft parameter adjusting platform and a working method thereof, wherein the platform comprises a main frame, a spherical hinge rotating shaft, a central plate, a central spherical hinge column and an installation bottom plate which are in modular design, wherein a plurality of second spherical hinge shells are arranged around the central plate, the central spherical hinge column is fixed on the central plate, and the top end of the central spherical hinge column is connected with an installation top plate; the main frame comprises a plurality of supports, the spherical hinge rotating shaft comprises a plurality of rod shafts, and two ends of each rod shaft are respectively connected with the supports of the main frame and the central plate. The invention has a plurality of degrees of freedom, can simulate the yaw-pitch-roll postures of the aircraft more truly, further can carry out experimental parameter adjustment and flight on various rotor type aircrafts, has simple structure, can be quickly disassembled and assembled, is simple to use, is suitable for the initial parameter adjustment of the aircraft, and has wide application prospect.)

1. The utility model provides a four degree of freedom's aircraft parameter adjusting platform which characterized in that: the device comprises a main frame, a spherical hinge rotating shaft, a central plate, a central spherical hinge column and an installation bottom plate, wherein the main frame is in modular design, a plurality of second spherical hinge shells are arranged around the central plate, the central spherical hinge column is fixed on the central plate, and a second spherical hinge universal joint is arranged at the top end of the central spherical hinge column; the mounting bottom plate comprises an aircraft mounting plate and a third spherical hinge shell, and the third spherical hinge shell is connected with the second spherical hinge universal joint in a matched manner; the main frame comprises a plurality of brackets, and each bracket is provided with a first spherical hinge shell; the spherical hinge rotating shaft comprises a plurality of shaft shafts, a first spherical hinge universal joint is respectively arranged at two ends of each shaft, and the shaft shafts are respectively connected with the first spherical hinge shell and the second spherical hinge shell in a matched mode through the first spherical hinge universal joints.

2. The four degree-of-freedom aircraft parameter adjustment platform according to claim 1, characterized in that: the aircraft mounting plate has different types of threaded holes.

3. The four degree-of-freedom aircraft parameter adjustment platform according to claim 1, characterized in that: the main frame comprises a frame bottom plate and four supports arranged on the periphery of the frame bottom plate, and the four supports are fixedly connected with the frame bottom plate through bolts for the quick-mounting plate.

4. A working method of a four-degree-of-freedom aircraft parameter adjusting platform is characterized by comprising the following working processes:

1) the aircraft is fixedly arranged on the installation bottom plate through bolts, and the central plate descends under the action of gravity to reach the lowest position;

2) when the lifting characteristic of the aircraft is tested by adjusting parameters, the aircraft increases the lifting force, and when the lifting force is greater than the gravity, the aircraft, the central plate and the central spherical hinge column can vertically lift along the y axis under the action of force; the aircraft reduces the lift force, and when the gravity is greater than the lift force, the aircraft, the central plate and the central spherical hinge column can vertically descend along the y axis under the action of force;

3) when the parameter is adjusted and the yaw characteristic of the aircraft is tested, the aircraft yaws rightwards, the mounting base plate is hinged with the central spherical hinge column, the aircraft rotates rightwards around the y axis, and the right yaw characteristic is displayed; the aircraft yaws leftwards, the mounting baseplate is hinged with the central spherical hinge column, the aircraft can rotate leftwards around the y axis, and the left yaw characteristic is shown;

4) when the parameter is adjusted and the rolling characteristic of the aircraft is tested, the aircraft rolls to the right, the mounting base plate is hinged with the central spherical hinge column, and the aircraft rotates anticlockwise around the z axis of the spherical hinge; the aircraft rolls transversely leftwards, the mounting base plate is hinged with the central spherical hinge column, and the aircraft rotates clockwise around the z axis of the spherical hinge; in addition, the pitching motion of the aircraft is similar to the pitching motion, and when the aircraft pitches forwards, the aircraft moves clockwise around the x axis of the spherical hinge; when the aircraft pitches backwards, the aircraft will make a counter-clockwise motion around the x-axis of the spherical hinge.

Technical Field

The invention relates to the technical field of aviation equipment, in particular to a four-degree-of-freedom aircraft parameter adjusting platform and a working method thereof.

Background

Various types of aircraft have become popular in recent years and are widely enjoyed by children and young men and women. Especially, the rotor aircraft is not only applied in the field of photography and videography, but also widely applied in the aspects of propaganda, performance and entertainment and the like due to the stable hovering and flying performance in the air. However, an aircraft as a complex mechanical device has a certain risk, and in order to improve the safety of the aircraft, the aircraft should be subjected to parameter adjustment and experimental flight to verify whether the flight state of the aircraft meets the expectation. The process is of great help to both the model airplane enthusiast and the scientific researchers.

Most of test equipment on the market at present is bulky, and it is inconvenient to carry, and is expensive, and the specialty is too strong, tests the equipment of a great variety. The method is suitable for the depth test of the aircraft, and is not suitable for the preliminary test and parameter adjustment of model airplane enthusiasts and scientific research experimenters.

Disclosure of Invention

The invention provides a simple detachable four-degree-of-freedom aircraft parameter adjusting platform and a working method thereof for solving the problems in the prior art, and after the aircraft is installed, the postures of the aircraft such as lifting, pitching, yawing and rolling and the effect of the aircraft flying in the air can be simulated. The test platform can enable model airplane enthusiasts and scientific research experimenters to carry out experimental flight and debugging of aircraft parameters on the test platform, so that the aircraft can obtain higher safety and better flight performance in the actual flight process, and the application prospect is wide.

The invention provides a four-degree-of-freedom aircraft parameter adjusting platform which comprises a main frame, a spherical hinge rotating shaft, a central plate, a central spherical hinge column and an installation bottom plate, wherein the main frame is in modular design; the mounting bottom plate comprises an aircraft mounting plate and a third spherical hinge shell, and the third spherical hinge shell is connected with the second spherical hinge universal joint in a matched manner; the main frame comprises a plurality of brackets, and each bracket is provided with a first spherical hinge shell; the spherical hinge rotating shaft comprises a plurality of shaft shafts, a first spherical hinge universal joint is respectively arranged at two ends of each shaft, and the shaft shafts are respectively connected with the first spherical hinge shell and the second spherical hinge shell in a matched mode through the first spherical hinge universal joints.

In a further improvement, the aircraft mounting plate is provided with threaded holes of different types, so that different aircrafts can be conveniently mounted. The test aircraft is a multi-rotor aircraft, a helicopter or a fixed wing type.

The improved structure comprises a main frame, a quick-mounting plate, a support, a bolt.

In a further development, the ball joint can be another type of joint.

Further improvement, the material of the test platform device can be any material under the condition of meeting the strength requirement.

In a further improvement, the quick-mounting plate of the main frame can be a quick-mounting structure in any form.

Further improved, the installation mode of the installation bottom plate and the aircraft can be bolt connection, or can be fixed in a clamping mode, or other effective fixed connection modes.

The further improvement, the main frame bottom plate can be a whole flat plate or a frame structure on the premise of ensuring the structural strength, or other types of structures convenient to disassemble and assemble.

The invention also provides a working method of the four-degree-of-freedom aircraft parameter adjusting platform, which comprises the following working processes:

1) the aircraft is fixedly arranged on the installation bottom plate through bolts, and the central plate descends under the action of gravity to reach the lowest position;

2) when the lifting characteristic of the aircraft is tested by adjusting parameters, the aircraft increases the lifting force, and when the lifting force is greater than the gravity, the aircraft, the central plate and the central spherical hinge column can vertically lift along the y axis under the action of force; the aircraft reduces the lift force, and when the gravity is greater than the lift force, the aircraft, the central plate and the central spherical hinge column can vertically descend along the y axis under the action of force;

3) when the parameter is adjusted and the yaw characteristic of the aircraft is tested, the aircraft yaws rightwards, the mounting base plate is hinged with the central spherical hinge column, the aircraft rotates rightwards around the y axis, and the right yaw characteristic is displayed; the aircraft yaws leftwards, the mounting baseplate is hinged with the central spherical hinge column, the aircraft can rotate leftwards around the y axis, and the left yaw characteristic is shown;

4) when the parameter is adjusted and the rolling characteristic of the aircraft is tested, the aircraft rolls to the right, the mounting base plate is hinged with the central spherical hinge column, and the aircraft rotates anticlockwise around the z axis of the spherical hinge; the aircraft rolls transversely leftwards, the mounting base plate is hinged with the central spherical hinge column, and the aircraft rotates clockwise around the z axis of the spherical hinge; in addition, the pitching motion of the aircraft is similar to the pitching motion, and when the aircraft pitches forwards, the aircraft moves clockwise around the x axis of the spherical hinge; when the aircraft pitches backwards, the aircraft will make a counter-clockwise motion around the x-axis of the spherical hinge.

The invention has the beneficial effects that:

1. the multi-degree-of-freedom simulation system has multiple degrees of freedom, can simulate the yaw-pitch-roll postures of the aircraft more truly, and further can perform experimental parameter adjustment and flight on various rotor type aircrafts.

2. The aircraft parameter adjusting device is simple in structure, can be quickly disassembled and assembled, is simple to use, is suitable for preliminary parameter adjustment of an aircraft, and has a wide application prospect.

Drawings

Fig. 1 is an overall structural view of the present invention.

Fig. 2 is a diagram of the experimental configuration of the present invention after installation on an aircraft.

FIG. 3 is a structural diagram of a main frame quick-mounting board of the present invention.

FIG. 4 is a schematic view showing the assembly and disassembly of the center plate according to the present invention.

Detailed Description

The invention will be further explained with reference to the drawings.

The structure of the invention is shown in fig. 1 to 4, and comprises a main frame 1, a spherical hinge rotating shaft 2, a central plate 3, a central spherical hinge column 4 and a mounting bottom plate 5 which are in modular design, wherein a plurality of second spherical hinge shells 13 are arranged around the central plate 3, the central spherical hinge column 4 is fixed on the central plate 3, and a second spherical hinge universal joint 15 is arranged at the top end of the central spherical hinge column 4; the mounting base plate 5 comprises an aircraft mounting plate 16 and a third spherical hinge shell 17, and the third spherical hinge shell 17 is connected with the second spherical hinge universal joint 15 in a matching way; the main frame 1 comprises a plurality of brackets 8, and each bracket is provided with a first spherical hinge shell 9; the spherical hinge rotating shaft 2 comprises a plurality of shaft shafts 11, two ends of each shaft 11 are respectively provided with a first spherical hinge universal joint 12, and the shaft shafts 11 are respectively connected with a first spherical hinge shell 9 and a second spherical hinge shell 13 in a matching way through the first spherical hinge universal joints 12.

The aircraft mounting plate is primarily used for mounting the test aircraft 10 and for bearing aircraft loads. The aircraft mounting panel has the screw hole of different grade type, supplies different aircraft easy to assemble.

The main frame 1 comprises a frame bottom plate 6 and four supports 8 arranged on the periphery of the frame bottom plate 6, wherein the four supports 8 are fixedly connected with the frame bottom plate 6 through fast-assembling plates 7 by bolts 14, as shown in fig. 3.

The take-off of various aircrafts is realized because the rotation of the motor drives the propeller to rotate and generate upward lift force, and when the lift force is greater than the dead weight of the aircrafts, the aircrafts can take off. After taking off, the aircraft can fly back and forth, left and right, by controlling the different rotating speeds of the propellers or by changing the angle of the tilter to generate lateral force.

The working method of the four-degree-of-freedom aircraft parameter adjusting platform comprises the following working processes:

1) the aircraft is fixedly installed on the installation base plate through the bolts, as shown in fig. 2, the testing platform is the highest position, and when the aircraft is fixedly installed on the installation base plate through the bolts (as shown in the figure, the aircraft nose faces to the negative direction of the z axis, the central plate will descend under the action of gravity to reach the lowest position.

2) When the lifting characteristic of the aircraft is tested by adjusting parameters, the aircraft increases the lifting force, and when the lifting force is greater than the gravity, the aircraft, the central plate and the central spherical hinge column can vertically lift along the y axis under the action of force; the aircraft reduces the lift force, and when the gravity is greater than the lift force, the aircraft, the central plate and the central spherical hinge column can vertically descend along the y axis under the action of force;

3) when the parameter is adjusted and the yaw characteristic of the aircraft is tested, the aircraft yaws rightwards, the mounting base plate is hinged with the central spherical hinge column, the aircraft rotates rightwards around the y axis, and the right yaw characteristic is displayed; the aircraft yaws leftwards, the mounting baseplate is hinged with the central spherical hinge column, the aircraft can rotate leftwards around the y axis, and the left yaw characteristic is shown;

4) when the parameter is adjusted and the rolling characteristic of the aircraft is tested, the aircraft rolls to the right, the mounting base plate is hinged with the central spherical hinge column, and the aircraft rotates anticlockwise around the z axis of the spherical hinge; the aircraft rolls transversely leftwards, the mounting base plate is hinged with the central spherical hinge column, and the aircraft rotates clockwise around the z axis of the spherical hinge; in addition, the pitching motion of the aircraft is similar to the pitching motion, and when the aircraft pitches forwards, the aircraft moves clockwise around the x axis of the spherical hinge; when the aircraft pitches backwards, the aircraft will make a counter-clockwise motion around the x-axis of the spherical hinge.

Because the central plate is hinged with the spherical hinge rotating shaft, when the aircraft does pitching and rolling motions, the central plate also has corresponding rotating motion, and the change of the attitude of the aircraft in the air can be further simulated. In addition, the spherical hinge also has a limiting effect, so that the aircraft posture can be simulated to a certain extent, the aircraft can be prevented from being overturned due to overlarge posture during parameter adjustment testing, and the safety is ensured.

The test platform is in a modular design and has portability. When the test platform is not used, the quick-assembly plate can be detached, then the main frame is detached, and the central plate and other parts are provided with the spherical hinge structures, so that the test platform is convenient to fold. Thereby guaranteed test platform's quick detach easy dismounting, otherwise also fast-assembling easy dismounting.

While the invention has been described in terms of its preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.