CN216887271U

CN216887271U - Unmanned helicopter rotor mode test fixture

Info

Publication number: CN216887271U
Application number: CN202220330760.9U
Authority: CN
Inventors: 邵松; 刘士明; 应旭成
Original assignee: No 60 Institute of Headquarters of General Staff of PLA
Current assignee: No 60 Institute of Headquarters of General Staff of PLA
Priority date: 2022-02-18
Filing date: 2022-02-18
Publication date: 2022-07-05
Anticipated expiration: 2032-02-18

Abstract

The utility model discloses a rotor wing modal test tool of an unmanned helicopter, and belongs to the field of unmanned aerial vehicle design and manufacture. The device comprises a rotor wing installation shaft, a blade installation seat fixing disc and a blade installation seat connecting rod; the rotor installation shaft is provided with a plurality of connecting holes for fixing a rotor hub along the circumferential direction; the blade mounting seat fixing disc is connected with the top of the rotor wing mounting shaft; a plurality of strip-shaped through grooves are uniformly arranged on the paddle mounting seat fixing disc at intervals along the circumferential direction, and the through grooves are distributed along the radial direction of the paddle mounting seat fixing disc; one end of the connecting rod of the paddle mounting seat can penetrate through the through groove and is fixed, and the other end of the connecting rod of the paddle mounting seat is of a circular ring structure. Through the cooperation between rotor installation axle, paddle mount pad connecting rod and the fixed disc three of paddle mount pad, can adjust unmanned helicopter rotor system's degree of freedom according to real-time test needs, realize the multi freedom restraint to unmanned helicopter rotor system to guarantee the degree of accuracy to unmanned helicopter rotor static mode measurement.

Description

Unmanned helicopter rotor mode test fixture

Technical Field

The utility model relates to a rotor wing modal test tool, in particular to a rotor wing modal test tool of an unmanned helicopter, and belongs to the field of unmanned aerial vehicle design and manufacture.

Background

The helicopter has the advantages of vertical take-off and landing, fixed-point hovering and the like. With the development of science and technology, unmanned helicopters are greatly popularized and applied in the military field in recent years. Compared with a fixed-wing unmanned aerial vehicle, the unmanned helicopter has the advantage of vertical take-off and landing in the aspect of shipboard, so that the unmanned helicopter has a great application prospect.

The rotor system is an important component of the structure of the unmanned helicopter, and the rotor system provides lift force for the unmanned helicopter and is also a main source of vibration load of the unmanned helicopter. In order to avoid the resonance problem of the rotor wing in the using process and ensure that the dynamic characteristic of the rotor wing meets the design requirement, the mode test is carried out on the rotor wing in the production process of the unmanned helicopter. However, because the independent rotor has a plurality of degrees of freedom, the rotational degree of freedom and the variable pitch degree of freedom of each blade mounting seat need to be fixed in the test process, no corresponding tool equipment in the prior art can meet the test requirements, and the accurate test of the rotor mode of the unmanned helicopter is directly restricted.

SUMMERY OF THE UTILITY MODEL

The utility model aims to overcome the defects of the prior art and provide a test tool and a test method which can restrain the multiple degrees of freedom of a rotor system of an unmanned helicopter and facilitate accurate measurement of the static mode of the rotor of the unmanned helicopter.

In order to solve the technical problem, the utility model provides a rotor mode testing tool of an unmanned helicopter, which comprises a rotor installation shaft, a blade installation seat fixing disc and a blade installation seat connecting rod;

the rotor installation shaft is circumferentially provided with a plurality of connecting holes for fixing a rotor hub;

the fixed disc of the blade mounting seat is connected with the top of the rotor wing mounting shaft;

a plurality of strip-shaped through grooves are uniformly arranged on the paddle mounting seat fixing disc at intervals along the circumferential direction, and the through grooves are distributed along the radial direction of the paddle mounting seat fixing disc;

one end of the connecting rod of the blade mounting seat penetrates through the through groove and is fixed, and the other end of the connecting rod of the blade mounting seat is of a circular ring structure.

According to the utility model, the top of the rotor wing installation shaft is provided with a connection hole, the center of the fixed disc of the blade installation seat is provided with a through hole, and the connection hole and the through hole are fixedly connected through the disc fixed hanging ring.

In the utility model, a rod end bearing is arranged in a circular ring of the connecting rod of the paddle mounting seat.

In the utility model, the bottom of the rotor wing installation shaft is connected with the base.

The utility model has the beneficial effects that: (1) the matching among the rotor wing installation shaft, the blade installation seat connecting rod and the blade installation seat fixing disc can adjust the degree of freedom of the unmanned helicopter rotor wing system according to the real-time test requirement, and realize the multi-degree-of-freedom constraint on the unmanned helicopter rotor wing system, thereby ensuring the accuracy of the static modal measurement of the unmanned helicopter rotor wing; (2) the whole tool is simple in structure, convenient to implement, low in manufacturing cost and high in reliability; (3) the blade mounting base is connected with the rod end bearing in the circular ring, so that the adjustment of the degree of freedom of the rotor system can be facilitated; (4) the lifting of the disc fixing lifting ring in the test process is convenient, the whole system is detachably connected, and the adaptability to the test site is good.

Drawings

FIG. 1 is a schematic structural view of a rotor mode testing tool of an unmanned helicopter according to the present invention;

FIG. 2 is a schematic illustration of a steel base;

figure 3 is a schematic view of a rotor mounting shaft;

FIG. 4 is a schematic view of a blade mounting fixture disk;

FIG. 5 is a schematic view of a blade mount link;

fig. 6 is a schematic view of a test installation.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

As shown in fig. 1, the unmanned helicopter rotor mode testing tool of the embodiment includes a base 1, a rotor installation shaft 2, a blade installation seat fixing disc 3, a disc fixing lifting ring 4 and a blade installation seat connecting rod 5. Wherein, the bottom and the base 1 of rotor installation axle 2 are connected fixedly, and the top of rotor installation axle 2 is passed through the fixed rings of disc 4 and is connected fixedly with paddle mount pad fixed disk 3. A plurality of paddle mount connecting rods 5 are mounted on the paddle mount fixed disk 3.

One end of the disc fixing lifting ring 4 is of a threaded rod structure, and the other end of the disc fixing lifting ring is of a circular ring structure, so that the tool can be conveniently adjusted and installed in the using process.

As shown in fig. 2, the base 1 is made of steel, and four through holes 11 are formed at four corners of the base 1 to fix the base 1 to other connectors. The middle of the base 1 is provided with four through holes 11 for connecting and fixing the base 1 and the rotor wing installation shaft 2; the number of through holes 11 can be increased or decreased as necessary, but the reliability of the connection between the base 1 and the rotor mounting shaft 2 should be ensured.

As shown in fig. 3, the rotor mounting shaft 2 is cylindrical, and has screw holes 21 at the bottom corresponding to the positions and the number of the through holes 11 in the middle of the base 1, and screw holes 21 at the top connected to the blade mounting base fixing disk 3 for screwing the disk fixing ring 4. The cylindrical surface of the rotor mounting shaft 2 is provided with a plurality of threaded connection holes 21, wherein the threaded connection holes 21 correspond to the rotor hub mounting holes in position and have the same size as the rotor hub mounting holes for fixing the rotor hub.

In this embodiment, 6 threaded holes are designed on the cylindrical surface of the rotor mounting shaft 2, and are arranged up and down at an interval of 120 °.

As shown in fig. 4, the blade mount fixing disk 3 is provided with a through hole 11 at the center of the disk, the size of the through hole is the same as the thread size of the disk fixing ring 4, and the blade mount fixing disk can be fixed on the rotor wing mounting shaft 2 through the disk fixing ring 4. Four rectangular through grooves 31 are formed in the blade mounting seat fixing disc 3 at intervals along the circumferential direction, and the interval between every two adjacent rectangular through grooves 31 is 90 degrees. The rectangular through grooves 31 are distributed outwards from the center of the blade mounting seat fixing disc 3. The dimensions of the rectangular through-groove 31 can be selected accordingly according to the actual requirements. The rectangular through groove 31 is used for connecting the disc fixing hanging ring 4 and adjusting and fixing the length of the disc fixing hanging ring 4.

In another embodiment, the three positions of the rectangular through slots 31 of the blade mount fixing disk 3 are arranged at an average interval of 120 °. The number of through rectangular slots 31 depends on the number of blades in the rotor system to be tested.

As shown in fig. 5, one end of the connecting rod 5 of the blade mounting seat is of a threaded structure, is connected to the fixed disc 3 of the blade mounting seat through a nut, and can adjust the connecting length through the nut; the other end of the blade is of a circular ring structure, a rod end bearing 51 is installed in the circular ring, and the rod end bearing 51 is connected with the blade installation base.

The specific assembly mode of the unmanned helicopter rotor mode test tool in the embodiment is as follows:

the bolt is threaded into the threaded connecting hole 21 on the lower surface of the rotor wing mounting shaft 2 through the through hole 11 in the middle of the base 1 until the bolt is screwed tightly;

sleeving a rotor wing hub on a rotor wing mounting shaft 2, and screwing a rotor wing mounting bolt into a threaded connection hole 21 on the cylindrical surface of the rotor wing mounting shaft 2 through a rotor wing hub mounting hole and screwing the rotor wing mounting bolt;

placing the blade mounting seat fixing disc 3 on the top of the rotor wing mounting shaft 2, screwing the disc fixing flying ring 4 into the threaded connecting hole 21 through the through hole 11 in the blade mounting seat fixing disc 3 and screwing the disc fixing flying ring tightly, and fixing the blade mounting seat fixing disc 3 and the rotor wing mounting shaft 2;

one end of the connecting rod 5 of the blade mounting seat is fixed on the fixed disc 3 of the blade mounting seat through a nut, and the bearing 51 at the end of the other end rod is fixed with the blade mounting seat through a bolt and a nut.

After the above-described mounting, the entire base 1 is fixed to the test platform through the through holes 11 at the four corners by using bolts and nuts, and the paddle is mounted as shown in fig. 6.

After the tool is assembled, the test is carried out according to the following steps:

(1) the rotary freedom degree of the fixed rotor wing and the variable pitch freedom degree of the blade mounting seat are adjusted according to measurement requirements, the connecting rod 5 of the blade mounting seat is adjusted to be connected with the length adjusting blade mounting angle, and the blade is mounted after adjustment is finished.

(2) A measuring point and a plurality of excitation points for rotor modal measurement are determined on the blade, the measuring point is generally positioned at 0.8R of the radius of the blade, and the excitation points are sequentially distributed at the front edge and the rear edge of each support arm of the rotor along the radius direction.

(3) The acceleration sensor is placed at a measuring point position, a force hammer is used for respectively exciting the excitation points in sequence along the blade flapping and shimmy directions, and each direction of each excitation point is excited for three times. The acceleration sensor and the force hammer are both connected with the existing multichannel data acquisition system.

(4) The multichannel data acquisition system acquires an excitation signal of the force hammer and a response signal measured by the acceleration sensor.

(5) The multichannel data acquisition system carries out average calculation and modal analysis on the acquired excitation signals and response signals through modal parameter identification software, and finally gives the natural frequency and the vibration mode of the shimmy, the flap and the torsion modes of the rotor.

The utility model provides a thought of a tool for testing a rotor mode of an unmanned helicopter, and a plurality of methods and ways for implementing the technical scheme are provided, the above description is only a preferred embodiment of the utility model, and it should be noted that, for a person skilled in the art, a plurality of improvements and decorations can be made without departing from the principle of the utility model, and the improvements and decorations should also be regarded as the protection scope of the utility model. All the components not specified in the present embodiment can be realized by the prior art.

Claims

1. The utility model provides an unmanned helicopter rotor mode test fixture which characterized in that: the device comprises a rotor wing installation shaft, a blade installation seat fixing disc and a blade installation seat connecting rod;

the rotor wing mounting shaft is circumferentially provided with a plurality of connecting holes for fixing a rotor wing hub;

the blade mounting seat fixing disc is connected with the top of the rotor wing mounting shaft;

one end of the connecting rod of the blade mounting seat can penetrate through the through groove and is fixed, and the other end of the connecting rod of the blade mounting seat is of a circular ring structure.

2. The unmanned helicopter rotor mode test frock of claim 1 characterized in that: the top of rotor installation axle is equipped with a connecting hole, the center of the fixed disc of paddle mount pad is equipped with a perforating hole, it is fixed to connect through the fixed rings of disc between connecting hole and the perforating hole.

3. The unmanned helicopter rotor mode test frock of claim 1 or 2, its characterized in that: and a rod end bearing is arranged in the circular ring of the connecting rod of the paddle mounting seat.

4. The unmanned helicopter rotor mode test frock of claim 3 characterized in that: the base is connected to the bottom of rotor installation axle.