CN108163228B - Whole-helicopter flexible suspension test device - Google Patents
Whole-helicopter flexible suspension test device Download PDFInfo
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- CN108163228B CN108163228B CN201711255853.XA CN201711255853A CN108163228B CN 108163228 B CN108163228 B CN 108163228B CN 201711255853 A CN201711255853 A CN 201711255853A CN 108163228 B CN108163228 B CN 108163228B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
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Abstract
The invention discloses a flexible suspension test device for a whole helicopter, and belongs to the technical field of whole-helicopter transfer function tests. The method comprises the following steps: the device comprises a test bench, a winch, a flexible assembly, a test piece, a hoisting installation assembly, a course adjusting hanging beam, a lateral adjusting hanging beam, a vibration exciter hanging rope, an electromagnetic vibration exciter and a loading assembly; one end of the winch is fixedly connected with the test bed, and the other end of the winch is connected with the hoisting installation assembly through the flexible assembly; the hoisting installation assembly is provided with an anti-twisting device which can prevent the test piece from rolling and twisting in the hoisting process; one end of the test piece is fixed on the hoisting installation component, and the other end of the test piece is connected with the electromagnetic vibration exciter; the electromagnetic vibration exciter is mounted on the test bed in a hanging mode, and vibration excitation tests are conducted on the test piece through the loading assembly. The invention can realize the simulation of the free state of the helicopter, realize different loading modes of the excitation source, and actually measure the transfer function from the center of the helicopter hub to each concerned position through the test of the transfer function of the whole helicopter.
Description
Technical Field
The invention belongs to the technical field of helicopter whole-machine transfer function testing, and particularly relates to a helicopter whole-machine flexible suspension testing device.
Background
In the stage from the model development of the helicopter to the design and sizing, three dynamic characteristic tests are required to be carried out on the whole helicopter to verify whether the structure and the whole layout of the helicopter are reasonable or not, wherein the transfer function test technology is the most complex technology. The flexible suspension of the whole machine is required to be realized, and in order to avoid conflict with a loading point, the suspension position needs to avoid the central position of a hub. Secondly, the safety, the test state condition and the like of the helicopter are ensured. At present, China has no test technology research which is specially used for a transfer function test and is related to a helicopter whole-machine flexible suspension test device, a few documents only stay in a mathematical simulation analysis stage, and no specific test implementation method exists.
Disclosure of Invention
The purpose of the invention is as follows: in order to solve the problems, the invention provides a flexible suspension test device for the whole helicopter, which can effectively simulate the free state of the helicopter, realize different loading modes and be used for completing a test for the transfer function of the whole helicopter.
The technical scheme of the invention is as follows: a flexible suspension test device for a full helicopter comprises: the device comprises a test bench, a winch, a flexible assembly, a test piece, a hoisting installation assembly, a course adjusting hanging beam, a lateral adjusting hanging beam, a vibration exciter hanging rope, an electromagnetic vibration exciter and a loading assembly;
one end of the winch is fixedly connected with the test bed, and the other end of the winch is connected with the hoisting installation assembly through a flexible assembly;
the anti-twisting devices are arranged at two ends of the hoisting installation assembly, so that the test piece can be prevented from rolling and twisting in the hoisting process;
one end of the test piece is fixed on the hoisting installation component, and the other end of the test piece is connected with the electromagnetic vibration exciter through the loading component;
the electromagnetic vibration exciter is mounted on the test bed in a hanging mode, and vibration excitation tests are conducted on the test piece through the loading assembly.
Preferably, the flexible assembly comprises: a keyhole hoisting ring and an elastic rope;
the elastic rope is wound into a circle, and two ends of the elastic rope are respectively connected with a keyhole hanging ring;
the keyhole hoisting ring close to one end of the winch is connected with a lower end hook of the winch;
the keyhole hoisting ring close to one end of the hoisting installation assembly is provided with a double-end fork lug and is connected with the hoisting installation assembly through the double-end fork lug.
Preferably, the hoisting installation component is provided with a hoisting installation beam, a wheel axle hoop and a hoisting lug;
the wheel shaft hoops are adjustably mounted on the lifting mounting beam, and anti-twisting devices are arranged at two ends of the lifting mounting beam;
the hoisting installation assembly is connected with the wheel shaft of the test piece through a wheel shaft hoop;
the lifting installation assembly is connected with the flexible assembly through a lifting hanging lug.
Preferably, the torsion preventing means includes: the anti-torsion limiting rod and the anti-rolling limiting rope;
the anti-torsion limiting rod is arranged on the side wall of the end head of the hoisting and mounting beam, so that the hoisting and mounting assembly is prevented from torsion in the hoisting process;
the two ends of the anti-rolling limiting rope are respectively sleeved at the two ends of the anti-twisting limiting rod and fixed on the ground, so that the lifting installation assembly is prevented from rolling in the lifting process.
Preferably, the loading assembly is provided with a loading mounting beam;
the electromagnetic vibration exciter is arranged on the course adjusting beam through a vibration exciter suspension rope, and the course adjusting beam is arranged on the test bench through a lateral adjusting hanging beam;
the loading end of the electromagnetic vibration exciter is connected to the loading mounting beam.
Preferably, the loading mounting beams are uniformly provided with insulating transition blocks;
and a vibration exciter mounting bolt is embedded in the insulating transition block and used for mounting the electromagnetic vibration exciter.
The technical scheme of the invention has the beneficial effects that: the invention can realize the simulation of the free state of the helicopter and realize different loading modes of the excitation source; the transfer function from the center of the helicopter hub to each concerned part can be actually measured through a helicopter whole-machine transfer function test, and test basis is provided for vibration analysis, vibration control and structural layout of the helicopter.
Drawings
FIG. 1 is a schematic structural component diagram of a preferred embodiment of the helicopter whole flexible suspension test device of the present invention;
FIG. 2 is a schematic structural view of the lifting mounting assembly of the embodiment of FIG. 1;
FIG. 3 is a schematic diagram of a loading assembly of the embodiment shown in FIG. 1;
the device comprises a test bench 1, a winch 2, a keyhole hoisting ring 3, an elastic rope 4, a test piece 5, an axle 6, a hoisting installation assembly 7, a double-ended fork lug 8, a course adjusting hanging beam 9, a lateral adjusting hanging beam 10, a vibration exciter hanging rope 11, an electromagnetic vibration exciter 12, a loading assembly 13, a hoisting installation beam 14, an axle hoop 15, a hoisting hanging lug 16, an anti-torsion limiting rod 17, an anti-rolling limiting rope 18, a vibration exciter installation bolt 19, an insulating transition block 20 and a loading installation beam 21.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
As shown in fig. 1, a helicopter whole machine flexible suspension test device includes: the device comprises a test bench 1, a winch 2, a flexible assembly, a test piece 5, a hoisting installation assembly 7, a course adjusting hanging beam 9, a lateral adjusting hanging beam 10, a vibration exciter suspension rope 11, an electromagnetic vibration exciter 12 and a loading assembly 13;
one end of the winch 2 is fixedly connected with the test bed 1, and the other end of the winch is connected with the hoisting installation component 7 through a flexible component;
the anti-twisting devices are arranged at two ends of the hoisting installation assembly 7, so that the test piece can be prevented from rolling and twisting in the hoisting process;
one end of the test piece is fixed on the hoisting installation component 7, and the other end of the test piece is connected with the electromagnetic vibration exciter 12 through a loading component 13;
the electromagnetic vibration exciter 12 is mounted on the test bed 1 in a hanging manner, and the test piece 5 is subjected to vibration excitation test through the loading assembly 13.
In this embodiment, the flexible assembly includes: the lock hole hoisting rings 3 and the elastic rope 4, the elastic rope 4 penetrates through the two lock hole hoisting rings 3 according to a certain length in a winding mode, and two rope ends at the tail end of the elastic rope 4 are fixedly clamped;
a keyhole hoisting ring 3 close to one end of the winch 2 is connected with a lower end hook of the winch;
another keyhole hoisting ring 3 on the elastic rope 4 is connected with a double-end fork ear 8, and the other side of the double-end fork ear 8 is connected with a hoisting hanging lug 16 on the hoisting installation component 7.
In this embodiment, as shown in fig. 2: the hoisting installation assembly is provided with a hoisting installation beam 14, an axle hoop 15 and a hoisting lug 16, the axle hoop 15 is adjustably installed on the hoisting installation beam 14, and anti-twisting devices are arranged at two end heads of the hoisting installation beam 14; the hoisting installation component 7 is connected with the wheel shaft of the test piece 5 through a wheel shaft hoop 15; the lifting installation assembly 7 is connected with the flexible assembly through a lifting lug 16.
In this embodiment, the anti-twist device includes: the anti-torsion limiting rod 17 is arranged on the side wall of the end head of the lifting installation beam 14, so that the lifting installation component 7 is prevented from torsion in the lifting process; two ends of the anti-rolling limiting rope 18 are respectively sleeved at two ends of the anti-twisting limiting rod 17 and fixed on the ground, so that the hoisting and mounting assembly 7 is prevented from rolling in the hoisting process.
In this embodiment, as shown in fig. 3: the loading assembly 13 is provided with a loading mounting beam 21, the electromagnetic vibration exciter 12 is mounted on the course adjusting beam 9 through a vibration exciter suspension rope 11, the course adjusting beam 9 is mounted on the test bench 1 through a lateral adjusting suspension beam 10, and the loading end of the electromagnetic vibration exciter 12 is connected to the loading mounting beam.
It can be understood that the loading mounting beams 21 are uniformly provided with insulating transition blocks 20, and vibration exciter mounting bolts 19 are embedded in the insulating transition blocks 20 and used for mounting the electromagnetic vibration exciter 12.
The specific assembly process is as follows:
1. building a test bench 1, and fixedly installing four winches 2 at preset positions of the test bench 1;
2. installing a course adjusting hanging beam 9 and a lateral adjusting hanging beam 10, selecting hanging points according to a loading mode, and installing an electromagnetic vibration exciter 12 on the course adjusting hanging beam 9 through a vibration exciter hanging rope 11.
3. And assembling a vibration exciter mounting bolt 19, an insulating transition block 20 and a loading mounting beam 21 on the loading assembly 13 together, and mounting the vibration exciter mounting bolt, the insulating transition block and the loading mounting beam 21 at the center of the hub of the helicopter test piece 5 through a mounting interface on the loading mounting beam 21.
4. The helicopter test piece 5 is put in place, the airplane wheels are dismantled, and after the hoisting mounting beam 14, the axle hoop 15, the hoisting hanging lug 16, the anti-torsion limiting rod 17 and the anti-rolling limiting rope 18 on the hoisting mounting assembly 7 are assembled, the helicopter test piece is connected with the axle 6 through the axle hoop 15.
5. And selecting the length according to the calculation result, penetrating the elastic rope 4 through the two keyhole hoisting rings 3 for winding, and fixing the two tail ends of the elastic rope 4 by using a rope clamp after the completion.
6. One keyhole hoisting ring 3 on the elastic rope 4 is hung on a hook of the hoist 2, the other is hung on a double-end fork ear 8, and the other end of the double-end fork ear 8 is connected with a hoisting hanging ear 16.
7. After the suspension device is completed, the four windlasses 2 are simultaneously started, the helicopter test piece 5 is hung to a preset height in a trial mode, then the other end of the anti-rolling limiting rope 14 is fixed with the ground, the position of the electromagnetic vibration exciter 12 is adjusted by adjusting the course hanging beam 9 and the lateral adjusting hanging beam 10 to enable the electromagnetic vibration exciter to be aligned to a loading point, and then the loading end of the vibration exciter is fixedly connected with a vibration exciter mounting bolt 19.
8. After all the tests are ready, the formal test is started, and the electromagnetic vibration exciter 12 is started until all the tests are completed.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (5)
1. The utility model provides a flexible test device that suspends of full machine of helicopter which characterized in that: the method comprises the following steps: the device comprises a test bench (1), a winch (2), a flexible assembly, a test piece (5), a hoisting installation assembly (7), a course adjusting hanging beam (9), a lateral adjusting hanging beam (10), a vibration exciter suspension rope (11), an electromagnetic vibration exciter (12) and a loading assembly (13);
one end of the winch (2) is fixedly connected with the test bench (1), and the other end of the winch is connected with the hoisting installation component through a flexible component;
the anti-twisting devices are arranged at two ends of the hoisting installation assembly, so that the test piece can be prevented from rolling and twisting in the hoisting process;
one end of the test piece is fixed on the hoisting installation component (7), and the other end of the test piece is connected with the electromagnetic vibration exciter (12) through a loading component (13);
the electromagnetic vibration exciter (12) is mounted on the test bench (1) in a hanging manner, and a loading assembly (13) is used for carrying out vibration excitation test on the test piece (5); the hoisting installation component is provided with a hoisting installation beam (14), a wheel axle hoop (15) and a hoisting hanging lug (16);
the wheel axle hoop (15) is adjustably mounted on the hoisting mounting beam (14), and anti-twisting devices are arranged at two ends of the hoisting mounting beam (14);
the hoisting installation assembly is connected with the wheel shaft of the test piece (5) through a wheel shaft hoop (15);
the hoisting mounting beam (14) is connected with the flexible assembly through a hoisting lug (16).
2. The helicopter whole flexible suspension test device of claim 1, characterized in that: the flexible assembly includes: a keyhole hoisting ring (3) and an elastic rope (4);
the elastic rope (4) is wound into a circle, and two ends of the elastic rope are respectively connected with a keyhole hanging ring (3);
a keyhole hoisting ring (3) close to one end of the winch is connected with a lower end hook of the winch;
the keyhole hoisting ring (3) close to one end of the hoisting installation component is provided with a double-end fork lug (8) and is connected with the hoisting installation component through the double-end fork lug (8).
3. The helicopter whole flexible suspension test device of claim 1, characterized in that: the anti-twist device includes: a torsion-proof limiting rod (17) and a rolling-proof limiting rope (18);
the anti-torsion limiting rod (17) is arranged on the side wall of the end head of the lifting mounting beam (14) to prevent the lifting mounting assembly (7) from torsion in the lifting process;
two ends of the anti-rolling limiting rope (18) are respectively sleeved at two ends of the anti-twisting limiting rod (17) and fixed on the ground, so that the lifting installation assembly (7) is prevented from rolling in the lifting process.
4. The helicopter whole flexible suspension test device of claim 1, characterized in that:
the loading assembly (13) is provided with a loading mounting beam (21);
the electromagnetic vibration exciter (12) is installed on the course adjusting hanging beam (9) through a vibration exciter suspension rope (11), and the course adjusting hanging beam (9) is installed on the test bench (1) through a lateral adjusting hanging beam (10);
the loading end of the electromagnetic vibration exciter (12) is connected to the loading mounting beam.
5. The helicopter whole flexible suspension test device of claim 4, characterized in that: the loading mounting beams (21) are uniformly provided with insulating transition blocks (20);
and a vibration exciter mounting bolt (19) is embedded in the insulating transition block (20) and used for mounting the electromagnetic vibration exciter (12).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711255853.XA CN108163228B (en) | 2017-12-03 | 2017-12-03 | Whole-helicopter flexible suspension test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711255853.XA CN108163228B (en) | 2017-12-03 | 2017-12-03 | Whole-helicopter flexible suspension test device |
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| CN108163228A CN108163228A (en) | 2018-06-15 |
| CN108163228B true CN108163228B (en) | 2021-03-23 |
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| CN109230990A (en) * | 2018-11-12 | 2019-01-18 | 中国直升机设计研究所 | A kind of aircraft suspension apparatus and its suspension system |
| CN110654568B (en) * | 2019-09-29 | 2022-09-06 | 中国直升机设计研究所 | Hub couple loading device |
| CN111644992B (en) * | 2020-04-23 | 2021-12-07 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Clamp for aviation equipment sample in hanging flight test |
| CN114115190B (en) * | 2021-11-19 | 2024-04-02 | 中国直升机设计研究所 | Simulation test bed for complex vibration environment of helicopter |
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