CN114486138A - Airplane vibration comfort test device and method in full-airplane state - Google Patents
Airplane vibration comfort test device and method in full-airplane state Download PDFInfo
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- CN114486138A CN114486138A CN202111658625.3A CN202111658625A CN114486138A CN 114486138 A CN114486138 A CN 114486138A CN 202111658625 A CN202111658625 A CN 202111658625A CN 114486138 A CN114486138 A CN 114486138A
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- 238000012360 testing method Methods 0.000 title claims abstract description 76
- 238000000034 method Methods 0.000 title description 8
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- 230000005284 excitation Effects 0.000 abstract description 25
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/06—Multidirectional test stands
Abstract
The application belongs to the technical field of airplane vibration comfort tests, and particularly relates to an airplane vibration comfort test device and a test method in a full-airplane state; wherein, the test device includes: the nose landing gear vibration load loading device is used for applying vibration load to the nose landing gear; the two main landing gear vibration load loading devices are used for applying vibration loads to the main landing gear on the corresponding side; the two engine spanwise vibration load loading devices are used for applying spanwise vibration loads to the engines on the corresponding sides; the two engine vertical vibration load loading devices are used for applying vertical vibration loads to the engines on the corresponding sides; and the two aircraft lift force simulation devices are used for applying simulated lift force loads to the main wing on the corresponding side. The airplane vibration comfort test device and the test method can realize accurate simulation loading of main vibration source excitation of the airplane in the full-airplane state in different flight states, and can obtain relatively more effective test results when the airplane vibration comfort test in the full-airplane state is carried out on the basis.
Description
Technical Field
The application belongs to the technical field of airplane vibration comfort tests, and particularly relates to an airplane vibration comfort test device and an airplane vibration comfort test method in a full-airplane state.
Background
In the aircraft structure test, the strength test related to the safety design of the aircraft structure is mature. However, the design emphasis of the present aircraft has been gradually shifted from the initial design of the safety of the aircraft structure to the design of the comfort of the passenger cabin environment, and the vibration environment of the passenger cabin is one of the important factors influencing the comfort of human bodies. When the airplane vibration comfort test is carried out at present, local structures and parts are selected as test objects, and the whole vibration environment information in the passenger cabin of the airplane in various flight states cannot be truly simulated, so that the test structure has deviation from the actual situation.
In order to effectively verify the vibration comfort performance of the airplane, the vibration comfort test of the airplane needs to be carried out in a full airplane state, and the vibration environment information in the passenger cabin of the airplane is simulated and reproduced by simulating different flight states of the airplane and the vibration excitation of the main vibration excitation source of the airplane in the flight state. The aircraft structure under the full-aircraft state comprises a full-aircraft body structure, a nose landing gear, two main landing gears and two engines, wherein the nose landing gear, the two main landing gears and the two engines can be used as vibration excitation sources of the aircraft under different flight states of the aircraft.
When the vibration comfort test is carried out on the airplane in the full-airplane state, how to accurately simulate different flight states of the airplane and the vibration source excitation load received in the flight states is of great significance to obtaining accurate test results.
However, in the existing vibration comfort test, an effective means for accurately simulating various flight states of the airplane in a full-airplane state and excitation of a main vibration excitation source is lacked, and an effective test result is difficult to obtain.
Disclosure of Invention
In order to solve at least one technical problem in the prior art, the application provides an aircraft vibration comfort test device and a test method under a full-aircraft state.
In a first aspect, the application discloses aircraft vibration comfort test device under full machine state includes:
the nose landing gear vibration load loading device is arranged at the vertical bottom of a nose landing gear of an airplane, so as to fixedly support the nose landing gear and apply vibration load to the nose landing gear;
the two main landing gear vibration load loading devices are respectively arranged at the vertical bottoms of the main landing gears at the left side and the right side of the airplane so as to fixedly support the main landing gears at the corresponding sides and apply vibration loads to the main landing gears;
the two engine spanwise vibration load loading devices are respectively arranged on the side surfaces of the engines on the left side and the right side of the airplane, are connected to the engines on the corresponding sides, and are used for applying spanwise vibration loads to the corresponding engines;
the two engine vertical vibration load loading devices are respectively arranged at the vertical bottoms of the engines at the left side and the right side of the airplane, are connected to the engines at the corresponding sides, and are used for applying vertical vibration loads to the corresponding engines;
each aircraft lift force simulation device is used for being correspondingly connected to a main wing on one side of the aircraft and applying a simulated lift force load to the corresponding main wing.
According to at least one embodiment of the present application, the nose landing gear vibration load loading device includes:
a front landing gear vibration exciter;
the nose landing gear connecting fixing plate is used for connecting the nose landing gear vibration exciter with the nose landing gear.
According to at least one embodiment of the present application, the main landing gear vibrational load loading apparatus comprises:
a main landing gear vibration exciter;
the main undercarriage connection fixing plate is used for connecting the main undercarriage vibration exciter with the main undercarriage on the corresponding side.
According to at least one embodiment of the present application, the engine spanwise vibration load loading apparatus includes:
the engine spanwise vibration exciter is fixedly installed through an engine spanwise vibration exciter support;
and one end of the engine spanwise vibration exciting rod is connected with the engine spanwise vibration exciter, and the other end of the engine spanwise vibration exciting rod is used for being connected to the corresponding engine.
According to at least one embodiment of this application, the engine vertical vibration load loading device includes:
the engine vertical vibration exciter is fixedly installed through an engine vertical vibration exciter support;
and one end of the engine vertical vibration exciting rod is connected with the engine vertical vibration exciter, and the other end of the engine vertical vibration exciting rod is used for being connected to the corresponding engine.
According to at least one embodiment of the present application, the aircraft lift simulation device comprises;
the main wing clamping plate is connected to the main wing on the corresponding side of the airplane;
the aircraft lift simulator is arranged at the top of the main wing on the corresponding side of the aircraft and is connected with the main wing clamping plate positioned at the vertical bottom of the aircraft.
According to at least one embodiment of the application, the aircraft lift simulator further comprises:
and each air pump is correspondingly connected with one aircraft lift simulator through a pipeline so as to inject air with corresponding pressure into the corresponding aircraft lift simulator.
According to at least one embodiment of the present application, the vibration comfort test apparatus further includes:
the loading frame is provided with the nose landing gear vibration load loading device, two main landing gear vibration load loading devices, two engine spanwise vibration load loading devices, two engine vertical vibration load loading devices and two aircraft lift force simulation devices.
According to at least one embodiment of the present application, the vibration comfort test apparatus further includes:
and the vibration load loading controller is connected with the nose landing gear vibration load loading device, the two main landing gear vibration load loading devices, the two engine extension vibration load loading devices and the two engine vertical vibration load loading devices so as to synchronously control the loading devices to apply vibration loads.
In a second aspect, the application further discloses an aircraft vibration comfort test method in a full-aircraft state, which is implemented based on any one of the aircraft vibration comfort test devices in the first aspect, and includes the following steps:
step one, installing two airplane lift force simulation devices;
step two, starting the two aircraft lift force simulation devices to apply lift force simulation loads to the corresponding aircraft main wings and lift the aircraft to a preset position;
step three, mounting a front landing gear vibration load loading device, two main landing gear vibration load loading devices, two engine spanwise vibration load loading devices and two engine vertical vibration load loading devices;
fourthly, starting the front landing gear vibration load loading device and each main landing gear vibration load loading device according to experimental requirements to apply vibration loads to the corresponding front landing gear and the corresponding main landing gear; or
Starting each engine spanwise vibration load loading device to apply spanwise vibration loads to the corresponding engines; or
And starting each engine vertical vibration load loading device to apply vertical vibration load to the corresponding engine.
The application has at least the following beneficial technical effects:
the device and the method for testing the vibration comfort of the airplane in the full-airplane state are applied to a vibration comfort test of the airplane in the full-airplane state, a vibration load is applied to a corresponding nose landing gear through a nose landing gear vibration load loading device, and vibration loads are applied to the corresponding two main landing gears through two main landing gear vibration load loading devices so as to simulate the vibration load generated in the sliding process of the airplane in the full-airplane state; applying vibration loads to the corresponding engines through the two engine spanwise vibration load loading devices and the two engine vertical vibration load loading devices so as to simulate vibration excitation generated in the working state of the engines; and applying a lift force simulation load to the corresponding main wing of the airplane through the airplane lift force simulation device so as to simulate the real flight state of the airplane, realizing the accurate simulation loading of the excitation of the main vibration source of the airplane in the full-airplane state under different flight states, and carrying out the airplane vibration comfort test in the full-airplane state based on the accurate simulation loading, thereby obtaining a relatively more effective test result.
Drawings
FIG. 1 is a schematic working diagram of an aircraft vibration comfort test device in a full-aircraft state according to an embodiment of the present application;
FIG. 2 is a partial schematic view of an aircraft vibration comfort test device in a full-aircraft state according to an embodiment of the present application;
wherein:
1-nose landing gear; 2-main landing gear; 3-an engine; 4-an airplane body; 5-a front landing gear vibration exciter; 6-main landing gear vibration exciter; 7-engine extension direction vibration exciter; 8-vertical vibration exciter of engine; 9-the nose landing gear is connected with a fixed plate; 10-the main landing gear is connected with a fixed plate; 11-an engine spanwise excitation rod; 12-an engine vertical excitation rod; 13-engine vertical vibration exciter support; 14-engine extension direction vibration exciter support; 15-aircraft lift simulation means; 16-main wing cleat; 17-main wing of the aircraft; 18-frame.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. 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 a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 application.
In a first aspect, as shown in fig. 1 and 2, the present application provides an aircraft vibration comfort test device in a full-aircraft state, including a nose landing gear vibration load loading device, two main landing gear vibration load loading devices, two engine spanwise vibration load loading devices, two aircraft lift force simulation devices, and two aircraft lift force simulation devices.
Specifically, the nose landing gear vibration load loading device is arranged at the vertical bottom of a nose landing gear 1 of an airplane, so as to fixedly support the nose landing gear 1 and apply vibration load to the nose landing gear 1; the two main undercarriage vibration load loading devices are respectively arranged at the vertical bottoms of the main undercarriages 2 at the left side and the right side of the airplane so as to fixedly support the main undercarriages 2 at the corresponding sides and apply vibration loads to the main undercarriages 2; the two engine spanwise vibration load loading devices are respectively arranged on the side surfaces of the engines on the left side and the right side of the airplane, are connected to the engines 3 on the corresponding sides, and are used for applying spanwise vibration loads to the corresponding engines 3; the two engine vertical vibration load loading devices are respectively arranged at the vertical bottoms of the engines at the left side and the right side of the airplane, are connected to the engines 3 at the corresponding sides, and are used for applying vertical vibration loads to the corresponding engines 3; each aircraft lift simulating device is used for being correspondingly connected to one side main wing 17 of the aircraft and applying a simulated lift load to the corresponding main wing 17.
For the aircraft vibration comfort test device in the full-aircraft state disclosed in the above embodiment, as can be understood by those skilled in the art, the vibration comfort test device is applied to a vibration comfort test of an aircraft in the full-aircraft state, and applies a vibration load to the corresponding nose landing gear 1 through a nose landing gear vibration load loading device, and applies a vibration load to the corresponding two main landing gears 2 through two main landing gear vibration load loading devices, so as to simulate the vibration load generated by the aircraft in the full-aircraft state during a sliding process; applying vibration loads to the corresponding engine 3 through two engine spanwise vibration load loading devices and two engine vertical vibration load loading devices to simulate vibration excitation generated in the working state of the engine; the aircraft lift force simulation device is used for applying lift force simulation loads to the corresponding aircraft main wing 17 to simulate the real flight state of the aircraft, so that accurate simulation loading of main vibration source excitation of the aircraft in the full-aircraft state in different flight states is realized, the aircraft vibration comfort test in the full-aircraft state is carried out on the basis, and a relatively more effective test result can be obtained.
For the aircraft vibration comfort test device in the full-aircraft state disclosed in the above embodiment, it can be further understood by those skilled in the art that when the vibration comfort test device is applied to the aircraft vibration comfort test in the full-aircraft state, the loading positions of the nose landing gear vibration load loading device, the two main landing gear vibration load loading devices, the two engine spanwise vibration load loading devices, the two engine vertical vibration load loading devices, and the two aircraft lift force simulation devices on the aircraft body may be obtained by calculation or selected according to experience by related technicians according to specific practice.
In some alternative embodiments, in the above vibration comfort testing apparatus, the nose landing gear vibration load loading apparatus may include a nose landing gear exciter 5 and a nose landing gear connection fixing plate 9; the nose landing gear connecting fixing plate (9) is used for connecting a nose landing gear vibration exciter (5) with a nose landing gear (1), specifically, one surface of the nose landing gear connecting fixing plate (9) corresponds to be connected with the nose landing gear vibration exciter (5), and the other surface of the nose landing gear connecting fixing plate is used for being connected to the nose landing gear (1).
For the vibration comfort test device disclosed in the above embodiment, as can be understood by those skilled in the art, the front landing gear vibration load loading device generates an excitation force through the front landing gear vibration exciter 5, transmits the excitation force to the corresponding front landing gear 1 through the front landing gear connecting fixing plate 9 connected to the front landing gear vibration exciter 5, and applies a vibration load to the corresponding front landing gear 1.
In some alternative embodiments, in the above vibration comfort testing apparatus, in the nose landing gear vibration load loading apparatus, the nose landing gear exciter 5 is connected to the nose landing gear connecting fixing plate 9 by a bolt.
In some alternative embodiments, in the vibration comfort testing apparatus described above, each main landing gear vibration load loading device may include a landing gear vibration exciter 6 and a main landing gear attachment fixing plate 10; wherein, main undercarriage connection fixed plate 10 is used for being connected main undercarriage vibration exciter 6 and the main undercarriage 2 that corresponds the side, and is specific, and the one side correspondence of main undercarriage connection fixed plate 10 is connected with main undercarriage vibration exciter 6, and the another side is used for being connected to main undercarriage 2.
For the vibration comfort test device disclosed in the above embodiment, as can be understood by those skilled in the art, each main landing gear vibration load loading device generates an excitation force through the main landing gear vibration exciter 6, and the excitation force is transmitted to the corresponding main landing gear 2 through the main landing gear connection fixing plate 10 connected to the main landing gear vibration exciter 6 to apply a vibration load to the corresponding nose landing gear 2.
In some alternative embodiments, in the vibration comfort testing device, in the main landing gear vibration load loading device, the main landing gear exciter 6 is connected with the main landing gear connecting fixing plate 10 through a bolt.
In some alternative embodiments, in the above-mentioned vibration comfort test apparatus, each of the engine spanwise vibration load loading apparatuses includes an engine spanwise exciter 7, an engine spanwise exciter support 14, and an engine spanwise exciter bar 11; wherein, engine spanwise vibration exciter 7 carries out fixed mounting through engine spanwise vibration exciter support 14, and engine spanwise vibration exciting rod 11's one end is connected with engine spanwise vibration exciter 7, and the other end is used for being connected to corresponding engine 3.
With respect to the vibration comfort test device disclosed in the above embodiment, as will be understood by those skilled in the art, each engine spanwise vibration excitation device generates an excitation force through the engine spanwise vibration exciter 7, and transmits the excitation force to the corresponding engine 3 through the engine spanwise vibration excitation rod 11 connected to the engine spanwise vibration exciter 7, so as to apply a spanwise vibration load to the corresponding engine 3.
In some alternative embodiments, in each of the vibration comfort test apparatuses, in each of the engine spanwise vibration load loading apparatuses, the engine spanwise exciter 7 is connected to the engine spanwise exciting rod 11 by a spherical hinge, which may be a hydraulic spherical hinge.
In some alternative embodiments, in the vibration comfort testing apparatus, each of the engine spanwise vibration load loading apparatuses may include an engine vertical vibration exciter 8, an engine vertical vibration exciter support 13, and an engine vertical vibration exciting rod 12; the engine vertical vibration exciter 8 is fixedly mounted through an engine vertical vibration exciter support 13, one end of an engine vertical vibration exciting rod 12 is connected with the engine vertical vibration exciter 8, and the other end of the engine vertical vibration exciting rod is used for being connected to the corresponding engine 3.
For the vibration comfort test device disclosed in the above embodiment, as can be understood by those skilled in the art, each engine vertical vibration excitation device generates an excitation force through the engine vertical vibration exciter 8, and the excitation force is transmitted to the corresponding engine 3 through the engine vertical vibration excitation rod 12 connected to the engine vertical vibration exciter 8, so as to apply a vertical vibration load to the corresponding engine 3.
In some alternative embodiments, in each of the vibration comfort test apparatuses, in each of the engine vertical vibration load loading apparatuses, the engine vertical vibration exciter 8 is connected to the engine vertical vibration exciting rod 12 through a spherical hinge, which may be a hydraulic spherical hinge.
In some optional embodiments, in the above-mentioned vibration comfort test apparatus, each aircraft lift simulator includes an aircraft lift simulator 15, a main wing cardboard 16; the main wing cardboard 16 is connected to a main wing (17) on the corresponding side of the aircraft, and the aircraft lift simulator 15 is arranged on the top of the main wing 17 on the corresponding side of the aircraft and connected to the main wing cardboard 16 on the vertical bottom thereof.
With respect to the vibration comfort test device disclosed in the above embodiments, it can be understood by those skilled in the art that each aircraft lift force simulation device generates a lift force simulation load through the aircraft lift force simulator 15, and transmits the lift force simulation load to the corresponding aircraft main wing 17 through the main wing snap-gauge 16 connected to the aircraft main wing 17 to apply the lift force simulation load to the corresponding aircraft main wing.
In some alternative embodiments, in the above-mentioned vibration comfort test apparatus, the aircraft lift simulator 15 in each aircraft lift simulation apparatus is connected with the main wing card board 16 through a spherical hinge.
In some optional embodiments, in the above vibration comfort test apparatus, each aircraft lift simulator further includes an air pump, and each air pump is connected to one aircraft lift simulator 15 through a pipeline, so as to flush air at a corresponding pressure into the corresponding aircraft lift simulator 15.
In some optional embodiments, in the vibration comfort test apparatus, the aircraft lift force simulation load loading controller is connected with each air pump.
For the vibration comfort test device disclosed in the above embodiment, as can be understood by those skilled in the art, each air pump is designed to be connected to the same aircraft lift force simulation load loading controller, so that each air pump can be synchronously controlled to flush air into the corresponding aircraft lift force simulator 15, and the flushing air of each aircraft lift force simulator 15 is coordinated and consistent.
In some optional embodiments, the vibration comfort testing apparatus further includes:
and the vibration load loading controller is connected with the nose landing gear vibration load loading device, the two main landing gear vibration load loading devices, the two engine spanwise vibration load loading devices and the two engine vertical vibration load loading devices so as to synchronously control the nose landing gear vibration load loading device, the two main landing gear vibration load loading devices, the two engine spanwise vibration load loading devices and the two engine vertical vibration load loading devices to apply vibration loads.
For the vibration comfort test device disclosed in the above embodiment, it can be understood by those skilled in the art that the vibration load loading controller is connected to the nose landing gear vibration load loading device, the two main landing gear vibration load loading devices, the two engine spanwise vibration load loading devices, and the two engine vertical vibration load loading devices, specifically, the vibration load loading controller is connected to the nose landing gear vibration exciter 5, the two main landing gear vibration exciters 6, the two engine spanwise vibration exciters 7, and the two engine vertical vibration exciters 8, that is, the nose landing gear vibration exciter 5, the two main landing gear vibration exciters 6, the two engine spanwise vibration exciters 7, the two engine vertical vibration exciters 8 are connected to the same vibration load loading controller, so that the nose landing gear 5, the two main landing gear vibration exciters 6, the two engine spanwise vibration exciters 7, the vibration exciters 7, and the vibration exciters can be synchronously controlled, The two vertical engine vibration exciters 8 apply corresponding vibration loads to the airplane body structure in the full-airplane state.
In some optional embodiments, the vibration comfort testing apparatus further includes a loading frame 18, on which the nose landing gear vibration load loading device, the two main landing gear vibration load loading devices, the two engine spanwise vibration load loading devices, the two engine vertical vibration load loading devices, and the two aircraft lift force simulation devices, specifically, the nose landing gear vibration exciter 5, the two main landing gear vibration exciters 6, the two engine spanwise vibration exciters 7, the two engine vertical vibration exciters 8, and the two aircraft lift force simulators 15 are provided for supporting.
In a second aspect, the present application further provides a method for testing vibration comfort of an aircraft in a full-aircraft state, which is implemented based on any one of the above vibration comfort test apparatuses, and includes the following steps:
step one, installing two airplane lift force simulation devices (namely the airplane lift force simulation device 15);
step two, starting each air pump, starting each aircraft lift force simulation device, applying a lift force simulation load to the corresponding aircraft main wing 17, and lifting the aircraft to a preset position;
step three, mounting a front landing gear vibration load loading device, two main landing gear vibration load loading devices, two engine spanwise vibration load loading devices and two engine vertical vibration load loading devices;
step four, starting a nose landing gear vibration load loading device (namely a nose landing gear vibration exciter 5) and each main landing gear vibration load loading device (namely a main landing gear vibration exciter 6) according to experimental requirements, and applying vibration loads to the corresponding nose landing gear 1 and the corresponding main landing gear 2; or
Starting each engine spanwise vibration load loading device (namely an engine spanwise vibration exciter 7) to apply a spanwise vibration load to the corresponding engine 3; or
And starting each engine vertical vibration load loading device (namely the engine vertical vibration exciter 8) to apply vertical vibration load to the corresponding engine 3, so as to perform an airplane vibration comfort test in a full-machine state.
For the method for testing the vibration comfort of the airplane in the full-airplane state disclosed in the embodiment, a person skilled in the art can understand that the method for testing the vibration comfort is implemented based on the device for testing the vibration comfort and can obtain a relatively more effective test result when applied to the test for testing the vibration comfort of the airplane in the full-airplane state.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides an aircraft vibration comfort test device under full machine state which characterized in that includes:
the nose landing gear vibration load loading device is arranged at the vertical bottom of a nose landing gear (1) of an airplane, so as to fixedly support the nose landing gear (1) and apply vibration load to the nose landing gear (1);
the two main undercarriage vibration load loading devices are respectively arranged at the vertical bottoms of the main undercarriages (2) on the left side and the right side of the airplane so as to fixedly support the main undercarriages (2) on the corresponding sides and apply vibration loads to the main undercarriages (2);
the two engine spanwise vibration load loading devices are respectively arranged on the side surfaces of the engines on the left side and the right side of the airplane, are connected to the engines (3) on the corresponding sides, and are used for applying spanwise vibration loads to the corresponding engines (3);
the two engine vertical vibration load loading devices are respectively arranged at the vertical bottoms of the engines at the left side and the right side of the airplane, are connected to the engines (3) at the corresponding sides, and are used for applying vertical vibration loads to the corresponding engines (3);
the aircraft lift simulation system comprises two aircraft lift simulation devices, wherein each aircraft lift simulation device is used for being correspondingly connected to a main wing (17) on one side of an aircraft and applying a simulated lift load to the corresponding main wing (17).
2. The apparatus according to claim 1, wherein the nose landing gear vibration load loading device comprises:
a front landing gear exciter (5);
the nose landing gear connecting fixing plate (9), the nose landing gear connecting fixing plate (9) is used for connecting the nose landing gear vibration exciter (5) with the nose landing gear (1).
3. The apparatus of claim 1, wherein the main landing gear vibrational load loading means comprises:
a main landing gear exciter (6);
the main landing gear connecting fixing plate (10) is used for connecting the main landing gear vibration exciter (6) with the main landing gear (2) on the corresponding side.
4. The apparatus according to claim 1, wherein the engine spanwise vibration load loading means comprises:
the engine spanwise vibration exciter (7) is fixedly installed through an engine spanwise vibration exciter support (14);
and one end of the engine extension vibration exciting rod (11) is connected with the engine extension vibration exciter (7), and the other end of the engine extension vibration exciting rod is connected to the corresponding engine (3).
5. The apparatus of claim 1, wherein the engine vertical vibration load loading device comprises:
the engine vertical vibration exciter (8), wherein the engine vertical vibration exciter (8) is fixedly installed through an engine vertical vibration exciter support (13);
and one end of the engine vertical vibration exciting rod (12) is connected with the engine vertical vibration exciter (8), and the other end of the engine vertical vibration exciting rod is connected to the corresponding engine (3).
6. The vibro-comfort testing apparatus according to claim 1, characterized in that the aircraft lift simulating means comprises;
a main wing catch plate (16), the main wing catch plate (16) being connected to the main wing (17) on a corresponding side of the aircraft;
the aircraft lift simulator (15) is arranged at the top of a main wing (17) on the corresponding side of the aircraft, and is connected with a main wing clamping plate (16) located at the vertical bottom of the aircraft lift simulator (15).
7. The apparatus for testing vibrational comfort of claim 6, wherein said aircraft lift simulating assembly further comprises:
each air pump is correspondingly connected with one aircraft lift simulator (15) through a pipeline so as to inject air with corresponding pressure into the corresponding aircraft lift simulator (15).
8. The vibration comfort test apparatus according to any one of claims 1 through 7, further comprising:
the loading frame (18) is provided with the nose landing gear vibration load loading device, two main landing gear vibration load loading devices, two engine spreading vibration load loading devices, two engine vertical vibration load loading devices and two aircraft lift force simulation devices.
9. The vibration comfort test apparatus according to claim 8, further comprising:
and the vibration load loading controller is connected with the nose landing gear vibration load loading device, the two main landing gear vibration load loading devices, the two engine extension vibration load loading devices and the two engine vertical vibration load loading devices so as to synchronously control the loading devices to apply vibration loads.
10. An aircraft vibration comfort test method in a full-aircraft state is characterized by being implemented based on the aircraft vibration comfort test device of any one of claims 1 to 9, and comprising the following steps of:
step one, installing two airplane lift force simulation devices;
step two, starting the two airplane lift force simulation devices, applying lift force simulation loads to the corresponding airplane main wings (17), and lifting the airplane to a preset position;
step three, mounting a front landing gear vibration load loading device, two main landing gear vibration load loading devices, two engine spanwise vibration load loading devices and two engine vertical vibration load loading devices;
fourthly, starting the vibration load loading device of the nose landing gear and the vibration load loading devices of the main landing gears according to experimental requirements, and applying vibration loads to the corresponding nose landing gear (1) and the corresponding main landing gear (2); or
Starting each engine spanwise vibration load loading device to apply spanwise vibration loads to the corresponding engine (3); or
And starting each engine vertical vibration load loading device to apply vertical vibration load to the corresponding engine (3).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114778051A (en) * | 2022-06-27 | 2022-07-22 | 中国飞机强度研究所 | Method for determining test load spectrum of airplane vertical vibration test and application |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1496446A1 (en) * | 1986-10-11 | 1996-07-20 | И.Н. Борисов | Full-sized aeroplane dynamic test bench |
| CN2419590Y (en) * | 1999-10-28 | 2001-02-14 | 北京航空航天大学 | Device for testing range of buffer for undercarriage unit landing shocks |
| US20080257051A1 (en) * | 2007-04-23 | 2008-10-23 | Airbus Deutschland Gmbh | Method for performing a ground vibration test in airplanes |
| CA2664670A1 (en) * | 2006-11-08 | 2008-10-30 | The Boeing Company | Flight in factory |
| CN103808483A (en) * | 2012-11-12 | 2014-05-21 | 中国飞机强度研究所 | Lifting power simulation device |
| US20160061686A1 (en) * | 2014-08-29 | 2016-03-03 | Mitsubishi Aircraft Corporation | Vibration excitation system for aircraft and aircraft |
| CN110501146A (en) * | 2019-07-16 | 2019-11-26 | 中国飞机强度研究所 | Imitative lift simulation and measuring device and measuring method |
| CN111323197A (en) * | 2020-03-25 | 2020-06-23 | 安徽三联学院 | Airplane shafting impact vibration simulation test device and use method thereof |
| CN111942614A (en) * | 2020-07-17 | 2020-11-17 | 中国飞机强度研究所 | Fatigue test device and method thereof |
| CN113049207A (en) * | 2021-03-30 | 2021-06-29 | 中国飞机强度研究所 | Drop test device and method thereof |
-
2021
- 2021-12-30 CN CN202111658625.3A patent/CN114486138B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1496446A1 (en) * | 1986-10-11 | 1996-07-20 | И.Н. Борисов | Full-sized aeroplane dynamic test bench |
| CN2419590Y (en) * | 1999-10-28 | 2001-02-14 | 北京航空航天大学 | Device for testing range of buffer for undercarriage unit landing shocks |
| CA2664670A1 (en) * | 2006-11-08 | 2008-10-30 | The Boeing Company | Flight in factory |
| US20080257051A1 (en) * | 2007-04-23 | 2008-10-23 | Airbus Deutschland Gmbh | Method for performing a ground vibration test in airplanes |
| CN103808483A (en) * | 2012-11-12 | 2014-05-21 | 中国飞机强度研究所 | Lifting power simulation device |
| US20160061686A1 (en) * | 2014-08-29 | 2016-03-03 | Mitsubishi Aircraft Corporation | Vibration excitation system for aircraft and aircraft |
| CN110501146A (en) * | 2019-07-16 | 2019-11-26 | 中国飞机强度研究所 | Imitative lift simulation and measuring device and measuring method |
| CN111323197A (en) * | 2020-03-25 | 2020-06-23 | 安徽三联学院 | Airplane shafting impact vibration simulation test device and use method thereof |
| CN111942614A (en) * | 2020-07-17 | 2020-11-17 | 中国飞机强度研究所 | Fatigue test device and method thereof |
| CN113049207A (en) * | 2021-03-30 | 2021-06-29 | 中国飞机强度研究所 | Drop test device and method thereof |
Non-Patent Citations (2)
| Title |
|---|
| 张飞: "某型飞机客舱座椅人体振动舒适性评价研究", 强度与环境, vol. 46, no. 4, 31 August 2019 (2019-08-31) * |
| 王鑫涛;杜星;: "飞机结构强度试验差动式加载方法研究", 机床与液压, no. 10, 28 May 2020 (2020-05-28) * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114778051A (en) * | 2022-06-27 | 2022-07-22 | 中国飞机强度研究所 | Method for determining test load spectrum of airplane vertical vibration test and application |
| CN114778051B (en) * | 2022-06-27 | 2022-09-02 | 中国飞机强度研究所 | Method for determining test load spectrum of airplane vertical vibration test and application |
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