CN114486138B - Device and method for testing vibration comfort of aircraft in full-aircraft state - Google Patents
Device and method for testing vibration comfort of aircraft in full-aircraft state Download PDFInfo
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- CN114486138B CN114486138B CN202111658625.3A CN202111658625A CN114486138B CN 114486138 B CN114486138 B CN 114486138B CN 202111658625 A CN202111658625 A CN 202111658625A CN 114486138 B CN114486138 B CN 114486138B
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- G—PHYSICS
- G01—MEASURING; TESTING
- 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
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Abstract
The application belongs to the technical field of aircraft vibration comfort tests, and particularly relates to an aircraft vibration comfort test device and an aircraft vibration comfort test method in a full-aircraft state; wherein, the test device includes: a nose landing gear vibration load loading device for applying a vibration load to the nose landing gear; the two main landing gear vibration load loading devices apply vibration loads to the main landing gear on the corresponding side; the two engine spanwise vibration load loading devices apply spanwise vibration loads to the engines at the corresponding sides; the two vertical vibration load loading devices apply vertical vibration load to the engine at the corresponding side; two aircraft lift simulation devices apply simulated lift loads to the main wings on the corresponding sides. According to the device and the method for testing the vibration comfort of the aircraft, accurate simulation loading of main vibration source excitation of the aircraft in different flight states of the aircraft in the whole aircraft state can be achieved, and based on the accurate simulation loading, the vibration comfort test of the aircraft in the whole aircraft state is conducted, so that relatively more effective test results can be obtained.
Description
Technical Field
The application belongs to the technical field of aircraft vibration comfort tests, and particularly relates to an aircraft vibration comfort test device and an aircraft vibration comfort test method under a full-aircraft state.
Background
In aircraft structural testing, strength tests involving aircraft structural safety design have matured. However, the design emphasis of aircraft today has gradually moved from the original aircraft structural safety design to the cabin environment comfort design, and the cabin vibration environment is one of the important factors affecting human comfort. When the vibration comfort test of the aircraft is carried out, the local structures and the parts are selected as test objects, so that the whole vibration environment information in the passenger cabin of the aircraft in various flight states cannot be truly simulated, and the test structures deviate from the actual conditions.
In order to effectively verify the vibration comfort performance of the aircraft, an aircraft vibration comfort test needs to be carried out in a full-aircraft state, and vibration excitation of a main vibration excitation source of the aircraft in different aircraft flight states is simulated by simulating the different aircraft flight states, so that vibration environment information in a passenger cabin of the aircraft is simulated and reproduced. The aircraft structure in the whole aircraft state comprises a whole aircraft body structure, a front landing gear, two main landing gears and two engines, and the front landing gear, the two main landing gears and the two engines can be used as vibration excitation sources of the aircraft in different flight states of the aircraft.
When the vibration comfort test is carried out on the aircraft in the whole aircraft state, how to accurately simulate different flight states and vibration source excitation loads received in the flight states has important significance for obtaining accurate test results.
However, at present, when vibration comfort tests are performed, effective means for accurately simulating various flight states of an aircraft in a full-aircraft state and excitation of a main vibration excitation source are not available, and effective test results are difficult to obtain.
Disclosure of Invention
In order to solve at least one technical problem existing in the prior art, the application provides an aircraft vibration comfort test device and an aircraft vibration comfort test method in a full aircraft state.
In a first aspect, the application discloses an aircraft vibration comfort test device under full-aircraft state, includes:
a nose landing gear vibration load loading device provided at a vertical bottom of a nose landing gear of an aircraft to fixedly support the nose landing gear and apply a 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 aircraft so as to fixedly support the main landing gears at the corresponding sides and apply vibration loads to the main landing gears;
two engine spanwise vibration load loading devices respectively arranged on the side surfaces of the engines on the left and right sides of the aircraft and connected to the engines on the corresponding sides, for applying spanwise vibration loads to the corresponding engines;
two vertical vibration load loading devices of the engines, which are respectively arranged at the vertical bottoms of the engines at the left side and the right side of the aircraft and are connected to the engines at the corresponding sides, and are used for applying vertical vibration load to the corresponding engines;
and the two aircraft lift simulation devices are used for correspondingly connecting to one side main wing of the aircraft and applying simulated lift load to the corresponding main wing.
According to at least one embodiment of the present application, the nose landing gear vibration load loading device comprises:
a nose landing gear vibration exciter;
the nose landing gear connecting and 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 vibration load loading device comprises:
a main landing gear vibration exciter;
the main landing gear connecting and fixing plate is used for connecting the main landing gear vibration exciter with the main landing gear on the corresponding side.
According to at least one embodiment of the present application, the engine spanwise vibration load loading apparatus includes:
the engine spread-out vibration exciter is fixedly installed through an engine spread-out vibration exciter support;
one end of the engine expanding direction exciting rod is connected with the engine expanding direction exciting device, and the other end of the engine expanding direction exciting rod is connected to the corresponding engine.
According to at least one embodiment of the present application, the engine vertical vibration load loading device includes:
the vertical vibration exciter of the engine is fixedly installed through an engine vertical vibration exciter support;
one end of the vertical vibration excitation rod of the engine is connected with the vertical vibration exciter of the engine, and the other end of the vertical vibration excitation rod of the engine is 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 aircraft;
and the aircraft lift force simulator is arranged at the top of the main wing at the corresponding side of the aircraft and is connected with the main wing clamping plate at the vertical bottom of the aircraft lift force simulator.
According to at least one embodiment of the present application, the aircraft lift simulation device further comprises:
and each air pump is correspondingly connected with one aircraft lift force simulator through a pipeline so as to flush air with corresponding pressure into the corresponding aircraft lift force simulator.
According to at least one embodiment of the present application, the vibration comfort test apparatus further includes:
and the loading frame is provided 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, the two engine vertical vibration load loading devices and the 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 spanwise vibration load loading devices and the two engine vertical vibration load loading devices so as to synchronously control each loading device to apply vibration load.
In a second aspect, the present application further discloses a method for testing the vibration comfort of an aircraft in a full-aircraft state, which is implemented based on the device for testing the vibration comfort of an aircraft in any one of the first aspect, and includes the following steps:
step one, installing two aircraft lift force simulation devices;
step two, starting two aircraft lift force simulation devices, applying lift force simulation loads to corresponding aircraft main wings, and lifting the aircraft to a preset position;
step three, installing a nose 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 and each main landing gear vibration load loading device according to experimental requirements, and applying vibration loads to the corresponding nose landing gear and main landing gear; or (b)
Starting each engine spanwise vibration load loading device, and applying spanwise vibration load to the corresponding engine; or (b)
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 aircraft in the full aircraft state are applied to the vibration comfort test of the aircraft in the full aircraft state, vibration loads are applied to corresponding nose landing gears through the nose landing gear vibration load loading device, and vibration loads are applied to corresponding two main landing gears through the two main landing gear vibration load loading devices so as to simulate the vibration loads generated in the sliding process of the aircraft in the full aircraft state; and applying vibration load to the corresponding engine 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 under the working state of the engine; and applying a lift simulation load to the corresponding aircraft main wing through the aircraft lift simulation device so as to simulate the real flight state of the aircraft, realizing the accurate simulation loading of main vibration source excitation of the aircraft in different flight states of the aircraft in the whole aircraft state, and carrying out the aircraft vibration comfort test in the whole aircraft state based on the accurate simulation loading, so that a relatively more effective test result can be obtained.
Drawings
FIG. 1 is a schematic operation diagram of an aircraft vibration comfort test apparatus in a full aircraft state provided in an embodiment of the present application;
FIG. 2 is a partial schematic view of an aircraft vibration comfort test apparatus in a full aircraft state provided by an embodiment of the present application;
wherein:
1-nose landing gear; 2-main landing gear; 3-engine; 4-an aircraft body; 5-a nose landing gear vibration exciter; 6-a main landing gear vibration exciter; 7-an engine direction-expanding vibration exciter; 8-an engine vertical vibration exciter; 9-connecting the nose landing gear with a fixed plate; 10-connecting the main landing gear with a fixing plate; 11-an engine direction-expanding excitation rod; 12-an engine vertical excitation rod; 13-an engine vertical vibration exciter support; 14-supporting a motor spread-out vibration exciter; 15-an aircraft lift simulation device; 16-main wing splint; 17-an aircraft main wing; 18-frame.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying 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 some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the 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 simulation devices, and two aircraft lift simulation devices.
Specifically, the nose landing gear vibration load loading device is arranged at the vertical bottom of the nose landing gear 1 of the aircraft to fixedly support the nose landing gear 1 and apply vibration load to the nose landing gear 1; the two main landing gear vibration load loading devices are respectively arranged at the vertical bottoms of the main landing gear 2 at the left side and the right side of the aircraft so as to fixedly support the main landing gear 2 at the corresponding side and apply vibration load to the main landing gear 2; two engine spanwise vibration load loading devices respectively provided at the sides of the engines at the left and right sides of the aircraft and connected to the engines 3 at the corresponding sides for applying spanwise vibration loads to the corresponding engines 3; two vertical vibration load loading devices of the engine are respectively arranged at the vertical bottoms of the engines at the left side and the right side of the aircraft and are connected to the engines 3 at the corresponding sides, and are used for applying vertical vibration load to the corresponding engines 3; each aircraft lift simulation device is configured to be coupled to a corresponding one of the main wings 17 of the aircraft to apply a simulated lift load to the corresponding main wing 17.
As for the aircraft vibration comfort test device in the all-aircraft state disclosed in the above embodiment, it will be understood by those skilled in the art that the vibration comfort test device is applied to perform a vibration comfort test on an aircraft in the all-aircraft state, and applies a vibration load to the corresponding nose landing gear 1 through the nose landing gear vibration load loading device, and applies a vibration load to the corresponding two main landing gears 2 through the two main landing gear vibration load loading devices, so as to simulate a vibration load generated during a running process of the aircraft in the all-aircraft state; applying vibration load to the corresponding engine 3 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 under the working state of the engine; by applying a lift simulation load to the corresponding aircraft main wing 17 through the aircraft lift simulation device so as to simulate the real flight state of the aircraft, the accurate simulation loading of main vibration source excitation of the aircraft in different flight states in the full-aircraft state is realized, and based on the accurate simulation loading, the aircraft vibration comfort test in the full-aircraft state is performed, so that relatively more effective test results can be obtained.
As for the aircraft vibration comfort test device in the all-aircraft state disclosed in the above embodiment, it will 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 all-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 in the aircraft body may be calculated or empirically selected by those skilled in the relevant arts according to specific practical situations.
In some alternative embodiments, in the vibration comfort test apparatus described above, the nose landing gear vibration load loading apparatus may include a nose landing gear vibration exciter 5 and a nose landing gear connection fixing plate 9; the nose landing gear connection fixing plate (9) is used for connecting the nose landing gear vibration exciter (5) with the nose landing gear (1), specifically, one surface of the nose landing gear connection fixing plate 9 is correspondingly connected with the nose landing gear vibration exciter 5, and the other surface is used for being connected to the nose landing gear 1.
For the vibration comfort test apparatus disclosed in the above embodiment, it will be understood by those skilled in the art that the nose landing gear vibration load loading apparatus generates an exciting force through the nose landing gear vibration exciter 5, and transmits the exciting force to the corresponding nose landing gear 1 through the nose landing gear connection fixing plate 9 connected to the nose landing gear vibration exciter 5, so as to apply a vibration load to the corresponding nose landing gear 1.
In some alternative embodiments, in the vibration comfort test apparatus described above, in the nose landing gear vibration load loading apparatus, the nose landing gear vibration exciter 5 is connected to the nose landing gear connection fixing plate 9 by bolts.
In some alternative embodiments, in the vibration comfort test apparatus described above, each main landing gear vibration load loading apparatus may comprise a landing gear exciter 6 and a main landing gear connection fixing plate 10; the main landing gear connection fixing plate 10 is used for connecting the main landing gear vibration exciter 6 with the main landing gear 2 on the corresponding side, specifically, one surface of the main landing gear connection fixing plate 10 is correspondingly connected with the main landing gear vibration exciter 6, and the other surface of the main landing gear connection fixing plate is used for being connected to the main landing gear 2.
For the vibration comfort test apparatus disclosed in the above embodiment, it will be understood by those skilled in the art that each main landing gear vibration load loading apparatus generates an exciting force through the main landing gear exciter 6, and transmits the exciting force to the corresponding main landing gear 2 through the main landing gear connection fixing plate 10 connected with the main landing gear exciter 6, so as to apply a vibration load to the corresponding nose landing gear 2.
In some alternative embodiments, in the vibration comfort test apparatus described above, in the main landing gear vibration load loading apparatus, the main landing gear vibration exciter 6 is connected to the main landing gear connection fixing plate 10 by bolts.
In some alternative embodiments, in the above-mentioned vibration comfort test apparatus, each of the engine spanwise vibration load loading devices includes an engine spanwise vibration exciter 7, an engine spanwise vibration exciter mount 14, and an engine spanwise vibration excitation rod 11; the engine direction-expanding vibration exciter 7 is fixedly installed through an engine direction-expanding vibration exciter support 14, one end of an engine direction-expanding vibration exciting rod 11 is connected with the engine direction-expanding vibration exciter 7, and the other end of the engine direction-expanding vibration exciting rod is connected to the corresponding engine 3.
As for the vibration comfort test device disclosed in the above embodiment, it will be understood by those skilled in the art that 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 rod 11 connected to the engine spanwise vibration exciter 7, thereby applying a spanwise vibration load to the corresponding engine 3.
In some alternative embodiments, in the above-mentioned vibration comfort test apparatus, in each engine spanwise vibration load loading apparatus, the engine spanwise vibration exciter 7 is connected to the engine spanwise vibration rod 11 by a spherical hinge, which may be a hydraulic spherical hinge.
In some alternative embodiments, in the vibration comfort test 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 excitation rod 12; the vertical vibration exciter 8 is fixedly installed through a vertical vibration exciter support 13, one end of a vertical vibration exciting rod 12 of the engine is connected with the vertical vibration exciter 8, and the other end of the vertical vibration exciting rod is connected to the corresponding engine 3.
As for the vibration comfort test apparatus disclosed in the above embodiment, it will be understood by those skilled in the art that each vertical vibration excitation device generates an excitation force through the vertical vibration exciter 8, and transmits the excitation force to the corresponding engine 3 through the vertical vibration excitation rod 12 connected to the vertical vibration exciter 8, so as to apply a vertical vibration load to the corresponding engine 3.
In some alternative embodiments, in the vibration comfort test apparatus, in each engine vertical vibration load loading apparatus, the engine vertical vibration exciter 8 and the engine vertical vibration excitation rod 12 are connected by a spherical hinge, and the spherical hinge may be a hydraulic spherical hinge.
In some alternative embodiments, in the vibration comfort test apparatus described above, each of the aircraft lift simulation apparatuses includes an aircraft lift simulator 15, a main wing card 16; wherein the main wing card 16 is connected to the main wing (17) on the corresponding side of the aircraft, and the aircraft lift simulator 15 is disposed on top of the main wing 17 on the corresponding side of the aircraft and is connected to the main wing card 16 at the vertical bottom thereof.
For the vibration comfort test apparatus disclosed in the above embodiment, it will be understood by those skilled in the art that each of the aircraft lift simulation apparatuses generates a lift simulation load by the aircraft lift simulator 15, transmits the lift simulation load to the corresponding aircraft main wing 17 by the main wing card 16 connected to the aircraft main wing 17, and applies the lift simulation load to the corresponding aircraft main wing.
In some alternative embodiments, in the vibration comfort test apparatus described above, the aircraft lift simulator 15 and the main wing card 16 in each aircraft lift simulator are connected by a spherical hinge.
In some alternative embodiments, in the vibration comfort test apparatus, each of the aircraft lift force simulation apparatuses further includes an air pump, and each air pump is connected to one of the aircraft lift force simulators 15 through a pipeline, so as to flush air with a corresponding pressure into the corresponding aircraft lift force simulator 15.
In some alternative embodiments, in the vibration comfort test apparatus described above, the aircraft lift force simulates a load-loading controller coupled to each air pump.
For the vibration comfort test device disclosed in the above embodiment, it can be understood by those skilled in the art that each air pump is designed to be connected with the same aircraft lift force simulation load loading controller, so that each air pump can be synchronously controlled to blow air into the corresponding aircraft lift force simulator 15, and the air blown into each aircraft lift force simulator 15 is coordinated and consistent.
In some alternative embodiments, the vibration comfort test apparatus further includes:
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 may be understood by those skilled in the art that 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, specifically, the vibration load loading controller is connected with the nose landing gear vibration exciter 5, the two main landing gear vibration exciter 6, the two engine spanwise vibration exciter 7, the two engine vertical vibration exciter 8, that is, the nose landing gear vibration exciter 5, the two main landing gear vibration exciter 6, the two engine spanwise vibration exciter 7, the two engine vertical vibration exciter 8 are connected with the same vibration load loading controller, so as to synchronously control the nose landing gear vibration exciter 5, the two main landing gear vibration exciter 6, the two engine spanwise vibration exciter 7, and the two engine vertical vibration exciter 8 to apply corresponding vibration loads to the aircraft fuselage structure in the full aircraft state.
In some alternative embodiments, the vibration comfort test 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, the two aircraft lift 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 simulator 15 are disposed to provide support.
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-mentioned vibration comfort testing devices, and includes the following steps:
step one, installing two aircraft lift force simulation devices (namely an aircraft lift force simulation device 15);
step two, starting each air pump, starting each aircraft lift simulation device, applying lift simulation load to the corresponding aircraft main wing 17, and lifting the aircraft to a preset position;
step three, installing a nose 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 main landing gear 2; or (b)
Starting each engine spanwise vibration load loading device (namely an engine spanwise vibration exciter 7) to apply spanwise vibration load to the corresponding engine 3; or (b)
And starting each engine vertical vibration load loading device (namely an engine vertical vibration exciter 8) to apply vertical vibration load to the corresponding engine 3, so as to perform an aircraft vibration comfort test in a full-aircraft state.
As for the method for testing the vibration comfort of the aircraft in the full-aircraft state disclosed in the above embodiment, it will be understood by those skilled in the art that the method for testing the vibration comfort is implemented based on the device for testing the vibration comfort of the aircraft in the full-aircraft state, and can obtain relatively more effective test results.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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 (9)
1. An aircraft vibration comfort test device under full machine state, which is characterized by comprising:
nose landing gear vibration load loading means provided at the vertical bottom of the nose landing gear (1) of the aircraft to fixedly support the nose landing gear (1) and to apply vibration load to the nose landing gear (1);
the two main landing gear vibration load loading devices are respectively arranged at the vertical bottoms of the main landing gears (2) at the left side and the right side of the aircraft so as to fixedly support the main landing gears (2) at the corresponding sides and apply vibration loads to the main landing gears (2);
two engine spanwise vibration load loading means, provided on the sides of the engines on the left and right sides of the aircraft, respectively, and connected to the engines (3) on the corresponding sides, for applying spanwise vibration loads to the corresponding engines (3);
two engine vertical vibration load loading devices respectively arranged at the vertical bottoms of the engines at the left side and the right side of the aircraft and connected to the engines (3) at the corresponding sides, and used for applying vertical vibration load to the corresponding engines (3);
two aircraft lift simulation devices, each one being intended to be connected to a main wing (17) of one side of the aircraft, for applying a simulated lift load to the corresponding main wing (17);
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 each loading device to apply vibration load.
2. The vibration comfort test apparatus of claim 1, wherein the nose landing gear vibration load loading apparatus comprises:
a nose landing gear exciter (5);
the nose landing gear connecting and fixing plate (9), wherein the nose landing gear connecting and fixing plate (9) is used for connecting the nose landing gear vibration exciter (5) with the nose landing gear (1).
3. The vibration comfort test apparatus of claim 1, wherein the main landing gear vibration load loading apparatus comprises:
a main landing gear exciter (6);
the main landing gear connecting and fixing plate (10), wherein the main landing gear connecting and 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 vibration comfort test apparatus according to claim 1, wherein the engine spanwise vibration load loading apparatus comprises:
the engine spread vibration exciter (7), the engine spread vibration exciter (7) is fixedly installed through an engine spread vibration exciter support (14);
and one end of the engine expanding direction exciting rod (11) is connected with the engine expanding direction exciting device (7), and the other end of the engine expanding direction exciting rod is connected to the corresponding engine (3).
5. The vibration comfort test apparatus of claim 1, wherein the engine vertical vibration load loading apparatus comprises:
the vertical vibration exciter (8) of the engine, the vertical vibration exciter (8) of the engine is fixedly installed through a vertical vibration exciter support (13) of the engine;
and one end of the vertical engine excitation rod (12) is connected with the vertical engine exciter (8), and the other end of the vertical engine excitation rod is connected to the corresponding engine (3).
6. The vibration comfort test apparatus of claim 1, wherein the aircraft lift simulation apparatus comprises;
a main wing card (16), the main wing card (16) being connected to the main wing (17) on the corresponding side of the aircraft;
and the aircraft lift force simulator (15) is arranged at the top of the main wing (17) at the corresponding side of the aircraft, and is connected with the main wing clamping plate (16) at the vertical bottom of the main wing.
7. The vibration comfort test apparatus of claim 6, wherein the aircraft lift simulation apparatus further comprises:
and each air pump is correspondingly connected with one aircraft lift force simulator (15) through a pipeline so as to flush air with corresponding pressure into the corresponding aircraft lift force simulator (15).
8. The vibration comfort test apparatus according to any one of claims 1 to 7, further comprising:
and 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 spanwise vibration load loading devices, two engine vertical vibration load loading devices and two aircraft lift force simulation devices.
9. An aircraft vibration comfort test method in a full-aircraft state, characterized in that it is implemented on the basis of an aircraft vibration comfort test apparatus according to any one of claims 1 to 8, comprising the steps of:
step one, installing two aircraft lift force simulation devices;
step two, starting two aircraft lift simulation devices, applying lift simulation loads to corresponding aircraft main wings (17), and lifting the aircraft to a preset position;
step three, installing a nose 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 and each main landing gear vibration load loading device according to experimental requirements, and applying vibration loads to the corresponding nose landing gear (1) and main landing gear (2); or (b)
Starting each engine spanwise vibration load loading device to apply spanwise vibration load to the corresponding engine (3); or (b)
Each engine vertical vibration load loading device is started, and vertical vibration load is applied to the corresponding engine (3).
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Citations (8)
| 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 |
| CN103808483A (en) * | 2012-11-12 | 2014-05-21 | 中国飞机强度研究所 | Lifting power simulation device |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007019402B4 (en) * | 2007-04-23 | 2011-08-25 | Airbus Operations GmbH, 21129 | Method for performing a soil vibration test on aircraft |
| JP6469389B2 (en) * | 2014-08-29 | 2019-02-13 | 三菱航空機株式会社 | Aircraft vibration system and aircraft |
-
2021
- 2021-12-30 CN CN202111658625.3A patent/CN114486138B/en active Active
Patent Citations (8)
| 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 |
| CN103808483A (en) * | 2012-11-12 | 2014-05-21 | 中国飞机强度研究所 | Lifting power simulation device |
| 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 |
|---|
| 某型飞机客舱座椅人体振动舒适性评价研究;张飞;强度与环境;20190831;第46卷(第4期);全文 * |
| 飞机结构强度试验差动式加载方法研究;王鑫涛;杜星;;机床与液压;20200528(第10期);全文 * |
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