CN111392064B - Full-size fuselage frame section vertical drop impact test system and method - Google Patents
Full-size fuselage frame section vertical drop impact test system and method Download PDFInfo
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- CN111392064B CN111392064B CN202010362984.3A CN202010362984A CN111392064B CN 111392064 B CN111392064 B CN 111392064B CN 202010362984 A CN202010362984 A CN 202010362984A CN 111392064 B CN111392064 B CN 111392064B
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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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Abstract
The invention belongs to the technical field of structural dynamic impact mechanical property tests, and relates to a full-size machine body frame section vertical drop impact test system and method. The system comprises: the device comprises a test frame, a lifting device, a special lock mechanism, a force measuring platform, a lifting/throwing control system, an airborne test system, an airborne sensor control system and a ground non-contact test system. The invention can meet the vertical drop impact test requirements of various narrow passenger plane and wide passenger plane fuselage sections.
Description
Technical Field
The invention belongs to the technical field of structural dynamic impact mechanical property tests, and relates to a full-size machine body frame section vertical drop impact test system and method.
Background
Safety is a critical factor in aircraft design considerations. In the operation of the aircraft, emergency falling collision accidents can be avoided due to weather, man-made, mechanical faults and other reasons. In the development process of the aircraft, the fuselage structure is required to be subjected to an anti-collision test by a test method so as to verify the crashworthiness of the aircraft. Related large-scale test facilities are built in the countries such as the United states, europe, japan and the like, and the crash test can be carried out on the whole machine or the full-size frame section.
In the aircraft drop crash test, the lifting height and the posture before throwing of the test piece are required to be accurately controlled, so that the test piece can be ensured to vertically drop into the crash force measuring platform. In the test process, response information such as structural deformation, strain, acceleration, dummy movement, seat deformation and the like needs to be synchronously acquired.
There are also many inventions in the study of the drop test system in China, and there are many patent technologies, for example: a general aircraft vertical drop impact test device and a test method (Chinese patent: CN 103645027A), a drop test device of a movable impact platform (Chinese patent: CN 101532903A), and a drop test platform of an unmanned plane skid landing system (Chinese patent: CN 204043883U). However, the test devices and the test methods are mainly aimed at a general aircraft or landing gear system, and the loading capacity and the test method of the test system cannot meet the test requirements of the landing test of the large aircraft fuselage structure.
Disclosure of Invention
A full-size fuselage frame section vertical crash test system and method are provided to meet crash test requirements of various aircraft full-size fuselage structures.
Technical solution
The invention provides a full-size machine body frame section vertical drop impact test system, which comprises: the device comprises a test frame, a lifting device, a special lock mechanism, a force measuring platform, a lifting/throwing control system, an airborne test system, an airborne sensor control system and a ground non-contact test system;
the top of the test frame is provided with a lifting device, and the lifting device hooks the test piece through a special lock mechanism; the force measuring platform is arranged on the bottom surface right below the test piece and is used for realizing free falling impact of the test piece and synchronously triggering all the test systems; the airborne sensor control system is electrically connected with the test piece impact force measuring platform through the airborne test system so as to receive impact parameters of the test piece; the lifting/throwing control system is arranged on the test frame, is electrically connected with the lifting device and is used for controlling the lifting device to lift or throw the test piece; and the airborne test system and the ground non-contact test system complete the falling collision response test of the test piece.
Further, the test frame includes: the auxiliary cross beam, two groups of upright posts and the ground fixed mounting plate; each group of upright posts comprises at least one section of upright post, the auxiliary cross beam is fixedly connected with the top end of the first section of upright post, the upright posts are fixedly connected, and the last section of upright post is fixedly connected with the bottom surface through a bottom surface fixing and mounting plate; the lifting device is arranged on the upper surface of the auxiliary cross beam.
Further, the special lock mechanism comprises an upper hook, an electromagnetic chuck, a holding plate, a limiting block, a lower hook and a protective hook;
the upper hook is arranged on the non-adsorption surface of the magnetic chuck through a rope, the upper hook is connected with the lifting device, the lower hook is arranged on the non-adsorption surface of the magnetic chuck, and the lower hook is connected with the test piece through a rope; the limiting block limits the electromagnetic force, so that the holding plate is accurately matched with the electromagnetic chuck; holding plate B 3 And electromagnetic chuck B 2 Magnetic force realization test piece betweenIs lifted by the lifting device; the protection hook is arranged at the non-adsorption position of the adsorption surface of the electromagnetic chuck, and the limit of the connecting rope is placed to prevent the connecting rope from injuring the test piece by smashing.
Further, the force measuring platform comprises: the force sensor senses force response of the test piece and the table top in the impact test and impact process.
Further, the airborne test system comprises an aviation dummy, an acceleration sensor, a strain sensor and a high-speed camera, and is used for testing dummy response, acceleration and strain response of key parts and deformation response of seats, dummy and fuselage structures in the falling collision process.
Further, the ground non-contact test system comprises a non-contact test system, a total station, a data acquisition system and a real-time monitoring system;
the non-contact test system is used for testing structural deformation of the falling collision test piece, the total station is used for testing the height and the gesture of the test piece before being put in, the data acquisition system is used for acquiring all acceleration and strain signals, and the real-time monitoring system is used for image recording of the whole test process.
Furthermore, the airborne test sensor and the ground test sensor are synchronously triggered by the impact force signals of the test piece and the force measuring platform, and the pre-acquisition for a certain time is set to ensure that the acquired signals cover the whole test process.
The invention provides a full-size machine body frame section vertical drop impact test method, which comprises the following steps:
a four-point hoisting and single-point throwing mode is adopted, and the test piece is lifted to a preset height by a special lifting device;
aiming at the center area of the force measuring platform, after the posture of the test piece is adjusted, the test piece is put in through a special lock mechanism;
when the free falling body of the test piece impacts the force measuring platform, synchronously triggering each test system, and completing the falling collision response test of the test piece through the airborne test system and the ground non-contact test system;
after the test piece is completely stationary, the test is ended.
THE ADVANTAGES OF THE PRESENT INVENTION
The invention fully utilizes the characteristics of free falling body falling impact test, adopts a four-point lifting and single-point throwing mode, combines the advantages of high-precision frequency conversion lifting control and electromagnetic holding/throwing technology, integrates the testing methods of non-contact test, large-size structure impact force test, multi-channel multi-physical quantity synchronous triggering and acquisition and the like, provides the full-size fuselage frame section vertical falling impact test device, system and method, can meet the vertical falling impact test requirements of various narrow-body airliners and wide-body airliner fuselage sections, has strong operability and high reliability, can obviously reduce the falling impact test risk, and has wide application prospect.
Drawings
FIG. 1 is a schematic illustration of a full-size fuselage frame section vertical drop impact test system;
FIG. 2 is a schematic illustration of a test frame;
fig. 3 is a schematic view of a dedicated lock mechanism.
Detailed Description
The invention provides a special test system and a special test method suitable for full-size machine body frame section vertical drop impact test based on a free falling body drop impact test principle. According to the test method, a four-point hoisting and single-point throwing mode is mainly adopted, a test piece is lifted to a preset height by a special lifting device, the test piece is aligned to the center area of a force measuring platform, after the posture of the test piece is adjusted, throwing of the test piece is achieved through a special locking mechanism, the test piece freely falls to strike the force measuring platform, each test system is triggered synchronously, the crash response test of the test piece is completed through an airborne test system and a ground non-contact test system, and the test is completed after the test piece is completely stationary.
As shown in fig. 1, the test system satisfying the requirements of the test method includes: the test device comprises a test frame 1, a lifting device 2, a special lock mechanism 3, a test piece 4, a force measuring platform 5, a lifting/throwing control system 6, an onboard test system 7, an onboard sensor control system 8, a ground non-contact test system 9, a total station 10 and a real-time monitoring system 11. As shown in fig. 2, the test frame includes an auxiliary beam a 1 Upper column A 2 Lower column A 3 Ground fixed mounting plate A 4 The four parts are connected with the auxiliary cross beam and the upper stand column through flanges, the upper stand column is connected with the lower stand column through flanges, the whole test frame is connected with a foundation through a ground fixed mounting plate through bolts, and the total height is 18.4m; the rated lifting capacity of the lifting device is 6 tons, the requirements of the falling collision test of the fuselage sections of the narrow-body airliners and the wide-body airliners can be met, and the lifting precision is 1mm through frequency conversion control; as shown in fig. 3, the special lock mechanism comprises an upper hook B 1 Electromagnetic chuck B 2 Holding plate B 3 Limiting block B 4 Lower hook B 5 Protective hook B 6 . In the test process, the upper hook is connected with the lifting device, the lower hook is connected with the test piece, and the upper hook passes through the limiting block B 4 Realizing the holding plate B 3 And electromagnetic chuck B 2 Precisely cooperate with each other through the holding plate B 3 And electromagnetic chuck B 2 The magnetic force between the two parts realizes the lifting of the test piece. After the holding plate is put in, the holding plate passes through the protective hook B 6 Limiting the connecting rope prevents the connecting rope from injuring the test piece by smashing; the force measuring platform mainly comprises a table top and densely distributed parallel unidirectional force sensors, and the size of the force measuring platform is 6m multiplied by 4m through force response in the impact process of the impact test of the test piece and the table top, so that the requirements of the falling and impact test of the narrow passenger plane and the wide passenger plane can be met; the airborne test system comprises an aviation dummy, an acceleration sensor, a strain sensor and a high-speed camera, and is used for testing dummy response, acceleration and strain response of key parts and deformation response of a seat, a dummy and a fuselage structure in the falling collision process; the ground non-contact test system comprises a non-contact test system, a total station, a data acquisition system and a real-time monitoring system. The non-contact test system is used for testing structural deformation of the falling collision test piece, the total station is used for testing the height and the gesture of the test piece before being put in, the data acquisition system is used for acquiring all acceleration and strain signals, and the real-time monitoring system is used for image recording of the whole test process. All the airborne test sensors and the ground test sensors are synchronously triggered by impact force signals of the test piece and the force measuring platform, and the pre-acquisition for a certain time is set to ensure that the acquired signals cover the whole test process.
The invention provides a full-size fuselage frame section vertical crash test device, a full-size fuselage frame section vertical crash test system and a full-size fuselage frame section vertical crash test method, based on the full-size fuselage frame section vertical crash test system and the full-size fuselage frame section vertical crash test method, the full-size fuselage frame section vertical crash test system is high in reliability and strong in operability, and the crash test risk can be remarkably reduced.
Claims (5)
1. A full-size fuselage frame section vertical drop impact test system, comprising: the device comprises a test frame, a lifting device, a special lock mechanism, a force measuring platform, a lifting/throwing control system, an airborne test system, an airborne sensor control system and a ground non-contact test system;
the top of the test frame is provided with a lifting device, and the lifting device hooks the test through a special lock mechanism; the force measuring platform is arranged on the bottom surface right below the test piece and is used for realizing free falling impact of the test piece and triggering each test system; the airborne sensor control system is electrically connected with the child impact force measuring platform of the test piece through the airborne test system so as to receive impact parameters of the test piece; the lifting/throwing control system is arranged on the second test frame and is electrically connected with the lifting device and used for controlling the lifting device to lift or throw the test piece; the ground non-contact test system of the airborne test system port completes the falling collision response test of the test piece;
the test piece is lifted to a preset height by a lifting device, the test piece is aligned to the center area of the force measuring platform, after the posture of the test piece is adjusted, the test piece is put in through a special lock mechanism, the test piece freely falls to strike the test spoon platform, each test system is triggered synchronously, and the test is finished through the airborne test system and the ground non-contact test system or the crash response test of the test piece, and the test is finished after the test piece is completely stationary;
the test frame includes: the auxiliary cross beam, two groups of upright posts and the ground fixed mounting plate; each group of upright posts comprises at least one section of upright post, the auxiliary cross beam is fixedly connected with the top end of the first section of upright post, the upright posts are fixedly connected, and the last section of upright post is fixedly connected with the bottom surface through a bottom surface fixing and mounting plate; the upper surface of the auxiliary cross beam is provided with a lifting device;
the special lock mechanism comprises an upper hook, an electromagnetic chuck, a holding plate, a limiting block, a lower hook and a protective hook;
the upper hook is arranged on the non-adsorption surface of the magnetic chuck through a rope, the upper hook is connected with the lifting device, the lower hook is arranged on the non-adsorption surface of the magnetic chuck, and the lower hook is connected with the test piece through a rope; the limiting block limits the electromagnetic force, so that the holding plate is accurately matched with the electromagnetic chuck; holding plate (B) 3 ) Electromagnetic chuck (B) 2 ) The magnetic force between the two parts realizes the lifting of the test piece; the protection hook is arranged at the non-adsorption position of the adsorption surface of the electromagnetic chuck, and the limit of the connecting rope is placed to prevent the connecting rope from injuring the test piece by smashing.
2. The system of claim 1, wherein the force platform comprises: the force sensor senses force response of the test piece and the table top in the impact test and impact process.
3. The system of claim 1, wherein the on-board test system comprises an aeronautical dummy, an acceleration sensor, a strain sensor, a high speed camera for testing the dummy response, the acceleration and strain response of the building site, and the deformation response of the seat, dummy, fuselage structure during a crash.
4. The system of claim 1, wherein the ground non-contact test system comprises a non-contact test system, a total station, a data acquisition system, a real-time monitoring system;
the data acquisition system is used for acquiring all acceleration and strain signals before throwing, and the real monitoring system is used for image recording of the whole test process.
5. The system of any of claims 1-4, wherein the on-board test sensor and the test sensor are triggered synchronously by the impact force signals of the test piece and the force measuring platform, and a timing scoop is provided to pre-collect the collected signals to ensure that the collected signals cover the whole test process.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010362984.3A CN111392064B (en) | 2020-04-30 | 2020-04-30 | Full-size fuselage frame section vertical drop impact test system and method |
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| CN202010362984.3A CN111392064B (en) | 2020-04-30 | 2020-04-30 | Full-size fuselage frame section vertical drop impact test system and method |
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| CN111392064B true CN111392064B (en) | 2023-06-23 |
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| CN117054036B (en) * | 2023-10-13 | 2024-06-14 | 中国飞机强度研究所 | System and method for dynamically measuring aircraft landing attitude in full-aircraft drop test |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101532903B (en) * | 2009-04-08 | 2010-08-18 | 南京航空航天大学 | Drop test device for movable impact platform |
| DE102013216920A1 (en) * | 2013-08-26 | 2015-02-26 | Airbus Operations Gmbh | Drop test device and method for performing a drop test |
| CN103645027A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | General-purpose plane vertical crash test device and test method |
| CN204043883U (en) * | 2014-08-18 | 2014-12-24 | 中国航天空气动力技术研究院 | A kind of unmanned plane skid landing system drop-test platform |
| CN109436371A (en) * | 2018-10-25 | 2019-03-08 | 中国民航大学 | Airplane in transportation category cargo deck substructure, which is vertically fallen, hits experimental rig and method |
| CN109515745B (en) * | 2018-11-02 | 2022-03-15 | 中国飞机强度研究所 | Cargo compartment lower upright post assembly falling and collision experimental device and experimental method |
| CN110940479A (en) * | 2019-12-05 | 2020-03-31 | 中国飞机强度研究所 | Armored vehicle seat explosion impact resistance performance test system and method |
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