CN106644431B - Fixing clamp for fatigue test of undercarriage - Google Patents
Fixing clamp for fatigue test of undercarriage Download PDFInfo
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- CN106644431B CN106644431B CN201611080664.9A CN201611080664A CN106644431B CN 106644431 B CN106644431 B CN 106644431B CN 201611080664 A CN201611080664 A CN 201611080664A CN 106644431 B CN106644431 B CN 106644431B
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- support
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- landing gear
- fatigue test
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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
- G01M13/00—Testing of machine parts
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a fixing clamp for an aircraft landing gear fatigue test, which comprises a frame, an outer support, a support rod support, a fastener and an inner support, wherein the outer support, the support rod support and the inner support are fixed on the frame through the fastener. The frame includes girder, load-carrying beam, assistance roof beam, and the girder is "T" type with the load-carrying beam, and the girder is "T" type with assisting the roof beam, and the girder passes through stiffening beam I and links to each other with the load-carrying beam, and the girder passes through stiffening beam II and assists the roof beam and link to each other with the load-carrying beam through stiffening beam III. The outer side support and the inner side support are fixed on the main beam, and the stay bar support is fixed on the auxiliary beam. The fixing clamp for the fatigue test of the aircraft landing gear disclosed by the invention has the advantages of ingenious conception, simple structure and sufficient strength and rigidity, and ensures the normal running of the fatigue test of the aircraft landing gear.
Description
Technical Field
The invention belongs to the technical field of aircraft fatigue tests, and particularly relates to a fixing clamp for an aircraft landing gear fatigue test.
Background
The purpose of the fatigue test of the landing gear of the aircraft is as follows: the fatigue resistance of the landing gear structure is verified, the fatigue weak part of the structure is exposed, and the service life, the first turning period and the repairing interval of the landing gear are determined, so that the method is an important link for determining the safety service life of the aircraft. The fatigue test of a certain type of aircraft landing gear needs to apply a relatively large load and needs to perform a long-time fatigue test, and the aircraft landing gear is generally subjected to a fatigue test alone, so that a set of tool clamps are required to be designed to support and fix the landing gear, so that the normal posture of the landing gear during the test and the stress condition of the landing gear connection position are simulated as truly as possible, and meanwhile, the fixing clamps must be ensured to have enough strength and rigidity.
Disclosure of Invention
The invention aims to solve the technical problems and provides the fixing clamp for the fatigue test of the undercarriage, so as to keep the normal posture of the undercarriage during the test and simulate the stress condition of the joint of the undercarriage as truly as possible.
In order to solve the technical problems of the invention, the invention is realized by the following technical scheme: the fixing clamp for the fatigue test of the undercarriage comprises a frame 1, an outer support 2, a stay bar support 3, a fastener 4 and an inner support 5, wherein the outer support 2, the stay bar support 3 and the inner support 5 are fixed on the frame 1 through the fastener 4; the frame 1 comprises a main beam 108, a bearing beam 102, an auxiliary beam 105, a reinforcing beam I109, a reinforcing beam II 107 and a reinforcing beam III 104, wherein the main beam 108 and the bearing beam 102 are in a T shape, the main beam 108 and the auxiliary beam 105 are in a T shape, the main beam 108 is connected with the bearing beam 102 through the reinforcing beam I109, the main beam 108 is connected with the auxiliary beam 105 through the reinforcing beam II 107, and the auxiliary beam 105 is connected with the bearing beam 102 through the reinforcing beam III 104; the outer support 2 and the inner support 5 are fixed on the main beam 108, and the stay bar support 3 is fixed on the auxiliary beam 105.
Preferably, the main beam 108 and the load beam 102 are made of 25# channel steel, the auxiliary beam 105 is made of 18# channel steel, and the main beam 108, the load beam 102 and the auxiliary beam 105 are of a ladder combination structure, so that the sizes of the inner support 5 and the outer support 2 are greatly reduced, and a large amount of raw materials and processing periods are saved.
Preferably, the upper surfaces of the main beam 108 and the load beam 102 are welded with the upper panel i 101, the upper surfaces of the auxiliary beam 105 are welded with the upper panel ii 106, the lower surfaces of the main beam 108, the load beam 102 and the auxiliary beam 105 are welded with the lower panel 103, that is, the upper surfaces of the main beam 108 and the load beam 102 are in the same plane, the upper surfaces of the auxiliary beam 105 are in another plane, the lower surfaces of the main beam 108, the load beam 102 and the auxiliary beam 105 are in the same plane, the strength of the joint of the main beam 108, the auxiliary beam 105 and the load beam 102 is enhanced, the flatness of the mounting surfaces of the outer support 2, the stay support 3 and the inner support 5 is ensured, and the mounting posture of the landing gear is ensured to the greatest extent.
Preferably, the left and right sides of the stay bar support 3 are respectively provided with a channel steel I111 and a channel steel II 112, one end of the channel steel I111 is fixed on the auxiliary beam 105, and the other end is fixed on the reinforcing beam III 104; one end of the channel steel II 112 is fixed on the auxiliary beam 105, the other end of the channel steel II is fixed on the reinforcing beam II 107, the strength and the rigidity of the support rod support 3 are enhanced, and the strength and the rigidity of the auxiliary beam 105 are enhanced.
Preferably, a certain height difference exists between the auxiliary beam 105 and the main beam 108, and a cushion block 110 is arranged at the joint to strengthen the strength of the joint.
Preferably, the main beam 108 is provided with a first steel plate 113 on the outer support 2 and the inner support 5, and the first steel plate 113 welds the upper panel I101 and the lower panel 103 together; the second steel plate 114 is arranged at the position where the stay bar support 3 is arranged on the auxiliary beam 105, the second steel plate 114 welds the upper panel II 106 and the lower panel 103 together, and the bending resistance of the channel steel edge strips at the support fixing positions of the outer support 2, the stay bar support 3 and the inner support 5 is enhanced.
Preferably, a first splicing steel plate 115 is arranged at the splicing position of the main beam 108 and the auxiliary beam 105, and a second splicing steel plate 116 is arranged at the splicing position of the main beam 108 and the load beam 102, so that the strength of the splicing position of the main beam 108, the load beam 102 and the auxiliary beam 105 is enhanced.
Compared with the prior art, the invention has the beneficial effects that:
the invention discloses a fixing clamp for an aircraft landing gear fatigue test, which has the advantages of ingenious conception, simple structure and enough strength and rigidity, and ensures the normal running of the aircraft landing gear fatigue test. The invention discloses a fixing clamp for an aircraft landing gear fatigue test, wherein a main beam and a bearing Liang Hefu beam adopt a ladder combined structure, so that the sizes of an inner side support and an outer side support are greatly reduced, and a large amount of raw materials and processing periods are saved; the upper and lower surfaces of the main beam and the bearing Liang Hefu beam are respectively welded with an upper panel and a lower panel, so that the strength of the joint of the frames is enhanced, the flatness of the mounting surfaces of the three supports is ensured, and the mounting posture of the landing gear is ensured to the greatest extent; the left side and the right side of the support rod support are provided with channel steel, so that the strength and the rigidity of the support rod support are enhanced, and the strength and the rigidity of the auxiliary beam are enhanced; the main beam and the auxiliary beam are provided with the support, steel plates are added to weld the upper panel and the lower panel together, and the bending resistance of the channel steel edge strip at the fixed position of the support is enhanced; and the girder and auxiliary girder spliced parts and the girder and bearing girder spliced parts are welded on the channel steel web plates, so that the strength of the channel steel spliced parts is enhanced.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention.
Fig. 2 is a schematic diagram of a frame.
Fig. 3 is a schematic diagram of frame channel welding.
Fig. 4 is a state diagram of the present invention.
Reference numerals: 1. a frame; 101. an upper panel I; 102. a load beam; 103. a lower panel; 104. reinforcing beam III; 105. an auxiliary beam; 106. an upper panel II; 107. a reinforcing beam II; 108. a main beam; 109. reinforcing beam I; 110. a cushion block; 111. channel steel I; 112. channel steel II; 113. a first steel plate; 114. a second steel plate; 115. a first spliced steel plate; 116. a second spliced steel plate; 2. an outer support; 3. a stay bar support; 4. a fastener; 5. an inner support; 6. landing gear; 61. a landing gear shaft; 62. landing gear braces.
Detailed Description
The embodiments are described in detail below with reference to the accompanying drawings.
Referring to fig. 1 and 2, a fixing clamp for fatigue test of an aircraft landing gear comprises a frame 1, an outer support 2, a support rod support 3, a fastener 4 and an inner support 5, wherein the outer support 2, the support rod support 3 and the inner support 5 are fixed on the frame 1 through the fastener 4; the frame 1 comprises a main beam 108, a bearing beam 102, an auxiliary beam 105, a reinforcing beam I109, a reinforcing beam II 107 and a reinforcing beam III 104, wherein the main beam 108 and the bearing beam 102 are in a T shape, the main beam 108 and the auxiliary beam 105 are in a T shape, the main beam 108 is connected with the bearing beam 102 through the reinforcing beam I109, the main beam 108 is connected with the auxiliary beam 105 through the reinforcing beam II 107, and the auxiliary beam 105 is connected with the bearing beam 102 through the reinforcing beam III 104; the outer support 2 and the inner support 5 are fixed on the main beam 108, and the stay bar support 3 is fixed on the auxiliary beam 105.
Further, the main beam 108 and the bearing beam 102 are made of 25# channel steel, the auxiliary beam 105 is made of 18# channel steel, and the main beam 108, the bearing beam 102 and the auxiliary beam 105 are of a ladder combination structure, so that the sizes of the inner side support 5 and the outer side support 2 are greatly reduced, and a large amount of raw materials and processing periods are saved.
Further, the upper surfaces of the main beam 108 and the load beam 102 are welded with the upper panel I101, the upper surfaces of the auxiliary beam 105 are welded with the upper panel II 106, the lower surfaces of the main beam 108, the load beam 102 and the auxiliary beam 105 are welded with the lower panel 103, namely, the upper surfaces of the main beam 108 and the load beam 102 are in the same plane, the upper surfaces of the auxiliary beam 105 are in another plane, the lower surfaces of the main beam 108, the load beam 102 and the auxiliary beam 105 are in the same plane, the strength of the joint of the main beam 108, the auxiliary beam 105 and the load beam 102 is enhanced, the flatness of the mounting surfaces of the outer support 2, the support rod support 3 and the inner support 5 is ensured, and the mounting posture of the landing gear is ensured to the greatest extent.
Further, the left side and the right side of the supporting rod support 3 are respectively provided with a channel steel I111 and a channel steel II 112, one end of the channel steel I111 is fixed on the auxiliary beam 105, and the other end is fixed on the reinforcing beam III 104; one end of the channel steel II 112 is fixed on the auxiliary beam 105, the other end of the channel steel II is fixed on the reinforcing beam II 107, the strength and the rigidity of the support rod support 3 are enhanced, and the strength and the rigidity of the auxiliary beam 105 are enhanced.
Further, there is a certain height difference between the auxiliary beam 105 and the main beam 108, and a cushion block 110 is disposed at the connection position to strengthen the strength of the connection position.
Further, a first steel plate 113 is respectively arranged on the outer support 2 and the inner support 5 which are arranged on the main beam 108, and the first steel plate 113 welds the upper panel I101 and the lower panel 103 together; the second steel plate 114 is arranged at the position where the stay bar support 3 is arranged on the auxiliary beam 105, the second steel plate 114 welds the upper panel II 106 and the lower panel 103 together, and the bending resistance of the channel steel edge strips at the support fixing positions of the outer support 2, the stay bar support 3 and the inner support 5 is enhanced.
Further, a first splicing steel plate 115 is arranged at the splicing position of the main beam 108 and the auxiliary beam 105, a second splicing steel plate 116 is arranged at the splicing position of the main beam 108 and the bearing beam 102, and the strength of the splicing position of the main beam 108, the bearing beam 102 and the auxiliary beam 105 is enhanced.
The fatigue test of the aircraft landing gear 6 adopts a landing gear flip-chip mode, and an outer support 2, a stay bar support 3 and an inner support 5 are fixed on a frame 1 through fasteners 4; then the outer end of the landing gear rotating shaft 61 is inserted into the joint bearing of the outer support 2, the inner end of the landing gear rotating shaft 61 is inserted into the joint bearing of the inner support 5, and the landing gear supporting rod 62 is connected with the supporting rod support 3; and finally, fixing the landing gear 6 fatigue test fixing clamp on the bearing ground rail through the foundation bolts, and starting to perform the landing gear 6 fatigue test. The outer support 2, the stay bar support 3 and the inner support 5 provide space position constraint consistent with the actual installation state so as to ensure the installation posture requirement of the landing gear 6, and the structure of the connection part of the three supports and the landing gear 6 simulates the structure of the corresponding connection position of the aircraft, so that the force transmission form consistent with the actual aircraft can be ensured.
The invention discloses a fixing clamp for a fatigue test of an aircraft landing gear 6, which has ingenious conception, simple structure and enough strength and rigidity, and ensures the normal running of the fatigue test of the aircraft landing gear 6.
The above list is only one of the embodiments of the present invention. It will be obvious that the invention is not limited to the above embodiments, but that many similar variants are possible. All modifications directly derived or suggested to one skilled in the art from the present disclosure should be considered as being within the scope of the present invention.
Claims (7)
1. The utility model provides an aircraft landing gear fatigue test mounting fixture, includes frame (1), outside support (2), vaulting pole support (3), fastener (4) and inboard support (5), outside support (2), vaulting pole support (3) and inboard support (5) are fixed through fastener (4) on frame (1), its characterized in that: the frame (1) comprises a main beam (108), a bearing beam (102), an auxiliary beam (105), a reinforcing beam I (109), a reinforcing beam II (107) and a reinforcing beam III (104), wherein the main beam (108) and the bearing beam (102) are in a T shape, the main beam (108) and the auxiliary beam (105) are in a T shape, the main beam (108) is connected with the bearing beam (102) through the reinforcing beam I (109), the main beam (108) is connected with the auxiliary beam (105) through the reinforcing beam II (107), and the auxiliary beam (105) is connected with the bearing beam (102) through the reinforcing beam III (104); the outer support (2) and the inner support (5) are fixed on the main beam (108), and the stay bar support (3) is fixed on the auxiliary beam (105).
2. An aircraft landing gear fatigue test fixture according to claim 1, wherein: the main beam (108) and the bearing beam (102) are made of 25# channel steel, the auxiliary beam (105) is made of 18# channel steel, and the main beam (108), the bearing beam (102) and the auxiliary beam (105) are of a ladder combined structure.
3. An aircraft landing gear fatigue test fixture according to claim 1, wherein: the upper surfaces of the main beams (108) and the bearing beams (102) are welded with the upper panel I (101), the upper surfaces of the auxiliary beams (105) are welded with the upper panel II (106), and the lower surfaces of the main beams (108), the bearing beams (102) and the auxiliary beams (105) are welded with the lower panel (104).
4. An aircraft landing gear fatigue test fixture according to claim 1, wherein: the left side and the right side of the support rod support (3) are respectively provided with a channel steel I (111) and a channel steel II (112), one end of the channel steel I (111) is fixed on the auxiliary beam (105), and the other end is fixed on the reinforcing beam III (104); one end of the channel steel II (112) is fixed on the auxiliary beam (105), and the other end of the channel steel II is fixed on the reinforcing beam II (107).
5. An aircraft landing gear fatigue test fixture according to claim 1, wherein: and a cushion block (110) is arranged at the joint of the auxiliary beam (105) and the main beam (108).
6. An aircraft landing gear fatigue test fixture according to claim 1, wherein: the main beam (108) is provided with an outer support (2) and an inner support (5) which are respectively provided with a first steel plate (113), and the first steel plates (113) are used for welding an upper panel I (101) and a lower panel (103) together; the auxiliary beam (105) is provided with a second steel plate (114) at the position of the supporting rod support (3), and the second steel plate (114) welds the upper panel II (106) and the lower panel (103) together.
7. An aircraft landing gear fatigue test fixture according to claim 1, wherein: the splicing part of the main beam (108) and the auxiliary beam (105) is provided with a first splicing steel plate (115), and the splicing part of the main beam (108) and the bearing beam (102) is provided with a second splicing steel plate (116).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611080664.9A CN106644431B (en) | 2016-11-30 | 2016-11-30 | Fixing clamp for fatigue test of undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611080664.9A CN106644431B (en) | 2016-11-30 | 2016-11-30 | Fixing clamp for fatigue test of undercarriage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106644431A CN106644431A (en) | 2017-05-10 |
| CN106644431B true CN106644431B (en) | 2023-06-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611080664.9A Active CN106644431B (en) | 2016-11-30 | 2016-11-30 | Fixing clamp for fatigue test of undercarriage |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107264835B (en) * | 2017-07-13 | 2020-04-28 | 江西洪都航空工业集团有限责任公司 | Undercarriage test load loading device |
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| KR20040023893A (en) * | 2002-09-12 | 2004-03-20 | 한국항공우주산업 주식회사 | Test fixture for a pylon of airplane |
| CN104062107A (en) * | 2014-04-01 | 2014-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Static force/fatigue performance test method for single section of reinforced frame/beam |
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| RU2260551C1 (en) * | 2004-03-30 | 2005-09-20 | Закрытое Акционерное Общество Конструкторское Бюро "Полет" (Зао Кб "Полет") | Adapter for group launching of micro-satellites |
| CN201053101Y (en) * | 2007-06-15 | 2008-04-30 | 冯贵法 | Bottom supporting steel truss |
| CN102759437B (en) * | 2011-04-28 | 2015-06-10 | 株洲南车时代电气股份有限公司 | Fixture for vibration test and mounting method thereof |
| CN103963993B (en) * | 2013-01-29 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Wing section simulation structure of aircraft iron bird test platform |
| CN103161168B (en) * | 2013-02-22 | 2015-06-17 | 东通岩土科技（杭州）有限公司 | Detachable prestress supporting frame system |
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