CN118457942B - Device and method for testing structural strength of control surface of navigation aircraft - Google Patents
Device and method for testing structural strength of control surface of navigation aircraft Download PDFInfo
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- CN118457942B CN118457942B CN202410924336.0A CN202410924336A CN118457942B CN 118457942 B CN118457942 B CN 118457942B CN 202410924336 A CN202410924336 A CN 202410924336A CN 118457942 B CN118457942 B CN 118457942B
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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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- 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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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a pilot plane control surface structural strength test device and a pilot plane control surface structural strength test method, wherein the test device comprises: the test piece clamping device comprises a gantry frame, a loading unit, a mounting platform, a ground rail and a test piece clamping device, wherein the gantry frame and the mounting platform are fixedly mounted on the ground rail, the mounting platform is arranged right below the gantry frame, the test piece clamping device is fixedly mounted on the mounting platform, the loading unit is mounted on the gantry frame and used for carrying out tension or thrust loading on a test loading point of a control surface structure test piece, the loading unit comprises a loading rod structure and a loading rod structure mounting seat, the loading rod structure mounting seat is mounted on the gantry frame, and the loading rod structure is a lever mechanism. The static strength test device for the navigation water plane pontoon has reasonable structure, simple operation, low cost and high reliability, and can perform static strength test and fatigue test on the plane control surface structure test piece to be detected.
Description
Technical Field
The invention relates to the technical field of general aviation aircraft structural strength static force/fatigue test, and provides a device and a method for testing the structural strength of a control surface of a navigation aircraft, which are used for testing the static strength and the fatigue strength of the control surface of a navigation small-sized aircraft.
Background
The control surface of the aircraft is an important part for controlling the aircraft, and is mainly used for ensuring the longitudinal and transverse flight balance and control of the aircraft. The structural designer of the aircraft firstly needs to consider the problem of structural strength/rigidity of the control surface when designing, so that the strength design and fatigue performance of each control surface of the aircraft under the action of certain loads in the development process of the aircraft are very important whether the use requirement of the aircraft is met. In order to ensure that the structure is not damaged in the use process, a large number of static strength tests and fatigue tests must be carried out on the aircraft before the aircraft first flies, wherein the static strength tests and the fatigue tests of the control surfaces are important part-level tests.
The development process of the navigation aircraft is also the same, but compared with large civil aircraft and military aircraft, the navigation aircraft rudder has the characteristics of smaller relative size, simple working condition, lower load and the like. When the control surface strength test is carried out, a nonstandard test device is designed to complete the test according to the configuration characteristics of a single control surface or each control surface of a single machine type, the implementation way is complex, the universality is poor, and great challenges are brought to the development cost and the period of the model of the airplane.
Therefore, the pilot plane structural strength test device with simple structure, high reliability and strong universality is provided, and becomes an urgent requirement for pilot plane research and development.
Disclosure of Invention
In view of the above, the invention aims to provide a device and a method for testing the structural strength of a control surface of a navigation aircraft, so as to solve the problems of the existing strength test of the control surface of the navigation aircraft.
In one aspect, the invention provides a device for testing structural strength of a rudder surface of a navigable aircraft, comprising: the device comprises a gantry frame, a loading unit, a mounting platform, a ground rail and a test piece clamp, wherein the gantry frame and the mounting platform are fixedly mounted on the ground rail, the mounting platform is arranged right below the gantry frame, the test piece clamp is fixedly mounted on the mounting platform and used for fixing a control surface structure test piece to be tested, the loading unit is mounted on the gantry frame and used for carrying out pulling force or pushing force loading on a test loading point of the control surface structure test piece, the loading unit comprises a loading rod structure and a loading rod structure mounting seat, the loading rod structure mounting seat is mounted on the gantry frame, the loading rod structure is a lever mechanism and comprises a servo electric cylinder, a first pull pressure sensor, a loading rod fixing seat, a loading rocker arm, a push-pull rod and a push-pull rod adjusting piece, the servo electric cylinder and the loading rod fixing seat are respectively fixed above and below the loading rod structure mounting seat, an output shaft of the servo electric cylinder is connected with one end of the loading rocker arm, and the other end of the push-pull rocker arm passes through one end of the loading rocker arm and then is connected with one end of the loading rod, the other end of the push-pull rod is used for being used for connecting a load sensor with a pull rod, and used for adjusting the length of the load sensor.
Preferably, the gantry frame is a gantry frame structure consisting of an upright post and a top frame, the bottom of the upright post is fixedly connected with the ground rail, and the top frame is connected with the top of the upright post.
Further preferably, a guide rail and a sliding block are installed at the top of the gantry frame, and the loading rod structure installation seat is slidably installed on the guide rail through the sliding block.
Further preferably, the loading units are multiple groups, and each group of loading units is installed on two guide rails through two groups of sliding blocks.
Further preferably, the loading rod structure mounting base is provided with a plurality of mounting interfaces with standard hole pitches along the direction perpendicular to the guide rail, and the mounting interfaces are used for mounting the servo electric cylinder.
Further preferably, a second tension pressure sensor is arranged on the output shaft of the servo electric cylinder and used for monitoring tension pressure load output by the output shaft of the servo electric cylinder in real time.
Further preferably, the mounting platform comprises a platform upright post, a porous mounting plate and a platform top frame, wherein the bottom of the platform upright post is fixedly connected with the ground rail, the platform top frame is connected with the top of the platform upright post, and the porous mounting plate is fixed on the platform top frame.
Further preferably, the porous mounting plate is a standard pitch reference mounting plane.
Further preferably, the pilot plane structural strength test device further comprises a control plane rib loading clamping plate, a through hole matched with the outer peripheral surface of the control plane structural test piece to be tested is formed in the middle of the control plane rib loading clamping plate, and the top of the control plane rib loading clamping plate is connected with the loading end of the push-pull rod and used for applying load to the corresponding position of the control plane structural test piece to be tested.
The invention also provides a method for testing the structural strength of the control surface of the navigation aircraft, which is used for carrying out static strength test/fatigue strength test on the control surface structural test piece to be tested.
The pilot plane structural strength test device provided by the invention has the advantages of reasonable structure, simplicity in operation, low cost, high reliability and strong universality, realizes load output by adopting the servo electric cylinder, reduces the components and maintenance cost of the traditional hydraulic loading system, increases and decreases the number and the mounting position of the loading units according to different test requirements, has wider application range, can meet the requirements of static strength and fatigue tests of the control planes such as ailerons, flaps, elevators and rudders of most pilot planes, plays an important role in the research and development and navigable approval processes of the pilot plane, and can shorten the research and development cost and research and development period.
Drawings
The invention will be described in further detail with reference to the accompanying drawings and embodiments:
FIG. 1 is a schematic structural diagram of a pilot plane structural strength test device for a navigable aircraft;
FIG. 2 is a schematic view of the structure of a gantry frame;
FIG. 3 is a schematic layout of a load unit;
FIG. 4 is a schematic diagram of a loading unit;
FIG. 5 is a partial schematic diagram of a load unit;
FIG. 6 is a schematic view of a test piece mounting platform;
FIG. 7 is a schematic view of the installation of a test piece fixture;
FIG. 8 is a schematic view of the installation of a test piece, test piece fixture and loading card.
Detailed Description
The invention will be further explained below in connection with specific embodiments, but is not limited to the invention.
In order to solve the problems of poor universality, poor reliability and the like of the conventional pilot plane structural strength test device, as shown in fig. 1 to 8, the invention provides a pilot plane structural strength test device, which comprises: the test piece clamping device comprises a gantry frame 100, a loading unit 200, a mounting platform 300, a ground rail 400 and a test piece clamping device 500, wherein the gantry frame 100 and the mounting platform 300 are fixedly mounted on the ground rail 400, the mounting platform 300 is arranged right below the gantry frame 100, the test piece clamping device 500 is fixedly mounted on the mounting platform 300 and is used for fixing a control surface structure test piece 600 to be tested, the loading unit 200 is mounted on the gantry frame 100 and is used for carrying out pulling or pushing loading on a test loading point of the control surface structure test piece 600, the loading unit 200 comprises a loading rod structure 210 and a loading rod structure mounting seat 220, the loading rod structure mounting seat 220 is mounted on the gantry frame 100, the loading rod structure 210 is a lever mechanism and comprises a servo electric cylinder 211, a first pull pressure sensor 212, a loading rod fixing seat 213, a loading rod 214, a push-pull rod 215 and a push-pull rod adjusting piece 216, the servo electric cylinder 211 and the loading rod fixing seat 213 are respectively fixed above and below the push-pull loading rod structure mounting seat 220, and an output shaft is connected with the push-pull rod 215 through the other end of the loading rod structure 215 and the loading rod adjusting piece 215, and the loading rod adjusting piece 215 is used for connecting the loading rod 215 and the other end of the loading rod adjusting piece 215.
The pilot plane control surface structural strength test device can perform static strength test and fatigue strength test on a control plane structural test piece 600 to be tested, in the test process, firstly, a gantry frame 100 and an installation platform 300 are installed on a ground rail 400, the control plane structural test piece 600 to be tested is fixed on the installation platform 300 through a test piece clamp 500, then, the installation position of a loading unit 200 is adjusted according to the load loading position, and a loading rocker 214 is driven to transmit load required by the test to a test piece end through a push-pull rod 215 and a push-pull rod adjusting piece 216, so that corresponding test data are obtained.
As an improvement of the technical solution, as shown in fig. 1 and fig. 2, the gantry frame 100 is a gantry frame structure formed by an upright post 101 and a top frame 102, the bottom of the upright post 101 is fixedly connected with a ground rail 400, the top frame 102 is connected with the top of the upright post 101, preferably, the upright post 101 is connected with the ground rail 400 through a bolt, and the distance between the upright posts 101 can be adjusted according to the size of a test piece and the working condition requirement.
As an improvement of the technical solution, as shown in fig. 1 and2, a guide rail 103 and a slider 104 are installed on the top of the gantry frame 100, and the loading rod structure installation seat 220 is slidably installed on the guide rail 103 through the slider 104. When the test load is applied, the guide rail 103 and the sliding block 104 provide reliable support for the loading unit 200, and the transverse loading position can be adjusted by adjusting the position of the loading rod structure mounting seat 220 on the guide rail 103, wherein, as shown in fig. 4, 2 groups of clamps 105 are arranged on the sliding block 104, and after the position is adjusted, the locking and fixing can be performed.
As an improvement of the technical solution, as shown in fig. 4, the loading units 200 are multiple groups, each group of loading units 200 is mounted on two guide rails 103 through two groups of sliding blocks 104, preferably, as shown in fig. 3, the number of loading units 200 in the test device is 8 groups, each group of loading units 200 is provided with 2 groups of sliding blocks 104, and the loading units 200 are fixedly connected with the top frame 102 through the guide rails 103, and when a test load is applied, the mounting position of the loading units 200 is adjusted according to the position requirement of the test loading point.
As an improvement of the technical solution, as shown in fig. 4, the loading rod structure mounting base 220 has a plurality of mounting interfaces with standard hole pitches along the direction perpendicular to the guide rail 103, and the longitudinal adjustment of the loading position can be achieved by adjusting the mounting position of the servo cylinder 211 on the loading rod structure mounting base 220.
As an improvement of the technical solution, as shown in fig. 5, a second tension-pressure sensor 217 is disposed on the output shaft of the servo electric cylinder 211, and is used for monitoring the tension-pressure load output by the output shaft of the servo electric cylinder 211 in real time.
As an improvement of the technical solution, as shown in fig. 6, the mounting platform 300 includes a platform upright 301, a porous mounting plate 302, and a platform top frame 303, where the bottom of the platform upright 301 is fixedly connected to a ground rail 400, the platform top frame 303 is connected to the top of the platform upright 301, and the porous mounting plate 302 is fixed on the platform top frame 303.
As an improvement of the technical solution, as shown in fig. 6, the porous mounting plate 302 is a standard mounting plane with standard hole pitch, which can adapt to the mounting requirements of test pieces with different sizes, and preferably, the porous mounting plate 302 has better strength and rigidity.
As an improvement of the technical solution, as shown in fig. 8, the device for testing the structural strength of the rudder plane of the navigation aircraft further includes a rudder surface rib loading clamping plate 700, a through hole matched with the outer peripheral surface of the rudder surface structural test piece 600 to be tested is provided in the middle of the rudder surface rib loading clamping plate 700, and the top of the rudder surface rib loading clamping plate 700 is connected with the loading end of the push-pull rod 215, so as to apply a load to the corresponding position of the rudder surface structural test piece 600 to be tested.
The invention also provides a method for testing the structural strength of the control surface of the navigation aircraft, which is used for carrying out static strength test/fatigue strength test on the control surface structural test piece 600 to be tested.
The embodiments of the invention have been written in an incremental manner with emphasis on the differences between the various embodiments being placed upon which similar parts may be seen.
The embodiments of the present invention have been described in detail with reference to the drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the spirit of the present invention.
Claims (6)
1. The utility model provides a navigation aircraft rudder face structural strength test device which characterized in that includes: the device comprises a gantry frame (100), a loading unit (200), a mounting platform (300), a ground rail (400) and a test piece clamp (500), wherein the gantry frame (100) and the mounting platform (300) are fixedly mounted on the ground rail (400) and the mounting platform (300) is arranged right below the gantry frame (100), the test piece clamp (500) is fixedly mounted on the mounting platform (300) and used for fixing a control surface structure test piece (600) to be tested, the loading unit (200) is mounted on the gantry frame (100) and used for carrying out tensile force or thrust loading on a test loading point of the control surface structure test piece (600), the loading unit (200) comprises a loading rod structure (210) and a loading rod structure mounting seat (220), the loading rod structure mounting seat (220) is mounted on the gantry frame (100), the loading rod structure (210) is a lever mechanism and comprises a servo electric cylinder fixing seat (211), a first push-pull pressure sensor (212), a loading rocker arm (213), a loading rod (214), a rocker arm (216) and an adjusting member (216) and a rocker arm (211) are respectively mounted on the loading rod structure and the loading rod structure (211), the output shaft of the servo electric cylinder (211) is connected with one end of the loading rocker arm (214), the other end of the loading rocker arm (214) penetrates through the loading rocker arm fixing seat (213) and then is connected with one end of the push-pull rod (215), the other end of the push-pull rod (215) is used as a loading end and is used for loading test load to a control surface structure test piece (600), the push-pull rod adjusting piece (216) is connected with the push-pull rod (215) and is used for adjusting the length of the push-pull rod (215), the first pull pressure sensor (212) is installed on the push-pull rod (215) and is used for monitoring loading load, a guide rail (103) and a sliding block (104) are installed at the top of the gantry frame (100), the loading rod structure installation seat (220) is slidably installed on the guide rail (103) through the sliding block (104), the loading rod structure installation seat (220) is used for installing the servo electric cylinder (211) along a plurality of installation interfaces which are perpendicular to the guide rail (103) and have standard hole distances, the installation platform (300) comprises a plurality of installation platform (301), a porous frame (301) and a platform (301) and a top platform (301) are fixedly connected with a stand (303), a stand (301) and a stand (301) are fixedly connected with the top platform (303), the multi-hole mounting plate (302) is fixed on the platform top frame (303), and the multi-hole mounting plate (302) is a standard mounting plane with standard hole pitch.
2. The pilot plane structural strength test device according to claim 1, wherein: the gantry frame (100) is a gantry frame structure formed by upright posts (101) and a top frame (102), the bottoms of the upright posts (101) are fixedly connected with ground rails (400), and the top frame (102) is connected with the tops of the upright posts (101).
3. The pilot plane structural strength test device according to claim 1, wherein: the loading units (200) are multiple groups, and each group of loading units (200) is arranged on two guide rails (103) through two groups of sliding blocks (104).
4. The pilot plane structural strength test device according to claim 1, wherein: and a second tension pressure sensor (217) is arranged on the output shaft of the servo electric cylinder (211) and used for monitoring the tension pressure load output by the output shaft of the servo electric cylinder (211) in real time.
5. The pilot plane structural strength test device according to claim 1, wherein: the control surface structure test piece (600) is characterized by further comprising a control surface rib loading clamping plate (700), wherein a through hole matched with the outer peripheral surface of the control surface structure test piece (600) to be tested is formed in the middle of the control surface rib loading clamping plate (700), and the top of the control surface rib loading clamping plate (700) is connected with the loading end of the push-pull rod (215) and used for applying load to the corresponding position of the control surface structure test piece (600) to be tested.
6. A pilot plane control surface structural strength test method is characterized in that: static strength test/fatigue strength test is performed on a control surface structure test piece (600) to be tested by using the pilot plane control surface structure strength test device according to any one of claims 1 to 5.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410924336.0A CN118457942B (en) | 2024-07-11 | 2024-07-11 | Device and method for testing structural strength of control surface of navigation aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410924336.0A CN118457942B (en) | 2024-07-11 | 2024-07-11 | Device and method for testing structural strength of control surface of navigation aircraft |
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| CN118457942B true CN118457942B (en) | 2024-09-24 |
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| CN119509956A (en) * | 2025-01-20 | 2025-02-25 | 辽宁通用航空研究院 | Device and method for testing strength of installation structure of airplane energy storage equipment |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003279439A (en) * | 2003-02-10 | 2003-10-02 | Tech Res & Dev Inst Of Japan Def Agency | Dynamic wind tunnel test apparatus and method |
| CN116698471A (en) * | 2023-08-07 | 2023-09-05 | 四川腾盾科技有限公司 | Static strength test method for aircraft control surface |
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| KR101115819B1 (en) * | 2009-04-30 | 2012-03-09 | 한국항공우주산업 주식회사 | Universal platform and method of assembling aerial vehicle using the same |
| FR2988851B1 (en) * | 2012-03-28 | 2014-04-25 | Dassault Aviat | METHOD FOR DETERMINING A CREDIBILITY STATE OF MEASUREMENTS OF AN AIRCRAFT INCIDENT SENSOR AND CORRESPONDING SYSTEM |
| KR102369169B1 (en) * | 2020-05-12 | 2022-03-03 | 한국항공우주산업 주식회사 | Apparatus of Inertial simulator for Aircraft Control Surface |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003279439A (en) * | 2003-02-10 | 2003-10-02 | Tech Res & Dev Inst Of Japan Def Agency | Dynamic wind tunnel test apparatus and method |
| CN116698471A (en) * | 2023-08-07 | 2023-09-05 | 四川腾盾科技有限公司 | Static strength test method for aircraft control surface |
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