CN113607559A - Static test platform for cockpit door - Google Patents
Static test platform for cockpit door Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 248
- 230000003068 static effect Effects 0.000 title claims abstract description 38
- 238000012546 transfer Methods 0.000 claims abstract description 10
- 229910000831 Steel Inorganic materials 0.000 claims description 63
- 239000010959 steel Substances 0.000 claims description 63
- 101000623895 Bos taurus Mucin-15 Proteins 0.000 claims description 4
- 238000003475 lamination Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 description 11
- 238000011056 performance test Methods 0.000 description 11
- 238000006073 displacement reaction Methods 0.000 description 10
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- 230000036316 preload Effects 0.000 description 2
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- 239000002390 adhesive tape Substances 0.000 description 1
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- G—PHYSICS
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
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Abstract
The invention discloses a cockpit door static test platform. The device comprises a test platform frame and test equipment; the test equipment is arranged on a test platform frame, and the test platform frame comprises a test platform frame assembly and a switching base; the cockpit door test piece is connected with the test platform frame through the adapter base; the test equipment comprises a load applying device and a load transferring device; the load applying device is arranged on the test platform frame A and is connected with the load transferring device; the load transfer device is in contact with the cockpit door test piece. The invention has the advantages of exquisite structure, reliable work, flexible working environment adaptability and simple and convenient operation.
Description
Technical Field
The invention relates to a test platform, in particular to a cockpit door static test platform.
Background
The civil aviation manufacturing industry in China just starts, and most of civil aviation equipment is imported from foreign countries. In the currently developed domestic projects of civil aircrafts, a cockpit door is one of important devices frequently used in the civil aircrafts, and is mainly used for protecting the safety of aircrews and preventing non-aircrews from entering the cockpit in the flight process.
The safety performance of cockpit doors has attracted considerable attention since the '911' event, and in the design and manufacture of cockpit doors, it is necessary to consider whether the cockpit doors have sufficient strength to prevent the cockpit doors from being forcibly damaged, and the development and implementation of the performance test of cockpit doors are particularly important. Therefore, the development of a corresponding performance test bed has important significance for guaranteeing and improving the safety of the cockpit door. At present, no known cockpit door performance test platform equipment exists.
Therefore, the development of a civil aircraft cockpit door performance test platform is necessary.
Disclosure of Invention
The invention aims to provide a static test platform for a cockpit door, which has the characteristics of exquisite structure, reliable work, flexible working environment adaptability and simplicity and convenience in operation and is mainly applied to static strength tests of the cockpit door structure of a civil aircraft.
In order to achieve the purpose, the technical scheme of the invention is as follows: cockpit door static test platform, its characterized in that: the device comprises a test platform frame and test equipment; the test equipment is arranged on a test platform frame, and the test platform frame comprises a test platform frame assembly and a switching base; the cockpit door test piece is connected with the test platform frame through the adapter base;
the test equipment comprises a load applying device and a load transferring device; the load applying device is arranged on the test platform frame and is connected with the load transferring device;
the load transfer device is in contact with the cockpit door test piece.
In the technical scheme, the switching base comprises a switching base I and a switching base II;
the upper end of the test platform frame assembly is provided with a fastener, the lower end of the test platform frame assembly is provided with a switching base I, and the side surface of the test platform frame assembly is provided with a switching base II;
the upper end of the cockpit door test piece stand column assembly is connected with the upper end of the test platform frame assembly through a fastener, the lower end of the cockpit door test piece stand column assembly is connected with the lower end of the test platform frame assembly through a switching base I, and the cockpit door test piece hinge plate assembly is connected with the side face of the test platform frame assembly through a switching base II;
the test platform frame assembly is provided with a bolt mounting hole.
In the technical scheme, the upper end and the front end of the test platform frame are provided with a plurality of fastener mounting holes.
In the above technical scheme, the load applying device comprises a hydraulic cylinder and a hand pump, and the hand pump is connected with the hydraulic cylinder.
In the technical scheme, the load transfer device comprises a channel steel assembly, a laminated plate and a tension and pressure sensor; the pulling pressure sensor is respectively connected with the hydraulic cylinder and the channel steel component; one end of the laminated board is connected with the channel steel assembly, and the other end of the laminated board is contacted with the cockpit door test piece.
In the technical scheme, the channel steel assembly and the laminated board are both of movable structures.
In the technical scheme, the channel steel assembly, the laminated board, the pulling pressure sensor and the hydraulic cylinder are all multiple.
In the technical scheme, the channel steel component comprises a channel steel component I and a channel steel component II;
the laminated board comprises a laminated board I and a laminated board II;
the pulling pressure sensor comprises a pulling pressure sensor I and a pulling pressure sensor II;
the hydraulic cylinder comprises a hydraulic cylinder I and a hydraulic cylinder II;
one end of the tension pressure sensor I is connected with the hydraulic cylinder I, and the other end of the tension pressure sensor I is connected with the channel steel component I; one end of the laminated board I is connected with the channel steel assembly I, and the other end of the laminated board I is in contact with the cockpit door test piece;
one end of the tension pressure sensor II is connected with the hydraulic cylinder II, and the other end of the tension pressure sensor II is connected with the channel steel assembly II; one end of the laminated board II is connected with the channel steel assembly II, and the other end of the laminated board II is in contact with the cockpit door test piece.
The invention has the following advantages:
(1) the connection mode of the cockpit door test piece and the test platform simulates the installation mode of a cockpit door machine; the test platform frame can be used as a main fixed rack of a cockpit door test piece and is combined with other performance test platforms of the cockpit door for use so as to meet the performance test requirements of different cockpit doors; the hand pump is shaken to pressurize the hydraulic cylinder, and load is transferred to the pull pressure sensor, the channel steel component and the laminated board: the laminated board is in direct contact with the cockpit door test piece, and loads are uniformly and stably applied to the cockpit door test piece; the tension and pressure sensor records the load applied to the test piece of the cockpit door; the test platform can test the damage resistance of the cockpit door test piece under different static loads, and has the advantages of exquisite structure, reliable work, flexible working environment adaptability, strong practicability, complete functions, simple and convenient operation, and easy use and popularization;
(2) the invention has the characteristics of stable loading mode, adjustable loading size, high loading control precision, easy disassembly, assembly and maintenance, and capability of meeting the static test requirement of the civil large-scale aircraft cockpit door, and can also be widely applied to the performance test field of other transportation large-scale aircraft cockpit doors;
(3) the cockpit door static test platform is a verification test platform used for verifying whether a cockpit door product can bear the maximum load, the deformation of the cockpit door product meets the requirement and the product is not damaged (namely, the cockpit door static test platform is used for verifying whether the cockpit door product can bear the limit load and has no harmful permanent deformation, and is used for verifying whether the cockpit door product is damaged when the limit load applied to the cockpit door structure is at least maintained at 3S), so as to determine whether the cockpit door meets the airworthiness standard of a transport airplane or not (the cockpit door static test platform is a special performance test platform for cockpit doors, is mainly applied to the static strength test of a civil large-scale aircraft cockpit door structure, can simulate the static load borne by the cockpit door under different conditions in the flight process, can bear larger static load, is used for verifying that the cockpit door can meet the relevant regulations in the airworthiness standard CCAR25-R3 of the transport airplane, the safety of the cockpit door is guaranteed);
the ultimate inertial load borne by the cockpit door is obtained through theoretical calculation according to parameters such as relevant regulation parameters (such as the magnitude of the ultimate inertial load, a material correction coefficient, a safety coefficient and the like) and the dead weight of the cockpit door in the airworthiness standard of the transport aircraft; the load requirement is a range of force values.
The measuring precision of the deformation of the test piece (namely, the cockpit door) and the measuring precision of the magnitude of the applied load are in direct proportion to the measuring precision of the tension and pressure sensor, the tension and pressure sensor is connected with the tester, the data of the deformation and the magnitude of the load of the test piece (namely, the cockpit door) are directly displayed on the screen of the tester, the operation is simple, convenient and visual, and the load can be conveniently adjusted in real time according to the displayed data.
Drawings
Fig. 1 is a schematic front structural view of a cockpit door test platform frame and a cockpit door test piece in the present invention.
Fig. 2 is a schematic top view of the connection between the cockpit door test platform frame and the cockpit door test piece according to the present invention.
Fig. 3 is a partial structural schematic diagram of the test device of the invention acting on the cockpit door test piece.
Fig. 4 is a schematic perspective view of the frame assembly of the test platform according to the present invention.
Fig. 5 is a schematic top view of fig. 4.
Fig. 6 is a bottom view of the structure of fig. 4.
Fig. 7 is a left side view of the structure of fig. 4.
Fig. 8 is a right-view structural diagram of fig. 4.
Fig. 9 is a schematic front view of the structure of fig. 4.
Fig. 10 is a rear view of fig. 4.
FIG. 11 is a graph showing the change of tension and displacement with time in the first loading mode according to the embodiment of the present invention.
FIG. 12 is a graph showing the change of the tension value and the displacement with time in the second loading mode according to the embodiment of the present invention.
FIG. 13 is a graph showing the change of the tension value and the displacement with time in the third loading mode according to the embodiment of the present invention.
FIG. 14 shows a first data record according to an embodiment of the present invention.
FIG. 15 shows a second embodiment of the present invention.
D in fig. 1 and 2 each indicates a fastener installation hole.
In the figure, 1-a test platform frame assembly, 2-a cockpit door test piece stand column assembly, 3-a switching base I, 4-a cockpit door test piece hinge plate assembly, 5-a switching base II, 6-a cockpit door test piece, 7-a laminated plate I, 8-a channel steel assembly I, 9-a laminated plate II, 10-a channel steel assembly II, 11-a pull pressure sensor I, 12-a hydraulic cylinder I, 13-a pull pressure sensor II, 14-a hydraulic cylinder II, an A-test platform frame and B-test equipment.
Detailed Description
The embodiments of the present invention will be described in detail with reference to the accompanying drawings, which are not intended to limit the present invention, but are merely exemplary. While the advantages of the invention will be clear and readily understood by the description.
With reference to the accompanying drawings: the cockpit door static test platform comprises a test platform frame A and test equipment B, and is used for completing a cockpit door static test; the test equipment B is arranged on a test platform frame A, and the test platform frame A comprises a test platform frame assembly 1 and a switching base; the cockpit door test piece 6 is connected with the test platform frame A through the switching base so as to achieve the purpose of simulating the installation of the cockpit door test piece on an airplane (the installation mode of the cockpit door test piece of the invention completely simulates the actual installation mode of the cockpit door), and the cockpit door static test platform can be used as a main test bench for fixing a door body in a cockpit door performance test; the test platform frame A is provided with the installation switching interface of the cockpit door, the installation mode of the cockpit door on an airplane can be completely simulated through the switching device, and the installation position of a test piece is unique; the test platform frame A is provided with other mounting structures (such as fastener mounting holes), can be connected with other test platform frames as required and serves as a main mounting rack of the cockpit door to assist in completing other tests of the cockpit door (the test platform frame A in the invention is provided with a plurality of fastener mounting holes, as can be seen from the static tests (such as figures 1 and 2) of the invention, the number of the fastener mounting holes at the upper end and the front end of the test platform frame A is more than that of the fastener mounting holes required for fixing a test piece (namely the cockpit door), and the extra fastener mounting holes can enable the test platform frame A to be assembled with other test racks for use, so as to complete the verification of other performance tests (such as impact tests) of the cockpit door);
the test equipment B comprises a load applying device and a load transferring device; the load applying device is arranged on the test platform frame A and is connected with the load transferring device;
the load transfer device is in contact with the cockpit door trial 6 (as shown in figures 1, 2, 3).
The cockpit door test piece 6 comprises a stand column assembly 2 of the cockpit door test piece and a cockpit door test piece hinge plate assembly 4.
Furthermore, the switching base comprises a switching base I3 and a switching base II 5;
the upper end of the test platform frame assembly 1 is provided with a fastener, the lower end of the test platform frame assembly is provided with a switching base I3, and the side surface of the test platform frame assembly is provided with a switching base II 5;
the upper end of the upright post component 2 of the cockpit door test piece is connected with the upper end of the test platform frame component 1 through a fastener, the lower end of the upright post component 2 is connected with the lower end of the test platform frame component 1 through a switching base I3, and the cockpit door test piece hinge plate component 4 is connected with the side surface of the test platform frame component 1 through a switching base II 5 (as shown in figures 4-10);
the test platform frame assembly is provided with bolt mounting holes, a plurality of bolt mounting holes are formed in the test platform frame assembly, and the upper end of the cockpit door test piece stand column assembly is fixedly connected with the upper end of the test platform frame through bolts, nuts and washers;
the lower end of the upright post component of the pilot cabin door test piece is fixedly connected with the test platform frame through bolts and screws by utilizing the adapter base I3;
and the cockpit door test piece hinge plate assembly is fixedly connected with the test platform frame through the adapter base II 5 by screws and gaskets.
Further, the upper end and the front end of the test platform frame are provided with a plurality of fastener mounting holes (as shown in figures 1 and 2), and the test platform frame can be combined with other performance test platforms of the cockpit door.
Furthermore, the load applying device comprises a hydraulic cylinder and a hand pump, the hand pump is connected with the hydraulic cylinder, the applied load is controllable, the hydraulic cylinder applies the load through the hand pump, and the load is stably and uniformly transmitted to the cockpit door test piece through the tension pressure sensor, the channel steel assembly and the laminated board, so that the operation is simple and safe, and the test requirements can be effectively met; the hydraulic cylinder and the hand pump can be combined with channel steel and pull pressure sensors of different specifications, so that the load applying mode is various, and the applied load is uniform and stable. The test piece mounting mode completely simulates the actual installation mode of the cockpit door, the loading mode basically simulates the static load condition of the cockpit door in the aircraft flying process, and the test piece mounting mode can be used for verifying whether the cockpit door meets the airworthiness standard of the transport aircraft.
Further, the load transfer device comprises a channel steel assembly, a laminated plate and a tension and pressure sensor; the pulling pressure sensor is respectively connected with the hydraulic cylinder and the channel steel component; the laminate is attached to the channel assembly at one end and is in contact with cockpit door trial 6 at the other end (as shown in figure 3). The hand pump and the hydraulic cylinder are combined to apply specific load to the cockpit door test piece. The laminated board is directly contacted with the pilot compartment door test piece, so that the pilot compartment door test piece is uniformly stressed. The invention is mainly applied to the static strength test of the cockpit door structure of the civil aircraft and is used for bearing larger static load, therefore, the force transmission structure of the invention is mainly composed of the laminated board and the channel steel, the laminated board directly adopts surface contact with the cockpit door test piece, the point contact is converted into the surface contact, and the stress of the test piece can be more uniform.
Furthermore, the channel steel assembly and the laminated plate are movable structures, the channel steel assembly and the laminated plate can move, the laminated plate is directly contacted with a test piece (namely a cockpit door), and the laminated plate and the test piece (namely the cockpit door) are temporarily fixed by using a C-shaped clamp or an adhesive tape; the channel steel assembly is in direct contact with the laminated plate, and the channel steel assembly is temporarily fixed with the laminated plate and a test piece (namely a cockpit door) by using a C-shaped clamp; then the hydraulic cylinder directly acts on the channel steel assembly, and a hand pump and the hydraulic cylinder are utilized to apply a preload force (the preload force is allowed in a cockpit door static test and is about 250N) to the channel steel assembly, so that the channel steel assembly, the laminated plate and the test piece (namely the cockpit door) are fixed; the positions of the channel steel assembly and the laminated plate are determined according to the stress conditions of the test piece under different working conditions.
The invention can flexibly adjust the positions of the channel steel and the laminated board according to the specific test requirements and test objects, thereby ensuring that the stress mode and the position of the test piece of the cockpit door meet the test requirements; the channel steel assembly and the laminated board are matched for use, different force application positions can be determined according to specific test requirements, and test required loads are evenly and stably transmitted to the cockpit door test piece through the laminated board.
The displacement sensor is respectively arranged on the hydraulic cylinder and a displacement measuring point at a designated position on the test piece (namely, the cockpit door) and is used for measuring the magnitude of applied load and the deformation of the test piece (namely, the cockpit door).
Furthermore, the channel steel assembly, the laminated plate, the pulling pressure sensor and the hydraulic cylinder are all multiple.
Furthermore, the channel steel assembly comprises a channel steel assembly I8 and a channel steel assembly II 10;
the laminated board comprises a laminated board I7 and a laminated board II 9;
the pulling pressure sensor comprises a pulling pressure sensor I11 and a pulling pressure sensor II 13;
the hydraulic cylinder comprises a hydraulic cylinder I12 and a hydraulic cylinder II 14;
one end of a tension pressure sensor I11 is connected with a hydraulic cylinder I12, and the other end of the tension pressure sensor is connected with a channel steel component I; one end of the laminated board I is connected with the channel steel assembly I, and the other end of the laminated board I is in contact with the cockpit door test piece 6;
one end of the tension and pressure sensor II 13 is connected with the hydraulic cylinder II 14, and the other end of the tension and pressure sensor II is connected with the channel steel assembly II 10; laminate II 9 is attached to channel assembly II 10 on one end and is in contact with cockpit door trial 6 on the other end (as shown in FIG. 3).
Examples
The static test platform of the cockpit door applied to the static test of the cockpit door of a large-scale aircraft for civil use is taken as an embodiment to explain the static test platform in detail, and the static test platform also has a guiding function on the static test of the cockpit door of the large-scale aircraft applied to other transportation.
Referring to fig. 1 to 3, in an embodiment of the present invention, a cockpit door static test platform includes a test platform frame a and a test device B. The test equipment B is installed on the test platform frame A, and the test platform frame A comprises a test platform frame assembly 1 and a switching base.
The upper end of the test platform frame assembly 1 is provided with 1 fastener mounting hole, and the upper end of the cockpit door test piece upright post assembly 2 can be directly fixed through a screw, a nut and a washer; the lower end of the test platform frame assembly 1 is connected with the adapter base 13 through 4 screws, and the lower end of the cockpit door test piece stand column assembly 2 is connected with the adapter base I3 through 4 bolts and nuts so as to fix the lower end of the cockpit door test piece stand column assembly 2 on the test platform frame assembly 1; the right side of the test platform frame assembly 1 is connected with the switching base II 5 through a fastening piece, and the cockpit door test piece hinge plate assembly 5 is connected with the switching base II 5 through 13 screws, so that the cockpit door test piece 6 is fixed on the test platform frame assembly 1.
Switching base I3 and switching base II 5 have guaranteed that this connected mode is unanimous with the installation mode on the cockpit door machine, and the dismouting is convenient. The test platform frame assembly 1 is formed by welding a plurality of channel steels, square steels and rectangular steels, has good bearing capacity, stable structure and simple manufacture, is made of common materials and has abundant sources. The length of the test platform frame A is about 1500mm, the width is about 1660mm, and the height is about 2130mm, so that the test platform frame A can reduce the occupied space as much as possible on the premise that the installation and fixation requirements of the cockpit door test piece 6 can be met.
The test equipment B comprises a laminated board I7, a channel steel component I8, a laminated board II 9, a channel steel component II 10, a pull pressure sensor I11, a hydraulic cylinder I12, a pull pressure sensor II 13, a hydraulic cylinder II 14 and a hand pump. The laminated board I7, the channel steel component I8, the tension and pressure sensor I11, the hydraulic cylinder I12 and the hand pump form a first group of force application devices (namely load application devices). The laminated plate II 9, the channel steel assembly II 10, the tension and pressure sensor 13, the hydraulic cylinder II 14 and the hand pump form a second group of force application devices (namely load application devices).
Wherein draw pressure sensor (draw pressure sensor I11, draw pressure sensor II 13 promptly) one end to pass through the fastener to be fixed on channel-section steel subassembly (i.e. channel-section steel subassembly I8, channel-section steel subassembly II 10), the other end passes through threaded connection on the pneumatic cylinder (i.e. pneumatic cylinder I12, pneumatic cylinder II 14). The hand pump and the hydraulic cylinder are installed in a universal connection mode, and the description is omitted.
The displacement sensors of the present embodiment are respectively installed on the hydraulic cylinder and displacement measurement points (such as loading position 1 and loading position 2) at designated positions on the test piece (i.e. cockpit door) for measuring the magnitude of the applied load and the deformation of the test piece (i.e. cockpit door).
F1, F2 in fig. 3 indicate the two components of the extreme inertial load (dead load) to which the test piece (i.e. the cockpit door) is subjected. For example: under this experimental operating mode, the testpieces (driving cabin door promptly) wholly bears the extreme inertial load (dead load) of FWD (aircraft head direction), for convenient experiment and make the testpieces atress even, adopts the component force formula application of force mode, carries out the load simulation testing machine actual stress condition under this experimental operating mode with two pneumatic cylinders. F1 and F2 in fig. 3 are the forces applied in the loading positions 1 and 2 of the present embodiment. The deformation test points 1 and 2 are used for measuring the deformation of the corresponding positions of the test piece (namely the cockpit door) according to the requirement of the cockpit door test outline.
The pull pressure sensor, the hydraulic cylinder and the hand pump are all existing equipment. The channel steel component is a section bar; channel assemblies and laminates are procured pieces. The channel steel and the laminated plate need to be cut according to the size of a test piece.
In the test process of the embodiment, the positions of the laminated board and the channel steel assembly are adjusted according to the specific test requirements so as to meet the requirements of the test load application position. The force application load is generated by pushing the hydraulic cylinder to pressurize through the hand-operated pump, and the requirement of applying the load stably, uniformly and accurately is met according to the test requirement. The channel steel assembly has good force transfer performance as a force transfer structure, the laminated board uniformly and stably transfers force to the pilot compartment door test piece in a dispersed manner, and the pilot compartment door test piece cannot be damaged by the laminated board. The size of the laminated board can be adjusted according to the specific test requirements and the state of the test piece, and the laminated board material is common wood, is about 25mm thick, is cheap and has abundant sources.
In the embodiment of the invention, the loading position 1 of the test piece (namely the cockpit door) is tested, and for the loading position 1 (as shown in a position F1 of fig. 3), the first test working condition is the load requirement 557.8N; the second test working condition is that the load requirement is 641.5N; the second test condition is a load requirement of 705.6N; the results of the test for the loading position 1 are shown in fig. 11-13.
FIG. 11 is a screenshot of a first loading mode (i.e., a first test condition, load requirement 557.8N for load position 1) according to an embodiment of the present invention at the end of loading; the value of the deformation in the record table is the displacement sensor value at the end of loading minus the initial value.
FIG. 12 is a screenshot illustrating a second loading mode (i.e., a second test condition, the load requirement for the loading position 1 is 641.5N) according to the embodiment of the present invention when the loading is finished; the value of the deformation in the record table is the displacement sensor value at the end of loading minus the initial value.
FIG. 13 is a screenshot illustrating the end of the third loading mode (i.e., the second test condition, the load requirement 705.6N for the loading position 1) according to the embodiment of the present invention; the value of the deformation in the record table is the displacement sensor value at the end of loading minus the initial value.
The embodiment of the invention also tests the loading position 2, and for the loading position 2 (as shown in the position F2 of FIG. 3), the first test working condition is the load requirement 557.8N; the second test working condition is that the load requirement is 641.5N; the second test condition is a load demand of 705.6N.
Fig. 14 and 15 show two parts of the recording table for the above-described test conditions, and fig. 14 and 15 are combined to form a complete recording table for the above-described test conditions.
As can be seen from fig. 11 to 15, the test device can test the test piece (i.e., the cockpit door) in different loading modes (test conditions), and simultaneously test a plurality of positions of the test piece (i.e., the cockpit door) to verify whether the test piece (i.e., the cockpit door) meets the airworthiness standard of the transportation type airplane.
Through the above experiments, the experimental conclusion of the present embodiment is that the airworthiness standard of the transport-class airplane is satisfied through (as shown in fig. 14 and fig. 15), i.e., the test piece (i.e., the cockpit door) of the present embodiment.
And (4) conclusion: the loading mode of the embodiment is stable, the loading size is adjustable, the loading control precision is high, the disassembly and the maintenance are easy, and the static test requirement of the cockpit door of the civil large-scale airplane can be met.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Other parts not described belong to the prior art.
Claims (8)
1. Cockpit door static test platform, its characterized in that: comprises a test platform frame (A) and test equipment (B); the test equipment (B) is arranged on a test platform frame (A), and the test platform frame (A) comprises a test platform frame assembly (1) and a switching base; the cockpit door test piece (6) is connected with the test platform frame (A) through a switching base;
the test equipment (B) comprises a load applying device and a load transferring device; the load applying device is arranged on the test platform frame (A) and is connected with the load transferring device;
the load transfer device is in contact with the cockpit door test piece (6).
2. The cockpit door static test platform of claim 1, wherein: the switching base comprises a switching base I (3) and a switching base II (5);
the upper end of the test platform frame assembly (1) is provided with a fastener, the lower end of the test platform frame assembly is provided with a switching base I (3), and the side surface of the test platform frame assembly is provided with a switching base II (5);
the upper end of the cockpit door test piece upright post assembly (2) is connected with the upper end of the test platform frame assembly (1) through a fastener, and the lower end of the cockpit door test piece upright post assembly is connected with the lower end of the test platform frame assembly (1) through a switching base I (3); the cockpit door test piece hinge plate component (4) is connected with the side face of the test platform frame component (1) through the adapter base II (5).
The test platform frame assembly is provided with a bolt mounting hole.
3. The cockpit door static test platform of claim 2, wherein: the upper end and the front end of the test platform frame (A) are provided with a plurality of fastener mounting holes.
4. The cockpit door static test platform of claim 3, wherein: the load applying device comprises a hydraulic cylinder and a hand pump, and the hand pump is connected with the hydraulic cylinder.
5. The cockpit door static test platform of claim 4, wherein: the load transfer device comprises a channel steel assembly, a laminated plate and a tension and pressure sensor; the pulling pressure sensor is respectively connected with the hydraulic cylinder and the channel steel component; one end of the laminated board is connected with the channel steel assembly, and the other end of the laminated board is contacted with a cockpit door test piece (6).
6. The cockpit door static test platform of claim 5, wherein: the channel steel assembly and the laminated board are both movable structures.
7. The cockpit door static test platform of claim 6, wherein: the channel-section steel subassembly, lamination board, draw pressure sensor, pneumatic cylinder all have a plurality ofly.
8. The cockpit door static test platform of claim 7, wherein: the channel steel component comprises a channel steel component I (8) and a channel steel component II (10);
the laminated board comprises a laminated board I (7) and a laminated board II (9);
the pulling pressure sensor comprises a pulling pressure sensor I (11) and a pulling pressure sensor II (13);
the hydraulic cylinder comprises a hydraulic cylinder I (12) and a hydraulic cylinder II (14);
one end of a tension pressure sensor I (11) is connected with a hydraulic cylinder I (12), and the other end of the tension pressure sensor I is connected with a channel steel component I (8); one end of the laminated board I (7) is connected with the channel steel component I (8), and the other end of the laminated board I is in contact with the cockpit door test piece (6);
one end of the tension and pressure sensor II (13) is connected with the hydraulic cylinder II (14), and the other end of the tension and pressure sensor II is connected with the channel steel component II (10); one end of the laminated board II (9) is connected with the channel steel assembly II (10), and the other end of the laminated board II is in contact with the cockpit door test piece (6).
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| CN202110795857.7A CN113607559A (en) | 2021-07-14 | 2021-07-14 | Static test platform for cockpit door |
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| CN202110795857.7A CN113607559A (en) | 2021-07-14 | 2021-07-14 | Static test platform for cockpit door |
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