CN111924129A - Airplane cargo hold weight-sharing carrier plate, load test device and method - Google Patents
Airplane cargo hold weight-sharing carrier plate, load test device and method Download PDFInfo
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- CN111924129A CN111924129A CN202010814697.1A CN202010814697A CN111924129A CN 111924129 A CN111924129 A CN 111924129A CN 202010814697 A CN202010814697 A CN 202010814697A CN 111924129 A CN111924129 A CN 111924129A
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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 provides a concentrated-load-sharing carrier plate of an airplane cargo compartment and a load test device and method, wherein an A-type load-sharing buckle plate is arranged at the bottom layer, and a B-type load-sharing buckle plate and a C-type load-sharing buckle plate are fixed in parallel at the middle part of the tops of two groups of A-type load-sharing buckle plates; the two groups of the type-A load-sharing buckle plates are respectively provided with a type-D load-sharing buckle plate and a type-E load-sharing buckle plate which are symmetrically arranged at the two sides of the top of the two groups of the type-A load-sharing buckle plates; all the load-sharing pinch plates are spliced and combined to form a strip-shaped integral bearing platform, and a transition plate structure is arranged at one end of the integral bearing platform through a connecting pin. The transition plate is paved on the cargo compartment floor of the airplane and used as a transition plate between the wheels of the weight-collecting wheel type equipment and the cargo compartment floor of the airplane, so that the wheels are prevented from directly contacting the cargo compartment floor, the weight of the weight-collecting equipment is effectively loaded in a sub-mode by increasing the contact area with the cargo compartment floor of the airplane, and the cargo compartment and the airplane body are prevented from being damaged due to the fact that local loads exceed the bearing capacity of the cargo compartment floor of the airplane.
Description
Technical Field
The invention relates to the field of test equipment of an airplane cargo hold collection and redistribution carrier plate, in particular to an airplane cargo hold collection and redistribution carrier plate, a load test device and a load test method.
Background
Due to the heavy weight of some heavy wheeled equipment, such as heavy remote rocket guns, heavy armored assault vehicles, etc., the transportability is poor, causing the local load on its load-bearing surface to exceed the maximum allowable load-bearing capacity of the length of the load-bearing surface of the transporter. Direct loading during transport can cause the floor of the cargo hold of the transporter to bend, deform, or even damage. Therefore, a corresponding load sharing scheme and measures are needed to disperse the pressure of the weight collecting equipment on the cargo compartment floor of the conveyor, so that the aim of safe transportation is fulfilled.
In addition, in the process of demonstrating the load sharing scheme, analog simulation and finite element strength analysis are often carried out by means of analysis software to carry out aid decision making, but the deviation of an analysis result is often caused because boundary conditions such as constraint and load applied in the analysis process are not consistent with the actual working condition, and potential safety hazards exist.
Disclosure of Invention
In order to solve the technical problems, the invention provides an aircraft cargo hold collection and re-distribution carrier plate and a load test device and a method, which can simulate the actual load distribution state and the actual working condition of collection and re-distribution equipment in an aircraft cargo hold, measure and collect pressure values of different areas under the collection and re-distribution working condition by adopting a plurality of pressure sensors distributed according to a rectangular array on the bottom plane of the carrier plate, display the pressure values of different areas of the bottom plane of the carrier plate in real time through data acquisition and processing software, comprehensively analyze the load distribution efficiency and the load distribution effect of the collection and re-distribution carrier plate according to the measured data and the distribution condition thereof, verify whether the result and the data analyzed by adopting simulation and finite element strength analysis software are consistent with the actual load distribution state or not through data comparison, demonstrate and decide the feasibility of a load distribution scheme according to the fact that the maximum local pressure after load distribution is less than the minimum local pressure born by the aircraft cargo hold floor and comprehensively consider factors such as safety factor and the like, evidence and data support may be provided for demonstration, validation and decision-making of the loading scheme.
In order to achieve the technical features, the invention is realized as follows: a concentrated-load carrier plate for an airplane cargo hold comprises an A-type load-sharing buckle plate, a B-type load-sharing buckle plate, a C-type load-sharing buckle plate, a D-type load-sharing buckle plate and an E-type load-sharing buckle plate which are different in specification and size; the A-type load-sharing buckle plates are arranged on the bottom layer, and the B-type load-sharing buckle plates and the C-type load-sharing buckle plates are fixed in parallel at the middle parts of the tops of the two groups of the A-type load-sharing buckle plates; the two groups of the type-A load-sharing buckle plates are respectively provided with a type-D load-sharing buckle plate and a type-E load-sharing buckle plate which are symmetrically arranged at the two sides of the top of the two groups of the type-A load-sharing buckle plates; all the load-sharing pinch plates are spliced and combined to form a strip-shaped integral bearing platform, and a transition plate structure is arranged at one end of the integral bearing platform through a connecting pin.
The A-type load-sharing buckle plate comprises a first bearing plate, edge-sealed rectangular pipes are symmetrically arranged on the edges of two sides of the top of the first bearing plate, and first rectangular pipes are arranged between the edge-sealed rectangular pipes at intervals;
the B-type load-sharing buckle plate comprises a second bearing plate, and second rectangular pipes are arranged at the bottom end of the second bearing plate at intervals;
the C-shaped load-sharing buckle plate comprises a third bearing plate, and a third rectangular pipe is arranged at the bottom of the third bearing plate;
the D-shaped load-sharing buckle plate comprises a fourth bearing plate, and fourth rectangular pipes are arranged at the bottom of the fourth bearing plate at intervals;
the E-shaped load-sharing buckle plate comprises a fifth bearing plate, and a fifth rectangular pipe is arranged at the bottom of the fifth bearing plate.
The section shape and the section size of the D-shaped load-sharing buckle plate are completely consistent with those of the B-shaped load-sharing buckle plate, and the length of the D-shaped load-sharing buckle plate is 1/2 of that of the B-shaped load-sharing buckle plate;
the shape and the size of the cross section of the E-shaped load-sharing buckle plate are completely consistent with those of the C-shaped load-sharing buckle plate, and the length of the E-shaped load-sharing buckle plate is 1/2 of that of the C-shaped load-sharing buckle plate;
the length sizes of the A-type load-sharing buckle plate, the B-type load-sharing buckle plate and the C-type load-sharing buckle plate are the same.
When the split-load buckle plates are longitudinally spliced and combined, the lower-layer split-load buckle plate completely uses the A-type split-load buckle plate, the upper-layer split-load buckle plate uses the D-type split-load buckle plate and the E-type split-load buckle plate at two ends, the middle part uses the B-type split-load buckle plate and the C-type split-load buckle plate, and the butt joint seam of the upper and lower split-load plates is convenient to stagger during longitudinal splicing.
When along horizontal concatenation and combination, the lower floor divides and carries the buckle and all uses A type branch to carry the buckle, selects D type branch to carry the buckle and B type branch to carry the buckle as upper strata branch and carries the board to inlay and the spiral-lock directly over the horizontal butt joint seam of lower floor's A type branch carries the buckle, ensures that the butt joint seam when the horizontal concatenation can be staggered from top to bottom branch carries the board, all the other positions according to the concrete quantity of concatenation and the suitable upper strata branch of scope selection carry the buckle fill up can.
The transition plate structure comprises a bottom plate, a top plate is fixedly supported at the top of the bottom plate through a plurality of first studs and second studs, an insertion head is arranged at the end part of each second stud, the insertion head is fixedly connected with the whole bearing platform through a connecting pin, and a pin hole matched with the connecting pin is machined at the top of the insertion head.
The test device for the load test of the airplane cargo hold collection and redistribution carrier plate comprises a plurality of auxiliary bottom plates for supporting the whole airplane cargo hold collection and redistribution carrier plate, wherein the auxiliary bottom plates are assembled into a support rail structure which is arranged in parallel, a test bottom plate is adopted at the tail end of one support rail structure to replace one group of auxiliary bottom plates, pressure sensor assemblies are arranged on the top of the test bottom plates in a rectangular array mode, a transition inclined platform is butted at the tail end of the support rail structure on the side opposite to the pressure sensor assemblies, the pressure sensor assemblies are connected with a measurement and control platform for signal transmission and acquisition through signal lines, and the measurement and control platform is connected with an industrial computer for data storage and analysis.
The testing bottom plate comprises a testing support frame, a testing support plate is fixed to the top of the testing support frame, an assembling reference hole is machined in one corner of the testing support plate, a first lifting lug is arranged on the outer side wall of the testing support frame, and first reinforcing ribs which are arranged longitudinally and transversely are arranged in the testing support frame.
The auxiliary bottom plate comprises an auxiliary supporting frame, an auxiliary supporting plate is fixed at the top of the auxiliary supporting frame, a second lifting lug is arranged on the outer side wall of the auxiliary supporting frame, and second reinforcing ribs which are arranged longitudinally and transversely are arranged in the auxiliary supporting plate;
the transition sloping platform comprises a sloping platform bottom plate, the top of the sloping platform bottom plate is supported and provided with a sloping platform top plate through a sloping platform supporting frame, and the outer side wall of the sloping platform supporting frame is provided with a third lifting lug;
the pressure sensor assembly comprises a pressure sensor, the pressure sensor is fixed to the top of a testing support plate of the testing bottom plate, a measuring support head is fixed to the top of the pressure sensor, and the measuring support head is in contact fit with the bottom end of the airplane cargo hold weight collection support plate.
The method for carrying out the load test on the airplane cargo hold weight-sharing carrier plate by adopting the test device comprises the following steps:
step 1: butting and installing a test bottom plate, an auxiliary bottom plate and a transition sloping platform;
step 2: checking and leveling a measuring support head on the pressure sensor, and adjusting the upper plane of the measuring support head to be coplanar;
and step 3: inspecting and leveling the auxiliary bottom plate;
and 4, step 4: the data transmission signal line and the power line are connected with the measurement and control console;
and 5: laying an airplane cargo hold collection redistribution carrier plate to be tested on the test bottom plate and the auxiliary bottom plate;
step 6: the mounting of the stop blocks prevents the concentrated weight distribution carrier plate of the aircraft cargo hold from moving in a dislocation in the test process;
and 7: connecting an industrial computer, and turning on a power supply and data acquisition and analysis software;
and 8: turning on a power supply of a measurement and control console, performing zero calibration on the pressure sensor, and checking and testing a data measurement, acquisition and transmission system of the pressure sensor to a normal working state;
and step 9: a specially-assigned person directs that the weight-collecting wheel type equipment for the loading test slowly drives into the upper plane of the weight-collecting carrier plate of the cargo hold of the airplane to carry out loading and testing;
step 10: aiming at different axle weights of the front and the back of the wheel type equipment, selecting the wheel with the largest axle weight for loading and testing;
step 11: taking not less than 3 positions in the data measurement area to respectively carry out loading and testing;
step 12: respectively acquiring test data of different loading positions, and storing data acquisition and processing results in computer software;
step 13: a specially-assigned person directs that the weight-collecting wheel type equipment for the loading test is slowly driven out of the upper plane of the weight-collecting carrier plate of the cargo hold of the airplane and driven away from the test device;
step 14: by comparing and analyzing the test data, analyzing, demonstrating and deciding the load sharing effect, the load sharing scheme and the load sharing measure, the analysis and demonstration principle is as follows:
a: the wider the distribution range of the measured data, the more uniform the distribution and the more gradual the data transition, the better the load sharing effect is;
b: the smaller the ratio between the maximum pressure after load sharing and the maximum pressure before load sharing is, the better the load sharing effect is;
c: and demonstrating and deciding feasibility of the load sharing scheme according to the fact that the maximum local pressure after load sharing is smaller than the minimum local pressure which can be borne by the cargo compartment floor of the airplane and factors such as safety factors are comprehensively considered.
The invention has the following beneficial effects:
1. the heavy-load collecting and distributing equipment is paved on the cargo compartment floor of the airplane and is used as a transition plate between wheels of the heavy-load collecting wheel type equipment and the cargo compartment floor of the airplane, so that the wheels are prevented from directly contacting the cargo compartment floor, the weight of the heavy-load collecting equipment is effectively distributed by increasing the contact area with the cargo compartment floor of the airplane, and the cargo compartment and the airplane body are prevented from being damaged due to the fact that local loads exceed the bearing capacity of the cargo compartment floor of the airplane.
2. The problems of insufficient floor bearing capacity, large potential safety hazard and the like existing in the process of delivering heavy wheeled equipment by a transporter can be effectively solved.
3. The split-type vertical embedded buckling type load-sharing buckle plate has the advantages that the split-type load-sharing buckle plates of 5 different specifications and sizes are freely spliced and combined to meet the use requirements of the load-sharing wheel type equipment of different specifications and sizes, the split-type vertical embedded buckling type load-sharing equipment and the split-type vertical embedded buckling type load-sharing equipment are combined, the butt joint seams are staggered when the split-type vertical buckling type load-sharing equipment and the split-type vertical buckling type load-sharing equipment are combined, the stress state is improved.
4. The transition inclined table is arranged along with the load sharing equipment and used for connecting the height difference between the load sharing buckle plate and the cargo compartment floor to realize the gentle transition of an inclined angle, and the wheel type equipment can smoothly drive into the upper plane of the load sharing plate to realize the loading and load sharing of the wheel type equipment in the cargo compartment.
5. The load-sharing pinch plate is made of high-strength aluminum alloy materials and has the advantages of light weight, simplicity in operation, convenience in use and maintenance and the like.
6. The load sharing pinch plates are directly embedded and buckled up and down during splicing, other connecting pieces and positioning pieces do not need to be added, the operation is simple, and the time for unfolding and folding the load sharing equipment can be effectively shortened.
7. The collection and heavy-load distribution equipment provides a material foundation for the future air containerized transportation of large-scale collection and heavy equipment and materials, and improves the air transportation guarantee efficiency.
8. The test device can simulate the actual load distribution state and the actual working condition of the load collection equipment in the cargo hold of the airplane, and a plurality of pressure sensors distributed according to a rectangular array are adopted on the bottom plane of the load distribution plate to measure and collect the pressure values of different areas under the load collection working condition.
9. In the test process, the pressure values of different areas of the bottom plane of the load-sharing plate can be displayed in real time through data acquisition and processing software.
10. The load sharing efficiency and the load sharing effect of the integrated load sharing carrier plate can be comprehensively analyzed according to the measured data and the distribution condition thereof, and the analysis principle is as follows:
the wider the distribution range of the measured data is, the more uniform the distribution is, and the more gradual the data transition is, the better the load sharing effect is;
the smaller the ratio of the maximum pressure after the load sharing and the maximum pressure before the load sharing is, the better the load sharing effect is.
11. And whether the result and the data analyzed by adopting simulation and finite element strength analysis software are consistent with the actual load sharing stress state or not can be verified through data comparison.
12. The feasibility of the load sharing scheme can be demonstrated and decided according to the fact that the maximum local pressure after load sharing is smaller than the minimum local pressure born by the cargo compartment floor of the airplane and factors such as safety factors are comprehensively considered.
13. Evidence and data support may be provided for demonstration, validation and decision-making of the loading scheme.
14. The test device and the test method can improve the safety and reliability of the airplane cargo compartment concentrated reloading scheme.
Drawings
The invention is further illustrated by the following figures and examples.
FIG. 1 is a three-dimensional view of the present invention.
Fig. 2 is an exploded view of the present invention.
FIG. 3 is a first perspective three-dimensional view of the assembly of five load-sharing gusset plates of the present invention.
FIG. 4 is a second perspective three-dimensional view of the assembly of five load-sharing gusset plates of the present invention.
Fig. 5 is an exploded view of the five load-sharing pinch plates of the present invention.
Fig. 6 is a first perspective three-dimensional view of a transition plate structure of the present invention.
Fig. 7 is a second perspective three-dimensional view of a transition plate structure of the present invention.
Fig. 8 is an exploded view of the transition plate structure of the present invention.
Fig. 9 is a first perspective three-dimensional view of the arrangement of the airplane cargo bay collection redistribution carrier plate of the invention on a test rig.
Fig. 10 is a second perspective three-dimensional view of the arrangement of the airplane cargo bay collection redistribution carrier plate of the invention on a test apparatus.
FIG. 11 is a first perspective three-dimensional view of a test device of the present invention.
FIG. 12 is a second perspective three-dimensional view of the test device of the present invention.
FIG. 13 is a first perspective three-dimensional view of a test base of the present invention.
FIG. 14 is a second perspective three-dimensional view of a test base of the present invention.
FIG. 15 is a first perspective three-dimensional view of a transition ramp of the present invention.
FIG. 16 is a second perspective three-dimensional view of a transition ramp of the present invention.
Fig. 17 is a first perspective three-dimensional view of an auxiliary base plate of the present invention.
Fig. 18 is a second perspective three-dimensional view of an auxiliary floor according to the present invention.
FIG. 19 is a schematic representation of the present invention during a particular test.
In the figure: the device comprises a transition plate structure 1, a connecting pin 2, a D-type load-sharing buckle plate 3, a B-type load-sharing buckle plate 4, an A-type load-sharing buckle plate 5, a C-type load-sharing buckle plate 6, an E-type load-sharing buckle plate 7, a transition sloping platform 8, an auxiliary bottom plate 9, a pressure sensor assembly 10, a test bottom plate 11, an industrial computer 12, a measurement and control platform 13 and a weight-collecting wheel type device 14;
a top plate 101, a second stud 102, a bottom plate 103, an insertion head 104, a bolt hole 105, a sealing plate 106 and a first stud 107;
a fourth bearing plate 301 and a fourth rectangular tube 302;
a second carrier plate 401, a second rectangular tube 402;
the device comprises a first bearing plate 501, an edge-sealed rectangular pipe 502 and a first rectangular pipe 503;
a third bearing plate 601 and a third rectangular tube 602;
a fifth bearing plate 701 and a fifth rectangular tube 702;
a sloping table top plate 801, a sloping table bottom plate 802, a sloping table supporting frame 803 and a third lifting lug 804;
an auxiliary support frame 901, an auxiliary support plate 902, a second lifting lug 903 and a second reinforcing rib 904;
the test device comprises a test supporting plate 1101, an assembly reference hole 1102, a first lifting lug 1103, a test supporting frame 1104 and a first reinforcing rib 1105.
Detailed Description
Embodiments of the present invention will be further described with reference to the accompanying drawings.
Example 1:
referring to fig. 1-8, an airplane cargo hold weight-sharing carrier plate comprises five types of A-type load-sharing pinch plates 5, B-type load-sharing pinch plates 4, C-type load-sharing pinch plates 6, D-type load-sharing pinch plates 3 and E-type load-sharing pinch plates 7 with different specifications and sizes; the A-type load-sharing buckle plates 5 are arranged at the bottom layer, and the B-type load-sharing buckle plates 4 and the C-type load-sharing buckle plates 6 are fixed in parallel at the middle parts of the tops of the two groups of the A-type load-sharing buckle plates 5; the two groups of the type-A load-sharing buckle plates 5 are respectively provided with a type-D load-sharing buckle plate 3 and a type-E load-sharing buckle plate 7 which are symmetrically arranged at the two sides of the top of the buckle plate; all the load-sharing pinch plates are spliced and combined to form a strip-shaped integral bearing platform, and a transition plate structure 1 is arranged at one end of the integral bearing platform through a connecting pin 2. When the load sharing equipment with the structure is used, the load sharing equipment is paved on the cargo compartment floor of an airplane and is used as a transition plate between the wheels of the load-sharing wheel type equipment and the cargo compartment floor of the airplane, so that the wheels are prevented from directly contacting the cargo compartment floor, the weight of the load sharing equipment is effectively shared by increasing the contact area with the cargo compartment floor of the airplane, and the situation that the local load exceeds the bearing capacity of the cargo compartment floor of the airplane to damage the cargo compartment and the airplane body is prevented.
Further, the type a load-sharing buckle plate 5 comprises a first bearing plate 501, edge-sealed rectangular pipes 502 are symmetrically arranged on edges of two sides of the top of the first bearing plate 501, and first rectangular pipes 503 are arranged between the edge-sealed rectangular pipes 502 at intervals. The first bearing plate 501 is made of a patterned anti-slip aluminum plate, and the edge-sealed rectangular pipe 502 and the first rectangular pipe 503 are made of rectangular aluminum pipes.
Further, the type-B load-sharing buckle plate 4 comprises a second bearing plate 401, and second rectangular tubes 402 are arranged at the bottom end of the second bearing plate 401 at intervals. The second bearing plate 401 is made of a patterned anti-slip aluminum plate, and the second rectangular tube 402 is made of a rectangular aluminum tube.
Further, the C-shaped load-sharing buckle 6 comprises a third bearing plate 601, and a third rectangular pipe 602 is arranged at the bottom of the third bearing plate 601. The third bearing plate 601 is made of a patterned anti-skid aluminum plate, and the third rectangular pipe 602 is made of a rectangular aluminum pipe.
Further, the D-type load-sharing buckle plate 3 comprises a fourth bearing plate 301, and fourth rectangular tubes 302 are arranged at the bottom of the fourth bearing plate 301 at intervals. The fourth bearing plate 301 is made of a patterned anti-slip aluminum plate, and the fourth rectangular tube 302 is made of a rectangular aluminum tube.
Further, the E-shaped load-sharing buckle 7 comprises a fifth bearing plate 701, and a fifth rectangular pipe 702 is arranged at the bottom of the fifth bearing plate 701. The fifth bearing plate 701 is made of a patterned anti-slip aluminum plate, and the fifth rectangular pipe 702 is made of a rectangular aluminum pipe.
Furthermore, the cross-sectional shape and the cross-sectional dimension of the D-shaped load-sharing buckle plate 3 are completely consistent with those of the B-shaped load-sharing buckle plate 4, and the length of the D-shaped load-sharing buckle plate 3 is 1/2 of that of the B-shaped load-sharing buckle plate 4; the shape and the size of the cross section of the E-shaped load-sharing buckle plate 7 are completely consistent with those of the C-shaped load-sharing buckle plate 6, and the length of the E-shaped load-sharing buckle plate 7 is 1/2 of that of the C-shaped load-sharing buckle plate 6; the A-type load-sharing buckle plate 5, the B-type load-sharing buckle plate 4 and the C-type load-sharing buckle plate 6 are the same in length size.
Furthermore, when the split-load buckle plates are longitudinally spliced and combined, the lower-layer split-load buckle plate completely uses the A-type split-load buckle plate 5, the upper-layer split-load buckle plate uses the D-type split-load buckle plate 3 and the E-type split-load buckle plate 7 at two ends, the middle part uses the B-type split-load buckle plate 4 and the C-type split-load buckle plate 6, and the butt joint seam of the upper split-load plate and the lower split-load plate is staggered when the split-load buckle plates.
Further, when along horizontal concatenation and combination, the lower floor divides and carries the buckle 5 that all uses A type branch, selects D type branch to carry buckle 3 and B type branch to carry buckle 4 as upper strata branch and carries the board to inlay and the spiral-lock directly over the horizontal butt joint seam of lower floor A type branch year buckle 5, ensures that the butt joint seam when the horizontal concatenation can be stagger to the branch support board from top to bottom, all the other positions select suitable upper strata branch to carry the buckle to fill up according to the concrete quantity and the scope of concatenation can.
Further, the transition plate structure 1 comprises a bottom plate 103, a top plate 101 is fixedly supported on the top of the bottom plate 103 through a plurality of first studs 107 and second studs 102, an end part of the second stud 102 is provided with an insertion head 104, the insertion head 104 is fixedly connected with the integral bearing platform through a connecting pin 2, and a pin hole 105 used for being matched with the connecting pin 2 is processed on the top of the insertion head 104.
The split-type vertical embedded buckling type load-sharing buckle plate has the advantages that the split-type load-sharing buckle plates of 5 different specifications and sizes are freely spliced and combined to meet the use requirements of the load-sharing wheel type equipment of different specifications and sizes, the split-type vertical embedded buckling type load-sharing equipment and the split-type vertical embedded buckling type load-sharing equipment are combined, the butt joint seams are staggered when the split-type vertical buckling type load-sharing equipment and the split-type vertical buckling type load-sharing equipment are combined, the stress state is improved. The transition inclined table is arranged along with the load sharing equipment and used for connecting the height difference between the load sharing buckle plate and the cargo compartment floor to realize the gentle transition of an inclined angle, and the wheel type equipment can smoothly drive into the upper plane of the load sharing plate to realize the loading and load sharing of the wheel type equipment in the cargo compartment.
Example 2:
referring to fig. 9-19, the test device for carrying out the load test on the aircraft cargo hold collection and redistribution carrier plate comprises a plurality of auxiliary bottom plates 9 for supporting the whole aircraft cargo hold collection and redistribution carrier plate, a plurality of the auxiliary bottom plates 9 are assembled and combined into a support rail structure arranged in parallel, a test bottom plate 11 is adopted at the tail end of one support rail structure to replace one group of the auxiliary bottom plates 9, pressure sensor assemblies 10 are arranged at the tops of the test bottom plates 11 in a rectangular array, transition ramps 8 are butted at the tail ends of the support rail structures at the side opposite to the pressure sensor assemblies 10, the pressure sensor assemblies 10 are connected with a measurement and control table 13 for signal transmission and acquisition through signal lines, and the measurement and control table 13 is connected with an industrial computer 12 for data storage and analysis. The testing device is adopted to distribute and install a plurality of pressure sensors on the testing bottom plate by adopting a rectangular array to construct a pressure data measuring system, the testing and control platform is adopted to install a signal transmitter and a data acquisition and transmission plate in the cabinet body to construct a pressure data acquisition and transmission system, and a notebook computer is arranged on the working table surface of the testing and control platform and data acquisition and processing software is installed to construct a data acquisition and processing system. The feasibility of the load sharing scheme can be demonstrated and decided according to the fact that the maximum local pressure after load sharing is smaller than the minimum local pressure born by the cargo compartment floor of the airplane and factors such as safety factors are comprehensively considered, and basis and data support can be provided for demonstration, verification and decision of the load sharing scheme.
Further, the testing base plate 11 includes a testing support frame 1104, a testing support plate 1101 is fixed to the top of the testing support frame 1104, an assembly reference hole 1102 is machined in one corner of the testing support plate 1101, a first lifting lug 1103 is arranged on the outer side wall of the testing support frame 1104, and first reinforcing ribs 1105 arranged in a vertical and horizontal manner are arranged inside the testing support frame 1104. The test base plate 11 can be used to effectively support the pressure sensor assembly 10.
The assembly datum hole 1102 is used for assembly and adjustment of the measurement support head, and can assist in high-precision digital assembly of the laser tracker to adjust the upper support surface of the measurement support head to be coplanar.
Further, the auxiliary bottom plate 9 includes an auxiliary support frame 901, an auxiliary support plate 902 is fixed on the top of the auxiliary support frame 901, a second lifting lug 903 is arranged on the outer side wall of the auxiliary support frame 901, and second reinforcing ribs 904 arranged in a vertical and horizontal manner are arranged inside the auxiliary support plate 902. Through the auxiliary bottom plate 9 for supporting the load-carrying plate.
Further, the transition sloping platform 8 comprises a sloping platform bottom plate 802, a sloping platform top plate 801 is supported and mounted at the top of the sloping platform bottom plate 802 through a sloping platform supporting framework 803, and a third lifting lug 804 is arranged on the outer side wall of the sloping platform supporting framework 803; the transition sloping platform is used for linking up the difference in height between auxiliary bottom plate and ground to realize the gentle transition of oblique angle, and the wheeled equipment of being convenient for can slowly roll into the last plane of auxiliary bottom plate.
Further, the pressure sensor assembly 10 includes a pressure sensor 1001, the pressure sensor 1001 is fixed on the top of a test support plate 1101 of the test base plate 11, a measurement support head 1002 is fixed on the top of the pressure sensor 1001, and the measurement support head 1002 is in contact fit with the bottom end of the aircraft cargo hold collection and redistribution board.
Example 3:
the method for carrying out the load test on the airplane cargo hold weight-sharing carrier plate by adopting the test device comprises the following steps:
step 1: butting and mounting a test bottom plate 11, an auxiliary bottom plate 9 and a transition sloping platform 8;
step 2: checking and leveling a measurement support head 1002 on a pressure sensor 1001, and adjusting the upper plane of the measurement support head 1002 to be coplanar;
and step 3: checking and levelling the auxiliary bottom plate 9;
and 4, step 4: a data transmission signal line and a power line connected with the measurement and control console 13;
and 5: laying an airplane cargo hold collection and redistribution carrier plate to be tested on the test bottom plate 11 and the auxiliary bottom plate 9;
step 6: the mounting of the stop blocks prevents the concentrated weight distribution carrier plate of the aircraft cargo hold from moving in a dislocation in the test process;
and 7: connecting the industrial computer 12, and turning on a power supply and data acquisition and analysis software;
and 8: turning on a power supply of the measurement and control console 13, performing zero calibration on the pressure sensor, and checking and testing a data measurement, acquisition and transmission system of the pressure sensor to a normal working state;
and step 9: a specially-assigned person directs that the weight-collecting wheel type equipment 14 for the loading test slowly drives into the upper plane of the airplane cargo compartment weight-collecting carrier plate for loading and testing;
step 10: aiming at different axle weights of the front and the back of the wheel type equipment, selecting the wheel with the largest axle weight for loading and testing;
step 11: taking not less than 3 positions in the data measurement area to respectively carry out loading and testing;
step 12: respectively acquiring test data of different loading positions, and storing data acquisition and processing results in computer software;
step 13: a specially-assigned person directs that the weight-collecting wheel type equipment 14 for the loading test is slowly driven out of the upper plane of the weight-collecting carrier plate of the cargo hold of the airplane and driven away from the test device;
step 14: by comparing and analyzing the test data, analyzing, demonstrating and deciding the load sharing effect, the load sharing scheme and the load sharing measure, the analysis and demonstration principle is as follows:
a: the wider the distribution range of the measured data, the more uniform the distribution and the more gradual the data transition, the better the load sharing effect is;
b: the smaller the ratio between the maximum pressure after load sharing and the maximum pressure before load sharing is, the better the load sharing effect is;
c: and demonstrating and deciding feasibility of the load sharing scheme according to the fact that the maximum local pressure after load sharing is smaller than the minimum local pressure which can be borne by the cargo compartment floor of the airplane and factors such as safety factors are comprehensively considered.
The working principle of the invention is as follows:
the invention provides a test device and a test method of an airplane cargo hold collection and re-distribution carrier plate, which can simulate the actual load distribution state and the actual working condition of collection and re-distribution equipment in an airplane cargo hold, measure and collect pressure values of different areas under the collection and re-distribution working condition by adopting a plurality of pressure sensors distributed according to a rectangular array on the bottom plane of the distribution plate, display the pressure values of different areas of the bottom plane of the distribution plate in real time through data acquisition and processing software, comprehensively analyze the load distribution efficiency and the load distribution effect of the collection and re-distribution carrier plate according to the measured data and the distribution condition thereof, verify whether the result and the data analyzed by adopting simulation and finite element strength analysis software are consistent with the actual load distribution stress state or not through data comparison, demonstrate and decide the feasibility of a load distribution scheme according to the fact that the maximum local pressure after load distribution is less than the minimum local pressure born by the airplane cargo hold floor and comprehensively consider factors such as safety factors and the like Verification and decision making provide basis and data support.
Claims (10)
1. The utility model provides an aircraft cargo hold collection redistribution carrier plate which characterized in that: the novel energy-saving type LED lamp comprises five type A load-sharing buckle plates (5), type B load-sharing buckle plates (4), type C load-sharing buckle plates (6), type D load-sharing buckle plates (3) and type E load-sharing buckle plates (7) with different specifications and sizes; the A-type load-sharing buckle plates (5) are arranged at the bottom layer, and the B-type load-sharing buckle plates (4) and the C-type load-sharing buckle plates (6) are fixed in parallel at the middle parts of the tops of the two groups of A-type load-sharing buckle plates (5); the two sides of the top of the two groups of A-type load-sharing buckle plates (5) are respectively and symmetrically provided with a D-type load-sharing buckle plate (3) and an E-type load-sharing buckle plate (7); all the load-sharing pinch plates are spliced and combined to form a long-strip-shaped integral bearing platform, and one end of the integral bearing platform is provided with a transition plate structure (1) through a connecting pin (2).
2. The test device of the airplane cargo bay gravity-sharing carrier plate as claimed in claim 1, wherein: the A-type load-sharing buckle plate (5) comprises a first bearing plate (501), edge-sealed rectangular pipes (502) are symmetrically arranged on the edges of two sides of the top of the first bearing plate (501), and first rectangular pipes (503) are arranged between the edge-sealed rectangular pipes (502) at intervals;
the B-type load-sharing buckle plate (4) comprises a second bearing plate (401), and second rectangular tubes (402) are arranged at the bottom end of the second bearing plate (401) at intervals;
the C-shaped load-sharing buckle plate (6) comprises a third bearing plate (601), and a third rectangular pipe (602) is arranged at the bottom of the third bearing plate (601);
the D-shaped load-sharing buckle plate (3) comprises a fourth bearing plate (301), and fourth rectangular tubes (302) are arranged at the bottom of the fourth bearing plate (301) at intervals;
the E-shaped load-sharing buckle plate (7) comprises a fifth bearing plate (701), and a fifth rectangular pipe (702) is arranged at the bottom of the fifth bearing plate (701).
3. The aircraft cargo bay collection redistribution carrier of claim 1, wherein: the section shape and the section size of the D-shaped load-sharing buckle plate (3) are completely consistent with those of the B-shaped load-sharing buckle plate (4), and the length of the D-shaped load-sharing buckle plate (3) is 1/2 of that of the B-shaped load-sharing buckle plate (4);
the shape and the size of the cross section of the E-shaped load-sharing buckle plate (7) are completely consistent with those of the C-shaped load-sharing buckle plate (6), and the length of the E-shaped load-sharing buckle plate (7) is 1/2 of that of the C-shaped load-sharing buckle plate (6);
the length sizes of the A-type load-sharing buckle plate (5), the B-type load-sharing buckle plate (4) and the C-type load-sharing buckle plate (6) are the same.
4. The aircraft cargo bay collection redistribution carrier of claim 1, wherein: when vertically splicing and combining, the lower-layer load-sharing buckle plate completely uses the A-type load-sharing buckle plate (5), the upper-layer load-sharing buckle plate uses the D-type load-sharing buckle plate (3) and the E-type load-sharing buckle plate (7) at the two ends, the middle part uses the B-type load-sharing buckle plate (4) and the C-type load-sharing buckle plate (6), and the butt joint seam of the upper and lower load-sharing plates is staggered when vertically splicing.
5. The aircraft cargo bay collection redistribution carrier of claim 1, wherein: when along horizontal concatenation and combination, the lower floor divides to carry the buckle and all uses A type branch to carry buckle (5), selects for use D type branch to carry buckle (3) and B type branch to carry buckle (4) as the upper strata branch to carry the board to inlay and the spiral-lock directly over the horizontal butt joint seam of lower floor A type branch carries buckle (5), ensures the butt joint seam when the branch support board can stagger horizontal concatenation from top to bottom, all the other positions select suitable upper strata branch to carry the buckle to fill up according to the concrete quantity and the scope of concatenation can.
6. The aircraft cargo bay collection redistribution carrier of claim 1, wherein: the transition plate structure (1) comprises a bottom plate (103), a top plate (101) is fixedly supported at the top of the bottom plate (103) through a plurality of first studs (107) and second studs (102), an insertion head (104) is arranged at the end part of each second stud (102), the insertion head (104) is fixedly connected with the whole bearing platform through a connecting pin (2), and a pin hole (105) matched with the connecting pin (2) is machined at the top of the insertion head (104).
7. Test device for carrying out a load test on an aircraft cargo bay weight-distribution carrier plate according to any one of claims 1 to 6, characterised in that: it is including being used for carrying out a plurality of auxiliary bottom plate (9) that support to whole aircraft cargo hold collection redistribution support plate, it is a plurality of auxiliary bottom plate (9) are assembled and are made up into parallel arrangement's support track structure, adopt test bottom plate (11) to replace one of them group auxiliary bottom plate (9) at one of them support track structure's end, are the rectangle permutation and arrange pressure sensor subassembly (10) at the top of test bottom plate (11), have transition sloping platform (8) at the end butt joint of the support track structure of one side relative with pressure sensor subassembly (10), pressure sensor subassembly (10) pass through the signal line and link to each other with measurement and control platform (13) that are used for signal transmission and collection, measurement and control platform (13) link to each other with industrial computer (12) that are used for data storage and analysis.
8. The testing device of claim 7, wherein: the testing bottom plate (11) comprises a testing support frame (1104), a testing support plate (1101) is fixed to the top of the testing support frame (1104), an assembling reference hole (1102) is machined in one corner of the testing support plate (1101), a first lifting lug (1103) is arranged on the outer side wall of the testing support frame (1104), and first reinforcing ribs (1105) which are arranged in a longitudinal and transverse mode are arranged in the testing support frame (1104).
9. The testing device of claim 7, wherein: the auxiliary bottom plate (9) comprises an auxiliary supporting frame (901), an auxiliary supporting plate (902) is fixed at the top of the auxiliary supporting frame (901), a second lifting lug (903) is arranged on the outer side wall of the auxiliary supporting frame (901), and second reinforcing ribs (904) which are arranged longitudinally and transversely are arranged in the auxiliary supporting plate (902);
the transition sloping table (8) comprises a sloping table bottom plate (802), the top of the sloping table bottom plate (802) is supported and provided with a sloping table top plate (801) through a sloping table supporting framework (803), and the outer side wall of the sloping table supporting framework (803) is provided with a third lifting lug (804);
the pressure sensor assembly (10) comprises a pressure sensor (1001), the pressure sensor (1001) is fixed to the top of a test support plate (1101) of a test bottom plate (11), a measurement support head (1002) is fixed to the top of the pressure sensor (1001), and the measurement support head (1002) is in contact fit with the bottom end of an aircraft cargo hold collection and redistribution support plate.
10. Method for carrying out a load test on an aircraft cargo bay collection and redistribution carrier plate according to claims 1 to 6 using a test rig according to any of claims 7 to 9, characterized in that it comprises the following steps:
step 1: butt joint and installation of a test bottom plate (11), an auxiliary bottom plate (9) and a transition sloping platform (8);
step 2: checking and leveling a measuring support head (1002) on a pressure sensor (1001), and adjusting the upper plane of the measuring support head (1002) to be coplanar;
and step 3: checking and levelling the auxiliary bottom plate (9);
and 4, step 4: a data transmission signal line and a power line which are connected with the measurement and control console (13);
and 5: laying an airplane cargo hold collection and redistribution carrier plate to be tested on the test bottom plate (11) and the auxiliary bottom plate (9);
step 6: the mounting of the stop blocks prevents the concentrated weight distribution carrier plate of the aircraft cargo hold from moving in a dislocation in the test process;
and 7: connecting an industrial computer (12), turning on a power supply and data acquisition and analysis software;
and 8: a power supply of the measurement and control console (13) is turned on, zero calibration is carried out on the pressure sensor, and the data measurement, acquisition and transmission system of the pressure sensor is checked and tested to be in a normal working state;
and step 9: a specially-assigned person directs that the weight-collecting wheel-type equipment (14) for the loading test slowly drives into the upper plane of the airplane cargo compartment weight-collecting carrier plate for loading and testing;
step 10: aiming at different axle weights of the front and the back of the wheel type equipment, selecting the wheel with the largest axle weight for loading and testing;
step 11: taking not less than 3 positions in the data measurement area to respectively carry out loading and testing;
step 12: respectively acquiring test data of different loading positions, and storing data acquisition and processing results in computer software;
step 13: a specially-assigned person directs that the weight-collecting wheel-type equipment (14) for the loading test is slowly driven out of the upper plane of the airplane cargo hold weight-collecting and distributing carrier plate and driven away from the test device;
step 14: by comparing and analyzing the test data, analyzing, demonstrating and deciding the load sharing effect, the load sharing scheme and the load sharing measure, the analysis and demonstration principle is as follows:
a: the wider the distribution range of the measured data, the more uniform the distribution and the more gradual the data transition, the better the load sharing effect is;
b: the smaller the ratio between the maximum pressure after load sharing and the maximum pressure before load sharing is, the better the load sharing effect is;
c: and demonstrating and deciding feasibility of the load sharing scheme according to the fact that the maximum local pressure after load sharing is smaller than the minimum local pressure which can be borne by the cargo compartment floor of the airplane and factors such as safety factors are comprehensively considered.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010814697.1A CN111924129A (en) | 2020-08-13 | 2020-08-13 | Airplane cargo hold weight-sharing carrier plate, load test device and method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010814697.1A CN111924129A (en) | 2020-08-13 | 2020-08-13 | Airplane cargo hold weight-sharing carrier plate, load test device and method |
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| CN111924129A true CN111924129A (en) | 2020-11-13 |
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| CN202010814697.1A Pending CN111924129A (en) | 2020-08-13 | 2020-08-13 | Airplane cargo hold weight-sharing carrier plate, load test device and method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114093211A (en) * | 2021-11-05 | 2022-02-25 | 河北汉光重工有限责任公司 | Full-section cargo hold roll-on training rack of conveyer |
-
2020
- 2020-08-13 CN CN202010814697.1A patent/CN111924129A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114093211A (en) * | 2021-11-05 | 2022-02-25 | 河北汉光重工有限责任公司 | Full-section cargo hold roll-on training rack of conveyer |
| CN114093211B (en) * | 2021-11-05 | 2024-04-12 | 河北汉光重工有限责任公司 | Rolling-on training bench for full-section cargo hold of conveyor |
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