CN112180127A - Model test bench and test method for aviation electrical system - Google Patents
Model test bench and test method for aviation electrical system Download PDFInfo
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- CN112180127A CN112180127A CN202010991711.5A CN202010991711A CN112180127A CN 112180127 A CN112180127 A CN 112180127A CN 202010991711 A CN202010991711 A CN 202010991711A CN 112180127 A CN112180127 A CN 112180127A
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- 238000012360 testing method Methods 0.000 title claims abstract description 112
- 238000010998 test method Methods 0.000 title claims abstract description 7
- 238000009434 installation Methods 0.000 claims abstract description 14
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 7
- 230000005540 biological transmission Effects 0.000 claims abstract description 5
- 238000004088 simulation Methods 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 6
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 238000004132 cross linking Methods 0.000 description 2
- 238000000429 assembly Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000012942 design verification Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/02—General constructional details
- G01R1/04—Housings; Supporting members; Arrangements of terminals
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D11/00—Component parts of measuring arrangements not specially adapted for a specific variable
- G01D11/28—Structurally-combined illuminating devices
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/02—General constructional details
- G01R1/04—Housings; Supporting members; Arrangements of terminals
- G01R1/0408—Test fixtures or contact fields; Connectors or connecting adaptors; Test clips; Test sockets
- G01R1/0425—Test clips, e.g. for IC's
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
Abstract
The invention belongs to the technical field of aviation aircraft bench tests, and discloses an aviation electrical system model test bench and a test method, wherein the test bench comprises the following steps: the movable wall plate support, the supporting plate, the telescopic top cover support, the clamping plate, the small wire harness support and the lighting assembly are arranged on the movable wall plate support; the movable wall plate support simulates a cabin wall of an aircraft, the supporting plate simulates a test piece mounting structural part, and the telescopic top cover support simulates a cabin top; wherein, the movable wallboard bracket is used for fixing and connecting other components of the test bench; the clamping plate is used for fixing the aluminum plate skin and is connected to the left frame plate and the right frame plate of the movable wallboard bracket; the small wiring harness bracket is used for testing the installation and laying of the power transmission and distribution cable and is connected to the clamping plate rib; the lighting assembly is used for testing on-site lighting and is connected to the panel of the movable wall plate bracket, so that the cost can be reduced, the space can be saved, and the multiplexing function of the test bed frame can be improved.
Description
Technical Field
The invention belongs to the technical field of aviation aircraft bench tests, and particularly relates to an aviation electrical system model test bench and a test method.
Background
Most of the existing model test bed configurations of the aviation electrical system are configuration modes of one model test bed or one model test room, the specific architecture is a plane table top or a customized simulation cabin, the plane table top is too simple and is only arranged in a plane, the mutual cross-linking among field test wire bundles, test cables and loading cables is complex, especially the influence characteristics of skins on the cable conduction characteristics cannot be simulated, and the customized simulation cabin is high in cost, poor in universality, high in test space requirement and single in function.
Disclosure of Invention
In view of the above technical problems, an object of the present invention is to provide an avionics system model test bed and a test method, which can reduce cost, save space, and improve the reuse function of the test bed.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
The first technical scheme is as follows:
an avionics system model test rig, the test rig comprising:
the device comprises a movable wallboard bracket 1, a supporting plate 2, a telescopic top cover bracket 3, a clamping plate 4, a small wiring harness bracket 5 and a lighting assembly 6;
the movable wall plate support simulates a cabin wall of an aircraft, the supporting plate simulates a test piece mounting structural part, and the telescopic roof support simulates a cabin roof;
wherein the movable wall plate bracket is used for fixing and connecting other components of the test bench;
the clamping plates are used for fixing the aluminum plate skin and are connected to the left frame plate and the right frame plate of the movable wallboard bracket;
the small wiring harness bracket is used for testing the installation and laying of the power transmission and distribution cable and is connected to the clamping plate rib;
the lighting assembly is used for testing field lighting and is connected to the panel of the movable wall plate bracket.
The first technical scheme of the invention has the characteristics and further improvements that:
(1) the movable wall plate support panel is uniformly provided with a plurality of strip holes, the support plate is provided with bolt holes matched with the strip holes on the movable wall plate support panel, and the support plate is fixed on the movable wall plate support panel through bolts.
(2) The plurality of strip holes are arranged at different horizontal positions and different height positions of the panel of the movable wall plate bracket;
the supporting plate can move left and right in the strip hole to adjust the position, and the supporting plate can also move up and down in the strip holes at different heights to adjust the position.
(3) The telescopic top cover support is fixed on the movable wall plate support beam connecting plate through bolts at two ends, bolt holes matched with the telescopic top cover support bolt holes are formed in the movable wall plate support beam connecting plate, and the width of the telescopic top cover support is adjusted through a horizontal pipe in the middle of the cover plate.
(4) The clamping plate is fixed on the movable wallboard support frame plate through a bolt, and a bolt hole in the movable wallboard support frame plate is matched with the clamping plate hole.
(5) The small wire harness support is fixed on a rib in the middle of a panel clamping plate of the movable wall plate support through a bolt, and a bolt hole matched with the bolt hole in the rib is formed in the small wire harness support.
(6) The lighting assembly is fixed on the panel of the movable wall plate support through bolts, bolt holes matched with the strip holes in the panel of the movable wall plate support are formed in the lighting assembly, and the mounting position of the lighting assembly is moved up and down and left and right according to the mounting requirements of a test piece.
The second technical scheme is as follows:
an aviation electrical system model combined type test bench comprises a plurality of test benches according to the first technical scheme;
a plurality of test benches are connected with each other by bolts.
The third technical scheme is as follows:
a test method of an aviation electrical system model test bench is applied to the test bench and comprises the following steps:
during testing, the simulation skin aluminum plate is fixed on the frame plates at the left, middle and right positions of the movable wallboard bracket through the clamping plates;
mounting the test piece on a supporting plate, mounting the test wire harness and the test cable in a front end bayonet of a small wire harness support, and butting interfaces on the test piece and the test cable; the test piece is a distribution box, a breaker plate, a generator controller, an emergency power supply, a power supply conversion box or an intelligent power distribution cabinet;
and finally, installing a simulation load according to the requirement of each test.
According to the technical scheme, the test bed of the model of the aviation electrical system is assembled by adopting the modularized components, the power distribution framework of the tested aviation electrical system is taken as a basis, and the optimal bed combination scheme is adopted, so that the problems of high cost, poor universality and single function of the existing test bed of the model of the aviation electrical system are effectively solved, and the test bed is suitable for the model test of the electrical system of most aviation aircrafts (such as fixed-wing aircrafts, helicopters, unmanned planes and floating airships).
Drawings
FIG. 1 is an isometric view of an avionics system model test rig provided in accordance with an embodiment of the present invention;
FIG. 2 is a bottom view of the structure of an avionics system model test rig;
FIG. 3 is an elevation view of a configuration of an avionics system model test rig;
FIG. 4 is a left side view of the configuration of an avionics system model test rig;
fig. 5 is a schematic structural view of a moving panel bracket according to an embodiment of the present invention;
FIG. 6 is a schematic structural view of a splint according to an embodiment of the present invention;
FIG. 7 is a schematic structural diagram of a modular test stand according to an embodiment of the present invention;
1-a movable wall plate support, 2-a supporting plate, 3-a telescopic top cover support, 4-a clamping plate, 5-a small wiring harness support and 6-a lighting assembly; 1-1-panel, 1-2-frame plate, 1-3-lock catch, 1-4-beam connecting plate, 1-5-strip hole, 2-1-supporting plate bolt hole and 4-1-clamping plate rib.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides an aviation electrical system model test bench, which adopts a modular combined framework and is shown in figure 1, which is formed by combining a movable wallboard bracket 1 (a simulation cabin wall, other components of a fixed and connected rack), a supporting plate 2 (a simulation test piece mounting structural part, a connected movable wallboard bracket), a telescopic top cover bracket 3 (a simulation cabin roof, a connecting two groups of movable wallboard brackets), a clamping plate 4 (used for fixing aluminum plate skins and connecting left and right frame plates of the movable wallboard bracket), a small wiring harness bracket 5 (used for testing the installation and laying of power transmission and distribution cables and connecting ribs on the clamping plate) and a lighting assembly 6 (used for testing the field lighting and connecting panels of the movable wallboard bracket), wherein layer board, scalable top cap support, splint, pencil little support and lighting components all install on removing the wallboard support, scalable top cap support is fixed on two sets of removal wallboard supports.
The model test bed for the aeronautical electrical system is shown in a bottom view in fig. 2, a front view in fig. 3 and a left view in fig. 4. The structure of the movable wallboard bracket is schematically shown in fig. 5, and the structure of the clamping plate is schematically shown in fig. 6.
The layer board passes through the bolt fastening on removing wallboard support panel, evenly be equipped with a plurality of rectangular holes on removing wallboard support panel, be equipped with on the layer board with remove the rectangular hole matched with bolt hole on the wallboard support panel, the layer board can remove the mounted position about the test piece installation needs from top to bottom, specifically be through removing the bolt of controlling connection installation layer board and removal wallboard support panel about removing in the rectangular hole on removing wallboard support panel and adjust, also can let bolt hole on the layer board and remove other rectangular holes matching on the wallboard support panel through reciprocating the layer board, reuse bolt fixes reciprocating of realization layer board.
The telescopic top cover bracket is fixed on the movable wall plate bracket beam connecting plate through bolts at two ends, bolt holes matched with the telescopic top cover bracket bolt holes are formed in the movable wall plate bracket beam connecting plate, and the width of the telescopic top cover bracket can be adjusted through a horizontal pipe in the middle of the cover plate.
The clamping plate is fixed on the movable wallboard support frame plate through a bolt, and a bolt hole in the movable wallboard support frame plate is matched with the clamping plate hole.
The small wire harness support is fixed on a rib in the middle of the panel clamping plate through a bolt, and a bolt hole matched with the bolt hole in the rib is formed in the support.
The lighting assembly passes through the bolt fastening on removing wallboard support panel, it evenly is equipped with a plurality of rectangular holes on the wallboard support panel to remove, be equipped with on the lighting assembly with remove rectangular hole matched with bolt hole on the wallboard support panel, lighting assembly can remove the mounted position about can be according to test piece installation needs, specifically for removing the bolt of controlling through removing on removing the wallboard support panel about rectangular downthehole connection installation lighting assembly and removing wallboard support panel and adjust, also can let bolt hole on the lighting assembly match with other rectangular holes on removing wallboard support panel through reciprocating lighting assembly, reuse bolt fixes reciprocating that realizes lighting assembly.
The combined test bench provided by the embodiment of the invention can be formed by connecting and combining any two movable wall plate supports through the upper lock catch and the lower lock catch on the left side and the right side of the supports, the number of the movable wall plate support combinations theoretically has no upper limit, and the combined test bench is determined according to the arrangement range of test pieces.
The embodiment of the invention also provides a combination method of the modular combined type aviation electrical system model test bed, which comprises the following steps:
step 1: determining the position of a first modularized movable support, in particular to determining the arrangement position of a primary distribution box mounting support according to the length of a main power system feeder line introduced into an arrangement area of a laboratory bench;
step 2: determining a rack form (a single-side rack or a double-side rack), specifically configuring one group or two groups of racks which are arranged in parallel and combined by modular movable supports according to a power distribution framework of a tested electrical system;
and step 3: determining the distance between the racks on the two sides, specifically, if a group of racks are configured, the racks can be flexibly arranged according to the space and operation requirements on the site under the condition of ensuring the effective access of a feeder line, if two groups of racks are configured, the distance between the two groups of racks needs to be determined according to the width size of an arrangement cabin body of an aircraft power distribution system, and specifically, the distance is realized by moving the parallel distance between the modular movable supports;
and 4, step 4: determining the arrangement direction of the rack, specifically determining the arrangement direction of the rack according to the distribution condition of the primary distribution boxes on the rack, if the primary distribution boxes are distributed on the left side and the right side of the cabin, the arrangement direction of the rack is recommended to be parallel to the introduction direction of the feeder line, and if the primary distribution boxes are distributed on one side of the cabin, the arrangement support of the primary distribution boxes of the rack is recommended to be close to the introduction direction of the feeder line;
and 5: determining the combined length of the gantry: firstly, preliminarily determining the length of a rack according to the installation position of a main power distribution device of a tested aviation electrical system on a machine, then properly optimizing the length of a wire according to the available space of a laboratory and combining the section and the turning radius of a cable, and finally determining the optimal rack combination length by integrating the conditions;
step 6: calculating the number of modular movable supports: specifically, the number of the modular movable supports is calculated according to the determined combined length and the length of the modular movable supports, and if the modular movable supports are double-sided, the number of the supports is doubled;
and 7: adjusting the height of the rack: specifically, the height of the rack is determined according to the height in the cabin of the aircraft or the height of the wiring channel, and then the height of the rack is adjusted through an upper adjusting wrench and a lower adjusting wrench of the modularized movable support, so that all the supports determined in the step 6 are adjusted to be at the same height;
and 8: a combined rack: preparing the number of the modularized movable supports calculated in the step 6, combining the modularized movable supports into a single-side rack by using the locking buckles on the left side and the right side, arranging the racks in the direction determined in the step 4, if the racks are the double-side racks, combining the racks into a single-side rack by adopting the same method, wherein the arrangement directions of the racks on the two sides are the same, and the distance between the racks on the two sides is movably adjusted according to the distance determined in the step 3;
and step 9: assembling a modular supporting plate: firstly assembling a modular support plate for installing a primary distribution box, wherein the installation height of the support plate can be determined by referring to the actual height in an aircraft cabin, and then determining the installation positions and heights of other power distribution devices by taking the primary distribution box as a coordinate and referring to the relative positions of the power distribution devices on the aircraft to complete the assembly of all the modular support plates;
step 10: assembling a modular top cover: the method specifically comprises the steps that whether a modular top cover is installed or not is determined according to the cross-linking condition of the distribution line of the tested aviation electrical system, if the left and right sides of the distribution cable are in left and right cross-connection, the modular top cover needs to be assembled at the corresponding cross-connection position, or the modular top covers are assembled completely, and if the left and right cross-connection condition of the distribution cable does not exist, the top cover does not need to be assembled;
step 11: assembling a clamping plate: specifically, the method comprises the steps of selecting and assembling according to the skin material characteristics of a tested aircraft, and if a conductive material is selected and a main power supply is an alternating current power supply, selecting a plate capable of simulating the skin characteristics for assembling, specifically, reliably fixing the plate on a modularized movable support by using a modularized clamp around;
step 12: assembling a small wire harness bracket: specifically, the wiring harness is arranged and installed according to the relative position of the wiring channel of the electrical system of the tested aircraft on the bulkhead of the aircraft, and the distance between the wiring harness and the plate in the step 11 can be adjusted by adjusting the height of the wiring harness bracket according to the distance between the wiring harness channel and the bulkhead;
step 13: assembling the modular lighting system components: the lighting system components are assembled at proper positions on the top of the modularized movable support, and the lighting system components are required to be free from interference with other components and provide effective lighting conditions for the site.
And (3) completing the combination of the modular combined type aviation electrical system model test bed in the steps 1-13, as shown in figure 7.
The model test bed and the combined test bed for the aviation electrical system provided by the embodiment of the invention have the advantages of simple structure, easiness in processing and low cost; the modular combination is adopted, the arrangement is flexible, and the space is saved; the distance between the power transmission and distribution cable and the skin can be adjusted by the height of the wire harness support, so that the test is close to a real aircraft environment, the verification is more sufficient, and the test conclusion can reflect the design condition of an electrical system of the aircraft more accurately; the movable wall plate supports can be combined in pairs at will, and the length of the rack can be combined as required, so that the test requirements of racks with different lengths can be met; the height of the movable wall plate bracket is adjustable, so that the requirements of different test heights can be met; the top of the rack is connected by a telescopic top cover bracket, the width is adjustable, and different test width requirements can be met; the rack adopts a modularized and combined structure, and each component can be repeatedly used for combining a new rack; the method has good universality, and can be suitable for model tests of the electrical systems of aerocrafts such as fixed-wing airplanes, helicopters, unmanned planes and floating airships; the same components are mounted on two sides of the movable wall plate support, so that the movable wall plate support can be used as a rack for multiple purposes, the condition that two types of electrical system model test pieces are arranged at the same time is provided, the test flight troubleshooting and improved design verification requirements of a certain type of airplane are met, at least 2/3 rack space is saved, 1 set of rack cost is saved, and space and equipment cost caused by the fact that a power supply model and a load model cannot be reused are saved.
The combined type electrical system model test bench shown in fig. 7 is a certain type of airplane electrical system model test bench, two tested electrical systems are simultaneously arranged on the bench, 1 test system is arranged on the outer side of the bench, and 3 test systems are arranged on the inner side of the bench. This test bench composite module includes: 18 moving wall panel brackets, 72 pallets, 9 telescoping roof brackets, 54 cleats, 324 harness cradles, and 36 lighting assemblies.
When the wall plate supports are combined, the height of the 18 wall plate supports is adjusted to 2400mm, the width of each wall plate support is 2000mm, the introduction range of a generator feeder line is determined, then every 9 movable wall plate supports are combined in pairs in the introduction range to form two groups, the length of each group is 18000mm, and the arrangement width of the two groups of wall plate supports is adjusted to 3200 mm; the length of the telescopic top cover bracket is adjusted to 2400mm, then the telescopic top cover bracket penetrates through the long holes in the beam connecting plates 1-4 of the left side wall plate bracket and the right side wall plate bracket respectively through bolts and is fixed by using an M10 standard component; fixing the supporting plate on a panel 1-1 of the movable wall plate bracket, specifically adjusting the height of the supporting plate, which is 1000mm from the ground, penetrating through long holes 1-5 at the lower part of the panel 1-1 of the wall plate bracket through bolts respectively, and fixing by using an M10 standard component; then adjusting the length of the small wire harness support to be 60mm away from the bottom of the clamping plate, and fixing the small wire harness support on a clamping plate rib through bolts respectively; and finally, fixing the lighting assembly on a fourth downward row of long holes 1-5 in the upper part of the panel of the movable wallboard bracket through bolts. And the model test bench is combined.
During the experiment, earlier fix simulation covering 2mm thick aluminum plate on the deckle board of removing wallboard support left and right department through the splint, install the test piece (block terminal, circuit breaker board, generator controller, emergency power supply, power conversion box and intelligent power distribution cabinet etc.) on the layer board again, then install test pencil and test cable in the front end bayonet socket of pencil little support, dock the interface on test piece and the test cable again (including generator feeder inserts a block terminal), carry out partial test piece and pencil installation adjustment according to the site conditions during the installation, install the simulation load according to every experimental requirement at last. And finishing the installation and the laying of the tested electrical system on the model test bench.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. An avionics system model test rig, the test rig comprising:
the device comprises a movable wall plate support (1), a supporting plate (2), a telescopic top cover support (3), a clamping plate (4), a small wiring harness support (5) and a lighting assembly (6);
the movable wall plate support simulates a cabin wall of an aircraft, the supporting plate simulates a test piece mounting structural part, and the telescopic roof support simulates a cabin roof;
wherein the movable wall plate bracket is used for fixing and connecting other components of the test bench;
the clamping plates are used for fixing the aluminum plate skin and are connected to the left frame plate and the right frame plate of the movable wallboard bracket;
the small wiring harness bracket is used for testing the installation and laying of the power transmission and distribution cable and is connected to the clamping plate rib;
the lighting assembly is used for testing field lighting and is connected to the panel of the movable wall plate bracket.
2. An avionics system model test rig in accordance with claim 1,
the movable wall plate support panel is uniformly provided with a plurality of strip holes, the support plate is provided with bolt holes matched with the strip holes on the movable wall plate support panel, and the support plate is fixed on the movable wall plate support panel through bolts.
3. An avionics system model test rig in accordance with claim 2,
the plurality of strip holes are arranged at different horizontal positions and different height positions of the panel of the movable wall plate bracket;
the supporting plate can move left and right in the strip hole to adjust the position, and the supporting plate can also move up and down in the strip holes at different heights to adjust the position.
4. An avionics system model test rig in accordance with claim 1,
the telescopic top cover support is fixed on the movable wall plate support beam connecting plate through bolts at two ends, bolt holes matched with the telescopic top cover support bolt holes are formed in the movable wall plate support beam connecting plate, and the width of the telescopic top cover support is adjusted through a horizontal pipe in the middle of the cover plate.
5. An avionics system model test rig in accordance with claim 1,
the clamping plate is fixed on the movable wallboard support frame plate through a bolt, and a bolt hole in the movable wallboard support frame plate is matched with the clamping plate hole.
6. An avionics system model test rig in accordance with claim 1,
the small wire harness support is fixed on a rib in the middle of a panel clamping plate of the movable wall plate support through a bolt, and a bolt hole matched with the bolt hole in the rib is formed in the small wire harness support.
7. An avionics system model test rig in accordance with claim 1,
the lighting assembly is fixed on the panel of the movable wall plate support through bolts, bolt holes matched with the strip holes in the panel of the movable wall plate support are formed in the lighting assembly, and the mounting position of the lighting assembly is moved up and down and left and right according to the mounting requirements of a test piece.
8. An avionics system model modular test rig, characterized in that the modular test rig comprises a plurality of test rigs according to any one of claims 1 to 7;
a plurality of test benches are connected with each other by bolts.
9. A method of testing an avionics system model test rig applied to a test rig according to any one of claims 1 to 7 or a modular test rig according to claim 8, the method comprising:
during testing, the simulation skin aluminum plate is fixed on the frame plates at the left, middle and right positions of the movable wallboard bracket through the clamping plates;
mounting the test piece on a supporting plate, mounting the test wire harness and the test cable in a front end bayonet of a small wire harness support, and butting interfaces on the test piece and the test cable; the test piece is a distribution box, a breaker plate, a generator controller, an emergency power supply, a power supply conversion box or an intelligent power distribution cabinet;
and finally, installing a simulation load according to the requirement of each test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010991711.5A CN112180127A (en) | 2020-09-18 | 2020-09-18 | Model test bench and test method for aviation electrical system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010991711.5A CN112180127A (en) | 2020-09-18 | 2020-09-18 | Model test bench and test method for aviation electrical system |
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| CN112180127A true CN112180127A (en) | 2021-01-05 |
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| CN202010991711.5A Pending CN112180127A (en) | 2020-09-18 | 2020-09-18 | Model test bench and test method for aviation electrical system |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101685124A (en) * | 2008-09-22 | 2010-03-31 | 北京航空航天大学 | Electromagnetic compatibility quick detecting platform for wire cable layout of helicopter |
| CN103143610A (en) * | 2013-02-22 | 2013-06-12 | 上海交通大学 | Holding device for skin and progressive stretch forming method of skin |
| CN109189046A (en) * | 2018-09-03 | 2019-01-11 | 西安飞机工业（集团）有限责任公司 | A kind of large aircraft Mechatronic Systems all-around test stand |
| CN209085938U (en) * | 2018-09-30 | 2019-07-09 | 江铃重型汽车有限公司 | A kind of electrical system testboard bay |
| CN110573423A (en) * | 2017-05-02 | 2019-12-13 | 庞巴迪公司 | Test equipment and method for passenger cabin management system of mobile platform |
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2020
- 2020-09-18 CN CN202010991711.5A patent/CN112180127A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101685124A (en) * | 2008-09-22 | 2010-03-31 | 北京航空航天大学 | Electromagnetic compatibility quick detecting platform for wire cable layout of helicopter |
| CN103143610A (en) * | 2013-02-22 | 2013-06-12 | 上海交通大学 | Holding device for skin and progressive stretch forming method of skin |
| CN110573423A (en) * | 2017-05-02 | 2019-12-13 | 庞巴迪公司 | Test equipment and method for passenger cabin management system of mobile platform |
| US20200115067A1 (en) * | 2017-05-02 | 2020-04-16 | Bombardier Inc. | Test rig and method for passenger cabin management system of mobile platform |
| CN109189046A (en) * | 2018-09-03 | 2019-01-11 | 西安飞机工业（集团）有限责任公司 | A kind of large aircraft Mechatronic Systems all-around test stand |
| CN209085938U (en) * | 2018-09-30 | 2019-07-09 | 江铃重型汽车有限公司 | A kind of electrical system testboard bay |
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Application publication date: 20210105 |
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| RJ01 | Rejection of invention patent application after publication |