CN113466580A - Test method and integrated test equipment of aviation simulation test system - Google Patents
Test method and integrated test equipment of aviation simulation test system Download PDFInfo
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- CN113466580A CN113466580A CN202110613118.1A CN202110613118A CN113466580A CN 113466580 A CN113466580 A CN 113466580A CN 202110613118 A CN202110613118 A CN 202110613118A CN 113466580 A CN113466580 A CN 113466580A
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- 238000012360 testing method Methods 0.000 title claims abstract description 167
- 238000004088 simulation Methods 0.000 title claims abstract description 22
- 238000010998 test method Methods 0.000 title claims abstract description 17
- 238000000034 method Methods 0.000 claims abstract description 10
- 230000008569 process Effects 0.000 claims abstract description 5
- 230000007613 environmental effect Effects 0.000 claims abstract description 4
- 238000012545 processing Methods 0.000 claims abstract description 4
- 230000017525 heat dissipation Effects 0.000 claims description 53
- 238000009423 ventilation Methods 0.000 claims description 35
- 238000005192 partition Methods 0.000 claims description 15
- 238000001816 cooling Methods 0.000 claims description 10
- 230000000694 effects Effects 0.000 claims description 9
- 238000006073 displacement reaction Methods 0.000 claims description 8
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 238000013016 damping Methods 0.000 claims description 4
- 239000004519 grease Substances 0.000 claims description 3
- 229910052742 iron Inorganic materials 0.000 claims description 3
- 229920001296 polysiloxane Polymers 0.000 claims description 3
- 230000001360 synchronised effect Effects 0.000 claims description 2
- 238000002360 preparation method Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 230000035939 shock Effects 0.000 description 3
- 239000002918 waste heat Substances 0.000 description 2
- 241000272165 Charadriidae Species 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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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
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20145—Means for directing air flow, e.g. ducts, deflectors, plenum or guides
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20181—Filters; Louvers
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2039—Modifications to facilitate cooling, ventilating, or heating characterised by the heat transfer by conduction from the heat generating element to a dissipating body
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- Engineering & Computer Science (AREA)
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- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention discloses a test method and integrated test equipment for an aviation simulation test system, which comprises part and component testing, single machine and component testing, subsystem testing and whole system testing, wherein in each stage of testing, a tester utilizes the test equipment for providing environmental conditions to enable a part to be tested to be in various test environments, then utilizes the test equipment for data processing to acquire, process and record data, and provides test guarantee through a series of special equipment, general equipment and guarantee equipment. According to the invention, the direct-current power supply and the tester body are integrally arranged, so that the overall size is smaller, the integrity of the equipment is improved, the convenience in use is improved, the transportation and the carrying are convenient, the rapid framework device is arranged, the test platform can be rapidly carried, the test preparation period is shortened, the test efficiency is improved, and meanwhile, the outdoor carrying equipment can be reduced.
Description
Technical Field
The invention relates to the field of aviation simulation test, in particular to a test method and integrated test equipment of an aviation simulation test system.
Background
The aviation simulation test is an indispensable important part in the aerospace field, various test technologies and equipment are widely applied to various engineering fields of aerospace to carry out scientific experiments, mathematical and physical simulation tests and various engineering tests, whether the selected scheme and design parameters are correct or not is verified, the harmony of each subsystem is checked, the reliability and the process quality are high, most of equipment for testing is large and inconvenient to carry and fast take, and due to the fact that the equipment works uninterruptedly for a long time and at a high frequency, a large amount of waste heat can be generated, heat dissipation equipment needs to be equipped to dissipate heat of the testing equipment, and the equipment is scattered, bulky in size and inconvenient to use.
Disclosure of Invention
The purpose of the invention is as follows: in order to overcome the defects in the prior art, the invention provides a testing method and integrated testing equipment of an aviation simulation testing system, which are convenient to carry, transport, take quickly, adjust freely and use.
The technical scheme is as follows: in order to achieve the purpose, the test method and the integrated test equipment of the aviation simulation test system comprise the following steps;
firstly, a tester carries out power-on self-test on test equipment;
a second step, using the test equipment providing environmental conditions to make the part to be tested in various test environments;
thirdly, a tester utilizes the test equipment for data processing to acquire, process and record data, and test guarantee is provided through a series of special equipment, general equipment and guarantee equipment;
and step four, the tester utilizes the test equipment with good test function to test the parts and the components, and test the single machine and the components, test the subsystem and test the whole system.
Further, the method comprises the following stages:
firstly, a tester tests parts and components and applies the tested qualified parts and components to the assembly of the single machine and the components;
in the second stage, a tester tests the single machine and the components, and applies the single machine and the components which are qualified in the test to the assembly of the subsystem;
in the third stage, a tester carries out subsystem testing and applies the subsystem qualified in the testing to the assembly of the whole system;
fourthly, the tester carries out the whole system test and puts the qualified products into use;
the tests in each stage are independent and synchronous.
Furthermore, the integrated testing equipment comprises a testing machine body, a battery compartment body detachably arranged on the outer wall of the testing machine body and a heat dissipation assembly arranged on the battery compartment body, wherein a battery pack is accommodated in the battery compartment body and is a direct-current power supply, the heat dissipation assembly dissipates heat of the battery pack in the inner cavity of the battery compartment body, and an air inlet and an air outlet are formed in the wall body of the battery compartment body corresponding to the heat dissipation assembly.
Furthermore, the heat dissipation assembly comprises a heat dissipation fan and heat dissipation partition plates, the heat dissipation partition plates are respectively arranged between the air inlet and the air outlet, the heat dissipation partition plates form a plurality of air cooling channels in the same direction as the heat dissipation direction, and the heat dissipation fan is arranged at one end of the air cooling channel corresponding to the air inlet; and a dustproof filter screen is arranged between the heat dissipation fan and the air inlet.
Furthermore, the battery compartment body is a box structure with an opening at one side, the opening side of the battery compartment body is covered on the wall body of the testing machine body, a heat-conducting plate is arranged on the opening side of the battery compartment body, a plurality of heat dissipation partition plates are arranged on the heat-conducting plate corresponding to one side wall of the battery pack, and the heat dissipation partition plates are pressed against the battery pack. The heat conducting plate is arranged in a way that one side wall of the heat conducting plate, which is far away from the battery pack, is in contact with the wall body of the testing machine body, and heat conducting silicone grease is filled between the heat conducting plate and the testing machine body;
an inner support frame is arranged in the inner cavity of the battery bin body corresponding to the heat-conducting plate, the heat-conducting plate and the heat-radiating fan are detachably arranged on the inner support frame through a fixing structure, and the fixing structure is a bolt and a screw;
the battery pack is characterized in that a battery cover is wrapped outside the battery pack and is a square shell, the battery cover comprises an inner layer and an outer layer, a ventilation channel is arranged between the inner layer and the outer layer, the inner layer shell is provided with ventilation holes in the shell in the air cooling flowing direction, and ventilation grooves are arranged on the side walls of the two sides of the inner layer and are attached to the side wall of the battery pack;
the small-sized fan is rotatably arranged on the inner wall of the ventilation groove, ventilation openings are formed in the outer end face of the ventilation groove, arc-surface grooves are formed in the inner side face of the shell between the ventilation openings, and the ventilation openings in the outer end face of the ventilation groove and the ventilation openings in the inner end face of the ventilation groove are arranged in a staggered mode.
Furthermore, the rapid framework device comprises a carrying box for loading the test equipment, the carrying box comprises an accommodating cavity for accommodating the test equipment, the carrying box comprises a bottom plate, movable side plates and fixed side plates, two groups of fixed side plates are oppositely and symmetrically arranged on the bottom plate, two movable side plates are movably arranged on two edges of the bottom plate corresponding to an operation panel and a back plate of the test equipment, and at least two movable side plates are turned over up and down in the vertical direction or adjusted by up and down displacement in the vertical plane; the bottom plate is supported to be separated from the ground through the turnover or the up-and-down displacement of the movable side plate.
Furthermore, the movable side plate is hinged to the side wall of the bottom plate through a hinge piece, the hinge piece is a hinge piece, the movable side plate is turned upwards to abut against the fixed side plate to form an accommodating cavity, or the movable side plate is turned downwards to be below the bottom plate to support the bottom plate;
the included angle alpha range of the movable side plate and the bottom surface of the bottom plate is more than or equal to 90 degrees and less than or equal to 270 degrees, namely the maximum overturning movable range of the movable side plate, and when the alpha is in the angle range of 90-180 degrees, the movable side plate and the bottom plate are obliquely arranged.
Further, the vertical-displacement-adjustable horizontal-displacement-adjustable vertical-displacement-adjustable horizontal-displacement mechanism further comprises another embodiment, the two movable side plates are adjusted in a vertical plane in a vertical direction, a sliding groove corresponding to the movable side plates is formed in the bottom plate, and locking bolts are arranged on the bottom plate corresponding to the movable side plates and the sliding groove.
The movable side plate is detachably sleeved on the outer ring of the two movable side plates; two the activity curb plate passes through the limit ring restriction and expands the scope outward, guarantees support stability.
The limiting ring is a flexible ring structure, such as an iron wire ring, and a limiting clamping groove is concavely arranged on the movable side plate corresponding to the limiting ring for clamping the limiting ring.
Furthermore, the support device also comprises a plurality of support columns, wherein the support columns are arranged on the bottom plate at intervals corresponding to the movable side plate and the fixed side plate respectively, the bottom ends of the support columns are hinged to the bottom plate, and the other ends of the support columns are free ends.
The inner side wall of the movable side plate is provided with an elastic damping plate, when the movable side plate is abutted against the fixed side plate, a containing cavity is enclosed, and the elastic damping plate is abutted against the testing equipment.
The bottom plate is provided with a plurality of supporting base plates corresponding to the wall surface of the accommodating cavity at intervals for supporting and overhead testing equipment, a bottom heat dissipation channel is reserved, a heat dissipation port is formed in the bottom plate, and a heat dissipation fan is arranged in the heat dissipation port.
Has the advantages that: according to the test method and the integrated test equipment of the aviation simulation test system, the direct-current power supply and the test machine body are integrally arranged, so that the overall size is smaller, the integrity of the equipment is improved, the use convenience is improved, the transportation and the carrying are convenient, the rapid framework device is arranged, the test platform can be rapidly carried, the test preparation period is shortened, the test efficiency is improved, and meanwhile, the outdoor carrying equipment can be reduced.
Drawings
FIG. 1 is a method block diagram of an aerial simulation test system;
FIG. 2 is a schematic structural diagram of an integrated test apparatus;
FIG. 3 is a schematic structural diagram of a battery compartment body;
FIG. 4 is a diagram showing the positional relationship of the internal components of the battery compartment;
FIG. 5 is a schematic view of a heat sink assembly;
FIG. 6 is a structural view of a battery cover;
FIG. 7 is a schematic view of the installation location of the quick mount device;
FIG. 8 is a front cross-sectional view of a fast frame device;
FIG. 9 is a diagram of a fast frame device support state;
FIG. 10 is a front cross-sectional view of the fast frame device in a supported state.
Detailed Description
The present invention will be further described with reference to the accompanying drawings.
The test method and the integrated test device 11 of the aviation simulation test system as shown in fig. 1-10 comprise the following steps;
firstly, a tester performs power-on self-test on the test equipment 11;
a second step in which the tester places the part to be tested in various test environments using the test equipment 11 that provides environmental conditions;
thirdly, a tester utilizes the test equipment 11 for data processing to acquire, process and record data, and test guarantee is provided through a series of special equipment, general equipment and guarantee equipment;
and step four, the tester uses the test equipment 11 with good test function to test the parts and the components, and test the single machine and the components, test the sub-system and test the whole system.
The method comprises the following steps:
firstly, a tester tests parts and components and applies the tested qualified parts and components to the assembly of the single machine and the components;
in the second stage, a tester tests the single machine and the components, and applies the single machine and the components which are qualified in the test to the assembly of the subsystem;
in the third stage, a tester carries out subsystem testing and applies the subsystem qualified in the testing to the assembly of the whole system;
fourthly, the tester carries out the whole system test and puts the qualified products into use;
the tests in all stages are mutually independent and synchronously carried out, the simple low-level test is gradually transited to the high-level test, the low-level test lays a foundation for the high-level test, the number of the high-level test is reduced, and the test cost is saved;
the test equipment 11 is integrated test equipment, the integrated test equipment is powered by a direct-current power supply, and the integrated test equipment dissipates heat through a self-contained heat dissipation assembly.
The integrated testing equipment 11 comprises a testing machine body 1, a battery bin body 2 detachably arranged on the outer wall of the testing machine body 1 and a heat dissipation assembly 3 arranged on the battery bin body 2, wherein a battery pack is accommodated in the battery bin body 2 and is a direct-current power supply, the heat dissipation assembly 3 dissipates the heat of the battery pack in the inner cavity of the battery bin body 2, an air inlet 4 and an air outlet 5 are formed in the wall body of the battery bin body 2 corresponding to the heat dissipation assembly 3, and the direct-current power supply and the testing machine body are integrally arranged, so that the overall size is smaller, the integrity of the equipment is improved, the convenience in use is improved, and the transportation are facilitated.
The heat dissipation assembly 3 comprises a heat dissipation fan 6 and heat dissipation partition plates 7, the heat dissipation partition plates 7 are respectively arranged between an air inlet and an air outlet, the heat dissipation partition plates 7 form a plurality of air cooling channels which are in the same direction as the heat dissipation direction, the heat dissipation fan 6 is arranged at one end of each air cooling channel corresponding to the air inlet 4, the distance between the battery pack and the wall body of the battery bin can be kept through the plurality of air cooling channels, the air receiving area of the battery pack is increased, and the heat dissipation efficiency is improved;
and a dustproof filter screen 8 is arranged between the heat dissipation fan 6 and the air inlet 4 to reduce dust entering the battery compartment.
The battery bin body 2 is a box body structure with an opening at one side, the opening side of the battery bin body 2 is covered on the wall body of the testing machine body 1, a heat conducting plate 9 is arranged on the opening side of the battery bin body 2, a plurality of heat dissipation partition plates 7 are arranged on one side wall of the heat conducting plate 9 corresponding to the battery pack, and the heat dissipation partition plates 7 are pressed on the battery pack. The heat conducting plate 9 is arranged in contact with the wall body of the testing machine body 1, and a heat conducting silicone grease is filled between the heat conducting plate 9 and the testing machine body 1;
an inner support frame 10 is arranged in the inner cavity of the battery bin body 2 corresponding to the heat-conducting plate 9, the heat-conducting plate 9 and the heat-radiating fan 6 are detachably arranged on the inner support frame 10 through a fixing structure, and the fixing structure is a bolt and a screw;
the battery pack is externally wrapped with a battery cover 23, the battery cover 23 is a square shell, the battery cover 23 comprises an inner layer and an outer layer, a ventilation channel 24 is arranged between the inner layer and the outer layer, the inner layer shell is provided with a ventilation hole 25 in the air cooling flowing direction, ventilation grooves 26 are arranged on the side walls of two sides of the inner layer, the ventilation grooves 26 are attached to the side walls of the battery pack, part of cold flow enters the inner layer through the ventilation hole of the inner layer and flows through the surface of the battery through the ventilation grooves to take away most of heat, the other part of cold flow flows through the ventilation channel between the inner layer and the outer layer, and the cold flow wraps the whole inner layer to take away waste heat;
rotate on the 26 inner walls of ventilation groove and set up small-size fan, when the cold flow passed the ventilation groove, received small-size fan to hinder and warp, driven small-size fan simultaneously and rotated, formed the vortex, small-size fan stirs the cold flow and blows to the resistance surface, set up vent 27 on the outer terminal surface, the medial surface in the casing between vent 27 is equipped with the cambered surface recess, vent 27 on the outer terminal surface with the inlayer is terminal the crisscross setting of ventilation hole on the face, and the terminal heat production of battery is efficient, and the heat is concentrated, through the ventilation hole and the vent of crisscross setting for the cold flow strikes the cambered surface recess between the ventilation hole after coming out from the inlayer, forms the gyration air current, makes the cold flow make certain time's stop between inlayer end and outer end, reaches better radiating effect.
The rapid framework device comprises a carrying box 12 used for loading the test equipment 11, the carrying box 12 comprises an accommodating cavity used for accommodating the test equipment 11, the carrying box 12 comprises a bottom plate 13, movable side plates 14 and fixed side plates 15, the two groups of fixed side plates 15 are oppositely and symmetrically arranged on the bottom plate 13, the two movable side plates 14 are movably arranged on two edges of the bottom plate 13 corresponding to an operation panel and a back plate of the test equipment 11, and at least two movable side plates 14 are turned over up and down in the vertical direction or adjusted in a vertical displacement manner in the vertical plane; the bottom plate 13 is supported to be separated from the ground through the overturning or up-and-down displacement of the movable side plate 14. The invention can support the bottom plate and the testing equipment 11 on the bottom plate by taking the movable side plate 14 of the carrying box 12 as a supporting structure, can quickly carry a testing platform, shortens the testing preparation period, improves the testing efficiency and can reduce outdoor carrying equipment.
The movable side plate 14 is hinged to the side wall of the bottom plate 13 through a hinge piece 16, the hinge piece 16 is a hinge piece, the movable side plate 14 is turned upwards to abut against the fixed side plate 14 to form an accommodating cavity, or the movable side plate 14 is turned downwards to be below the bottom plate 13 to support the bottom plate, and the movable side plate supporting device is simple in overall structure and easy and convenient to operate;
the included angle alpha range of the movable side plate 14 and the bottom surface of the bottom plate 13 is more than or equal to 90 degrees and less than or equal to 270 degrees, namely the maximum overturning movable range of the movable side plate 14, when the alpha is within the angle range of 90 degrees to 180 degrees, the movable side plate and the bottom plate are obliquely arranged, a larger effective supporting area can be provided, the gravity center of the whole device is lower, and the supporting is stable.
The movable side plates 14 can move up and down in the vertical plane for adjustment, sliding grooves corresponding to the movable side plates 14 can move up and down are formed in the bottom plate, and locking bolts are arranged on the bottom plate corresponding to the movable side plates 14 and the sliding grooves and used for locking the adjusted movable side plates.
The device also comprises a limiting ring 17, wherein the limiting ring 17 is detachably sleeved on the outer rings of the two movable side plates 14; the two movable side plates 14 limit the outward expansion range through the limiting rings 17, and the support stability is guaranteed.
The limiting ring 17 is a flexible ring structure, such as an iron wire ring, and a limiting clamping groove 18 is concavely arranged on the movable side plate 14 corresponding to the limiting ring 17 for clamping the limiting ring 17 to prevent the limiting ring from slipping
Still include a plurality of support post 19, it is a plurality of support post 19 sets up on bottom plate 13 corresponding to the interval of activity curb plate 14 and fixed curb plate 15 respectively, support post 19's bottom articulates on the bottom plate, just support post's the other end is the free end, and support stability is guaranteed to further promotion support intensity through support post 19.
Be provided with elasticity shock attenuation board 20 on the inside wall of activity curb plate 14, enclose synthetic the chamber that holds when the activity curb plate butt in fixed curb plate, elasticity shock attenuation board 20 supports to press in test equipment 1, promotes shock attenuation, resistance to compression protection.
The bottom plate 13 is provided with a plurality of supporting backing plates 21 corresponding to the interval on the wall that holds the chamber to be used for bearing and built on stilts test equipment 1, leave bottom heat dissipation channel, the thermovent has been seted up on the bottom plate 13, be provided with heat dissipation fan 22 in the thermovent, promote test equipment 1's radiating efficiency through the heat dissipation that looses.
While the preferred embodiments of the present invention have been described, it will be apparent to those skilled in the art that various changes and modifications can be made without departing from the principles of the invention and these are to be considered within the scope of the invention.
Claims (10)
1. A test method of an aviation simulation test system is characterized by comprising the following steps: comprises the following steps;
the method comprises the following steps that firstly, a tester carries out power-on self-test on test equipment (11);
a second step in which the test person uses a test device (11) providing environmental conditions to subject the part to be tested to various test environments;
thirdly, a tester utilizes the test equipment (11) for data processing to acquire, process and record data, and test guarantee is provided through a series of special equipment, general equipment and guarantee equipment;
and step four, the tester uses the test equipment (11) with good test function to test the parts and the components, and test the single machine and the components, test the sub-system and test the whole system.
2. The test method of the aviation simulation test system according to claim 1, wherein: the method comprises the following steps:
firstly, a tester tests parts and components and applies the tested qualified parts and components to the assembly of the single machine and the components;
in the second stage, a tester tests the single machine and the components, and applies the single machine and the components which are qualified in the test to the assembly of the subsystem;
in the third stage, a tester carries out subsystem testing and applies the subsystem qualified in the testing to the assembly of the whole system;
fourthly, the tester carries out the whole system test and puts the qualified products into use;
the tests in each stage are independent and synchronous.
3. The integrated test device used in the test method of the aviation simulation test system according to any one of claims 1 to 2, wherein: the testing equipment (11) comprises a testing machine body (1), a battery compartment body (2) detachably arranged on the outer wall of the testing machine body (1) and a heat dissipation assembly (3) arranged on the battery compartment body (2), wherein a battery pack is accommodated in the battery compartment body (2), the battery pack is a direct-current power supply, the heat dissipation assembly (3) dissipates heat of the battery pack in the inner cavity of the battery compartment body (2), and an air inlet (4) and an air outlet (5) are formed in the wall body of the battery compartment body (2) corresponding to the heat dissipation assembly (3).
4. The integrated test equipment used in the test method of the aviation simulation test system according to claim 3, wherein: the heat dissipation assembly (3) comprises a heat dissipation fan (6) and heat dissipation partition plates (7), the heat dissipation partition plates (7) are respectively arranged between an air inlet and an air outlet, the heat dissipation partition plates (7) form a plurality of air cooling channels which are in the same direction as the heat dissipation direction, and the heat dissipation fan (6) is arranged at one end of the air cooling channel corresponding to the air inlet (4); and a dustproof filter screen (8) is arranged between the heat dissipation fan (6) and the air inlet (4).
5. The integrated test equipment used in the test method of the aviation simulation test system according to claim 4, wherein: the battery bin body (2) is of a box body structure with an opening at one side, the opening side of the battery bin body (2) is covered on the wall body of the testing machine body (1), a heat conducting plate (9) is arranged on the opening side of the battery bin body (2), a plurality of heat dissipation partition plates (7) are arranged on one side wall of the heat conducting plate (9) corresponding to the battery pack, and the heat dissipation partition plates (7) are pressed on the battery pack; the heat conducting plate (9) is arranged in a manner that one side wall departing from the battery pack is in contact with the wall body of the testing machine body (1), and heat conducting silicone grease is filled between the heat conducting plate (9) and the testing machine body (1);
an inner support frame (10) is arranged in the inner cavity of the battery bin body (2) corresponding to the heat-conducting plate (9), the heat-conducting plate (9) and the heat-radiating fan (6) are detachably arranged on the inner support frame (10) through a fixing structure, and the fixing structure is a bolt and a screw;
a battery cover (23) is wrapped outside the battery pack, the battery cover (23) is a square shell, the battery cover (23) comprises an inner layer and an outer layer, a ventilation channel (24) is arranged between the inner layer and the outer layer, the inner layer shell is provided with a ventilation hole (25) in the air cooling flowing direction, the inner side walls of the two sides of the inner layer are provided with ventilation grooves (26), and the ventilation grooves (26) are attached to the side walls of the battery pack;
the small-size fan is rotationally arranged on the inner wall of the ventilation groove (26), ventilation openings (27) are formed in the outer end face of the ventilation groove, arc-surface grooves are formed in the inner side face of the shell between the ventilation openings (27), and the ventilation openings (27) in the outer end face of the ventilation groove and the ventilation holes in the inner end face of the ventilation groove are arranged in a staggered mode.
6. The integrated test equipment used in the test method of the aviation simulation test system according to claim 3, wherein: quick framework device is including carrying case (12) that is used for loading test equipment (11), carrying case (12) contain and hold the chamber to be used for holding test equipment (11), carrying case (12) include bottom plate (13), activity curb plate (14) and fixed curb plate (15), and are two sets of fixed curb plate (15) are relative and the symmetry sets up on bottom plate (13), two activity curb plate (14) are corresponding to operating panel, the backplate activity of test equipment (11) and are set up on the both edges of bottom plate (13), and at least two activity curb plate (14) are upset or are adjusted at vertical displacement from top to bottom in the vertical direction.
7. The integrated test equipment used in the test method of the aviation simulation test system according to claim 6, wherein: the movable side plate (14) is hinged to the side wall of the bottom plate (13) through a hinge piece (16), the hinge piece (16) is a hinge piece, the movable side plate (14) is upwards turned to abut against the fixed side plate (14) to form an accommodating cavity, or the movable side plate (14) is downwards turned to be below the bottom plate (13) to support the bottom plate;
the included angle alpha range of the movable side plate (14) and the bottom surface of the bottom plate (13) is more than or equal to 90 degrees and less than or equal to 270 degrees, namely the maximum overturning movable range of the movable side plate (14), and when the alpha is in the angle range of 90 degrees to 180 degrees, the movable side plate and the bottom plate are obliquely arranged.
8. The integrated test equipment used in the test method of the aviation simulation test system according to claim 7, wherein: the two movable side plates (14) are adjusted in a vertical plane in a vertical displacement mode, sliding grooves corresponding to the movable side plates (14) in a vertical displacement mode are formed in the bottom plate, and locking bolts are arranged on the bottom plate corresponding to the movable side plates (14) and the sliding grooves.
9. The integrated test equipment used in the test method of the aviation simulation test system according to claim 2, wherein: the device also comprises a limiting ring (17), wherein the limiting ring (17) is detachably sleeved on the outer rings of the two movable side plates (14); the two movable side plates (14) limit the outward expansion range through the limiting rings (17), and support stability is guaranteed.
The limiting ring (17) is a flexible ring structure, such as an iron wire ring, and a limiting clamping groove (18) is concavely arranged on the movable side plate (14) corresponding to the limiting ring (17) and used for clamping the limiting ring (17).
10. The integrated test equipment used in the test method of the aviation simulation test system according to claim 2, wherein: the support device is characterized by further comprising a plurality of support upright posts (19), wherein the support upright posts (19) are arranged on the bottom plate (13) respectively corresponding to the intervals between the movable side plate (14) and the fixed side plate (15), the bottom ends of the support upright posts (19) are hinged to the bottom plate, and the other ends of the support upright posts are free ends;
an elastic damping plate (20) is arranged on the inner side wall of the movable side plate (14), when the movable side plate abuts against the fixed side plate, an accommodating cavity is enclosed, and the elastic damping plate (20) abuts against the testing equipment (1);
the bottom plate (13) is provided with a plurality of supporting base plates (21) corresponding to the wall of the containing cavity at intervals to be used for bearing and overhead testing equipment (1), a bottom heat dissipation channel is reserved, a heat dissipation opening is formed in the bottom plate (13), and a heat dissipation fan (22) is arranged in the heat dissipation opening.
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