CN114537707B - Large aircraft temperature impact testing device and testing method - Google Patents
Large aircraft temperature impact testing device and testing method Download PDFInfo
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- CN114537707B CN114537707B CN202210441295.0A CN202210441295A CN114537707B CN 114537707 B CN114537707 B CN 114537707B CN 202210441295 A CN202210441295 A CN 202210441295A CN 114537707 B CN114537707 B CN 114537707B
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L1/00—Enclosures; Chambers
- B01L1/02—Air-pressure chambers; Air-locks therefor
- B01L1/025—Environmental chambers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L7/00—Heating or cooling apparatus; Heat insulating devices
- B01L7/02—Water baths; Sand baths; Air baths
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Abstract
The invention provides a large airplane temperature impact testing device and a large airplane temperature impact testing method, and belongs to the technical field of airplane testing. The device comprises a climate laboratory large room for simulating a low-temperature environment, an environment chamber arranged in the climate laboratory large room and used for simulating a high-temperature environment, a hydraulic lifting assembly arranged in the environment chamber, a low-temperature control assembly communicated with the climate laboratory large room, and a high-temperature control assembly communicated with the environment chamber; the test airplane is converted in two environments in a vertical movement mode, so that the temperature impact environment simulation is realized, the simulation of the high-temperature environment in the environment cabin is beneficial to protecting the test equipment, and the test airplane has the advantages of energy conservation and emission reduction, and is short in construction period, low in cost and easy to realize.
Description
Technical Field
The invention belongs to the technical field of airplane testing, and particularly relates to a large airplane temperature impact testing device and a testing method.
Background
The temperature impact test is a necessary test for verifying the environmental adaptability of equipment, is used for checking whether physical damage or performance reduction occurs when the complete machine and parts of various products in the fields of aviation, machinery, electronic and electrician and the like are subjected to rapid changes of ambient atmospheric temperature, and is suitable for scenes of aircraft flying exposure, air transportation-desert exposure, land transportation or air transportation-cold exposure and the like. The national military standard GJB150.5A-2009, the national standard GB/T2423.22-2002 and the like in China all provide typical temperature impact test methods. To simulate a temperature shock environment, two test chambers or a two chamber test chamber is typically used. The test chamber is divided into 3 types according to the structural form of the test chamber, and the 3 types comprise: three-compartment type, vertical lifting type and horizontal moving type. The three forms have advantages and disadvantages, and are suitable for different situations. For the temperature impact test of medium and large-scale equipment, a horizontal moving type test box is generally adopted. This proof box has two railway carriage or compartment bodies about, removes through removing the basket and removes realization high temperature and microthermal conversion, consequently this proof box not only requires extreme high temperature environment adaptability to removing basket drive arrangement, also requires extreme low temperature environment adaptability for its design degree of difficulty is big, and the fault rate is higher. In addition, for the temperature impact test of ultra-large equipment, such as an aircraft complete machine, a large-sized vehicle and the like, at present, enough large test equipment can not accommodate the size of the ultra-large equipment, the complete machine level temperature impact test cannot be carried out, the test is only verified through a component level test, the comprehensive examination cannot be carried out, and certain risks exist.
At present, China has an airplane complete machine climate laboratory, the environmental chamber of the laboratory is designed to be in a convex layout, the environmental chamber is divided into a large environmental chamber and a small environmental chamber through an isolation door, the effective size of the large chamber is 72m multiplied by 60m multiplied by 22m, the size of the small chamber is 27m multiplied by 30m multiplied by 22m, the large chamber and the small chamber are respectively provided with an independent air treatment system, the temperature range which can be realized is-55 ℃ to 74 ℃, and the laboratory does not have the capability of developing temperature impact tests, so that a large airplane temperature impact testing device based on the airplane climate laboratory for developing the temperature impact tests is urgently needed.
Disclosure of Invention
Aiming at the problems, the invention provides a large airplane temperature impact testing device and a testing method which are short in construction period, low in cost and easy to realize.
The technical scheme of the invention is as follows: a large-scale aircraft temperature impact testing device and a testing method comprise a climate laboratory large room used for simulating a low-temperature environment, an environment chamber arranged in the climate laboratory large room and used for simulating a high-temperature environment, a hydraulic lifting assembly arranged in the environment chamber, a low-temperature control assembly communicated with the climate laboratory large room, and a high-temperature control assembly communicated with the environment chamber;
each side wall of the environment compartment is respectively provided with a fixed platform and three turnable moving platforms for test operation, the interior of the environment compartment can be divided into an upper compartment body and a lower compartment body through the fixed platform and the moving platforms, an upper side isolation door is arranged on the side wall of the upper compartment body and at the position of the fixed platform, an escalator is arranged at the position of the upper side isolation door, and a lower side isolation door is arranged on the side wall of the lower compartment body;
the top end of the upper cabin body is provided with a pull cover plate assembly, the pull cover plate assembly comprises a main position hollow shell which is arranged at the right upper end of the upper cabin body and the left side and the right side of the main position hollow shell are communicated with each other, two auxiliary position cover plates which are arranged at the left side and the right side of the interior of the main position hollow shell and can slide in the main position hollow shell through sliding rails, abutting ports are arranged on the upper surface and the lower surface of the main position hollow shell, and the auxiliary position cover plates can move left and right through external driving equipment;
the hydraulic lifting assembly is provided with a lifting platform, the lifting platform is provided with an anti-skidding groove, the anti-skidding groove is of an inverted trapezoidal platform structure, the bottom surface of the anti-skidding groove is provided with an anti-skidding pad, and a plurality of anti-skidding lines are uniformly distributed on the anti-skidding pad;
the side walls of the climate laboratory large room and the upper cabin body are both of a hollow structure, a plurality of air outlets are formed in the side walls of the climate laboratory large room and the upper cabin body, and the low-temperature control assembly comprises a low-temperature air inlet pipe communicated with the inner wall of the climate laboratory large room and an air cooler connected with the low-temperature air inlet pipe;
the high-temperature control assembly comprises a high-temperature air inlet pipe communicated with the inner wall of the upper cabin body and an air heater connected with the high-temperature air inlet pipe.
Furthermore, a plurality of first mounting grooves are uniformly formed in the inner wall of the climate laboratory, a first stainless steel patch is connected into each first mounting groove in a clamping manner, a plurality of second mounting grooves are uniformly formed in the inner wall of the upper cabin body, a second stainless steel patch is connected into each second mounting groove in a clamping manner, an air-dispersing net cover is arranged at each air outlet, the inner part of the climate laboratory wall body is divided into latticed channels through the arrangement of the first stainless steel patches, when cold air enters the interior of the climate laboratory through the low-temperature air inlet pipe, the cold air is uniformly dispersed through the latticed channels to cool the climate laboratory, meanwhile, the cold air is in contact with the first stainless steel patches to cool the first stainless steel patches to replace partial cold air to cool the climate laboratory, so that the energy consumption of the air cooler can be reduced, and the energy saving and emission reduction effects are achieved, through the setting of second stainless steel paster, become latticed passageway with last cabin wall body internal partitioning, when hot-air got into the upper cabin body through the high temperature air-supply line inside, can be through latticed passageway homodisperse, heat the upper cabin body, meanwhile, hot-air and the contact of second stainless steel paster can make the second stainless steel paster heat up, replace partial hot-air to heat up in the upper cabin body, can reduce the energy consumption of air heater, have energy saving and emission reduction's effect.
Furthermore, a plurality of first inserting limiting teeth are uniformly arranged on the peripheral side wall of the lifting platform, second inserting limiting teeth which are distributed in a staggered manner with the first inserting limiting teeth are arranged on the side walls of the fixed platform and the movable platform, horizontal fixed inserting rods are arranged on the side walls of the upper cabin body, the first inserting limiting teeth and the second inserting limiting teeth which are distributed in a staggered manner are connected through the horizontal fixed inserting rods, the fixed platform, the movable platform and the peripheral side wall of the lifting platform are mutually inserted and limited in a staggered manner through the first inserting limiting teeth and the second inserting limiting teeth, meanwhile, the first inserting limiting teeth and the second inserting limiting teeth are fixed through the horizontal fixed inserting rods, the connecting strength of the contact positions of the fixed platform, the movable platform and the lifting platform with the side wall of the lifting platform can be increased, the fixed platform, the movable platform and the lifting platform are connected into a same plane, and the stress directly applied to the lifting platform and the hydraulic lifting assembly by the test airplane can be decomposed, the service life of the device is prolonged.
Furthermore, the fixed platform, the moving platform and the lifting platform are all of a cavity structure, a heat insulation net is attached to the inner wall of the cavity structure, a fold-line-shaped partition board is arranged in the cavity structure in the horizontal direction, the cavity structure is partitioned into a plurality of containing intervals through the fold-line-shaped partition board, heat insulation materials are arranged in each containing interval, a detachable sealing cover is arranged at the bottom end of the cavity structure, a plurality of dispersing openings are uniformly formed in the fold-line-shaped partition board, the mechanical performance of the plate can be improved through the arrangement of the fold-line-shaped partition board, the strength is improved, the upper side and the lower side of the heat insulation net play a heat insulation role, the heat insulation materials insulate the interior of the cavity structure, the fixed platform, the moving platform and the lifting platform are enabled to have excellent high temperature resistance, and the heat entering the interior of the cavity structure is uniformly dispersed to each position of the heat insulation materials to be isolated through the arrangement of the dispersing openings in the fold-line-shaped partition board, the heat insulation performance is prevented from being reduced by local high temperature, the heat dissipated into the lower cabin body is greatly reduced by the arrangement of the structure, the damage probability of the high temperature to each electric element in the lower cabin body is reduced, and the service life is prolonged.
Further, the heat insulation net is made of a heat insulation metal net material, and the heat insulation material is a nano-microporous heat insulation material.
Further, hydraulic lifting unit includes that bottom four corners department all is equipped with the installation landing leg adjust the support frame, locates each the hydraulic stem of installation landing leg department, locate the slope drive frame of lift platform one side, is equipped with vertical installation opening on the installation landing leg, just in vertical installation opening is located to the hydraulic stem, the lift platform bottom is connected with each hydraulic stem upper end, slope drive frame side evenly is equipped with a plurality of horizontal roll section of thick bamboos, and hydraulic stem drive lift platform through each installation landing leg department reciprocates in adjust support frame department, accomplishes the adjustment of test aircraft position, through the setting of slope drive frame, simultaneously, is equipped with horizontal roll section of thick bamboo, makes things convenient for the test aircraft to move on to lift platform, increases the simple operation nature.
Furthermore, a reinforcing rod is arranged between every two adjacent mounting support legs, so that the supporting strength of the adjusting support frame is improved, and the working reliability is improved.
Furthermore, a locking and adjusting component is arranged at the position of the horizontal rolling cylinder at the bottommost end, the locking and adjusting component comprises a connecting rod penetrating through the bottom end of the slope driving frame, a braking strip arranged on the inner side of the bottom end of the slope driving frame along the length direction of the horizontal rolling cylinder and connected through the connecting rod, and an auxiliary strip arranged on the outer side of the bottom end of the slope driving frame along the length direction of the horizontal rolling cylinder and connected through the connecting rod, a compression spring is arranged between the connecting rod and the slope driving frame, an electromagnetic attraction component is arranged on the opposite sides of the bottom end of the slope driving frame and the auxiliary strip, when the test airplane needs to move onto the lifting platform, the auxiliary strip can move towards the side close to the slope driving frame through the horizontal rolling cylinder, at the moment, the auxiliary strip applies force to the compression spring, and the braking strip is tightly attached to the horizontal rolling cylinder at the bottommost end, so that when the test airplane moves, the horizontal rolling cylinder at the bottommost end is locked, so that the safety of the test airplane in the moving process is ensured, and the phenomenon of slipping is avoided.
The testing method of the large aircraft temperature impact testing device comprises the following steps:
s1, driving the lifting platform to move through the hydraulic rods at the positions of the mounting support legs to enable the lifting platform to be in the lowest state, placing the test airplane on the lifting platform through the slope driving frame, placing wheels of the test airplane in the corresponding anti-skidding grooves to avoid inertial movement, and then mooring;
s2, turning the three mobile platforms to a horizontal position, driving the lifting platform to move upwards through hydraulic rods at the positions of the mounting support legs, enabling the fixed platform, the mobile platforms and the peripheral side walls of the lifting platform to be mutually staggered, inserted and limited through first insertion limiting teeth and second insertion limiting teeth, and meanwhile fixing the first insertion limiting teeth and the second insertion limiting teeth through horizontal fixing inserted rods;
s3, at the moment, the upper cabin body is in a sealed state, the hot air blower is started, hot air enters the interior of the upper cabin body through the high-temperature air inlet pipe, simulation test of a high-temperature environment is carried out, after the test is finished, the two sub-position shielding plates are pulled outwards through external driving equipment, meanwhile, the lifting platform is continuously driven to move upwards through the hydraulic rods at the positions of the installation supporting legs, the lifting platform is clamped and connected into the abutting ports, the air cooler is started, cold air enters the interior of the climate laboratory through the low-temperature air inlet pipe, and simulation test of the high-low-temperature impact environment is realized;
s4, the two sub-position shielding plates are inwards buckled through external driving equipment, meanwhile, the lifting platform is driven to move downwards through the hydraulic rods at the installation supporting legs, the lifting platform is clamped with the fixed platform and the moving platform again, the test airplane enters the upper cabin body again, and the low-temperature-high-temperature impact environment simulation test is achieved.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention provides a large-scale airplane temperature impact testing device and a testing method thereof based on a Chinese airplane climate laboratory, realizes the capability of developing a temperature impact test in the climate laboratory, is applied to the temperature impact test of ultra-large equipment, and makes the verification of the temperature impact performance of the ultra-large equipment possible; by a nested design method, an environment compartment is built in a large climate laboratory, and the airplane is converted in two environments in a vertical movement mode, so that the temperature impact environment simulation is realized, and the airplane temperature impact test is further developed.
(2) The invention utilizes the existing laboratory hardware to a great extent, has short construction period, low cost and easy realization, in addition, the test piece needs to be moved, the top door needs to be opened and the like in the environment chamber, the driving equipment is more, and the low-temperature environment has great influence on the performance of the driving equipment, so the simulation of the high-temperature environment in the environment chamber is more beneficial to the reliability of the test equipment.
(3) According to the invention, through the arrangement of the pull cover plate component, the environmental chamber for simulating a high-temperature environment is separated from the climate laboratory large chamber for simulating a low-temperature environment, the energy consumed by additionally recovering the balance of high-temperature and low-temperature temperatures when high-temperature and low-temperature simulation operations are repeatedly switched is reduced, and the pull cover plate component has the advantages of energy conservation and emission reduction.
Drawings
FIG. 1 is a schematic view of the internal structure of the present invention;
FIG. 2 is a top view of the interior of the present invention;
FIG. 3 is a schematic view of the slide of the sub position shutter of the present invention from the main position hollow shell;
FIG. 4 is an internal cross-sectional view of the present invention;
FIG. 5 is a cross-sectional view of the mounting platform of the present invention;
FIG. 6 is a schematic structural view of the lift platform of the present invention;
fig. 7 is a schematic structural view of the locking adjustment assembly of the present invention.
Wherein, 1-climate laboratory large room, 10-air outlet, 100-air dispersing net cover, 11-first mounting groove, 12-first stainless steel patch, 2-environment compartment, 20-fixed platform, 21-mobile platform, 22-upper cabin body, 220-upper side isolation door, 221-staircase, 222-second mounting groove, 223-second stainless steel patch, 224-horizontal fixed inserted rod, 23-lower cabin body, 230-lower side isolation door, 24-pull cover plate component, 240-main hollow shell, 241-auxiliary shield plate, 242-butt joint port, 25-second butt joint limit tooth, 3-hydraulic lifting component, 30-lifting platform, 300-first butt joint limit tooth, 31-anti-skid groove, 310-anti-skid pad, 311-anti-skid pattern, 32-adjusting support frames, 320-mounting support legs, 321-vertical mounting notches, 322-reinforcing rods, 33-hydraulic rods, 34-slope driving frames, 340-horizontal rolling cylinders, 35-locking adjusting components, 350-connecting rods, 351-stopping strips, 352-auxiliary strips, 353-compression springs, 354-electromagnetic attraction components, 4-low temperature control components, 40-low temperature air inlet pipes, 41-air coolers, 5-high temperature control components, 50-high temperature air inlet pipes, 51-hot air blowers, 6-cavity structures, 60-heat insulation nets, 61-fold line-shaped partition plates, 610-dispersion ports, 62-containing intervals, 620-heat insulation materials and 63-detachable sealing covers.
Detailed Description
In order to further understand the contents of the present invention, the present invention is described in detail by examples below.
Example 1
The large-scale aircraft temperature impact testing device shown in fig. 1 comprises a climate laboratory large room 1 for simulating a low-temperature environment, an environment chamber 2 arranged in the climate laboratory large room 1 and used for simulating a high-temperature environment, a hydraulic lifting assembly 3 arranged in the environment chamber 2, a low-temperature control assembly 4 communicated with the climate laboratory large room 1, and a high-temperature control assembly 5 communicated with the environment chamber 2;
as shown in fig. 2, each side wall of the environment compartment 2 is respectively provided with a fixed platform 20 and three turnable moving platforms 21 for test operation, and the inside of the environment compartment 2 can be divided into an upper cabin body 22 and a lower cabin body 23 through the fixed platform 20 and the moving platforms 21, an upper side isolation door 220 is arranged on the side wall of the upper cabin body 22 and at the position of the fixed platform 20, an escalator 221 is arranged at the position of the upper side isolation door 220, and a lower side isolation door 230 is arranged on the side wall of the lower cabin body 23;
as shown in fig. 3, a drawing cover plate assembly 24 is arranged at the top end of the upper cabin 22, the drawing cover plate assembly 24 includes a main position hollow shell 240 which is arranged at the right upper end of the upper cabin 22 and has mutually communicated left and right sides, and two sub position cover plates 241 which are arranged at the left and right sides inside the main position hollow shell 240 and can slide in the main position hollow shell 240 through sliding rails, abutting ports 242 are arranged on the upper and lower sides of the main position hollow shell 240, and the sub position cover plates 241 are moved left and right through external driving equipment;
as shown in fig. 2, a lifting platform 30 is arranged on the hydraulic lifting assembly 3, an anti-slip groove 31 is arranged on the lifting platform 30, the anti-slip groove 31 is of an inverted trapezoidal platform structure, an anti-slip mat 310 is arranged on the bottom surface of the anti-slip groove 31, and a plurality of anti-slip threads 311 are uniformly distributed on the anti-slip mat 310;
as shown in fig. 1, the side walls of the climate laboratory large room 1 and the upper cabin 22 are both hollow structures, and a plurality of air outlets 10 are respectively arranged on the side walls of the climate laboratory large room 1 and the upper cabin 22, and the low temperature control assembly 4 comprises a low temperature air inlet pipe 40 communicated with the inner wall of the climate laboratory large room 1 and an air cooler 41 connected with the low temperature air inlet pipe 40;
the high temperature control assembly 5 comprises a high temperature air inlet pipe 50 communicated with the inner wall of the upper chamber body 22 and a hot air blower 51 connected with the high temperature air inlet pipe 50.
Example 2
This embodiment is substantially the same as embodiment 1 except that:
as shown in fig. 4, a plurality of first mounting grooves 11 are uniformly formed in the inner wall of the climate laboratory large room 1, a first stainless steel patch 12 is connected to each first mounting groove 11 in a clamping manner, a plurality of second mounting grooves 222 are uniformly formed in the inner wall of the upper cabin body 22, a second stainless steel patch 223 is connected to each second mounting groove 222 in a clamping manner, and an air-dispersing mesh enclosure 100 is arranged at each air outlet 10.
Example 3
This embodiment is substantially the same as embodiment 2 except that:
as shown in fig. 2, a plurality of first inserting limiting teeth 300 are uniformly arranged on the peripheral side wall of the lifting platform 30, second inserting limiting teeth 25 which are distributed in a staggered manner with the first inserting limiting teeth 300 are respectively arranged on the side walls of the fixed platform 20 and the moving platform 21, horizontal fixing inserted rods 224 are respectively arranged on the side walls of the upper cabin body 22, and the first inserting limiting teeth 300 which are distributed in a staggered manner are connected with the second inserting limiting teeth 25 through the horizontal fixing inserted rods 224.
Example 4
This example is substantially the same as example 3, except that:
as shown in fig. 5, the fixed platform 20, the moving platform 21 and the lifting platform 30 are all internally provided with a cavity structure 6, the inner wall of the cavity structure 6 is adhered with a heat insulation net 60, a fold line-shaped partition board 61 is horizontally arranged in the cavity structure 6, the interior of the cavity structure 6 is divided into a plurality of containing intervals 62 through the fold line-shaped partition board 61, a heat insulation material 620 is arranged in each containing interval 62, the bottom end of the cavity structure 6 is provided with a detachable sealing cover 63, and a plurality of dispersing ports 610 are uniformly arranged on the fold line-shaped partition board 61;
the heat insulation net 60 is made of heat insulation metal net material, and the heat insulation material 620 is a nano-microporous heat insulation material.
Example 5
This example is substantially the same as example 4, except that:
as shown in fig. 6, the hydraulic lifting assembly 3 includes an adjusting support frame 32 having mounting legs 320 at four corners of the bottom end, hydraulic rods 33 disposed at the mounting legs 320, and a slope driving frame 34 disposed at one side of the lifting platform 30, wherein the mounting legs 320 are provided with vertical mounting notches 321, the hydraulic rods 33 are disposed in the vertical mounting notches 321, the bottom end of the lifting platform 30 is connected to the upper ends of the hydraulic rods 33, and a plurality of horizontal rolling cylinders 340 are uniformly disposed on the side surface of the slope driving frame 34;
a reinforcing rod 322 is arranged between two adjacent mounting supporting legs 320, so that the supporting strength of the adjusting supporting frame 32 is improved, and the working reliability is improved;
as shown in fig. 7, a locking adjustment assembly 35 is disposed at the horizontal rolling cylinder 340 located at the bottom end, the locking adjustment assembly 35 includes a connecting rod 350 penetrating through the bottom end of the slope driving frame 34, a stopping strip 351 disposed at the inner side of the bottom end of the slope driving frame 34 along the length direction of the horizontal rolling cylinder 340 and connected through the connecting rod 350, an auxiliary strip 352 disposed at the outer side of the bottom end of the slope driving frame 34 along the length direction of the horizontal rolling cylinder 340 and connected through the connecting rod 350, a compression spring 353 is disposed between the connecting rod 350 and the slope driving frame 34, and an electromagnetic attraction component 354 is disposed at the opposite side of the bottom end of the slope driving frame 34 and the auxiliary strip 352.
Example 6
The embodiment describes a testing method of the large aircraft temperature impact testing device in embodiment 5, which includes the following steps:
s1, driving the lifting platform 30 to move through the hydraulic rods 33 at the mounting legs 320 to enable the lifting platform to be in the lowest state, placing the test airplane on the lifting platform 30 through the slope driving frame 34, placing wheels of the test airplane in the corresponding anti-skid grooves 31 to avoid inertial movement, and then mooring;
s2, turning the three mobile platforms 21 to horizontal positions, driving the lifting platform 30 to move upwards through the hydraulic rods 33 at the mounting support legs 320, enabling the fixed platform 20, the mobile platforms 21 and the peripheral side walls of the lifting platform 30 to be mutually staggered, inserted and limited through the first inserting limiting teeth 300 and the second inserting limiting teeth 25, and meanwhile fixing the first inserting limiting teeth 300 and the second inserting limiting teeth 25 through the horizontal fixing inserted rods 224;
s3, at the moment, the upper cabin body 22 is in a sealed state, the hot air blower 51 is started, hot air enters the interior of the upper cabin body 22 through the high-temperature air inlet pipe 50, a simulation test of a high-temperature environment is carried out, after the test is finished, the two sub-position shielding plates 241 are pulled outwards through external driving equipment, meanwhile, the lifting platform 30 is continuously driven to move upwards through the hydraulic rods 33 at the mounting supporting legs 320, the lifting platform 30 is clamped and connected into the abutting port 242, the air cooler 41 is started, cold air enters the interior of the climate laboratory large room 1 through the low-temperature air inlet pipe 40, and a simulation test of a high-low-temperature impact environment is realized;
s4, the two sub-position shielding plates 241 are buckled inwards through external driving equipment, meanwhile, the lifting platform 30 is driven to move downwards through the hydraulic rods 33 at the positions of the mounting supporting legs 320, the lifting platform 30 is connected with the fixed platform 20 and the movable platform 21 in a clamping mode again, the test airplane enters the upper cabin 22 again, and the low-temperature-high-temperature impact environment simulation test is achieved.
Claims (7)
1. The large-scale airplane temperature impact testing device is characterized by comprising a climate laboratory large room (1) for simulating a low-temperature environment, an environment chamber (2) which is arranged in the climate laboratory large room (1) and used for simulating a high-temperature environment, a hydraulic lifting assembly (3) which is arranged in the environment chamber (2), a low-temperature control assembly (4) which is communicated with the climate laboratory large room (1), and a high-temperature control assembly (5) which is communicated with the environment chamber (2);
each side wall of the environment compartment (2) is respectively provided with a fixed platform (20) used for test operation and three turnable moving platforms (21), the interior of the environment compartment (2) can be divided into an upper cabin body (22) and a lower cabin body (23) through the fixed platform (20) and the moving platforms (21), an upper side isolation door (220) is arranged on the side wall of the upper cabin body (22) and positioned at the position of the fixed platform (20), an escalator (221) is arranged at the position of the upper side isolation door (220), and a lower side isolation door (230) is arranged on the side wall of the lower cabin body (23);
the top end of the upper cabin body (22) is provided with a pull cover plate assembly (24), the pull cover plate assembly (24) comprises a main position hollow shell (240) which is arranged at the right upper end of the upper cabin body (22) and the left side and the right side of which are communicated with each other, and two auxiliary position cover plates (241) which are arranged at the left side and the right side of the inside of the main position hollow shell (240) and can slide in the main position hollow shell (240) through slide rails, abutting ports (242) are arranged on the upper surface and the lower surface of the main position hollow shell (240), and the auxiliary position cover plates (241) can move left and right through external driving equipment;
the hydraulic lifting assembly (3) is provided with a lifting platform (30), the lifting platform (30) is provided with an anti-skid groove (31), the anti-skid groove (31) is of an inverted trapezoidal platform structure, the bottom surface of the anti-skid groove is provided with an anti-skid pad (310), and a plurality of anti-skid grains (311) are uniformly distributed on the anti-skid pad (310);
a plurality of first inserting limiting teeth (300) are uniformly arranged on the peripheral side wall of the lifting platform (30), second inserting limiting teeth (25) which are distributed with the first inserting limiting teeth (300) in a staggered mode are arranged on the side walls of the fixed platform (20) and the movable platform (21), and the first inserting limiting teeth (300) and the second inserting limiting teeth (25) which are distributed in a staggered mode are connected through horizontal fixing inserted rods (224);
the side walls of the climate laboratory large room (1) and the upper cabin body (22) are both of a hollow structure, a plurality of air outlets (10) are formed in the side walls of the climate laboratory large room and the upper cabin body, and the low-temperature control assembly (4) comprises a low-temperature air inlet pipe (40) communicated with the inner wall of the climate laboratory large room (1) and an air cooler (41) connected with the low-temperature air inlet pipe (40);
the high-temperature control assembly (5) comprises a high-temperature air inlet pipe (50) communicated with the inner wall of the upper cabin body (22) and a hot air blower (51) connected with the high-temperature air inlet pipe (50);
fixed platform (20), moving platform (21) and lift platform (30) are inside to be cavity structure (6), just cavity structure (6) inner wall subsides are equipped with heat insulating screen (60), are equipped with zigzag-shaped space bar (61) and pass through along the horizontal direction in cavity structure (6) zigzag-shaped space bar (61) are a plurality of intervals (62) that hold with cavity structure (6) internal separation, every hold and be equipped with thermal insulation material (620) in interval (62), cavity structure (6) bottom is equipped with detachable cover (63), evenly is equipped with a plurality of scattered mouths (610) on zigzag-shaped space bar (61).
2. The large aircraft temperature impact testing device according to claim 1, wherein a plurality of first mounting grooves (11) are uniformly formed in the inner wall of the climate laboratory large room (1), a first stainless steel patch (12) is clamped in each first mounting groove (11), a plurality of second mounting grooves (222) are uniformly formed in the inner wall of the upper cabin body (22), a second stainless steel patch (223) is clamped in each second mounting groove (222), and an air dispersing net cover (100) is arranged at each air outlet (10).
3. The large aircraft temperature impact testing device according to claim 2, wherein the heat insulation net (60) is made of a heat insulation metal net material, and the heat insulation material (620) is a nano-microporous heat insulation material.
4. The large aircraft temperature impact testing device according to claim 3, wherein the hydraulic lifting assembly (3) comprises adjusting support frames (32) with mounting legs (320) arranged at four corners of the bottom end, hydraulic rods (33) arranged at the mounting legs (320), and a slope driving frame (34) arranged on one side of the lifting platform (30), wherein vertical mounting notches (321) are formed in the mounting legs (320), the hydraulic rods (33) are arranged in the vertical mounting notches (321), the bottom end of the lifting platform (30) is connected with the upper ends of the hydraulic rods (33), and a plurality of horizontal rolling cylinders (340) are uniformly arranged on the side surfaces of the slope driving frame (34) from top to bottom.
5. A large aircraft temperature impact testing device according to claim 4, characterized in that a reinforcing rod (322) is arranged between two adjacent mounting legs (320).
6. The large-scale aircraft temperature impact testing device according to claim 5, wherein a locking adjusting component (35) is arranged at the horizontal rolling cylinder (340) at the bottommost end, the locking adjusting component (35) comprises a connecting rod (350) penetrating through the bottom end of the slope driving frame (34), a stopping strip (351) arranged on the inner side of the bottom end of the slope driving frame (34) along the length direction of the horizontal rolling cylinder (340) and connected through the connecting rod (350), and an auxiliary strip (352) arranged on the outer side of the bottom end of the slope driving frame (34) along the length direction of the horizontal rolling cylinder (340) and connected through the connecting rod (350), a compression spring (353) is arranged between the connecting rod (350) and the slope driving frame (34), and an electromagnetic attraction element (354) is arranged on the opposite side of the bottom end of the slope driving frame (34) and the auxiliary strip (352).
7. A large aircraft temperature impact testing method is based on the large aircraft temperature impact testing device of claim 6, and is characterized by comprising the following steps:
s1, driving the lifting platform (30) to move through the hydraulic rods (33) at the positions of the mounting support legs (320) to enable the lifting platform to be in the lowest state, placing the test airplane on the lifting platform (30) through the slope driving frame (34), placing wheels of the test airplane in the corresponding anti-skid grooves (31) to avoid inertial movement, and then mooring;
s2, turning the three mobile platforms (21) to a horizontal position, driving the lifting platform (30) to move upwards through the hydraulic rods (33) at the positions of the mounting support legs (320), enabling the fixed platforms (20), the mobile platforms (21) and the peripheral side walls of the lifting platform (30) to be mutually staggered, inserted and limited through the first inserting limiting teeth (300) and the second inserting limiting teeth (25), and meanwhile fixing the first inserting limiting teeth (300) and the second inserting limiting teeth (25) through the horizontal fixing inserting rods (224);
s3, at the moment, the upper cabin body (22) is in a sealed state, the hot air blower (51) is started, hot air enters the upper cabin body (22) through the high-temperature air inlet pipe (50), a simulation test of a high-temperature environment is carried out, after the test is finished, the two sub-position shielding plates (241) are pulled outwards through external driving equipment, meanwhile, the lifting platform (30) is continuously driven to move upwards through the hydraulic rods (33) at the positions of the mounting support legs (320), the lifting platform (30) is clamped and enters the butt joint port (242), the air cooler (41) is started, and cold air enters the interior of the climate laboratory large room (1) through the low-temperature air inlet pipe (40), so that a simulation test of a high-low-temperature impact environment is realized;
s4, the two sublevel shielding plates (241) are buckled inwards through external driving equipment, meanwhile, the lifting platform (30) is driven to move downwards through the hydraulic rods (33) at the positions of the mounting supporting legs (320), the lifting platform (30) is enabled to be buckled with the fixed platform (20) and the movable platform (21) again, the test airplane enters the upper cabin body (22) again, and the low-temperature-high-temperature impact environment simulation test is achieved.
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| CN114813199A (en) * | 2022-06-29 | 2022-07-29 | 中国飞机强度研究所 | Closed high-temperature test device and method for aerospace plane structure |
| CN116224032B (en) * | 2023-03-16 | 2023-09-05 | 上海聚跃检测技术有限公司 | Chip reliability test method and device |
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