CN114486320A - Emergency processing system and method for pressure imbalance for aircraft testing - Google Patents
Emergency processing system and method for pressure imbalance for aircraft testing Download PDFInfo
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- CN114486320A CN114486320A CN202210394930.4A CN202210394930A CN114486320A CN 114486320 A CN114486320 A CN 114486320A CN 202210394930 A CN202210394930 A CN 202210394930A CN 114486320 A CN114486320 A CN 114486320A
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- 238000012360 testing method Methods 0.000 title claims abstract description 35
- 238000012545 processing Methods 0.000 title claims abstract description 18
- 238000000034 method Methods 0.000 title claims description 11
- 238000007789 sealing Methods 0.000 claims abstract description 147
- 238000005485 electric heating Methods 0.000 claims abstract description 33
- 238000013016 damping Methods 0.000 claims abstract description 19
- 238000009413 insulation Methods 0.000 claims abstract description 15
- 230000003139 buffering effect Effects 0.000 claims abstract description 5
- 238000010438 heat treatment Methods 0.000 claims description 7
- 238000000429 assembly Methods 0.000 claims description 3
- 230000000712 assembly Effects 0.000 claims description 3
- 238000003672 processing method Methods 0.000 abstract description 8
- 230000035939 shock Effects 0.000 abstract description 6
- 238000010521 absorption reaction Methods 0.000 abstract description 3
- 238000013461 design Methods 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000004321 preservation Methods 0.000 description 10
- 230000000694 effects Effects 0.000 description 4
- 230000002349 favourable effect Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
-
- 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
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
- E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
- E04B1/62—Insulation or other protection; Elements or use of specified material therefor
- E04B1/66—Sealings
- E04B1/665—Sheets or foils impervious to water and water vapor
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
- E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
- E04B1/62—Insulation or other protection; Elements or use of specified material therefor
- E04B1/74—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls
- E04B1/76—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to heat only
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
- E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
- E04B1/62—Insulation or other protection; Elements or use of specified material therefor
- E04B1/74—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls
- E04B1/76—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to heat only
- E04B1/78—Heat insulating elements
- E04B1/80—Heat insulating elements slab-shaped
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/05—Programmable logic controllers, e.g. simulating logic interconnections of signals according to ladder diagrams or function charts
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D27/00—Simultaneous control of variables covered by two or more of main groups G05D1/00 - G05D25/00
- G05D27/02—Simultaneous control of variables covered by two or more of main groups G05D1/00 - G05D25/00 characterised by the use of electric means
Abstract
The invention discloses a pressure unbalance emergency processing system for airplane testing and a processing method thereof, and belongs to the technical field of airplane testing, wherein the processing system comprises a heat-insulating sealing plate, a driving assembly, a sealing assembly, a damping assembly and a PLC (programmable logic controller), the heat-insulating sealing plate is hinged inside a fire fighting channel, the driving assembly comprises a first hydraulic rod and a second hydraulic rod, one end of the first hydraulic rod is hinged with the fire fighting channel, the other end of the first hydraulic rod is hinged with the heat-insulating sealing plate, and the second hydraulic rod is arranged at the bottom of the fire fighting channel and is movably connected with the heat-insulating sealing plate; the sealing assembly comprises an electric heating plate and a sealing strip, the electric heating plate is arranged on the side wall of the heat-insulation sealing plate, and the sealing strip is sleeved outside the electric heating plate; the shock absorption assembly is arranged in the fire fighting channel and is used for buffering the shock generated when the heat insulation sealing plate descends; the PLC is respectively electrically connected with each electric device; the system of the invention has reasonable structural design, and the heat-insulating sealing plate has rapid response action, thereby being beneficial to improving the safety and reliability of the test work of the airplane.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to an emergency processing system and method for pressure imbalance for airplane testing.
Background
The climate environment laboratory is used as a large bearing facility for the airplane environment test, can accommodate full-size airplanes, and can provide all-weather and time-unlimited environmental conditions of high temperature, low temperature and the like. The engine driving environment simulation is to simulate the low-temperature, high-temperature, damp-heat and other weather environments encountered in the starting or running process of an aircraft engine in a weather environment laboratory, and an air compensation system and an exhaust emission system are required to be arranged in the environment laboratory. Because the air quantity consumed during the ground driving test in the engine laboratory is huge. If in the starting process of the engine, the dynamic response of the laboratory air compensation system is delayed relative to the change of the air suction quantity of the engine, so that the indoor pressure is greatly changed in a short time, the indoor and outdoor pressure difference exceeds the allowable value of building design, the test environment is adversely affected, the building structure of the laboratory is damaged, and the safety of personnel, test pieces and equipment is threatened.
Meanwhile, because the tested airplane is stored in an extreme climatic environment, the fuel oil, the hydraulic oil and the lubricating oil of the airplane can be leaked and volatilized greatly. The climate environment laboratory is a closed space, and the oil gas concentration is increased due to leakage and volatilization, so that the risk of flash explosion or fire disaster exists. And because the engine driving test needs, the tested aircraft carries a large amount of fuel, so that the risk is further aggravated, and the safety of the whole laboratory is seriously threatened.
Therefore, it is necessary to design an emergency processing system and an emergency processing method thereof capable of dealing with pressure imbalance and fire risk in an aircraft test laboratory, so as to ensure the safety of the aircraft test experiment.
Disclosure of Invention
Aiming at the technical problems, the invention provides an emergency processing system and a processing method for pressure unbalance for aircraft testing.
The technical scheme of the invention is as follows: an emergency processing system for pressure unbalance for aircraft testing comprises a heat-insulating sealing plate, a driving assembly, a sealing assembly, a damping assembly and a PLC (programmable logic controller); the heat-insulating sealing plate is movably hinged in the fire fighting channel, the longitudinal section of the fire fighting channel is a regular quadrangle, and the shape of the heat-insulating sealing plate is matched with that of the fire fighting channel; a first accommodating groove and a second accommodating groove are formed in the bottom of the fire fighting channel, and sliding grooves are formed in two sides of the first accommodating groove; the second accommodating groove is positioned at the lower end of the first accommodating groove, two sides of the heat-insulating sealing plate are slidably clamped in the sliding groove through a rotating shaft, and the heat-insulating sealing plate can be accommodated in the first accommodating groove;
the driving assembly comprises a first hydraulic rod and a second hydraulic rod, one end of the first hydraulic rod is movably hinged with the side wall of the second accommodating groove, and the other end of the first hydraulic rod is hinged with the outer wall of the heat-insulating sealing plate; two second hydraulic rods are arranged, the two second hydraulic rods are arranged in the two sliding grooves in a one-to-one correspondence mode, and the free ends of the two second hydraulic rods are sleeved on the two rotating shafts in a one-to-one correspondence mode respectively; the first hydraulic rod and the second hydraulic rod are respectively driven by an external motor;
the sealing assembly comprises electric heating plates and sealing strips, the side wall of the heat-insulation sealing plate is provided with 4 annular clamping grooves, the 4 electric heating plates are uniformly distributed in the annular clamping grooves, and the sealing strips are sleeved outside the electric heating plates;
the damping component is arranged in the first accommodating groove and used for buffering vibration generated when the heat-insulation sealing plate descends;
the PLC controller is respectively electrically connected with the first hydraulic rod, the second hydraulic rod and the electric heating plate.
Furthermore, an auxiliary sealing groove is formed in the inner wall of the fire fighting channel, a sealing strip is arranged inside the auxiliary sealing groove, and the sealing strip is hollow and connected with an external air source device; when the heat-insulating sealing plate is in a sealing state, the sealing strip corresponds to the sealing strip in position; when the heat-insulating sealing plate is in a sealing state, the PLC is utilized to control the starting of the external air source device so as to inflate the sealing strip, thereby improving the sealing effect between the heat-insulating sealing plate and the fire fighting channel.
Further, each electric heating board and ring groove junction all are provided with the electro-magnet in pairs, and each electric heating board and ring groove junction just are located each both ends to the electro-magnet and all are provided with damping spring, and when the electro-magnet inter attraction, electric heating board, sealing strip are close to ring groove simultaneously to the sealing strip rubs between the inner wall of fire control passageway when having avoided the heat preservation closing plate to remove, thereby improves the high efficiency that the heat preservation closing plate moved under emergency.
Further, the symmetry is provided with the arc spacing groove on two relative inner walls about the fire control passageway, and the joint is rotated respectively to the both sides of heat preservation closing plate has guide roller, and two guide roller one-to-one activity joints are respectively on two arc spacing grooves, use through guide roller and arc spacing groove cooperation, have improved the stability when heat preservation closing plate opens, closes.
Furthermore, a locking assembly is arranged inside the side wall of the fire fighting channel, the number of the locking assemblies corresponds to the number of the guide rollers, the locking assembly comprises a locking gear, a sector toothed plate and a driving disc, the locking gear is arranged on the guide rollers, the sector toothed plate is connected inside the side wall of the fire fighting channel in a sliding clamping mode through an ejector rod, the sector toothed plate can be meshed and connected with the locking gear, the driving disc is connected inside the side wall of the fire fighting channel in a rotating clamping mode, a groove plate is arranged on the driving disc, one end, far away from the sector toothed plate, of the ejector rod is movably connected with the groove plate in a clamping mode, and the driving disc is driven by an external driving motor; utilize the PLC controller to control outside driving motor and start, utilize the driving-disc to drive the frid rotatory to make the ejector pin promote fan-shaped pinion rack and be close to the locking gear back meshing locking, improved the stability under the heat preservation closing plate encapsulated situation, be favorable to promoting the high efficiency of aircraft test work to go on.
Furthermore, the shock absorption assembly comprises a plurality of lifting pillars, a buffer frame and a guide slide rod, the lifting pillars are arranged and penetrate through the bottom in the fire fighting channel respectively and are located in the first accommodating groove, and the guide slide rod is arranged on the inner side of the bottom of the fire fighting channel; the number of the buffer frames is consistent with that of the lifting support columns, one end of each buffer frame is sleeved on the guide slide rod through the slide sleeve, buffer springs are sleeved at the upper end and the lower end of the slide sleeve on the guide slide rod, and the other end of each buffer frame is correspondingly connected with the bottom end of each lifting support column; the lifting support is extruded when the heat-insulation sealing plate falls, at the moment, each buffer frame pushes the sliding sleeve to move on the guide sliding rod, and the vibration generated when the heat-insulation sealing plate falls is buffered by using the buffer spring.
Furthermore, buffer grooves are formed in the joints of the buffer frames and the lifting support columns, the lifting support columns are respectively connected to the buffer grooves in a sliding and clamping mode in a one-to-one correspondence mode, the buffer frames are movably hinged to the sliding sleeve, auxiliary buffer rods are connected to the lower ends of the buffer frames in a sliding and clamping mode, and the auxiliary buffer rods are respectively movably hinged to the inner wall of the fire fighting channel; through setting up supplementary buffer beam, be favorable to improving the buffering effect of buffering frame.
Further, the upper end of one side, close to the first hydraulic stem, of the heat-insulating sealing plate is provided with a balancing weight, and the heat-insulating sealing plate can be opened more rapidly under emergency conditions by the aid of the balancing weight, so that the safety of airplane test work is improved.
Further, when the heat-insulating sealing plate is in a sealing state, an included angle between the heat-insulating sealing plate and the longitudinal section of the fire fighting channel is 30-60 degrees; through the contained angle between the longitudinal section of control heat preservation closing plate and fire control passageway, under the prerequisite of guaranteeing heat preservation sealing performance of heat preservation closing plate, make opening of heat preservation closing plate more smooth.
The invention also provides an emergency processing method for the pressure unbalance for the airplane test, which comprises the following steps:
s1, arranging a pressure sensor and a fire detector in a laboratory, electrically connecting the pressure sensor and the fire detector with a PLC (programmable logic controller) respectively, and controlling an external motor connected with a first hydraulic rod and a second hydraulic rod to start by the PLC when the pressure in the laboratory is smaller than the pressure of a building structure and needs a positive pressure value; the heat-insulating sealing plate is inclined in the fire fighting channel; then, the PLC is used for controlling the electric heating plate to be opened, and the sealing strip expands under the heating action of the electric heating plate, so that the sealing between the heat-insulating sealing plate and the fire fighting channel is realized;
s2, when the pressure in the laboratory reaches the positive pressure value required by the pressure of the building structure, the PLC controls the electric heating plate to be closed, and simultaneously controls the first hydraulic rod and the second hydraulic rod to release the pressure, so that the heat-insulation sealing plate falls into the first accommodating groove, and the vibration generated in the falling process of the heat-insulation sealing plate is buffered by the aid of the damping assembly; at this point, the air flow in the laboratory flowed out and the pressure in the laboratory stopped increasing.
Compared with the prior art, the beneficial effects of the invention are embodied in the following points:
the quick opening of the heat-insulation sealing plate can be realized by utilizing the first hydraulic rod and the second hydraulic rod, so that the pressure relief speed and the rescue convenience in the case of pressure imbalance in a laboratory are improved, and the reliability and the safety of airplane test work are improved;
secondly, the electric heating plate is arranged between the sealing strip and the heat-insulating sealing plate, so that the sealing performance of the heat-insulating sealing plate and a fire fighting channel can be improved, and the heat-insulating effect in an airplane test laboratory is improved; the opening blockage of the heat-insulating sealing plate due to the adhesion of the sealing strip and the fire fighting channel when the temperature in the laboratory is too low can be avoided, and the reliability of the heat-insulating sealing plate is improved;
thirdly, the heat-insulating sealing plate and the driving assembly can be stored in the fire fighting channel and keep consistent with the height of the fire fighting channel terrace, so that the normal use of the fire fighting channel cannot be influenced, and the reliability of the laboratory emergency channel is ensured.
Drawings
FIG. 1 is a flow chart of a process of the present invention;
FIG. 2 is a schematic structural view of embodiment 1 of the present invention;
FIG. 3 is a schematic view of the structure of the heat-insulating sealing plate of the present invention received in the first receiving groove;
FIG. 4 is a schematic view of the connection of the first hydraulic rod to the heat-insulating sealing plate according to the present invention;
FIG. 5 is a schematic view of the connection of the insulating sealing plate of the present invention to a fire passage;
FIG. 6 is a profile view of the first and second hydraulic rams of the present invention within a fire passageway;
FIG. 7 is a schematic view of the connection of the seal assembly of the present invention to a heat-retaining seal plate;
FIG. 8 is a schematic structural view of the shock absorbing assembly of the present invention;
FIG. 9 is a schematic illustration of the connection of the sealing strip of the present invention to a fire fighting access;
FIG. 10 is an enlarged, fragmentary, schematic view at A of FIG. 5 of the present invention;
wherein, 1-a heat preservation sealing plate, 10-a rotating shaft, 11-a ring-shaped clamping groove, 12-a guide roller, 13-a balancing weight, 2-a driving component, 20-a first hydraulic rod, 21-a second hydraulic rod, 3-a sealing component, 30-an electric heating plate, 31-a sealing strip, 32-an electromagnet, 33-a damping spring, 4-a shock absorption component, 40-a lifting support, 41-a buffer frame, 410-a sliding sleeve, 411-a buffer groove, 42-a guide sliding rod, 420-a buffer spring, 43-an auxiliary buffer rod, 5-a fire fighting channel, 50-a first holding tank, 51-a second holding tank, 52-a sliding tank, 53-an auxiliary sealing groove, 54-a sealing strip, 55-an arc limiting groove, 6-a locking component, 2-a driving component, 3-a buffer groove, 42-a guide sliding rod, 420-a buffer spring, 43-an auxiliary buffer rod, 5-a fire fighting channel, 50-a first holding tank, 51-a second holding tank, a sliding groove, a, 60-locking gear, 61-sector toothed plate, 62-driving disk, 620-grooved plate and 63-push rod.
Detailed Description
Example 1
As shown in fig. 2, 3, 4 and 6, the pressure imbalance emergency processing system for the aircraft test comprises a heat-insulating sealing plate 1, a driving assembly 2, a sealing assembly 3, a damping assembly 4 and a PLC controller; the heat-insulating sealing plate 1 is movably hinged in the fire fighting passage 5, the longitudinal section of the fire fighting passage 5 is a regular quadrangle, and the shape of the heat-insulating sealing plate 1 is adapted to the shape of the fire fighting passage 5; a first accommodating groove 50 and a second accommodating groove 51 are formed in the bottom of the fire fighting channel 5, and sliding grooves 52 are formed in two sides of the first accommodating groove 50; the second accommodating groove 51 is positioned at the lower end of the first accommodating groove 50, two sides of the heat-insulating sealing plate 1 are slidably clamped in the sliding groove 52 through the rotating shaft 10, and the heat-insulating sealing plate 1 can be accommodated in the first accommodating groove 50;
as shown in fig. 2, 3 and 5, the driving assembly 2 includes a first hydraulic rod 20 and a second hydraulic rod 21, one end of the first hydraulic rod 20 is movably hinged to the side wall of the second accommodating groove 51, and the other end is hinged to the outer wall of the heat-insulating sealing plate 1; two second hydraulic rods 21 are arranged, the two second hydraulic rods 21 are arranged in the two sliding grooves 52 in a one-to-one correspondence manner, and the free ends of the two second hydraulic rods 21 are respectively sleeved on the two rotating shafts 10 in a one-to-one correspondence manner; the first hydraulic rod 20 and the second hydraulic rod 21 are respectively driven by an external motor;
as shown in fig. 2 and 7, the sealing assembly 3 includes electrical heating plates 30 and sealing strips 31, the side wall of the heat-insulating sealing plate 1 is provided with annular clamping grooves 11, the number of the electrical heating plates 30 is 4, the 4 electrical heating plates 30 are uniformly distributed in the annular clamping grooves 11, and the sealing strips 31 are sleeved outside the electrical heating plates 30;
as shown in fig. 6, the damping member 4 is disposed inside the first receiving groove 50 for damping vibration generated when the heat-insulating sealing plate 1 descends, and the damping member 4 is a commercially available damping spring;
when the heat-insulating sealing plate 1 is in a sealing state, an included angle between the heat-insulating sealing plate and the longitudinal section of the fire fighting channel 5 is 45 degrees;
the PLC controller is respectively with first hydraulic stem 20, second hydraulic stem 21 and electric heating plate 30 electric connection, and PLC controller, first hydraulic stem 20, second hydraulic stem 21 and electric heating plate 30 are the product of selling on the market.
Example 2
The embodiment describes a processing method of the pressure imbalance emergency processing device for aircraft testing in embodiment 1, which includes the following steps:
s1, arranging a pressure sensor and a fire detector in a laboratory, electrically connecting the pressure sensor and the fire detector with a PLC (programmable logic controller) respectively, and controlling an external motor connected with the first hydraulic rod 20 and the second hydraulic rod 21 to start by the PLC when the pressure in the laboratory is smaller than the pressure of the building structure and needs a positive pressure value; the heat-insulating sealing plate 1 is inclined in the fire fighting passage 5; then, the PLC is used for controlling the electric heating plate 30 to be opened, and the sealing strip 31 expands under the heating action of the electric heating plate 30, so that the sealing between the heat-insulating sealing plate 1 and the fire fighting channel 5 is realized;
s2, when the pressure in the laboratory reaches the positive pressure value required by the pressure of the building structure, the PLC controls the electric heating plate 30 to be closed, and simultaneously controls the first hydraulic rod 20 and the second hydraulic rod 21 to be decompressed, so that the heat-insulating sealing plate 1 falls into the first accommodating groove 50, and the vibration generated in the falling process of the heat-insulating sealing plate 1 is buffered by the damping component 4; at this point, the air flow in the laboratory flowed out and the pressure in the laboratory stopped increasing.
Example 3
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2 and 9, an auxiliary sealing groove 53 is arranged on the inner wall of the fire fighting tunnel 5, a sealing strip 54 is arranged inside the auxiliary sealing groove 53, and the sealing strip 54 is hollow and connected with an external air source device; when the heat-insulating sealing plate 1 is in a sealing state, the sealing strip 54 corresponds to the sealing strip 31.
Example 4
The processing method of the pressure imbalance emergency processing device for the aircraft test in embodiment 3 described in this embodiment is different from that in embodiment 2 in that:
in step S1, when the heat-insulating sealing plate 1 is in the sealed state, the PLC controller controls the external air source device to start up, so as to inflate the sealing strip 54, and the expanded sealing strip 54 abuts against the sealing strip 31, thereby achieving secondary sealing.
Example 5
The present embodiment is different from embodiment 1 in that:
as shown in fig. 7, electromagnets 32 are disposed at the joints of the electric heating plates 30 and the ring slot 11 in pairs, and damping springs 33 are disposed at the joints of the electric heating plates 30 and the ring slot 11 and at the two ends of each pair of electromagnets 32.
Example 6
The present embodiment describes a processing method of the pressure imbalance emergency processing device for aircraft testing in embodiment 5, which is different from embodiment 2 in that:
in step S1, in the moving process of the heat-insulating sealing plate 1, the PLC controller controls the electromagnets 32 to be powered on, and when the two electromagnets 32 arranged in pair attract each other, the electric heating plate 30 and the sealing strip 31 are close to the ring-shaped clamping groove 11 at the same time; when the heat-insulating sealing plate 1 is in a sealing state, the PLC controller controls the electromagnets 32 to be powered off, and the two electromagnets 32 arranged in pairs are mutually far away under the action of the damping spring 33.
Example 7
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, arc-shaped limiting grooves 55 are symmetrically arranged on two inner walls opposite to each other on the left and right of the fire fighting access 5, guide rollers 12 are rotatably clamped on two sides of the heat insulation sealing plate 1 respectively, and the two guide rollers 12 are movably clamped on the two arc-shaped limiting grooves 55 in a one-to-one correspondence manner respectively;
as shown in fig. 10, the inside locking subassembly 6 that is provided with of fire fighting passageway 5 lateral wall, the quantity of locking subassembly 6 corresponds unanimously with the quantity of guide roller 12, locking subassembly 6 includes locking gear 60, sector toothed plate 61 and driving-disc 62, locking gear 60 sets up on guide roller 12, sector toothed plate 61 passes through ejector pin 63 slip joint inside fire fighting passageway 5 lateral wall, and sector toothed plate 61 can be connected with locking gear 60 meshing, driving-disc 62 rotates the joint inside fire fighting passageway 5 lateral wall, be provided with slotted plate 620 on the driving-disc 62, the one end and the slotted plate 620 activity joint of sector toothed plate 61 are kept away from to ejector pin 63, driving-disc 62 is driven by outside driving motor.
Example 8
The present embodiment describes a processing method of the pressure imbalance emergency processing device for aircraft testing in embodiment 7, which is different from embodiment 2 in that:
in step S1, when the heat-insulating sealing plate is in a sealed state, the PLC controller controls the external driving motor to start, and the driving disc 62 drives the slot plate 620 to rotate, so that the ejector pin 63 pushes the sector toothed plate 61 to approach the locking gear 60 and then engages and locks.
Example 9
The present embodiment is different from embodiment 1 in that:
as shown in fig. 6 and 8, the shock absorbing assembly 4 includes 4 lifting pillars 40, a buffer frame 41 and guide sliding rods 42, the lifting pillars 40 are respectively arranged at the bottom of the fire fighting channel 5 in a penetrating manner and are located inside the first accommodating groove 50, and the guide sliding rods 42 are arranged at the inner side of the bottom of the fire fighting channel 5; the number of the buffer frames 41 is correspondingly consistent with that of the lifting struts 40, one end of each buffer frame 41 is sleeved on the guide slide rod 42 through the slide sleeve 410, the buffer springs 420 are sleeved at the upper end and the lower end of the slide sleeve 410 on the guide slide rod 42, and the other end of each buffer frame 41 is correspondingly connected with the bottom end of each lifting strut 40 one by one;
as shown in fig. 8, the junction of each buffer frame 41 and the lifting support 40 is provided with a buffer slot 411, each lifting support 40 is slidably connected to the buffer slot 411 in a one-to-one manner, each buffer frame 41 is movably hinged to the sliding sleeve 410, the lower end of each buffer frame 41 is slidably connected to an auxiliary buffer rod 43, and each auxiliary buffer rod 43 is movably hinged to the inner wall of the fire fighting access 5.
Example 10
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, a counterweight 13 is arranged at the upper end of one side of the heat-insulating sealing plate 1 close to the first hydraulic rod 20.
Example 11
As shown in fig. 2, when the heat-insulating sealing plate 1 is in a sealing state, the included angle between the heat-insulating sealing plate and the longitudinal section of the fire fighting tunnel 5 is 30 degrees.
Example 12
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2, when the heat-insulating sealing plate 1 is in a sealing state, the included angle between the heat-insulating sealing plate and the longitudinal section of the fire fighting tunnel 5 is 60 degrees.
Claims (9)
1. The pressure unbalance emergency processing system for the aircraft test is characterized by comprising a heat-insulation sealing plate (1), a driving assembly (2), a sealing assembly (3), a damping assembly (4) and a PLC (programmable logic controller); the heat-insulation sealing plate (1) is movably hinged inside the fire fighting channel (5), the longitudinal section of the fire fighting channel (5) is a regular quadrangle, and the shape of the heat-insulation sealing plate (1) is adapted to that of the fire fighting channel (5); a first accommodating groove (50) and a second accommodating groove (51) are formed in the bottom of the fire fighting channel (5), and sliding grooves (52) are formed in two sides of the first accommodating groove (50); the second accommodating groove (51) is positioned at the lower end of the first accommodating groove (50), two sides of the heat-insulating sealing plate (1) are slidably clamped in the sliding groove (52) through the rotating shaft (10), and the heat-insulating sealing plate (1) can be accommodated in the first accommodating groove (50);
the driving assembly (2) comprises a first hydraulic rod (20) and a second hydraulic rod (21), one end of the first hydraulic rod (20) is movably hinged with the side wall of the second accommodating groove (51), and the other end of the first hydraulic rod is hinged with the outer wall of the heat-insulating sealing plate (1); two second hydraulic rods (21) are arranged, the two second hydraulic rods (21) are correspondingly arranged in the two sliding grooves (52) one by one, and the free ends of the two second hydraulic rods (21) are respectively sleeved on the two rotating shafts (10) one by one; the first hydraulic rod (20) and the second hydraulic rod (21) are respectively driven by an external motor;
the sealing assembly (3) comprises electric heating plates (30) and sealing strips (31), annular clamping grooves (11) are formed in the side wall of the heat-insulating sealing plate (1), the number of the electric heating plates (30) is 4, the 4 electric heating plates (30) are uniformly distributed in the annular clamping grooves (11), and the sealing strips (31) are sleeved outside the electric heating plates (30);
the damping assembly (4) is arranged in the first accommodating groove (50) and is used for buffering vibration generated when the heat-insulation sealing plate (1) descends;
the PLC controller is respectively electrically connected with the first hydraulic rod (20), the second hydraulic rod (21) and the electric heating plate (30).
2. The pressure imbalance emergency treatment system for the aircraft test according to claim 1, wherein an auxiliary sealing groove (53) is formed in the inner wall of the fire fighting tunnel (5), a sealing belt (54) is arranged inside the auxiliary sealing groove (53), and the sealing belt (54) is hollow inside and is connected with an external air source device; when the heat-insulating sealing plate (1) is in a sealing state, the sealing strip (54) corresponds to the sealing strip (31).
3. The emergency pressure imbalance handling system for the aircraft test according to claim 1, wherein electromagnets (32) are disposed at the joints of the electric heating plates (30) and the ring slots (11) in pairs, and damping springs (33) are disposed at the joints of the electric heating plates (30) and the ring slots (11) and at two ends of each pair of electromagnets (32).
4. The pressure imbalance emergency processing system for the aircraft test according to claim 1, wherein arc-shaped limiting grooves (55) are symmetrically formed in two inner walls, which are opposite to each other, of the fire fighting tunnel (5), guide rollers (12) are rotatably clamped on two sides of the heat insulation sealing plate (1) respectively, and the two guide rollers (12) are movably clamped on the two arc-shaped limiting grooves (55) in a one-to-one correspondence manner respectively.
5. The pressure imbalance emergency management system for aircraft testing of claim 4, the side wall of the fire fighting channel (5) is internally provided with locking assemblies (6), the number of the locking assemblies (6) is correspondingly consistent with that of the guide rollers (12), each locking assembly (6) comprises a locking gear (60), a sector toothed plate (61) and a driving disc (62), the locking gear (60) is arranged on the guide roller (12), the sector toothed plate (61) is clamped inside the side wall of the fire fighting channel (5) in a sliding way through a mandril (63), the sector toothed plate (61) can be meshed and connected with the locking gear (60), the driving disc (62) is rotationally clamped inside the side wall of the fire fighting channel (5), a groove plate (620) is arranged on the driving disc (62), one end of the ejector rod (63) far away from the sector toothed plate (61) is movably clamped with the groove plate (620).
6. The pressure imbalance emergency processing system for the aircraft test according to claim 1, wherein the damping assembly (4) includes a plurality of lifting pillars (40), a plurality of buffer frames (41), and a plurality of guide rods (42), the plurality of lifting pillars (40) are respectively disposed at the bottom of the fire passage (5) and located inside the first accommodating groove (50), and the plurality of guide rods (42) are disposed at the bottom of the fire passage (5); the quantity of buffer frame (41) corresponds unanimously with the quantity of lifting support post (40), and the one end of each buffer frame (41) is established respectively through sliding sleeve (410) cover and is established on direction slide bar (42), lies in on the direction slide bar (42) both ends all are equipped with buffer spring (420) about sliding sleeve (410), and the other end of each buffer frame (41) is connected with each lifting support post (40) bottom one-to-one respectively.
7. The pressure imbalance emergency treatment system for the aircraft test is characterized in that a counterweight (13) is arranged at the upper end of one side, close to the first hydraulic rod (20), of the heat-insulating sealing plate (1).
8. The pressure imbalance emergency treatment system for the aircraft test according to claim 1, wherein the heat-insulating sealing plate (1) forms an angle of 30-60 degrees with a longitudinal section of the fire fighting tunnel (5) when in a sealing state.
9. The method for processing the pressure imbalance emergency processing system for the aircraft test according to any one of claims 1 to 8, characterized by comprising the following steps:
s1, arranging a pressure sensor and a fire detector in a laboratory, electrically connecting the pressure sensor and the fire detector with a PLC (programmable logic controller) respectively, and controlling an external motor connected with a first hydraulic rod (20) and a second hydraulic rod (21) to start by the PLC when the pressure in the laboratory is smaller than the pressure of a building structure and needs a positive pressure value; the heat-insulating sealing plate (1) is inclined in the fire fighting channel (5); then, the PLC is used for controlling the electric heating plate (30) to be opened, and the sealing strip (31) expands under the heating action of the electric heating plate (30) to realize the sealing between the heat-insulating sealing plate (1) and the fire fighting channel (5);
s2, when the pressure in the laboratory reaches the positive pressure value required by the pressure of the building structure, the PLC controls the electric heating plate (30) to be closed, and simultaneously controls the first hydraulic rod (20) and the second hydraulic rod (21) to be decompressed, the heat-insulating sealing plate (1) falls into the first accommodating groove (50), and the vibration generated in the falling process of the heat-insulating sealing plate (1) is buffered by the damping component (4); at this point, the air flow in the laboratory flowed out and the pressure in the laboratory stopped increasing.
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