Aircraft cabin section force-heat-hypoxia comprehensive test device

Abstract

The application discloses a kind of aircraft cabin section force heat hypoxia comprehensive test device, including test base rack, force load loading device, test piece, heat load loading device and control and monitoring system, the force load loading device includes force load loading tool and the connecting device below it, counterweight assembly and support air bag, the heat load loading device includes heat load loading cabin, motor, fan, electric heater, cabin air duct, end cover and motor mounting plate, the heat load loading cabin is formed with passageway inside, rear end is provided with nitrogen interface, air is heated after passing through electric heater, hot air enters passageway from tool A air inlet, enters test piece cabin by tool B air outlet, then enters electric heater by cabin air duct, and forms gas circulation.The application can realize multiple physical field synchronous simulation, and have strong generalizability, applicable to multiple models of similar needs.

Description

Technical Field

[0001] This invention belongs to the field of aircraft testing technology, specifically relating to a comprehensive mechanical, thermal, and hypoxic testing device for aircraft compartments. Background Technology

[0002] Aircraft compartments play a crucial role in the aircraft structure by loading equipment, connecting components, and transferring loads. In the design and verification research of aircraft structures, compartment structures are subject to the combined effects of complex environmental factors such as force loads, thermal loads, and low-oxygen environments, which may lead to structural damage and material failure in severe cases.

[0003] To verify the structural reliability of the compartment, it is necessary to conduct simulated tests under combined environmental conditions of force load, thermal load, and low oxygen environment in ground tests.

[0004] However, existing technologies have shortcomings. Environmental simulation is limited, especially for larger aircraft modules, and there is a lack of composite environmental testing devices capable of simultaneously simulating temperature, force loads, and low-oxygen environments. Traditional testing methods for temperature loading of large aircraft modules typically rely on large walk-in test chambers, but such large equipment presents significant technical challenges in achieving low-oxygen control. Furthermore, the operating costs are high for long-cycle testing. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention provides a comprehensive test device for mechanical, thermal, and hypoxic conditions in aircraft compartments.

[0006] This invention provides the following technical solution:

[0007] A comprehensive mechanical, thermal, and hypoxic test apparatus for an aircraft compartment includes a test base, a force load loading device, a test piece, a thermal load loading device, and a control and monitoring system, wherein:

[0008] The test foundation frame includes a ground rail cast beam platform, steel structure casting blocks and constraint fixtures, and the constraint fixtures include a support frame and a pair of fixtures of the same shape and size on it;

[0009] The force load loading device includes a force load loading fixture and a connecting device, a counterweight assembly, and a support airbag arranged sequentially below it. A limit device is also provided below the counterweight assembly. The force load loading fixture is generally hollow cylindrical and includes fixture A and fixture B. Fixture A, fixture B, and the test piece are axially connected in sequence.

[0010] The test piece includes a front hollow frustum-shaped test piece loading section and a rear hollow cylindrical test piece fixing section, wherein the test piece fixing section is clamped and fixed by the constraint fixture;

[0011] The heat load loading device includes a heat load loading chamber, a motor, a fan, an electric heater, an internal air duct, an annular end cover, and a circular motor mounting plate inside the annular end cover. The heat load loading chamber is in the shape of a hollow frustum cone with a channel inside. A nitrogen port is provided at the rear end of the heat load loading chamber.

[0012] The control and monitoring system includes a controller, an oxygen concentration sensor, a temperature sensor, a pressure regulating valve, and a power distribution cabinet.

[0013] Furthermore, the fan, electric heater, and cabin air duct are sequentially arranged inside tooling A, tooling B, and the test piece loading section, the thermal load loading chamber is arranged outside tooling A, tooling B, and the test piece loading section, the end cover is arranged at the front end of tooling A, and the fan is connected to the motor outside the motor mounting plate via a connecting shaft.

[0014] Furthermore, both tooling A and tooling B are provided with flange ends at their front and rear ends. Tooling A has air inlets evenly distributed along its circumference, and tooling B has air outlets evenly distributed along its circumference. After the air is heated by the electric heater, the hot air enters the channel from the air inlet under the blowing of the fan, passes through the cavity between the heat load chamber and the outer wall of the test piece, enters the test piece chamber through the air outlet, and then enters the electric heater through the air duct inside the chamber, forming a gas circulation.

[0015] Furthermore, the oxygen concentration sensor monitors the oxygen concentration in the test chamber and feeds it back to the controller in real time. The controller controls the nitrogen source pressure regulating valve to control the flow rate of nitrogen entering the test chamber. The temperature sensor monitors the ambient temperature in the test chamber and feeds it back to the controller in real time. When the temperature sensor detects that the temperature exceeds the tolerance range, the controller controls the electric heater to adjust the heating output by adjusting the power output of the power distribution cabinet.

[0016] Furthermore, the support frame includes two parallel mounting base plates and two front columns, two rear columns, and a crossbeam on them. The two front columns or two rear columns are respectively mounted on the two mounting base plates. The clamp is generally circular and includes an upper clamp and a lower clamp of the same shape and size. Flange blocks are formed on both sides of the upper clamp and the lower clamp. Fixing holes are opened on the flange blocks. A pair of clamps are respectively set between the two front columns and between the two rear columns. The upper clamp and the lower clamp of each pair of clamps are respectively connected and fixed at the top of the two front columns and the top of the two rear columns by screws passing through the flange blocks.

[0017] Furthermore, the connecting device includes a first double-eared lifting ring, a connecting rod, a force sensor, a second double-eared lifting ring, and a lifting lug arranged sequentially from top to bottom. The first double-eared lifting ring, the connecting rod, the force sensor, and the second double-eared lifting ring are all connected to each other by screws, and the second double-eared lifting ring and the lifting lug are connected by bolts. The flange end at the front end of the tooling A extends outward to form a first ear. The upper end of the first double-eared lifting ring is connected to the first ear. The counterweight assembly includes a counterweight block and a rectangular counterweight mounting plate below it. The lifting lug is connected to the counterweight block. The support airbag is disposed below the counterweight mounting plate. The limiting device includes a rectangular support frame and limiting posts above its four corners. The counterweight assembly is disposed within the limiting device.

[0018] Furthermore, the four corners of the counterweight mounting plate and the supporting airbags are located outside the supporting frame, and there are four supporting airbags, which are respectively located below the four corners of the counterweight mounting plate.

[0019] Furthermore, the heat load loading chamber includes a pair of symmetrically arranged chambers of the same shape and size. Each chamber includes an outer chamber plate, an inner chamber plate, and connecting plates on both sides. The outer chamber plate is larger in axial dimension than the inner chamber plate. A front hatch is formed between the front ends of the outer and inner chamber plates, and a rear hatch is formed between the rear ends of the outer and inner chamber plates. A baffle plate extends inward from the rear end of the outer chamber plate, and the nitrogen inlet is located on the baffle plate. The front end of the outer chamber plate contacts the outer side wall of the front end of tooling A. The lower end of the baffle plate contacts the outer wall of the loading section of the test piece. A cavity is formed between the inner chamber plate and the outer wall of the loading section of the test piece. Multiple reinforcing ribs are evenly distributed along the axial direction on the inner wall of the outer chamber plate. Multiple partitions are evenly distributed circumferentially between the outer and inner chamber plates, and the partitions divide the gap between the outer and inner chamber plates into multiple independent channels.

[0020] Furthermore, the front end of the electric heater is connected to the rear flange end of tooling A, the rear flange end of tooling B is connected to the front end of the test piece, the rear flange end of tooling B extends inward to form a second ear, and the front end of the cabin air duct is connected to the second ear.

[0021] Furthermore, the front part of the cabin air duct is a hollow cylinder, and the rear part is a hollow frustum.

[0022] Compared with the prior art, the beneficial effects of the present invention are:

[0023] 1. Modular conformal heat loading chamber design: Utilizing a symmetrical, split, arc-shaped chamber structure, hollow air ducts are formed through inner and outer steel panels. Electric heaters are directly integrated into the rear end of the load-bearing fixture, creating a closed-loop airflow system. This design offers excellent spatial adaptability; the arc-shaped chamber conforms to the outer contour of the aircraft section, resolving the issue of uneven temperature loading in large sections under traditional walk-in test chambers. Thermal efficiency is improved; the multi-duct design increases the uniformity of hot air distribution by 40%, and the integrated layout of the electric heaters and circulating air ducts reduces heat loss. Compatibility is expanded; the modular structure can adapt to the testing needs of equipment with different diameters and other dimensions, increasing equipment reusability.

[0024] 2. The system integrates force and thermal load co-loading with low-oxygen control. The force load loading device employs a three-stage loading mechanism consisting of a counterweight component, a support airbag, and a limiting device, sharing the same test platform as the thermal load loading device. Low-oxygen control is achieved through a nitrogen interface, an oxygen concentration sensor, and a pressure regulating valve, regulating the oxygen concentration within the test chamber. Multi-physics coupling simulates the coupling effects of thermal load, force load, and low-oxygen environment. The system exhibits good stability in the low-oxygen environment, with a closed-loop nitrogen control system maintaining the oxygen concentration at no more than 5%. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the present invention. Figure 1 ;

[0026] Figure 2 This is a schematic diagram of the present invention. Figure 2 ;

[0027] Figure 3 yes Figure 1 or Figure 2 A schematic diagram with the heat load loading chamber removed;

[0028] Figure 4 This is a schematic diagram of the test specimen;

[0029] Figure 5 This is a schematic diagram of a constraint fixture;

[0030] Figure 6 This is a schematic diagram of a force load loading fixture;

[0031] Figure 7 yes Figure 6 Schematic diagram of tooling A;

[0032] Figure 8 yes Figure 6 Schematic diagram of tooling B;

[0033] Figure 9 This is a schematic diagram of the connecting device;

[0034] Figure 10 yes Figure 9A schematic diagram of the first or second double-eared ring;

[0035] Figure 11 yes Figure 9 A schematic diagram of the connecting rod in the middle;

[0036] Figure 12 yes Figure 9 A schematic diagram of a force sensor;

[0037] Figure 13 yes Figure 9 A schematic diagram of the central lifting lug;

[0038] Figure 14 yes Figure 9 A schematic diagram of the central screw;

[0039] Figure 15 This is a schematic diagram of the limit device;

[0040] Figure 16 This is a schematic diagram of the cabin;

[0041] Figure 17 This is a schematic diagram of an electric heater;

[0042] Figure 18 This is a schematic diagram of the combination of a force load loading fixture and an electric heater;

[0043] Figure 19 This is a schematic diagram of the cabin's air ducts;

[0044] Figure 20 This is a schematic diagram of the combination of force load loading fixture, electric heater and cabin air duct;

[0045] Figure 21 This is a schematic diagram of the temperature and oxygen concentration simulation control process;

[0046] Figure 22 This is a diagram of air circulation.

[0047] Among them, 1-test piece, 111-test piece loading section, 112-test piece fixing section, 2-ground rail cast beam platform, 3-steel structure casting block, 4-constraint clamp, 411-mounting base plate, 412-front column, 413-rear column, 414-crossbeam, 415-upper clamp, 416-lower clamp, 417-flange block, 5-force load loading fixture, 511-fixture A, 5111-air inlet, 5112-first ear, 512-fixture B, 5121-air outlet, 5122-second ear, 6-connecting device, 611-first double-ear lifting ring, 612-connecting rod, 613-force sensor, 614-second double-ear lifting ring, 615-lifting lug, 616-screw, 7-counterweight assembly, 7 11-Counterweight block, 712-Counterweight mounting plate, 8-Support airbag, 9-Limiting device, 911-Support frame, 912-Limiting column, 10-Hot load loading chamber, 1011-Passage, 1012-Outer hatch plate, 1013-Inner hatch plate, 1014-Connecting plate, 1015-Forward hatch, 1016-Rear hatch, 1017-Baffle plate, 1018-Reinforcing rib, 1019-Block, 11-Motor, 12-Fan, 13-Electric heater, 14-Internal air duct, 15-End cover, 16-Motor mounting plate, 17-Nitrogen interface, 18-Cavity, 19-Controller, 20-Oxygen concentration sensor, 21-Temperature sensor, 22-Pressure regulating valve, 23-Electrical control cabinet, 24-Nitrogen source. Detailed Implementation

[0048] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0049] like Figures 1-22 As shown, a comprehensive test apparatus for mechanical, thermal, and hypoxic conditions in an aircraft compartment includes a test base, a force load loading device, a test piece 1, a thermal load loading device, and a control and monitoring system, wherein:

[0050] The test foundation frame includes a ground rail cast beam platform 2, a steel structure casting block 3, and a constraint clamp 4. The constraint clamp 4 includes a support frame and a pair of clamps of the same shape and size on it.

[0051] The force load loading device includes a force load loading fixture 5 and a connecting device 6, a counterweight assembly 7 and a support airbag 8 arranged sequentially below it. A limit device 9 is also provided below the counterweight assembly 7. The force load loading fixture 5 is generally hollow cylindrical and includes fixture A511 and fixture B512. Fixture A511, fixture B512 and test piece 1 are axially connected in sequence.

[0052] The test piece 1 includes a front hollow frustum-shaped test piece loading section 111 and a rear hollow cylindrical test piece fixing section 112, wherein the test piece fixing section 112 is clamped and fixed by the constraint clamp 4.

[0053] The heat load loading device includes a heat load loading chamber 10, a motor 11, a fan 12, an electric heater 13, an internal air duct 14, an annular end cover 15, and a circular motor mounting plate 16 inside the annular end cover 15. The heat load loading chamber 10 is generally in the shape of a hollow frustum cone, with a channel 1011 formed inside. A nitrogen port 17 is provided at the rear end of the heat load loading chamber 10.

[0054] The control and monitoring system includes a controller 19, an oxygen concentration sensor 20, a temperature sensor 21, a pressure regulating valve 22, and a power distribution cabinet 23.

[0055] The aforementioned aircraft section thermal hypoxia integrated test device has a fan 12, an electric heater 13, and an internal air duct 14 sequentially arranged inside the fixture A511, fixture B512, and test piece loading section 111. The thermal load loading chamber 10 is arranged outside the fixture A511, fixture B512, and test piece loading section 111. The end cover 15 is arranged at the front end of fixture A511. The fan 12 is connected to the motor 11 outside the motor mounting plate 16 via a connecting shaft.

[0056] The aforementioned aircraft compartment thermal hypoxia integrated test device has flange ends at both the front and rear ends of tooling A511 and tooling B512. Tooling A511 has air inlets 5111 evenly distributed along its circumference, and tooling B512 has air outlets 5121 evenly distributed along its circumference. After being heated by electric heater 13, the hot air enters the channel 1011 from the air inlet 5111 under the blowing of fan 12, passes through the cavity 18 between the thermal load loading chamber 10 and the outer wall of the test piece 1, enters the test piece 1 chamber through the air outlet 5121, and then enters the electric heater 13 through the chamber air duct 14, forming a gas circulation.

[0057] The aforementioned aircraft compartment thermal hypoxia integrated test device has an oxygen concentration sensor 20 that monitors the oxygen concentration inside the test specimen 1 compartment and provides real-time feedback to the controller 19. The controller 19 controls the nitrogen source pressure regulating valve 22 to control the flow rate of nitrogen entering the test specimen 1 compartment. The temperature sensor 21 monitors the ambient temperature inside the test specimen 1 compartment and provides real-time feedback to the controller 19. When the temperature sensor 21 detects that the temperature exceeds the allowable range, the controller 19 controls the electric heater 13 to adjust the heating output by adjusting the power output of the power distribution cabinet 23.

[0058] The aforementioned aircraft section thermal hypoxia integrated test device has a support frame comprising two parallel mounting base plates 411 and two front columns 412, two rear columns 413, and a crossbeam 414 on them. The two front columns 412 or the two rear columns 413 are respectively mounted on the two mounting base plates 411. The clamp is generally circular and includes an upper clamp 415 and a lower clamp 416 of the same shape and size. Flange blocks 417 are formed on both sides of the upper clamp 415 and the lower clamp 416. Fixing holes are provided on the flange blocks 417. A pair of clamps are respectively set between the two front columns 412 and between the two rear columns 413. The upper clamp 415 and the lower clamp 416 of each pair of clamps are connected and fixed to the top of the two front columns 412 and the top of the two rear columns 413 by screws passing through the flange blocks 417.

[0059] The aforementioned aircraft compartment force-thermal-hypoxia integrated test device includes a connecting device 6 comprising a first double-eared lifting ring 611, a connecting rod 612, a force sensor 613, a second double-eared lifting ring 614, and a lifting lug 615 arranged sequentially from top to bottom. The first double-eared lifting ring 611, the connecting rod 612, the force sensor 613, and the second double-eared lifting ring 614 are all connected to each other by screws 616, and the second double-eared lifting ring 614 and the lifting lug 615 are connected by bolts. The flange at the front end of the tooling A511... The first ear 5112 is formed by extending outward from the end. The upper end of the first double-eared hanging ring 611 is connected to the first ear 5112. The counterweight assembly 7 includes a counterweight block 711 and a rectangular counterweight mounting plate 712 below it. The hanging ear 615 is connected to the counterweight block 711. The support airbag 8 is disposed below the counterweight mounting plate 712. The limiting device 9 includes a rectangular support frame 911 and limiting posts 912 above its four corners. The counterweight assembly 7 is disposed inside the limiting device 9.

[0060] The aforementioned aircraft compartment thermal hypoxia integrated test device has a counterweight mounting plate 712 with four corners and support airbags 8 outside the support frame 911. There are four support airbags 8, which are respectively set below the four corners of the counterweight mounting plate 712.

[0061] The aforementioned integrated thermal hypoxia test device for aircraft modules includes a thermal load loading chamber 10 comprising a pair of symmetrically arranged chambers of the same shape and size. Each chamber includes an outer panel 1012, an inner panel 1013, and two connecting plates 1014 on both sides. The outer panel 1012 is larger in axial dimension than the inner panel 1013. A front hatch 1015 is formed between the front ends of the outer panel 1012 and the inner panel 1013, and a rear hatch 1016 is formed between the rear ends of the outer panel 1012 and the inner panel 1013. A baffle 1017 extends inward from the rear end of the outer panel 1012. The nitrogen inlet... 17 is set on the baffle 1017. The front end of the outer compartment 1012 contacts the outer side wall of the front end of the tooling A511. The lower end of the baffle 1017 contacts the outer wall of the loading section 111 of the test piece. A cavity 18 is formed between the inner compartment 1013 and the outer wall of the loading section 111 of the test piece. Multiple reinforcing ribs 1018 are evenly distributed along the axial direction on the inner wall of the outer compartment 1012. Multiple partitions 1019 are evenly distributed along the circumferential direction between the outer compartment 1012 and the inner compartment 1013. The partitions 1019 divide the gap between the outer compartment 1012 and the inner compartment 1013 into multiple independent channels 1011.

[0062] The aforementioned aircraft compartment thermal hypoxia integrated test device has an electric heater 13 whose front end is connected to the rear flange end of tooling A511, the rear flange end of tooling B512 connected to the front end of test piece 1, the rear flange end of tooling B512 extending inward to form a second ear 5122, and the front end of the cabin air duct 14 connected to the second ear 5122.

[0063] The aforementioned aircraft compartment thermal hypoxia integrated test device has a hollow cylinder at the front of its internal air duct 14 and a hollow frustum shape at the rear.

[0064] The test piece 1 can be divided into two parts: a front end (test piece loading section 111) and a rear end (test piece fixing section 112), which are screwed together. During the test, only the front end (test piece loading section 111) of the test piece 1 needs to be heated.

[0065] The ground rail cast beam platform 2 is a cast beam platform made of high-strength cast iron, and adopts a T-slot design for the assembly of test equipment.

[0066] The number of steel structure casting blocks 3 is N, where N≥2, and the steel structure casting blocks are used to mount the constraint clamps 4.

[0067] The lower clamp 416 of the constraint clamp 4 is connected to the crossbeam 414 by welding.

[0068] The force load loading fixture 5 is a ring frame structure, and the whole is cylindrical.

[0069] like Figure 18As shown, tooling A511 has 8 through holes and 8 threaded holes evenly distributed at its rear end. Tooling A511 is fixedly connected to tooling B512 through the 8 through holes; tooling A511 is fixedly connected to electric heater 13 through the 8 threaded holes.

[0070] The rear flange end of the tooling B512 has evenly distributed through holes, which are fixedly connected to the threaded holes on the front end face of the test piece 1 section with bolts.

[0071] The second ear 5122 at the rear end of tooling B512 is connected to the cabin air duct 14 by bolts.

[0072] The rear flange end of tooling A511 is connected to the front flange end of tooling B512 by evenly distributed bolts.

[0073] The tooling A511 and tooling B512 have straight grooves evenly distributed along the annular direction on their frame surfaces, which are respectively the air inlet 5111 and the air outlet 5121.

[0074] like Figure 9 As shown, from top to bottom, the first double-eared lifting ring 611 and the connecting rod 612 are screwed together by a screw 616. The upper and lower ends of the connecting rod 612 have reverse threads, which allows the connection length of the force load connecting device 6 to be adjustable. The connecting rod 612 and the force sensor 613 are screwed together by a screw 616. The force sensor 613 and the second double-eared lifting ring 614 are screwed together by a screw 616. The second double-eared lifting ring 614 and the lifting lug 615 are connected by high-strength bolts passing through the lug holes of the second double-eared lifting ring 614 and the lifting lug 615 in sequence. The first double-eared lifting ring 611 and the second double-eared lifting ring 614 have the same structure and size.

[0075] The first double-eared lifting ring 611 of the force load connecting device 6 is connected to the first ear 5112 of the tooling A511, the lifting lug 615 is connected to the counterweight block 711 of the counterweight assembly 7, the screw 616 and the connecting rod 612 cooperate to realize the transmission of force load, and the force sensor 613 is used to detect the magnitude of the force load.

[0076] The counterweight assembly 7 comprises a counterweight block 711 in the form of a weight and a counterweight mounting plate 712. The counterweight block 711 is adjustable in terms of quantity and specifications to achieve adjustable force load. The counterweight block 711 is mounted on the counterweight mounting plate 712.

[0077] The support airbags 8 are located at the four corners of the lower side of the counterweight mounting plate 712. They are filled with air before the test to achieve an initial state of zero load. The force load is slowly loaded from zero to the specified value by adjusting the pressure relief of the support airbags.

[0078] The limiting device 9 is located at the lower end of the counterweight assembly 7. The bottom support frame 911 of the limiting device 9 is fixedly installed on the ground rail cast beam platform 2. The counterweight assembly 7 is constrained in a specified position by four limiting columns 912 to prevent the counterweight from shifting during the application of force load.

[0079] The force of the counterweight is transmitted to tooling A511 through the force load connection device, and finally acts on the end face of section 1 of the test piece to achieve the application of the specified shear force and bending moment load.

[0080] The heat load loading chamber 10 adopts a symmetrical split structure, consisting of an upper chamber and a lower chamber. The two chambers have the same structure and together constitute the heat load application chamber for the loading section 111 of the test piece.

[0081] The walls of the heat load loading chamber 10 are made of 2mm thick steel plates in an arc shape.

[0082] The heat load loading chamber 10 has two parts, both of which are hollow bodies formed by inner and outer curved wall panels 1013, outer panel 1012 and connecting plates 1014 on both sides. Five curved reinforcing ribs 1018 are evenly arranged axially in the hollow body. Eight partitions 1019 are evenly distributed circumferentially in the hollow body, thereby dividing the body into nine independent channels 1011.

[0083] The inner and outer wall panels at the front end of the heat load loading chamber 10 both extend upwards in the thickness direction to form vertical edge structures. The vertical edge of the outer wall panel at the front end of the heat load loading chamber 10 overlaps with the front end of fixture A511; the vertical edge of the inner wall panel at the front end of the heat load loading chamber 10 overlaps with the rear end of fixture A511. The outer wall panel at the rear end of the heat load loading chamber 10 extends upwards in the thickness direction to form a vertical edge structure, overlapping the outer wall surface of the test piece 1. That is, the front end of the heat load loading chamber 10 is in contact with the outer wall of fixture A511, and the rear end of the heat load loading chamber 10 is in contact with the outer wall of the loading section 111 of the test piece.

[0084] The electric heater 13 is a cylindrical structure with a circular array of heating wires installed inside. The heating wires are evenly arranged to ensure uniform hot air and low air resistance. The electric heater 13 is mounted and fixed to the rear flange end of tooling A511 via an end flange.

[0085] The front end of the internal air duct 14 is cylindrical, and the rear end is a progressive horn-shaped structure. The internal air duct 14 is fixed to the rear flange end of tooling B512 via the front flange.

[0086] The motor 11 is fixedly mounted on the motor mounting plate 16 by a bottom support.

[0087] After being heated by the electric heater 13, the hot air enters the channel 1011 of the heat load loading chamber 10 from the front hatch 1015 through the air inlet 5111 of tooling A511, passes through the cavity 18 between the heat load loading chamber 10 and the outer surface of the test piece 1 from the rear hatch 1016, enters the test piece 1 chamber through the air outlet 5121, and enters the electric heater 13 through the air duct 14 inside the chamber, forming a gas circulation. The hot air heats the test piece chamber to the specified temperature.

[0088] When the fan 12 is turned on, air flows in the direction of the fan 12 (the circumference of the electric heater 13 is sealed, so air cannot flow in the circumference). The air is heated by the electric heater 13 and flows into the force load loading fixture 5 (there is no flow between fixture A511 and fixture B512 because of the electric heater 13). The air can only flow out through the air inlet 5111 on fixture A511 and enter the channel 1011.

[0089] The oxygen concentration sensor 20 is used to measure the oxygen concentration inside the test specimen chamber.

[0090] The temperature sensor 21 is used to measure the temperature of the environment inside the test chamber.

[0091] Both the oxygen concentration sensor 20 and the temperature sensor 21 are installed inside the tooling A511.

[0092] A nitrogen port 17 is provided on the upper part of the rear side baffle 1017 of the heat load loading chamber 10.

[0093] The nitrogen source 24 is used to supply nitrogen into the heat load chamber 10, thereby replacing the air inside the chamber.

[0094] The control and monitoring system monitors the oxygen concentration in the test chamber through oxygen concentration sensor 20. When the oxygen concentration exceeds the specified oxygen concentration, the flow rate of nitrogen entering the test chamber is controlled by adjusting nitrogen source pressure regulating valve 22. The system also monitors the ambient temperature in the test chamber through temperature sensor 21. When the temperature monitored by temperature sensor 21 is not within the allowable range of the control temperature, the controller 19 controls the electric heater 13 to adjust the heating output by adjusting the power output of the external power distribution cabinet 23.

[0095] The specific steps of the experiment are as follows:

[0096] 1. First, construct the test foundation frame and place at least two steel structure casting blocks 3 in parallel at a fixed distance on the ground rail casting beam platform 2.

[0097] 2. The constraint clamp 4 is installed and fixed on the steel structure casting block 3 via the mounting base plate 411.

[0098] 3. Fix the test specimen fixing section 112 to the test base frame using the upper and lower clamps of the constraint clamp 4.

[0099] 4. Place the air duct 14 inside the test specimen loading section 111, and fix the test specimen loading section 111 and the test specimen fixing section 112 with end bolts.

[0100] 5. Install the load-bearing fixture and fix the rear end of fixture B512 to the front end of test specimen section 1. Install and fix the internal air duct 14 to the rear end lug of fixture B512 via the front flange.

[0101] 6. The end cap 15 is rigidly connected to the front end of tooling A511 through a circumferentially distributed array of bolt holes.

[0102] 7. Install and fix the fan 12 on the motor 11. The motor 11 is fixedly installed on the motor mounting plate 16 through the bottom support. The motor mounting plate 16 is fixedly connected to the end cover 15 through the circumferentially distributed bolt hole array.

[0103] 8. Install the heat load loading chamber 10. Place the front and rear ends of the heat load loading chamber 10 directly onto the tooling A511 and the test piece 1. Then, connect and seal the front and rear ends of the heat load loading chamber 10 with the outer surface of the tooling A511 and the test piece 1 chamber section using 704 silicone to ensure the airtightness of the chamber.

[0104] 9. The first double-eared lifting ring 611 of the force load connection device is connected to the first ear 5112 at the front end of the tooling A511 via a pin. The installation screw 616, connecting rod 612, force sensor 613, second double-eared lifting ring 614, and lifting lug 615 are installed. The lower end of the lifting lug 615 is connected to the counterweight assembly. Support airbags 8 are installed at the four corners of the lower side of the counterweight mounting plate 712.

[0105] 10. Set up the measurement and control system, connect temperature sensor 21, oxygen concentration sensor 20, and nitrogen source 24 to nitrogen interface 17.

[0106] 11. High-temperature resistant thermal insulation material is wrapped around the outside of the heat load chamber 10, the outside of the test piece fixing section 112, and the outside of the end cap 15 to maintain the temperature of the test system.

[0107] 12. Before the test, depressurize the support airbag 8 to slowly load the force load from zero to the specified value.

[0108] 13. When motor 11 is powered on, the air circulation inside the test system is achieved through the interaction of motor 11 and fan 12. A schematic diagram of the air circulation within the system is shown below. Figure 22 As shown.

[0109] 14. Open the nitrogen inlet and continuously blow nitrogen into the heat load chamber 10. After the oxygen concentration sensor 20 monitors and reaches a low oxygen state (oxygen concentration not greater than 5%), adjust the pressure regulating valve 22 to adjust the nitrogen charging volume. The oxygen concentration in the test specimen 1 chamber is obtained by monitoring the oxygen concentration sensor 20. When the oxygen concentration exceeds the specified oxygen concentration, the flow rate of nitrogen entering the test specimen 1 chamber is controlled by adjusting the nitrogen source pressure regulating valve 22.

[0110] 15. After being heated by the electric heater 13, the hot air enters the internal channel 1011 of the heat load loading chamber 10 through the air inlet 5111 of the tooling A511, passes through the cavity 18 between the heat load loading chamber 10 and the outer surface of the test piece 1, enters the test piece 1 chamber through the air outlet 5121, and enters the electric heater 13 through the air duct 14 inside the chamber, forming a gas circulation. The hot air heats the test piece chamber to the specified temperature.

[0111] 16. The ambient temperature inside the test chamber is monitored by temperature sensor 21. When the temperature monitored by temperature sensor 21 is not within the allowable range of the control temperature, controller 19 controls the electric heater 13 to adjust the heating output by adjusting the power output of the external power distribution cabinet 23.

[0112] Compared with existing technologies, this invention designs a combined mechanical, thermal, and hypoxic test device for aircraft compartments, which can realize simultaneous simulation of multiple physical fields and has strong scalability, applicable to similar needs of various models.

[0113] This article uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only for the purpose of helping to understand the method and core ideas of the present invention. The above descriptions are only preferred embodiments of the present invention. It should be noted that due to the limitations of textual expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of the present invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of the present invention.

Claims

1. A comprehensive test device for mechanical, thermal, and hypoxic conditions in aircraft compartments, characterized in that, It includes a test base frame, a force load loading device, a test piece (1), a thermal load loading device, and a control and monitoring system, wherein: The test foundation platform includes a ground rail cast beam platform (2), a steel structure casting block (3), and a constraint fixture (4). The constraint fixture (4) includes a support frame and a pair of fixtures of the same shape and size on it. The force load loading device includes a force load loading fixture (5) and a connecting device (6), a counterweight assembly (7), and a support airbag (8) arranged sequentially below it. The connecting device (6) includes a first double-eared lifting ring (611), a connecting rod (612), a force sensor (613), a second double-eared lifting ring (614), and a lifting lug (615) arranged sequentially above and below it. The first double-eared lifting ring (611), the connecting rod (612), the force sensor (613), and the second double-eared lifting ring (614) are all connected to each other by screws (616), and the second double-eared lifting ring (614) and the lifting lug (615) are connected by bolts. The counterweight assembly (7) includes a counterweight block (711) and a rectangular counterweight mounting plate (712) below it. The lifting lug (615) and the The counterweight (711) is connected, the support airbag (8) is located below the counterweight mounting plate (712), and a limit device (9) is also provided below the counterweight assembly (7). The limit device (9) includes a rectangular support frame (911) and limit posts (912) above its four corners. The counterweight assembly (7) is located inside the limit device (9). The force load loading fixture (5) is in the shape of a hollow cylinder and includes fixture A (511) and fixture B (512). Fixture A (511), fixture B (512) and test piece (1) are connected axially in sequence. The flange end of the front end of fixture A (511) extends outward to form a first ear (5112). The upper end of the first double ear lifting ring (611) is connected to the first ear (5112). The test piece (1) includes a front hollow frustum-shaped test piece loading section (111) and a rear hollow cylindrical test piece fixing section (112), and the test piece fixing section (112) is clamped and fixed by the constraint clamp (4); The heat load loading device includes a heat load loading chamber (10), a motor (11), a fan (12), an electric heater (13), an internal air duct (14), an annular end cover (15), and a circular motor mounting plate (16) inside the annular end cover (15). The heat load loading chamber (10) is in the shape of a hollow frustum, with a channel (1011) formed inside. A nitrogen port (17) is provided at the rear end of the heat load loading chamber (10). The control and monitoring system includes a controller (19), an oxygen concentration sensor (20), a temperature sensor (21), a pressure regulating valve (22), and a power distribution cabinet (23).

2. The integrated mechanical, thermal, and hypoxic test apparatus for aircraft compartments according to claim 1, characterized in that, The fan (12), electric heater (13) and cabin air duct (14) are sequentially arranged inside the fixture A (511), fixture B (512) and test piece loading section (111). The heat load loading chamber (10) is arranged outside the fixture A (511), fixture B (512) and test piece loading section (111). The end cover (15) is arranged at the front end of fixture A (511). The fan (12) is connected to the motor (11) outside the motor mounting plate (16) through a connecting shaft.

3. The integrated mechanical, thermal, and hypoxic test apparatus for aircraft compartments according to claim 1, characterized in that, The tooling A (511) and tooling B (512) are provided with flange ends at both ends. The tooling A (511) has air inlets (5111) evenly distributed along the circumference, and the tooling B (512) has air outlets (5121) evenly distributed along the circumference. After the air is heated by the electric heater (13), the hot air enters the channel (1011) from the air inlet (5111) under the blowing of the fan (12), passes through the cavity (18) between the heat load loading chamber (10) and the outer wall of the test piece (1), enters the test piece (1) chamber through the air outlet (5121), and then enters the electric heater (13) through the air duct (14) in the chamber, forming a gas circulation.

4. The integrated mechanical, thermal, and hypoxic test apparatus for aircraft compartments according to claim 1, characterized in that, The oxygen concentration sensor (20) monitors the oxygen concentration in the test specimen (1) chamber and feeds it back to the controller (19) in real time. The controller (19) controls the nitrogen source pressure regulating valve (22) to control the flow rate of nitrogen entering the test specimen (1) chamber. The temperature sensor (21) monitors the ambient temperature in the test specimen (1) chamber and feeds it back to the controller (19) in real time. When the temperature sensor (21) monitors the temperature exceeding the tolerance range, the controller (19) controls the electric heater (13) to adjust the heating output by adjusting the power output of the power distribution cabinet (23).

5. The integrated mechanical, thermal, and hypoxic test apparatus for aircraft compartments according to claim 1, characterized in that, The support frame includes two parallel mounting base plates (411) and two front columns (412), two rear columns (413) and a crossbeam (414) on them. The two front columns (412) or two rear columns (413) are respectively mounted on the two mounting base plates (411). The clamp is circular in shape and includes an upper clamp (415) and a lower clamp (416) of the same shape and size. Flange blocks (417) are formed on both sides of the upper clamp (415) and the lower clamp (416). Fixing holes are opened on the flange blocks (417). A pair of clamps are respectively set between the two front columns (412) and between the two rear columns (413). The upper clamp (415) and the lower clamp (416) of each pair of clamps are connected and fixed by screws passing through the flange blocks (417) at the top of the two front columns (412) and the top of the two rear columns (413).

6. The integrated mechanical, thermal, and hypoxic test apparatus for aircraft compartments according to claim 1, characterized in that, The four corners of the counterweight mounting plate (712) and the support airbags (8) are outside the support frame (911). There are four support airbags (8), which are respectively set below the four corners of the counterweight mounting plate (712).

7. The integrated mechanical, thermal, and hypoxic test apparatus for aircraft compartments according to claim 3, characterized in that, The heat load loading chamber (10) includes a pair of symmetrically arranged chambers of the same shape and size. Each chamber includes an outer panel (1012), an inner panel (1013), and two side connecting plates (1014). The outer panel (1012) is larger in axial dimension than the inner panel (1013). A front hatch (1015) is formed between the front ends of the outer panel (1012) and the inner panel (1013), and a rear hatch (1016) is formed between the rear ends of the outer panel (1012) and the inner panel (1013). A baffle (1017) extends inward from the rear end of the outer panel (1012). The nitrogen port (17) is located on the baffle (1014). 7) The front end of the outer panel (1012) contacts the outer side wall of the front end of the tooling A (511), the lower end of the baffle (1017) contacts the outer wall of the loading section (111) of the test piece, and a cavity (18) is formed between the inner panel (1013) and the outer wall of the loading section (111) of the test piece. Multiple reinforcing ribs (1018) are evenly distributed along the axial direction on the inner wall of the outer panel (1012). Multiple partitions (1019) are evenly distributed along the circumferential direction between the outer panel (1012) and the inner panel (1013). The partitions (1019) divide the gap between the outer panel (1012) and the inner panel (1013) into multiple independent channels (1011).

8. The integrated mechanical, thermal, and hypoxic test apparatus for aircraft compartments according to claim 1, characterized in that, The front end of the electric heater (13) is connected to the rear flange end of tooling A (511), the rear flange end of tooling B (512) is connected to the front end of the test piece (1), the rear flange end of tooling B (512) extends inward to form a second ear (5122), and the front end of the cabin air duct (14) is connected to the second ear (5122).

9. The integrated mechanical, thermal, and hypoxic test apparatus for aircraft compartments according to claim 1, characterized in that, The front part of the cabin air duct (14) is a hollow cylinder, and the rear part is a hollow frustum.

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