CN219065388U

CN219065388U - Burn-through resistant experimental device for aircraft lining plate material

Info

Publication number: CN219065388U
Application number: CN202222801827.5U
Authority: CN
Inventors: 贾旭宏; 张晓宇; 代尚沛; 汤婧; 马俊豪; 徐松涛; 陈现涛
Original assignee: Civil Aviation Flight University of China
Current assignee: Civil Aviation Flight University of China
Priority date: 2022-10-24
Filing date: 2022-10-24
Publication date: 2023-05-23
Anticipated expiration: 2032-10-24

Abstract

The utility model discloses a burn-through resistance experimental device for an aircraft lining plate material, and belongs to the technical field of burn-through resistance testing equipment. An aircraft liner material burn-through resistant experimental apparatus comprising: the burner and the bracket are arranged at the top of the base plate, and the camera is arranged on the bracket and used for shooting and recording the flame of the burner and the experimental surface of the lining plate; the support frame is in sliding fit with the base plate, a locking part is connected to the support frame through threads and used for fixing a lining plate material, a thermocouple is fixedly connected to the support frame and positioned in front of an experimental surface of the lining plate, and a heat flow meter is fixedly connected to the support frame and used in cooperation with the thermocouple; according to the utility model, through the basic burner and the recording equipment, the data of the lining board burn-through experiment are collected in real time, the whole experiment process is simple and quick, the experiment platform is built to meet the test requirements, and the measurement accuracy is higher.

Description

Burn-through resistant experimental device for aircraft lining plate material

Technical Field

The utility model relates to the technical field of burn-through resistance test equipment, in particular to an aircraft lining plate material burn-through resistance experimental device.

Background

In aircraft design, fire protection requirements for materials, structures and equipment, if they exist, require that they be qualified for airworthiness. And (3) carrying out burn-through resistance test on the cargo compartment liner plate of the cargo compartment liner material on the aircraft according to the standard of civil aviation industry. Most of the existing equipment exists in some research institutions, the measurement cost is high, the structure of the testing device is complex, the operation is complex, the testing time is too long, and the equipment cannot be popularized.

The device specially aiming at the burn-through resistance test of the aircraft lining plate material has high measurement cost, expensive equipment, complex structure, complex operation and incapability of popularizing, and in addition, the burn-through resistance device existing on the market does not accord with the test method in the third part of annex F of the CCAR25 part, namely the test method for determining the flame burn-through resistance of the cargo compartment liner, and the test method in the MH/T6086-2012, namely the burn-through resistance test of the aircraft cargo compartment lining plate, and does not meet the measurement requirement of the aircraft cargo compartment lining plate.

Disclosure of Invention

The utility model aims to solve the problems that an experimental device in the prior art is complex in structure, the experimental process does not meet the test standard, and the provided burn-through resistant experimental device for the aircraft lining plate material is provided.

In order to achieve the above purpose, the present utility model adopts the following technical scheme:

an aircraft liner material burn-through resistant experimental apparatus comprising: the burner and the bracket are arranged at the top of the base plate, and the camera is arranged on the bracket and used for shooting and recording the flame of the burner and the experimental surface of the lining plate; the support frame is in sliding fit with the base plate, wherein the support frame is provided with a locking part in a threaded manner and is used for fixing a lining plate material, a thermocouple is fixedly connected to the support frame and is positioned in front of an experimental surface of the lining plate, and the support frame is fixedly connected with a heat flow meter which is matched with the thermocouple for use.

In order to ensure the stability of equipment installation, preferably, the support frame comprises three vertical rods which are parallel to each other and a cross rod which is sequentially connected with the three vertical rods, a frame with a hollowed cross section of triangle is formed, and the locking part, the thermocouple and the heat flow meter are arranged on the cross rod.

In order to promote the stability to welt centre gripping, further, locking portion includes: the two groups of screws are symmetrically arranged on the upper cross rod and the lower cross rod, threaded holes are formed in the cross rods, and the screws are in threaded connection in the threaded holes; the stepped clamping blocks are fixedly connected to one end of the screw rod, and steps of the two clamping blocks are oppositely arranged; the knob is fixedly connected to the other end of the screw rod and is used for increasing a force arm for applying a rotating force to the screw rod.

In order to improve the accuracy of monitoring temperature, furthermore, set up multiunit locating hole on the horizontal pole, many thermocouples peg graft respectively in the locating hole, and the position of at least one thermocouple just is to the central line of the flame export of combustor, heat flow meter fixed connection just is located the side of thermocouple under the horizontal pole.

For the distance between accurate control test welt and the combustor, preferably, fixed connection guide bar on the support frame, the guiding hole has been seted up to the bottom of base plate, guide bar sliding connection is in the guiding hole, one side threaded connection of guiding hole has the locking bolt that can offset with the guide bar outer wall, just be provided with the scale mark on the guide bar.

In order to be convenient for supply air for the combustor, preferably, the top fixedly connected with arc splint of base plate, centre gripping gas holder on the arc splint, the gas holder is linked together through pipeline and combustor, the combustor just is connected with the injection pipe to the direction fixedly connected with of support frame.

In order to facilitate the monitoring of the combustion condition by the camera, preferably, the bracket comprises a positioning column fixedly connected with the top of the substrate, the top of the positioning column is rotationally connected with a placing frame in a concave shape, and the camera is clamped in the placing frame.

For real-time recording of experimental data, preferably, a recorder is fixedly connected to the top of the substrate, and the thermocouple and the heat flow meter are electrically connected with the recorder.

Compared with the prior art, the utility model provides the burn-through resistant experimental device for the aircraft lining plate material, which has the following beneficial effects:

1. according to the burn-through resistant experimental device for the aircraft lining plate material, one face and one edge of the triangular support frame can be opposite to the jet orifice of the burner, and the support frame cannot shake or roll over in the experimental process, so that the experimental safety is ensured;

2. according to the burn-through resistant experimental device for the aircraft lining plate material, the steps of the two clamping blocks are arranged oppositely, so that the position of the lining plate is effectively controlled, dislocation is prevented when flame is impacted, and the stability of an experiment is further improved;

3. the burn-through resistant experimental device for the aircraft lining material is simple in device, easy to obtain in equipment, capable of being completely and independently built, widely applicable to composite material manufacturers, universities and the like for experimental study of the aircraft lining material, capable of checking whether the aircraft lining material is qualified or not in a short time, knowing specific influence factors of burn-through resistance of the aircraft lining material, and accelerating research and development of the aircraft lining material in China.

The device has the advantages that the parts which are not involved in the device are the same as or can be realized by adopting the prior art, the data of the lining board burn-through experiment are collected in real time through the basic burner and the recording equipment, the whole experiment process is simple and quick, the experiment platform is built to meet the test requirements, and the measurement accuracy is higher.

Drawings

FIG. 1 is a schematic diagram of an experimental device for burn-through resistance of an aircraft liner material according to the present utility model;

FIG. 2 is a schematic diagram II of an experimental device for burn-through resistance of an aircraft liner material according to the present utility model;

fig. 3 is a schematic structural diagram III of an experimental device for burn-through resistance of an aircraft lining material.

In the figure: 1. a substrate; 101. an arc clamping plate; 102. a recorder; 103. positioning columns; 104. a placing rack; 105. a guide hole; 2. a gas storage tank; 3. a burner; 301. a jet pipe; 4. a camera; 5. a support frame; 501. a guide rod; 502. a locking bolt; 6. a screw; 601. a clamping block; 602. a knob; 7. a thermocouple; 8. a heat flow meter.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments.

In the description of the present utility model, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present utility model and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model.

Examples:

referring to fig. 1-3, an aircraft liner material burn-through resistant experimental apparatus comprising: the device comprises a base plate 1 with at least one basically flat surface, wherein a burner 3 is arranged at the top of the base plate 1, a positioning column 103 is fixedly connected to the top of the base plate 1, a rack 104 in a concave shape is rotatably connected to the top of the positioning column 103, a bracket is formed, a high-definition camera 4 with a camera shooting function is clamped in the rack 104, and the camera 4 is used for shooting and recording the burning state of flames of the burner 3 and the ablation condition of an experimental surface of a lining plate; the support frame 5 is in sliding fit with the base plate 1, wherein a locking part is in threaded connection with the support frame 5 and is used for fixing a lining plate material, so that a certain distance is kept between the experimental lining plate and the combustor 3, the experimental surface of the lining plate is ensured to be opposite to combustion flame, a thermocouple 7 is fixedly connected to the support frame 5 and positioned in front of the experimental surface of the lining plate and used for collecting flame temperature sprayed on the lining plate in real time, and a heat flow meter 8 is fixedly connected to the support frame 5, the distance between the heat flow meter and the flame is kept at 300mm and is matched with the thermocouple 7.

In the scheme, the type of the thermocouple 7 is preferably K-type armoured couple, the type of the heat flow meter 8 is preferably TS-34C type, in the experimental process, the paperless recorder 102 can be fixedly connected to the top of the base plate 1, the thermocouple 7 and the heat flow meter 8 are electrically connected with the recorder 102, thus the flame temperature and the data of the heat flow meter 8 are collected, displayed and stored in real time, a lining plate to be tested with a specified thickness is selected before the experiment and is fixed on the supporting frame 5 through the locking part, the distance between the supporting frame 5 and the base plate 1 is regulated to be about 500mm, the flame and the lining plate can be shot when the camera 4 rotates to a proper position, the burner 3 is preheated, the flame does not contact with the sample during preheating, and the burner 3 is opened to burn for at least 2min to ensure that the stable burning heat flow density is not less than 8.6w/cm ² And then the burner 3 ablates the sample, and simultaneously starts a timer, the thermocouple temperature on the sample is recorded at least once every second during the test, the temperature of each thermocouple is not lower than 871 ℃, the sample is placed in flame for 5min, if the flame burns through the sample within 5min, the test can be terminated in advance, the whole test process is simple and quick, the test platform is built to meet the test requirement, and the measurement accuracy is higher.

In the scheme, the support frame 5 comprises three vertical rods which are parallel to each other and a cross rod which is sequentially connected with the three vertical rods, a hollowed triangular prism frame is formed, the cross section of the hollowed triangular prism frame is triangular, the locking part, the thermocouple 7 and the heat flow meter 8 are arranged on the cross rod, one surface and one edge of the triangular prism can be opposite to the injection port of the combustor 3, the support frame 5 cannot shake or roll over in the experimental process, and the experimental safety is guaranteed.

In an aircraft liner material burn-through resistant experimental apparatus, a locking portion thereof includes: the number of each screw rod 6 is at least two, and the two screw rods 6 are symmetrically arranged on the upper cross rod and the lower cross rod, so that an experimental lining plate can be supported and clamped up and down, and the stability of an experimental process is ensured, wherein threaded holes are formed in the cross rods, and the screw rods 6 are in threaded connection in the threaded holes, so that the adjustment is convenient, and the flexibility of the experiment is improved according to the size of the lining plate; the stepped clamping blocks 601 are fixedly connected to one end of the screw rod 6, steps of the two clamping blocks 601 are oppositely arranged, namely, the side face of a step with a higher step is attached to the side face of the lining plate, the top face of a step with a lower step is abutted against the upper end face and the lower end face of the lining plate, so that the position of the lining plate is effectively controlled, dislocation is prevented when flame is impacted, and the stability of an experiment is further improved; the knob 602 fixedly connected to the other end of the screw 6 is used for increasing the arm of force for applying the rotating force to the screw 6, so that the lining plate is conveniently fixed.

The cross rod is provided with a plurality of groups of positioning holes, three, four or five thermocouples 7 are respectively inserted in the positioning holes, the position of at least one thermocouple 7 is opposite to the central line of the flame outlet of the burner 3 and is used for recording the temperature of the flame center in real time, the heat flow meter 8 is fixedly connected under the upper cross rod and is positioned at the side edge of the thermocouple 7, and the flame is prevented from being damaged due to direct contact with the heat flow meter 8.

The guide rod 501 is fixedly connected to the support frame 5, the guide hole 105 is formed in the bottom of the base plate 1, the guide rod 501 is slidably connected to the guide hole 105, the distance between the support frame 5 and the base plate 1 is convenient to pull and adjust, and when the guide rod is not used, the guide rod can be stored, the laboratory space is not occupied, one side of the guide hole 105 is in threaded connection with the locking bolt 502 which can be abutted against the outer wall of the guide rod 501, after the guide rod is pulled to a proper position, the position of the guide rod 501 can be fixed through the locking bolt 502, the uniformity of the burning distance of multiple tests is guaranteed, and the guide rod 501 is provided with scale marks, so that the burning distance can be controlled conveniently.

In addition, we are at the top fixedly connected with arc splint 101 of base plate 1, and gas holder 2 such as centre gripping propane is linked together through pipeline and combustor 3 on the arc splint 101, and gas holder 2 to for combustor 3 provides the fuel to be convenient for change, promote the convenience of experiment, combustor 3 just has injection pipe 301 to the direction fixedly connected with of support frame 5, is used for guiding flame just to burning experiment welt, promotes the standardization and the stability of experiment.

In the whole experiment, the burner 3 is used for researching the burn-through resistance of materials with different thicknesses, the experimental conditions are met, and the flame temperature of the materials with different thicknesses is 935-984 ℃ and the heat flux density is 9.4-10.6W/cm ² Next, the layering time, burn-through time, maximum flame temperature of the unburnt material and occurrence time of the materials with different thicknesses were observed and recorded, and we obtained the following data:

therefore, the corresponding relation between the thickness of the lining plate and the burning-through time can be intuitively seen, and subsequent material selection and improvement are facilitated.

The foregoing is only a preferred embodiment of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art, who is within the scope of the present utility model, should make equivalent substitutions or modifications according to the technical scheme of the present utility model and the inventive concept thereof, and should be covered by the scope of the present utility model.

Claims

1. The utility model provides an aircraft welt material burn-through resistant experimental apparatus which characterized in that includes:

the device comprises a base plate (1), wherein a burner (3) and a bracket are arranged at the top of the base plate (1), and a camera (4) is arranged on the bracket and used for shooting and recording flames of the burner (3) and an experimental surface of a lining plate;

a supporting frame (5) which is in sliding fit with the base plate (1),

the support frame (5) is connected with a locking part in a threaded manner and is used for fixing lining plate materials, and a thermocouple (7) fixedly connected to the support frame (5) is located in front of an experimental surface of the lining plate, and the support frame (5) is fixedly connected with a heat flow meter (8) which is matched with the thermocouple (7).

2. The burn-through resistant experimental device for aircraft liner materials according to claim 1, wherein the supporting frame (5) comprises three vertical rods which are parallel to each other and a cross rod which is sequentially connected with the three vertical rods, a frame with a hollowed cross section which is triangular is formed, and the locking part, the thermocouple (7) and the heat flow meter (8) are arranged on the cross rod.

3. The aircraft liner material burn-through resistant test device of claim 2, wherein the locking portion comprises:

at least two groups of screw rods (6), wherein the number of each group of screw rods (6) is at least two, the two groups of screw rods (6) are symmetrically arranged on the upper cross rod and the lower cross rod,

the cross rod is provided with a threaded hole, and the screw rod (6) is in threaded connection with the threaded hole;

the stepped clamping blocks (601) are fixedly connected to one end of the screw (6), and steps of the two clamping blocks (601) are oppositely arranged;

and the knob (602) is fixedly connected to the other end of the screw (6) and is used for increasing a force arm for applying a rotating force to the screw (6).

4. The burn-through resistant experimental device for the aircraft liner material according to claim 2, wherein a plurality of groups of positioning holes are formed in the cross rod, a plurality of thermocouples (7) are respectively inserted into the positioning holes, the position of at least one thermocouple (7) is opposite to the center line of a flame outlet of the combustor (3), and the heat flow meter (8) is fixedly connected under the cross rod and is positioned at the side edge of the thermocouple (7).

5. The burn-through resistant experimental device for aircraft lining material according to claim 1, wherein a guide rod (501) is fixedly connected to the support frame (5), a guide hole (105) is formed in the bottom of the base plate (1), the guide rod (501) is slidably connected in the guide hole (105), a locking bolt (502) capable of propping against the outer wall of the guide rod (501) is connected to one side of the guide hole (105) in a threaded manner, and scale marks are arranged on the guide rod (501).

6. The burn-through resistant experimental device for the aircraft lining material according to claim 1, wherein the top of the base plate (1) is fixedly connected with an arc-shaped clamping plate (101), the arc-shaped clamping plate (101) is used for clamping an air storage tank (2), the air storage tank (2) is communicated with a burner (3) through a pipeline, and the burner (3) is fixedly connected with a jet pipe (301) in the direction opposite to the supporting frame (5).

7. The burn-through resistant experimental device for aircraft liner material according to claim 1, wherein the bracket comprises a positioning column (103) fixedly connected with the top of the base plate (1), a placing frame (104) in a concave shape is rotatably connected to the top of the positioning column (103), and the camera (4) is clamped in the placing frame (104).

8. The burn-through resistant experimental device for aircraft liner materials according to claim 1, wherein a recorder (102) is fixedly connected to the top of the base plate (1), and the thermocouple (7) and the heat flow meter (8) are electrically connected with the recorder (102).