CN116628845A - High-speed friction test platform and test method for aircraft fuel tank - Google Patents
High-speed friction test platform and test method for aircraft fuel tank Download PDFInfo
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- CN116628845A CN116628845A CN202310487674.8A CN202310487674A CN116628845A CN 116628845 A CN116628845 A CN 116628845A CN 202310487674 A CN202310487674 A CN 202310487674A CN 116628845 A CN116628845 A CN 116628845A
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- 239000002828 fuel tank Substances 0.000 title claims abstract description 117
- 238000012360 testing method Methods 0.000 title claims abstract description 46
- 238000010998 test method Methods 0.000 title claims abstract description 9
- 238000004880 explosion Methods 0.000 claims abstract description 26
- 238000002485 combustion reaction Methods 0.000 claims abstract description 25
- 238000000034 method Methods 0.000 claims abstract description 17
- 230000001105 regulatory effect Effects 0.000 claims abstract description 13
- 230000008569 process Effects 0.000 claims abstract description 11
- 238000006073 displacement reaction Methods 0.000 claims abstract description 9
- 238000003825 pressing Methods 0.000 claims description 42
- 238000005303 weighing Methods 0.000 claims description 41
- 230000009471 action Effects 0.000 claims description 19
- 238000007906 compression Methods 0.000 claims description 19
- 230000006835 compression Effects 0.000 claims description 18
- 239000000203 mixture Substances 0.000 claims description 11
- 230000000087 stabilizing effect Effects 0.000 claims description 11
- 230000005484 gravity Effects 0.000 claims description 7
- 230000001133 acceleration Effects 0.000 claims description 4
- 238000004364 calculation method Methods 0.000 claims description 2
- 238000012544 monitoring process Methods 0.000 claims description 2
- 238000005096 rolling process Methods 0.000 claims description 2
- 238000005507 spraying Methods 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 230000007246 mechanism Effects 0.000 abstract description 9
- 238000011160 research Methods 0.000 abstract description 4
- 238000011056 performance test Methods 0.000 abstract description 2
- 210000001015 abdomen Anatomy 0.000 description 5
- 229910000831 Steel Inorganic materials 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000003746 surface roughness Effects 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 238000006467 substitution reaction Methods 0.000 description 1
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- 238000001931 thermography Methods 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/08—Thermal analysis or thermal optimisation
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/10—Greenhouse gas [GHG] capture, material saving, heat recovery or other energy efficient measures, e.g. motor control, characterised by manufacturing processes, e.g. for rolling metal or metal working
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Abstract
The invention discloses a high-speed friction test platform and a test method for an aircraft fuel tank, which relate to the technical field of safety performance test of the aircraft fuel tank, wherein the test platform comprises: the device comprises a fuel tank, a fixing subsystem, a rotary friction subsystem, a pressurizing subsystem, a variable-frequency speed regulating subsystem, a data acquisition subsystem and a safety protection subsystem; a motor in the rotary friction subsystem drives the grinding disc to rotate, and a reticulate pattern notch is arranged on the surface of the grinding disc to simulate a rough contact surface; the fuel tank is placed on the millstone; the fixing subsystem limits the horizontal displacement of the fuel tank, so that friction is generated between the fuel tank and the millstone; the pressurizing subsystem applies a downward positive pressure to the fuel tank; the variable-frequency speed regulating subsystem regulates the rotating speed of the grinding disc. The test platform provided by the invention can simulate the process of large-area continuous high-speed friction between the oil tank and the ground caused by landing accidents of an aircraft, and research the influence of different roughness contact surfaces, different positive pressures and different friction speeds on the combustion and explosion mechanism of the oil tank of the aircraft.
Description
Technical Field
The invention relates to the technical field of safety performance test of an aircraft fuel tank, in particular to a high-speed friction test platform and a high-speed friction test method of an aircraft fuel tank.
Background
The fuel tank of the aircraft provides combustible mixture fuel for the combustion engine and is an important component of the fuel system of the aircraft. The burning and explosion of combustible mixtures in the fuel tanks of an aircraft can seriously jeopardize the flight safety of the aircraft. In the landing stage of the aircraft, serious friction accidents occur between the aircraft body and the ground due to the fault of a landing braking system, and the combustion or explosion of combustible mixtures in a fuel tank of the aircraft is extremely easy to be caused. The main reason is that the bottom machine body is severely broken and destroyed, so that a large-area continuous high-speed friction effect occurs between the central oil tank at the belly of the machine and the road surface, the combustible mixture in the central oil tank can be in a high-temperature and high-pressure state due to the intense friction effect, and the combustion or explosion of the central oil tank can be initiated when the combustible mixture reaches the ignition energy. The combustion or explosion of the central oil tank can seriously increase the casualties of personnel in the landing accident of the aircraft, so that the mechanism of the combustion or explosion of the combustible mixture in the central oil tank of the aircraft under the action of large-area continuous high-speed friction is necessary to be researched, and related safety measures are provided for inhibiting the combustion or explosion of the central oil tank under the action of high-speed friction, so that guiding suggestions are provided for the explosion-proof design of the fuel tank. From the analysis of the physical process of the aircraft landing, the friction speed between the aircraft and the ground, the positive pressure borne by the central oil tank and the roughness of the contact surface between the central oil tank and the ground are all main factors affecting the combustion and explosion of the central oil tank. Therefore, it is necessary to conduct an intensive analysis of the influence of these factors on the combustion explosion mechanism of the central tank by means of experimental investigation.
However, the research on the mechanism of combustion and explosion of an aircraft fuel tank is relatively few at present, and particularly, the experimental research on combustion or explosion of an aircraft central fuel tank under continuous high-speed friction action due to landing accidents is lacked. The main problems existing in the research technology about the combustion explosion of the fuel tank of an airplane include the following two points: 1. lack of a test platform and a test method for simulating combustion or explosion of a central oil tank of an aircraft under the action of large-area continuous high-speed friction; 2. the influence of factors such as friction speed, positive pressure and roughness of contact surface on the combustion and explosion mechanism of the central oil tank of the airplane is lacked. Meanwhile, the realization of the large-area high-speed friction test of the central oil tank of the aircraft has the following two technical difficulties: 1. the friction speeds in the test are difficult to reach at high speeds (about 70 m/s) in the extreme case of aircraft landing; 2. existing test platforms have difficulty simulating large area continuous friction processes with different contact surface roughness. Therefore, development and development of a combustion explosion test simulating an aircraft central oil tank under the action of large-area continuous high-speed friction is necessary and has important engineering significance.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a high-speed friction test platform for an aircraft fuel tank, which is used for simulating the process of large-area continuous high-speed friction between an aircraft belly central fuel tank and the ground caused by landing accidents and researching the influence of different roughness contact surfaces, different positive pressures and different friction speeds on the combustion and explosion mechanism of the aircraft belly central fuel tank.
In order to achieve the above purpose, the present invention adopts the following technical scheme, including:
an aircraft fuel tank high-speed friction test platform, the test platform includes: the device comprises a fuel tank, a fixed subsystem, a rotary friction subsystem, a pressurizing subsystem, a variable-frequency speed regulating subsystem and a data acquisition subsystem;
the rotary friction subsystem comprises a motor and a grinding disc connected with the motor, the motor drives the grinding disc to rotate, and the upper surface of the grinding disc is a rough contact surface; the fuel tank is placed on the millstone; the fixing subsystem is used for limiting the horizontal displacement generated by the fuel tank under the rotation action of the millstone, so that friction is generated between the fuel tank and the millstone; the pressurization subsystem is used for applying downward positive pressure to the fuel tank; the variable-frequency speed regulation subsystem is used for regulating the frequency of the motor, namely regulating the rotating speed of the grinding disc; the data acquisition subsystem is used for acquiring image data of the fuel tank when friction occurs and acquiring temperature field data of the fuel tank when friction occurs.
Preferably, the pressurizing subsystem comprises a bearing seat, a weighing beam, a screw, a weight, a pressing rod and a control switch;
the bearing seat is fixed at the free end of the cantilever bracket, one end of the weighing beam is arranged in the bearing seat, and the other end of the weighing beam is connected with the weight through a screw rod; the upper end of the pressing rod is contacted with the weighing rod, and the lower end of the pressing rod passes through the axial hole of the cantilever bracket to be contacted with the top surface of the fuel tank; one end of the control switch is fixed on the arm column of the cantilever bracket, and the other end of the control switch is movably connected with the scale beam and used for supporting the scale beam; when the control switch is turned on, the weighing beam is pressed down by the gravity action of the weight, and the pressing rod applies downward positive pressure to the fuel tank; when the control switch is turned on, the weighing beam does not apply downward pressure to the pressing rod.
Preferably, the pressing rod is a square rod piece with a sliding groove, and the sliding groove of the pressing rod is connected with a vertical corner bracket through an embedded part; the cantilever bracket is provided with a compression screw, one end of the compression screw is connected with the cantilever bracket, and the other end of the compression screw passes through a through hole in the corner bracket; the outside of the compression screw is wrapped with an extensible and compressible spring, one end of the spring is connected with the cantilever bracket, and the other end of the spring is connected with the corner bracket; the pressing rod and the corner brace can move mutually along the chute, and the corner brace and the cantilever bracket can move mutually along the height direction of the pressing screw rod;
when the control switch is turned on, the weighing beam acts on the upper part of the compression rod, the spring is in a compressed state under pressure, and the compression rod vertically moves downwards and applies downward positive pressure to the fuel tank; when the control switch is turned off, the weighing beam is separated from the upper part of the hold-down lever, and the spring is not compressed at this time, so that the hold-down lever does not apply downward positive pressure to the fuel tank.
Preferably, the fixing subsystem comprises a seat frame, a cantilever bracket, a motor fixing plate, a first fixing stop lever, a second fixing stop lever and a third fixing stop lever;
the fixed end of the cantilever bracket is fixed on the seat frame; the motor fixing plate is arranged at the top of the seat frame and corresponds to the top surface of the seat frame; the motor is arranged below the motor fixing plate, and the grinding disc is positioned above the motor fixing plate and connected with the motor through a through hole on the motor fixing plate;
the first fixed stop lever is located in the right limiting hole of the cantilever bracket, the second fixed stop lever is located in the left limiting hole of the cantilever bracket, the third fixed stop lever is located in the axial limiting hole of the cantilever bracket, and the fuel tank is limited by the three fixed stop levers to generate horizontal displacement under the rotation action of the millstone, so that friction is generated between the fuel tank and the millstone.
Preferably, the test platform further comprises: a safety protection subsystem;
the safety protection subsystem comprises an explosion-proof camera, a display and a fire-fighting lance;
the explosion-proof camera is connected with the display and used for monitoring the whole combustion and explosion process of the combustible mixture in the fuel tank, and the fire-fighting lance is used for spraying water to extinguish the fire of the combustion and explosion flame of the combustible mixture in the fuel tank.
Preferably, the rotary friction subsystem comprises a motor, a coupling, a bearing sleeve mounting plate, a central shaft, a millstone, a steady disc, a bearing sleeve and a connecting piece;
the motor is connected with the coupler, the coupler is connected with the central shaft, the grinding disc is arranged above the central shaft, the grinding disc is fixed on the surface of the grinding disc, the circle center of the grinding disc is coincident with the circle center of the grinding disc, and reticulate pattern notch grooves are formed in the upper surface of the grinding disc; the outside of center pin is wrapped up in the bearing housing, and the bearing housing is fixed on the bearing housing mounting panel, and the bearing housing mounting panel is fixed on the connecting piece, and the connecting piece is fixed on the seat frame.
Preferably, the variable-frequency speed regulation subsystem comprises a rotation speed sensor, an anti-noise signal wire, a rotation speed digital display, a variable-frequency speed regulator and an electric wire;
the laser signal of the rotation speed sensor is emitted to the grinding disc from the front surface and is used for measuring the rotation speed of the grinding disc in real time; the rotating speed sensor is connected with a rotating speed digital display through an anti-noise signal line, and the rotating speed digital display displays the rotating speed of the millstone in real time; the motor is connected with a variable frequency speed regulator through an electric wire, and the variable frequency speed regulator is used for regulating the frequency of the motor so as to regulate the rotating speed of the grinding disc.
Preferably, the upper surface of the grinding disc is provided with reticulate pattern notch grooves for simulating a rough contact surface.
Preferably, the data acquisition subsystem comprises a camera, a thermal infrared imager and a computer;
the camera is used for collecting image data of the fuel tank when friction occurs, the infrared thermal imager is used for collecting temperature field data of the fuel tank when friction occurs, and the camera and the infrared thermal imager respectively transmit the collected data to the computer.
The invention also provides a high-speed friction test method for the fuel tank of the aircraft, which comprises the following steps:
s1, a reticulate pattern notch is formed in the upper surface of a grinding disc and used for simulating a rough contact surface; according to the roughness required by the test, determining the depth of the reticulate pattern notch on the upper surface of the grinding disc as h 0 mm, width b 0 mm; the grooving depth of the upper surface of the millstone is h by adopting a grooving machine 0 mm and groove width b 0 Performing reticulation rolling in two directions with an angle difference of 90 DEG in mm;
s2, measuring the horizontal distance d between the pressing rod and the bearing seat Pressing rod Measuring the horizontal distance d between the weight and the bearing seat Weight of weighing machine The method comprises the steps of carrying out a first treatment on the surface of the According to the positive pressure F required to be sustained by the fuel tank required by the test N Calculating the mass m of the weight Weight of weighing machine The method comprises the steps of carrying out a first treatment on the surface of the Selecting a mass of m Weight of weighing machine The weight of the balance weight is fixed below the screw rod, and the control switch is set to be in a closed state;
wherein, the weight mass m Weight of weighing machine The calculation mode of (a) is as follows:
wherein F is N Is the positive pressure F that the fuel tank required for the test is required to withstand N The unit is N; g is the gravity acceleration, and the value is 9.81m/s 2 ；d Pressing rod Is the horizontal distance from the bearing seat, and the unit is m; d, d Weight of weighing machine The horizontal distance between the weight and the bearing seat is m;
s3, the laser signal of a rotation speed sensor in the variable-frequency speed regulation subsystem is emitted to the grinding disc from the front surface and is used for measuring the rotation speed of the grinding disc in real time; measuring the distance r between the laser of the rotation speed sensor and the center of the grinding disc;
s4, calculating the rotating speed n of the grinding disc according to the friction speed v required by the test; starting a motor and observing the real-time rotating speed of the grinding disc until the real-time rotating speed of the grinding disc reaches the calculated rotating speed n, and keeping the grinding disc to rotate at a constant speed with the rotating speed n;
the rotating speed n of the grinding disc is calculated by the following steps:
wherein v is the friction speed required for the test in m/s; r is the distance between the laser of the rotation speed sensor and the center of the grinding disc, and the unit is m; the unit of the rotation speed n of the grinding disc is round/min;
s5, placing the fuel tank on the rotating millstone, and simultaneously sequentially installing a first fixed stop lever, a second fixed stop lever and a third fixed stop lever in a limiting hole of the cantilever bracket to limit the horizontal displacement of the fuel tank under the rotation action of the millstone;
s6, setting a control switch to be in an on state, starting a camera and an infrared thermal imager in the data acquisition subsystem, acquiring image data of the fuel tank when friction occurs through the camera, and acquiring temperature field data of the fuel tank when friction occurs through the infrared thermal imager.
The invention has the advantages that:
(1) The invention can simulate the process of large-area continuous high-speed friction between the central oil tank of the aircraft belly and the ground caused by landing accidents, and solves the problem that the prior art lacks a fuel tank large-area continuous high-speed friction test platform and a test method with combustible mixtures.
(2) The invention creatively provides the rotary friction subsystem, the pressurizing subsystem and the variable-frequency speed regulating subsystem, which can respectively study the influence of different contact surface roughness, different positive pressure and different friction speeds on the combustion and explosion mechanism of the central oil tank of the aircraft, and can also study the influence of the coupling effect of the roughness, the positive pressure and the friction speeds on the combustion and explosion mechanism of the central oil tank;
(3) The rotary friction subsystem provided by the invention successfully simulates high speed (about 70 m/s) under extreme conditions when an aircraft lands, and simultaneously simulates a large-area continuous friction process between the bottom surface of the oil tank and the contact surface.
(4) The data acquisition subsystem provided by the invention can accurately capture the flame form evolution process of the fuel tank which generates combustion explosion under the action of high-speed sliding friction and the fuel tank temperature field change process, and provides a scientific and reliable measurement method for researching the combustion explosion generation mechanism of the fuel tank under the action of high-speed sliding friction.
Drawings
FIG. 1 is a schematic structural view of an aircraft fuel tank high-speed friction test platform.
FIG. 2 is an enlarged view of a portion of the rotary friction subsystem.
Fig. 3 is a schematic top view of the mount.
Fig. 4 is a schematic top view of the motor fixing plate.
Fig. 5 is a schematic cross-sectional and top view of the connector.
Fig. 6 is a schematic top view of the cantilever bracket.
Fig. 7 is a schematic side view of a cantilever bracket.
Fig. 8 is a schematic side view of the hold-down bar.
Fig. 9 is a schematic structural view of a stabilizer.
Fig. 10 is a schematic structural view of the abrasive disc.
Fig. 11 is a schematic cross-sectional structure of the grinding disc and the stabilizing disc.
Fig. 12 is a schematic view of the structure of the scale beam.
Fig. 13 is a schematic view of the structure of the fixed stop lever.
Fig. 14 is a schematic cross-sectional and top view of a coupling.
Fig. 15 is a schematic cross-sectional and top view of the central axis.
Fig. 16 is a schematic view of the structure of the screw and weight.
Fig. 17 is a schematic top and cross-sectional view of the bearing housing mounting plate.
Fig. 18 is a schematic sectional and top view of the bearing housing.
Fig. 19 is a schematic structural view of the bearing housing.
The meaning of the reference numerals in the figures is as follows:
1-fuel tank, 2-seat frame, 3-cantilever bracket, 4-motor fixed plate, 5-first fixed stop lever, 6-second fixed stop lever, 7-third fixed stop lever, 8-motor, 9-coupler, 10-bearing housing mounting plate, 11-central shaft, 12-millstone, 13-steady-state, 14-bearing seat, 15-weighing beam, 16-screw, 17-weight, 18-hold-down bar, 19-control switch, 20-rotation speed sensor, 21-anti-noise signal wire, 22-rotation speed digital display, 23-variable frequency speed regulator, 24-wire, 25-camera, 26-infrared thermal imaging instrument, 27-computer, 28-first tripod, 29-second tripod, 30-explosion-proof camera, 31-display 32-fire-fighting lance, 33-right limit hole, 34-left limit hole, 35-axial limit hole, 36-axial hole, 37-angle sign indicating number, 38-compression screw, 39-spring, 40-bearing bush, 41-M12 bolt, 42-M8 bolt, 43-bearing, 44-bearing hole, 45-first screw hole, 46-second screw hole, 47-foundation bolt hole, 48-connector, 49-fixed cantilever bracket bolt hole, 50-fixed motor fixing plate bolt hole, 51-fixed connector bolt hole, 52-connecting central shaft bolt hole, 53-fixed bearing bush mounting plate bolt hole, 54-fixed bearing bush bolt hole, 55-fixed grinding disc bolt hole, 56-bolt holes for the stationary motor.
Detailed Description
The following description of the embodiments of the present invention 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 invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
1-19, an aircraft fuel tank high-speed friction test platform, comprising: the system comprises a fuel tank 1, a fixed subsystem, a rotary friction subsystem, a pressurizing subsystem, a variable-frequency speed regulating subsystem, a data acquisition subsystem and a safety protection subsystem.
The fuel tank 1 is an aircraft fuel tank, is in a cuboid shape and is positioned at the belly of an aircraft, and is also called an aircraft central fuel tank, and aviation kerosene is filled in the fuel tank 1.
The fixing subsystem comprises a seat frame 2, a cantilever bracket 3, a motor fixing plate 4, a first fixing stop lever 5, a second fixing stop lever 6 and a third fixing stop lever 7. As shown in fig. 3, the saddle 2 is fixed on the horizontal ground by bolting at the anchor bolt holes 47 to support the upper structural member; the fixed end of the cantilever bracket 3 is fixed on the seat frame 2 through the bolt connection at the bolt hole 49 for fixing the cantilever bracket; the motor fixing plate 4 is arranged on the top of the seat frame 2 through the bolt connection of the bolt hole 50 for fixing the motor fixing plate, which is equivalent to the top surface of the seat frame 2; as shown in fig. 6, 7 and 13, the first fixed stop lever 5 is located in the right limit hole 33 of the cantilever bracket 3, the second fixed stop lever 6 is located in the left limit hole 34 of the cantilever bracket 3, the third fixed stop lever is located in the axial limit hole 35 of the cantilever bracket 3, and the three fixed stop levers are used for limiting the horizontal displacement of the fuel tank 1, specifically, limiting the horizontal displacement of the fuel tank 1 generated under the rotation action of the grinding disc 12, so that friction is generated between the fuel tank 1 and the grinding disc 12.
The rotary friction subsystem comprises a motor 8, a coupler 9, a bearing sleeve mounting plate 10, a central shaft 11, a grinding disc 12, a stabilizing disc 13, a bearing sleeve 40, an M12 bolt 41, an M8 bolt 42 and a connecting piece 48. As shown in fig. 4, motor 8 is mounted below motor mounting plate 4 by bolting at motor mounting bolt holes 56 to power the rotary friction subsystem; as shown in fig. 2, 9, 14 and 15, the motor 8 passes through a through hole on the motor fixing plate 4 to be connected with the coupler 9, the coupler 9 is connected with the central shaft 11, and the stabilizer 13 is arranged above the central shaft 11 through an M8 bolt 42 and a bolt hole 52 connected with the central shaft and is used for bearing the positive pressure applied by the fuel tank 1; as shown in fig. 2, 5, 17 and 18, the bearing bush 40 wraps the central shaft 11, the bearing bush 40 is fixed on the bearing bush mounting plate 10 through the bolt 41 of the M12 and the bolt hole 54 for fixing the bearing bush, the bearing bush mounting plate 10 is fixed on the connecting piece 48 through the bolt connection at the bolt hole 53 for fixing the bearing bush mounting plate, the connecting piece 48 is fixed on the seat frame 2 through the bolt connection at the bolt hole 51 for fixing the connecting piece, and the bearing bush 40 and the bearing bush mounting plate 10 jointly enhance the stability of the central shaft 11 under high-speed rotation; as shown in fig. 10 and 11, the grinding disc 12 is fixed on the surface of the stabilizing disc 13 through screw connection at the screw hole 55 for fixing the grinding disc, the circle center of the grinding disc 12 coincides with the circle center of the stabilizing disc 13, and the surface of the grinding disc 12 is provided with reticulate pattern grooving to simulate the roughness of the contact surface.
The pressurizing subsystem comprises a bearing seat 14, a weighing beam 15, a screw 16, a weight 17, a pressing rod 18 and a control switch 19. As shown in fig. 1, a bearing seat 14 is fixed at the free end of the cantilever bracket 3; as shown in fig. 12 and 19, one end of the scale beam 15 is installed in the bearing seat 14 through a bearing hole 44 and a bearing 43 on the bearing seat 14, and the other end of the scale beam 15 is connected with the screw 16 through a first screw hole 45; as shown in fig. 16, the screw 16 is connected with the weight 17 through a second screw hole 46; the upper end of the pressing rod 18 is contacted with the weighing beam 15, and the lower end of the pressing rod 18 passes through the axial hole 36 of the cantilever bracket 3 to be contacted with the top surface of the fuel tank 1; one end of a control switch 19 is fixed on an arm column of the cantilever bracket 3, and the other end of the control switch 19 is movably connected with the weighing beam 15 and is used for supporting the weighing beam 15; when the control switch 19 is opened, the weight 15 is pressed down by the gravity of the weight 17 to press the pressing rod 18, and the pressing rod 18 applies downward positive pressure to the fuel tank 1; when the control switch 19 is opened, the weighing beam 15 is separated from the pressing beam 18, i.e. the weighing beam 15 does not exert downward pressure on the pressing beam 18.
The variable-frequency speed regulation subsystem comprises a rotation speed sensor 20, an anti-noise signal wire 21, a rotation speed digital display 22, a variable-frequency speed regulator 23 and an electric wire 24. The rotating speed sensor 20 is arranged on a cantilever of the cantilever bracket 3, the rotating speed sensor 20 measures the rotating speed of the grinding disc 12 in real time, the anti-noise signal wire 21 is connected with the rotating speed sensor 20 and the rotating speed digital display 22, the wire 24 is connected with the motor 8 and the variable frequency speed regulator 23, and the variable frequency speed regulator 23 can adjust the rotating speed of the grinding disc 12.
The data acquisition subsystem includes a camera 25, a thermal infrared imager 26, a computer 27, an anti-noise signal line 21, a first tripod 28, a second tripod 29. Image data of the fuel tank 1 when friction occurs are acquired through the camera 25, and temperature field data of the fuel tank 1 when friction occurs are acquired through the thermal infrared imager 26; the camera 25 is mounted on a first tripod 28 and the thermal infrared imager 26 is mounted on a second tripod 29, with the anti-noise signal line 21 transmitting the image data of the camera 25 and the temperature field data of the thermal infrared imager 26, respectively, to the computer 27. In the present embodiment, the camera 25 is a high-speed camera.
The safety protection subsystem comprises an explosion-proof camera 30, a display 31 and a fire-fighting lance 32. The anti-explosion camera 30 is connected with the display 31 by adopting the anti-noise signal wire 21, so that the whole process of the combustion explosion test under the condition of high-speed friction of the fuel tank 1 can be monitored in a short distance, the fire-fighting lance 32 can extinguish the flame of the fuel tank 1 in the test in time, and the safety of the test site is ensured.
In this embodiment, all the structural members are steel structural members, and all the structural members are Q235A, wherein a seamless steel pipe is welded at the free end of the cantilever bracket 3, the grinding disc 12 is a hot rolled steel plate with the thickness of 4mm, the stabilizing disc 13 is a hot rolled steel plate with the thickness of 16mm, and 16M 6 screws are used to fix the grinding disc 12 on the stabilizing disc 13.
In this embodiment, as shown in fig. 8, the compression rod 18 in the compression subsystem is a square rod with a chute, the chute of the compression rod 18 is connected with a vertical corner bracket 37 through an embedded part, the cantilever bracket 3 is provided with a compression screw 38, one end of the compression screw 38 is connected with the cantilever bracket 3, and the other end of the compression screw 38 passes through a through hole on the corner bracket 37; the outside of the compression screw 38 is wrapped with an extensible and compressible spring 39, one end of the spring 39 is connected with the cantilever bracket 3, and the other end of the spring 39 is connected with the corner bracket 37; the pressing rod 18 and the corner bracket 37 can move mutually along the chute, and the corner bracket 37 and the cantilever bracket 3 can move mutually along the height direction of the screw rod; when the control switch 19 is turned on, the scale beam 15 acts on the upper end of the hold-down bar 18, the spring 39 is under compression, the hold-down bar 18 moves vertically downward and applies a downward positive pressure to the upper surface of the fuel tank 1, and when the control switch 19 is turned off, the scale beam 15 and the upper end of the hold-down bar 18 are separated from each other, the spring 39 is not compressed, and the hold-down bar 18 does not apply a downward positive pressure to the fuel tank 1.
In this embodiment, the surface of the grinding disc 12 has a textured groove to simulate the roughness of the contact surface, and the depth h of the textured groove 0 And width b 0 Is the primary factor affecting the surface roughness of the abrasive disc 12, wherein the depth h 0 The larger value of (a) indicates a rougher surface of the grinding disc 12, width b 0 The larger value of (2) indicates a rougher surface of the grinding disc 12, 0<h 0 <4mm，0<b 0 <8mm; in this embodiment, the roughness of the contact surface is required to satisfy the depth h of the reticulate pattern notch 0 =1.2 mm, width b 0 And the surface of the grinding disc 12 is rolled by reticulate patterns in two directions with the angle difference of 90 degrees according to the grooving depth of 1.2mm and the grooving width of 2.0mm by adopting a numerical control high-speed grooving machine, and finally the surface of the grinding disc 12 can reach the roughness of the contact surface required by a test. The using method of the numerical control high-speed notching machine is operated according to the instruction method of the commercial numerical control high-speed notching machine.
In this embodiment, the friction speed v=70m/s between the surface of the grinding disc 12 and the bottom surface of the fuel tank 1 is required, the basic working principle of the above-mentioned rotary friction subsystem for enabling the fuel tank 1 to receive large-area continuous high-speed friction action is that the motor 8 running at high speed transmits mechanical power to the stabilizing disc 13 through the coupling 9 and the central shaft 11, the stabilizing disc 13 drives the grinding disc 12 to jointly keep high-speed circular motion, the large-area high-speed friction action occurs between the surface of the grinding disc 12 and the bottom surface of the fuel tank 1, when the friction speed v=70m/s required by this embodiment is known, the rotating speed n of the circular motion of the grinding disc 12 can be calculated, and the variable-frequency speed regulator 23 is operated to enable the grinding disc 12 to reach the rotating speed n, so that the grinding disc 12 can reach the friction speed v=70m/s required by this embodiment.
In this embodiment, the pressing rod 18 applies positive pressure to the fuel tank 1 by amplifying the weight force of the weight 17, and in this embodiment, the fuel tank 1 is required to be subjected to the force F N Positive pressure of 4000N, calculate the mass of the required weight 17 to be m Weight of weighing machine The mass is m Weight of weighing machine The weight 17 of the weight 17 is arranged on the screw 16, the control switch 19 is started, the weight lever 15 impacts the pressing rod 18 under the gravity action of the weight 17, and the pressing rod 18 applies positive pressure with the size of 4000N to the fuel tank 1.
Example 2
The high-speed friction test method for the fuel tank of the aircraft comprises the following steps of:
s21, fixing the cantilever bracket 3 on the seat frame 2, mounting the motor fixing plate 4 on the top of the seat frame 2, fixedly connecting the motor 8 below the motor fixing plate 4 by bolts, and fixing the connecting piece 48 on the seat frame 2.
S22, the motor 8 passes through the motor fixing plate 4 to be connected with the coupler 9, the coupler 9 is connected with the central shaft 11, the bearing sleeve mounting plate 10 and the bearing sleeve 40 are fixed, and the stabilizing disc 13 is mounted on the central shaft 11.
S23, determining the grooving depth of the reticulation on the surface of the grinding disc 12 as h according to the requirements of the embodiment 0 =1.2 mm, groove width b 0 =2.0 mm, the grooved grinding disc 12 is mounted on a stabilizing disc 13.
S24, measuring the horizontal distance d between the pressing rod 18 and the bearing seat 14 Pressing rod =0.2m, measuring the horizontal distance d of the weight 17 from the bearing block Weight of weighing machine =1.0m, the fuel tank 1 is subjected to a positive pressure F as required in this embodiment N =4000N, the mass m of the weight 17 is calculated Weight of weighing machine ＝81.5kg。
In step S24, the formula for calculating the weight mass is as follows:
wherein F is N In this embodiment, the positive pressure required to be borne by the fuel tank is that g is the acceleration of gravity, and the value is 9.81m/s 2 。
S25, mounting the left end of the weighing beam 15 in the bearing seat 14, connecting the right end of the weighing beam 15 with the screw 16, and selecting the mass m Weight of weighing machine A weight 17 of =81.5 kg is fixed below the screw 16 and the control switch 19 is set to the off state.
And S26, the rotating speed sensor 20 is arranged on the cantilever bracket 3, the distance r=0.60 m between the laser of the rotating speed sensor 20 and the center of the grinding disc 12 is measured, and the rotating speed sensor 20 and the rotating speed digital display 22 are connected by adopting the anti-noise signal line 21.
S27, the camera 25 is mounted on the first tripod 28, the infrared thermal imager 26 is mounted on the second tripod 29, the camera 25 and the infrared thermal imager 26 are sequentially connected to the computer 27 by using the anti-noise signal line 21, the explosion-proof camera 30 is mounted, and the explosion-proof camera 30 is connected to the display 31 by using the anti-noise signal line 21.
And S28, connecting the motor 8 and the variable frequency speed regulator 23 by adopting the electric wire 24, calculating the grinding disc rotating speed n=1114 round/min according to the friction speed v=70 m/S required by the embodiment, starting the variable frequency speed regulator 23, observing the rotating speed on the rotating speed digital display 22, operating the acceleration button until the rotating speed reaches the required grinding disc rotating speed n=1114 round/min, and keeping the grinding disc 12 to rotate at a constant speed at the rotating speed n=1114 round/min.
In step S28, the formula for calculating the rotation speed n of the grinding disc is specifically as follows:
where v is the friction speed (unit: m/s) required by the present embodiment, and r is the horizontal distance (unit: m) of the rotation speed sensor from the center of the grinding disc.
S29, placing the fuel tank 1 filled with aviation kerosene on the millstone 12 rotating at a high speed, and simultaneously sequentially installing the first fixed stop lever 5, the second fixed stop lever 6 and the third fixed stop lever 7 in a limiting hole of the cantilever bracket 3 to limit the horizontal displacement of the fuel tank 1.
S210, setting a control switch 19 to be in an on state, starting a camera 25 and an infrared thermal imager 26 to record test data, specifically, acquiring image data of the fuel tank 1 when friction occurs through the camera 25, and acquiring temperature field data of the fuel tank 1 when friction occurs through the infrared thermal imager 26; after one test is completed, the motor 8 is turned off, the fire gun 32 is used for extinguishing the fire of the fuel tank 1, and the test data are analyzed and processed based on the computer 27.
The above embodiments are merely preferred embodiments of the present invention and are not intended to limit the present invention, and any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of the present invention.
Claims (10)
1. The utility model provides an aircraft fuel tank high-speed friction test platform which characterized in that, the test platform includes: the device comprises a fuel tank (1), a fixed subsystem, a rotary friction subsystem, a pressurizing subsystem, a variable-frequency speed regulation subsystem and a data acquisition subsystem;
the rotary friction subsystem comprises a motor (8) and a grinding disc (12) connected with the motor (8), wherein the motor (8) drives the grinding disc (12) to rotate, and the upper surface of the grinding disc (12) is a rough contact surface; the fuel tank (1) is placed on the millstone (12); the fixing subsystem is used for limiting horizontal displacement generated by the fuel tank (1) under the rotation action of the millstone (12) so as to generate friction between the fuel tank (1) and the millstone (12); the pressurizing subsystem is used for applying downward positive pressure to the fuel tank (1); the variable-frequency speed regulation subsystem is used for regulating the frequency of the motor (8), namely regulating the rotating speed of the grinding disc (12); the data acquisition subsystem is used for acquiring image data of the fuel tank (1) when friction occurs and acquiring temperature field data of the fuel tank (1) when friction occurs.
2. The aircraft fuel tank high-speed friction test platform according to claim 1, wherein the pressurizing subsystem comprises a bearing seat (14), a scale beam (15), a screw (16), a weight (17), a pressing rod (18) and a control switch (19);
the bearing seat (14) is fixed at the free end of the cantilever bracket (3), one end of the weighing beam (15) is arranged in the bearing seat (14), and the other end of the weighing beam (15) is connected with the weight (17) through the screw rod (16); the upper end of the pressing rod (18) is in contact with the weighing beam (15), and the lower end of the pressing rod (18) passes through an axial hole (36) of the cantilever bracket (3) to be in contact with the top surface of the fuel tank (1); one end of a control switch (19) is fixed on an arm column of the cantilever bracket (3), and the other end of the control switch (19) is movably connected with the weighing beam (15) and is used for supporting the weighing beam (15); when the control switch (19) is opened, the weighing beam (15) presses the pressing rod (18) under the action of the gravity of the weight (17), and the pressing rod (18) applies downward positive pressure to the fuel tank (1); when the control switch (19) is opened, the weighing beam (15) does not exert downward pressure on the pressing rod (18).
3. The high-speed friction test platform of the aircraft fuel tank according to claim 2, wherein the pressing rod (18) is a square rod with a chute, and the chute of the pressing rod (18) is connected with a vertical corner bracket (37) through an embedded part; a compression screw (38) is arranged on the cantilever bracket (3), one end of the compression screw (38) is connected with the cantilever bracket (3), and the other end of the compression screw (38) passes through a through hole on the corner bracket (37); an extensible and compressible spring (39) is wrapped outside the compression screw (38), one end of the spring (39) is connected with the cantilever bracket (3), and the other end of the spring (39) is connected with the corner bracket (37); the pressing rod (18) and the corner bracket (37) can move mutually along the chute, and the corner bracket (37) and the cantilever bracket (3) can move mutually along the height direction of the pressing screw rod (38);
when the control switch (19) is turned on, the weighing beam (15) acts on the upper part of the pressing rod (18), the spring (39) is in a compressed state under pressure, and the pressing rod (18) moves vertically downwards and applies downward positive pressure to the fuel tank (1); when the control switch (19) is closed, the weighing beam (15) and the upper part of the pressing rod (18) are separated from each other, the spring (39) is not compressed, and the pressing rod (18) does not apply downward positive pressure to the fuel tank (1).
4. The aircraft fuel tank high-speed friction test platform according to claim 2, wherein the fixing subsystem comprises a seat frame (2), a cantilever bracket (3), a motor fixing plate (4), a first fixing stop lever (5), a second fixing stop lever (6) and a third fixing stop lever (7);
the fixed end of the cantilever bracket (3) is fixed on the seat frame (2); the motor fixing plate (4) is arranged at the top of the seat frame (2) and corresponds to the top surface of the seat frame (2); the motor (8) is arranged below the motor fixing plate (4), and the grinding disc (12) is positioned above the motor fixing plate (4) and is connected with the motor (8) through a through hole on the motor fixing plate (4);
the first fixed stop lever (5) is located in a right side limiting hole (33) of the cantilever bracket (3), the second fixed stop lever (6) is located in a left side limiting hole (34) of the cantilever bracket (3), the third fixed stop lever is located in an axial limiting hole (35) of the cantilever bracket (3), and the fuel tank (1) is limited to horizontally displace by utilizing the three fixed stop levers under the rotation action of the millstone (12), so that friction is generated between the fuel tank (1) and the millstone (12).
5. The aircraft fuel tank high-speed friction test platform of claim 1, further comprising: a safety protection subsystem;
the safety protection subsystem comprises an explosion-proof camera (30), a display (31) and a fire-fighting lance (32);
the explosion-proof camera (30) is connected with the display (31) and is used for monitoring the whole combustion and explosion process of the combustible mixture in the fuel tank (1), and the fire-fighting lance (32) is used for spraying water to extinguish the fire of the combustion and explosion flame of the combustible mixture in the fuel tank (1).
6. The high-speed friction test platform for the fuel tank of the aircraft according to claim 1, wherein the rotary friction subsystem comprises a motor (8), a coupler (9), a bearing sleeve mounting plate (10), a central shaft (11), a grinding disc (12), a stabilizing disc (13), a bearing sleeve (40) and a connecting piece (48);
the motor (8) is connected with the coupler (9), the coupler (9) is connected with the central shaft (11), the grinding disc (12) is fixed on the surface of the grinding disc (13) above the central shaft (11), the circle center of the grinding disc (12) coincides with the circle center of the grinding disc (13), and reticulate pattern notch grooves are formed in the upper surface of the grinding disc (12); the bearing sleeve (40) is wrapped outside the central shaft (11), the bearing sleeve (40) is fixed on the bearing sleeve mounting plate (10), the bearing sleeve mounting plate (10) is fixed on the connecting piece (48), and the connecting piece (48) is fixed on the seat frame (2).
7. The aircraft fuel tank high-speed friction test platform according to claim 1, wherein the variable-frequency speed regulation subsystem comprises a rotation speed sensor (20), an anti-noise signal wire (21), a rotation speed digital display (22), a variable-frequency speed regulator (23) and an electric wire (24);
the laser signal of the rotation speed sensor (20) is emitted to the grinding disc (12) at the front and is used for measuring the rotation speed of the grinding disc (12) in real time; the rotating speed sensor (20) is connected with a rotating speed digital display instrument (22) through an anti-noise signal line (21), and the rotating speed digital display instrument (22) displays the rotating speed of the grinding disc (12) in real time; the motor (8) is connected with a variable frequency speed regulator (23) through an electric wire (24), and the variable frequency speed regulator (23) is used for regulating the frequency of the motor (8), so that the rotating speed of the grinding disc (12) is regulated.
8. An aircraft fuel tank high-speed friction test platform according to claim 1, characterized in that the upper surface of the grinding disc (12) is provided with reticulate pattern grooves for simulating rough contact surfaces.
9. An aircraft fuel tank high-speed friction test platform according to claim 1, wherein the data acquisition subsystem comprises a camera (25), a thermal infrared imager (26), a computer (27);
the camera (25) is used for acquiring image data of the fuel tank (1) when friction occurs, the infrared thermal imager (26) is used for acquiring temperature field data of the fuel tank (1) when friction occurs, and the camera (25) and the infrared thermal imager (26) respectively transmit the acquired data to the computer (27).
10. The test method applied to the high-speed friction test platform of the fuel tank of the airplane as claimed in claim 4 is characterized by comprising the following steps:
s1, a reticulate pattern notch is formed in the upper surface of a grinding disc (12) and used for simulating a rough contact surface; determining the depth of reticulate pattern grooves on the upper surface of the grinding disc (12) to be h according to the roughness required by the test 0 mm, width b 0 mm; the grooving depth of the upper surface of the millstone (12) is h by adopting a grooving machine 0 mm and groove width b 0 Performing reticulation rolling in two directions with an angle difference of 90 DEG in mm;
s2, measuring the horizontal distance d of the pressing rod (18) from the bearing seat (14) Pressing rod Measuring the horizontal distance d of the weight (17) from the bearing seat (14) Weight of weighing machine The method comprises the steps of carrying out a first treatment on the surface of the According to the positive pressure F required to be borne by the fuel tank (1) required by the test N Calculating the mass m of the weight (17) Weight of weighing machine The method comprises the steps of carrying out a first treatment on the surface of the Selecting a mass of m Weight of weighing machine The weight (17) is fixed below the screw (16) and is provided with a control switch (19) in a closed state;
wherein the weight (17) has a mass m Weight of weighing machine The calculation mode of (a) is as follows:
wherein F is N Is the positive pressure F required to be borne by the fuel tank (1) required for the test N The unit is N; g is the gravity acceleration, and the value is 9.81m/s 2 ；d Pressing rod Is the horizontal distance (18) from the bearing seat (14) in m; d, d Weight of weighing machine The horizontal distance between the weight (17) and the bearing seat (14) is m;
s3, the laser signal of a rotating speed sensor (20) in the variable-frequency speed regulating subsystem is emitted to the grinding disc (12) from the front surface and is used for measuring the rotating speed of the grinding disc (12) in real time; measuring the distance r between the laser of the rotating speed sensor (20) and the center of the grinding disc (12);
s4, calculating the rotating speed n of the grinding disc (12) according to the friction speed v required by the test; starting the motor (8) and observing the real-time rotating speed of the grinding disc (12) until the real-time rotating speed of the grinding disc (12) reaches the calculated rotating speed n, and keeping the grinding disc (12) to rotate at the constant speed of the rotating speed n;
the rotating speed n of the grinding disc (12) is calculated by the following steps:
wherein v is the friction speed required for the test in m/s; r is the distance between the laser of the rotating speed sensor (20) and the center of the grinding disc (12), and the unit is m; the unit of the rotation speed n of the grinding disc (12) is round/min;
s5, placing the fuel tank (1) on a rotary millstone (12), and simultaneously sequentially installing a first fixed stop lever (5), a second fixed stop lever (6) and a third fixed stop lever (7) in a limiting hole of a cantilever bracket (3) to limit the horizontal displacement of the fuel tank (1) under the rotation action of the millstone (12);
s6, setting a control switch (19) to be in an on state, starting a camera (25) and an infrared thermal imager (26) in the data acquisition subsystem, acquiring image data of the fuel tank (1) when friction occurs through the camera (25), and acquiring temperature field data of the fuel tank (1) when friction occurs through the infrared thermal imager (26).
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