CN108645452A - A kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device - Google Patents
A kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device Download PDFInfo
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- CN108645452A CN108645452A CN201810775204.0A CN201810775204A CN108645452A CN 108645452 A CN108645452 A CN 108645452A CN 201810775204 A CN201810775204 A CN 201810775204A CN 108645452 A CN108645452 A CN 108645452A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
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- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Abstract
A kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device belongs to airborne power supply system cable insulation aging life-span technical field of measurement and test.It can be changed position fixture, tensile stress loading device, insulation measurement instrument, force snesor, electric controller and host computer PC by cable bend stress loading device, thermal stress load program control type high low temperature cycles test case, test cable and formed.Thermal stress load program control type high low temperature cycles test case is connected with pedestal bottom plate, test cable can be changed position fixture and be connected with tensile stress loading device, cable bend stress loading device is tensioned to by test cable in thermal stress load program control type high low temperature cycles test case, insulation measurement instrument is connect with tensile stress loading device mounting plate, and test cable can be changed position fixture and be connect respectively with tensile stress loading device mounting plate and pedestal bottom plate.The present invention ensures the reliability service of airborne power supply system for assessing the production domesticization aircraft equipment wire cable insulating service life.
Description
Technical field
The present invention relates to a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test devices, for assessing production domesticization
The aircraft equipment wire cable insulating service life, and then ensure the reliability service of airborne power supply system, belong to airborne power supply system cable
Insulated aging life-span technical field of measurement and test.
Background technology
With the high speed development of modern Aviation technical level of science and technology, aircraft piece electrical automatization level is obviously improved, and is drawn
All kinds of advanced airborne equipments are entered.Most advanced airborne equipments are all made of electric energy working method, all kinds of transmissions of electricity at present
Cable mainly undertakes the transmission and control of electric energy between different electrical equipments in power distribution network.Aviation of the aircraft as Highgrade integration
Device arranges that line footpath differs in fuselage narrow space, length not equal all kinds of distribution cables, including power of alterating and direct current line,
Three power cords and individual event power cord etc..It is generally sealed in due to Aviation cable in narrow fuselage, working environment is than ground work
Industry equipment badly much because aircraft in flight, using with parking period, ambient climatic conditions are sufficiently complex, and temperature becomes
Change acutely, the oxidation course of cable insulation will be accelerated, and then accelerates the expansion of the tiny crackle of insulating layer under the action of electric field
Exhibition.On the other hand, due to the limitation in the space that the structure of aircraft itself limits and connects up, cable is bundled into a beam bending and wears mostly
For shuttle between metal framework and covering, when aircraft flight, vibration causes cable to bear alternation mechanical stress for a long time, will accelerate
The aging of cable insulation is even broken.The engineer of Letromec companies Boeing-747 once retired to a frame, A300, L-
1011 and two the installation cable of frame DC-9 be detected, test result is shown：It just insulate at 13 in the every 1000m cables of L-1011
Aging crackle, wherein there are 1.6 insulation ag(e)ing crackles in the 1000m cables of a frame DC-9 aircrafts.L-1011 complete machines there are about
240km cables, crackle sum are more than 3000.The United States Transportation Security committee (NTSB) 1996 is to Trans-World Airlines 800
It draws a conclusion after the very long investigation of secondary flight crash accident, a main cause of accident is that wire short-circuiting spark causes its center
Wing tank explodes.U.S. army once carried out comprehensive inspection to the P-3C antisubmarine planes of frame active service installation cable, found cable aging
Phenomenon is serious, and there are serious potential dangers.According to China's Statistical, statistics indicate that, the aviation Shenzhen maintenance factory of south in 2002 is in charge of
In 10 frame A320 aircrafts, multiple cable fault was occurred as soon as, arranges aircraft to stop field repair, replace cable more than ten times thus, shadow
Normal flight operation is rung.Therefore, the gradual aging of the insulating materials of cable or even damage are the great of threat Flight Safety
Hidden danger.
The assessment of Aviation cable life model and life-span prediction method research are both needed to based on ageing failure data, mesh
Lack the estimated means of effective service life using domestic electric wire on preceding aircraft electrical power supply system, even if there is a small amount of experiment dress
It sets and is also mainly limited to cable degradation under single influence factor, objective can not comprehensively reflect aircraft electrical power supply system distribution
Ager process of the electric wire under actual condition environment in net.Aviation cable insulation ag(e)ing process is not a certain influence factor list
One effect, but under the influence of many factors as a result, but it is between each influence factor and asymmetrical, wherein key factor is to aviation
The service life of cable plays a leading role, and other factors play synergistic effect.Therefore, it is based on similarity principle, establishes the reality with cable
The matched experimental situation of ageing process realizes the reasonable characterization of aircraft wire cable aging life-span, is that highly important research is appointed
Business.
The present invention is meeting work for the lower degradation demand of aircraft electrical power supply system electric wire multi- scenarios method synergistic effect
Under the conditions of the hypothesis of journey practice, the degradation environment that simulation heat, machinery, an electric field multiple physical field couple is established, to drop
Low single factor test assesses the deviation brought to aging life-span, makes the assessment result of Aging Test closer to the practical aging of cable
Service life, to ensure the reliability of airborne power supply system electric wire real work.
Invention content
The purpose of the present invention is providing authentic experiments means for cable service life is estimated, to ensure the aircraft equipment that domesticizes
A kind of reliability that electric wire works under complicated coupling stress field, it is proposed that aircraft electrical power supply system cable multi- scenarios method insulation
Ageing test apparatus.
The purpose of the present invention is what is be achieved through the following technical solutions：
A kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device mainly by cable bend stress loading device,
Thermal stress loads program control type high low temperature cycles test case, test cable can be changed position fixture, tensile stress loading device, insulation resistance are surveyed
Measure instrument, force snesor, electric controller and host computer PC composition.
Test cable is the test specimen of this experimental rig；
The cable bend stress loading device includes：Lock nut, end rubber stopper, cable aperture rubber stopper and simulation
Aircraft skin metal tube；
Simulation aircraft skin metal tube in cable bend stress loading device is hollow cylinder, and one is opened up along central symmetry plane
The spacing of one group of through-hole of determining deviation, through-hole is determined according to test cable minimum radius bend；End rubber stopper is ladder shaft type
Structure is equipped with through-hole along axial location, and the size of through-hole determines that the diameter of through-hole is bigger in principle according to the line footpath of test cable
In the diameter of test cable；End rubber stopper small end journal size and simulation aircraft skin metal tube inner hole, big end-journal
Size is consistent with simulation aircraft skin metal pipe outside diameter；It simulates aircraft skin metal tube both ends and processes screw thread；
The test cable can be changed position fixture：Slide lower platen mounting blocks, top board, sliding lower platen in pulling force end
And fixing end slides lower platen mounting blocks；
The tensile stress loading device includes：Stepper motor, installation transfer block, first bearing seat, second bearing seat, ladder
Shape screw pair is oriented to round guide, linear bearing, mounting plate, force snesor holder, fixing end holder and pedestal bottom plate；
Wherein, first bearing seat is identical with second bearing seat function, plays a supporting role, but internal structure is somewhat different,
First bearing seat is to put angular contact ball bearing, and second bearing seat is to put deep groove ball bearing；
It is that standard modular structure, test cable can be changed position fixture pair from top to bottom that the test cable, which can be changed position fixture,
Answer two groups of dynamometry end and fixing end, two groups of corresponding top boards and sliding lower platen consistent；Two groups of test cable variable bit folders
Dynamometry end group in tool is that pulling force end sliding lower platen mounting blocks are fixedly connected with force snesor dynamometry end；Fixing end group is to fix
End sliding lower platen mounting blocks are fixedly connected by fixing end holder with pedestal bottom plate；Pulling force end slide lower platen mounting blocks and
It is rectangular groove structure that fixing end, which slides lower platen mounting blocks, and nearly test cable one end side processes two screw threads along its length
Hole；Top board is strip cube, and length direction is evenly distributed with one group of half-round cross hole, and half-round cross hole runs through in the width direction, semicircle
Through-hole lower boundary is overlapped with top board ground, and the radius of one group of half-round cross hole is slightly less than the determination of test cable specification line footpath, semicircle
Through-hole both sides symmetrical machining counter sink；The strip cube that lower platen is section inverted T-shaped is slided, length is consistent with top board,
Upper end width and top board equivalent width, lower end width in certain proportion relationship and are more than top board width with top board width；
The connection relation of each module is as follows in a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device：
Thermal stress load program control type high low temperature cycles test case is connected with pedestal bottom plate, and test cable can be changed position fixture and draw
Stress loading device is connected, and cable bend stress loading device is tensioned to thermal stress by test cable and loads program control type high/low temperature alternation
In chamber, insulation measurement instrument is connect with tensile stress loading device mounting plate, and it is logical that test cable can be changed position fixture pulling force end
It crosses pulling force end sliding lower platen mounting blocks to connect with tensile stress loading device mounting plate, it is logical that test cable can be changed position fixture fixing end
Fixing end sliding lower platen mounting blocks are crossed to connect with pedestal bottom plate.
Wherein, the connection relation of each module is as follows in cable bend stress loading device：Cable aperture rubber stopper and test cable
It is connected, end rubber stopper is connected with simulation aircraft skin metal tube, and simulation aircraft skin metal tube is connect with lock nut, is locked
Nut is connect with end rubber stopper；
The connection relation that test cable can be changed each module in position fixture is as follows：Sliding lower platen is connected with top board, tests
Cable is connected with top board and sliding lower platen respectively；Top board is slided with pulling force end respectively with sliding lower platen both sides location hole
Lower platen mounting blocks are connected with fixing end sliding lower platen mounting blocks；
The connection type of each module is as follows in tensile stress loading device：Mounting plate and trapezoidal screw pair of nut and linear bearing
Connection；Force snesor is connect with force snesor holder and mounting plate；Stepper motor output end is connect with trapezoidal screw pair of nut；
Round guide is oriented to connect with pedestal bottom plate；Linear bearing is flexibly connected with round guide is oriented to.
The installation of cable bend stress loading device and the course of work are as follows：
One group of through hole that cable bend stress loading device opens up a determining deviation along central symmetry plane is installed with cable
To avoid test cable under action of pulling stress in through-hole knee mechanical wear occurs for hole rubber stopper；Test cable is from hollow
Cylinder penetrates inside side, is pierced by one side from first through-hole, is then penetrated by second through-hole and is pierced by from another side on one side,
It repeats the above process and is pierced by inside hollow cylinder after test cable penetrates on one side from the last one through-hole；End rubber stopper
Small end journal size and simulation aircraft skin metal tube inner hole, big end journal size and simulation aircraft skin metal pipe outside diameter
Unanimously；The screw thread of simulation aircraft skin metal tube both ends processing is connect with lock nut, and test cable is logical from lock nut center
Hole is pierced by, and central through hole size is slightly larger than test cable；As lock nut is tightened step by step, lock nut squeezes end rubber
Plug, radially compressive deformation is shunk end rubber stopper central through hole, and by test cable clamping and positioning, simulation test cable exists
The fixed effect of harness in aircraft skin.
The installation process that test cable can be changed position fixture is as follows：
Lower platen upper end to be slided with top board to coordinate, corresponding top board countersunk head hole site processes matched threaded hole,
The consistent half-round cross hole of corresponding top board half-round cross hole position machine direction size；Test cable passes through under the sliding of correspondingly-sized
Pressing plate half-round cross hole, test cable are cased with the pyrocondensation protection of pipe of correspondingly-sized with sliding lower platen half-round cross hole contact position, on
Pressing plate is connected through a screw thread fastening with sliding lower platen, and the both ends of test cable are fixedly clamped by top board with sliding lower platen；
To be formed by through-hole center consistent with force snesor dynamometry axis and test cable axis with the cooperation of sliding lower platen for top board；It is sliding
The side of the dynamic nearly test cable in lower platen lower end corresponds to half-round cross hole both sides and is symmetrily processed with location hole；Slide lower platen in pulling force end
Mounting blocks, fixing end sliding lower platen mounting blocks are rectangular groove structure, and nearly test cable one end side is processed along its length
Two threaded holes, sliding lower platen lower end can be slided in rectangular channel；Under determining top board according to test cable line footpath and slide
Whole position location after pressing plate combination, corresponding top board are formed by the positioning of through-hole center both sides with lower platen cooperation is slided
Hole is overlapped with pulling force end sliding lower platen mounting blocks, fixing end sliding lower platen mounting blocks threaded hole, then passes through holding screw
Positioning is fixed.
The installation process of the tensile stress loading device is as follows：Mounting plate is fixedly connected with feed screw nut and linear bearing,
It is moved along linear bearing guide direction under the traction of trapezoidal screw pair of nut with realizing；Force snesor passes through force snesor branch
Frame is fixedly installed in mounting plate, and host computer PC exports control command to electrical control according to tensile stress needed for Aging Test
Device, stepper motor driver control stepper motor rotation, stepper motor output shaft drive silk by shaft coupling in electric controller
Thick stick pair of nut, mounting plate move under the traction of trapezoidal screw pair of nut along test cable tensile stress direction, force sensor measuring
Axial tension suffered by test cable feeds back to host computer PC, and when reaching nominative testing force value, stepper motor stops operating, trapezoidal spiral shell
Female secondary positioned by latching characteristics realization keeps.
The aircraft electrical power supply system cable multi- scenarios method Aging Test device can provide mechanical stress simultaneously, heat is answered
The ambient stress of three kinds of coupled fields of power and electric field；Wherein, mechanical stress includes two kinds of tensile stress and bending stress, and tensile stress passes through
Tensile stress loading device generates, and bending stress is generated by cable bend stress loading device；Thermal stress loads journey by thermal stress
Control formula high low temperature cycles test case generates；Electric field is generated by insulation measurement instrument internal high pressure power supply；
Test cable one end can be changed position fixture by test cable and be fixed on fixing end holder, and the other end runs through cable bend
Cable bend stress loading device is penetrated silicon corundum inside thermal stress load program control type high low temperature cycles test case by stress loading device
Heating in heating tube, Aging Test temperature are that thermal stress loads temperature transducer inside program control type high low temperature cycles test case
The temperature-rise period of directly measured quantities, thermal stress load program control type high low temperature cycles test case is directly controlled and is adopted by host computer PC
Collect real time temperature.One end of test cable output heating tube can be changed position fixture by test cable and be fixed on force snesor dynamometry
End measures test cable institute tension stress during Aging Test；Insulation measurement instrument includes high voltage power supply, and anode is surveyed
Examination line is connected on the nearly force snesor one end test cable interior metal conductor of test cable, and cathode p-wire is connected to test electricity
Cable fixing end insulate on epidermis；The output of insulation measurement instrument test voltage is controlled by host computer PC, and acquisition is surveyed in real time
Measure insulating resistance value of the test cable between coupling stress environment lower conductor and insulation epidermis；When insulating resistance value is reduced to one
When determining resistance value, show that ageing failure occurs for test cable.
The function of each module of this experimental rig is as follows：
The function of cable bend stress loading device is that simulation test cable is coated with the work condition environment in aircraft skin；Test electricity
The function that cable can be changed position fixture is compatible different line footpath test cable positioning clamping demands, the applicability of expanding test device；Power
The function of sensor is to measure axial tension suffered by test cable and feed back to host computer PC, when reaching nominative testing force value, is walked
Stepper motor is stopped operating by electric controller control, and screw pair realizes that positioning is kept by itself latching characteristics；Electric-controlled
The function of device processed is to control stepper motor rotation by its internal stepper motor driver；The function of host computer PC is to acquire simultaneously
Store test cable life-cycle Aging Test data under coupling stress environment.
Advantageous effect
A kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device, with existing Aging Test device phase
Than having the advantages that：
1. the present invention lacks Acceptable life for domestic aircraft equipment electric wire at present estimates research technique, it is based on
Similarity principle is established the Aging Test devices being physically coupled to such as heat, machinery, electric field more, is tried with reducing existing aging
Single factor test assesses the deviation brought to aging life-span during testing, and makes the assessment result of Aging Test closer to the reality of cable
Border aging life-span；
2. cable bend stress loading device introduces influence of the bending stress to test cable insulation ag(e)ing, mould in the present invention
Intended test cable be coated in aircraft skin, the fixed effect of harness, improve Aging Test result accuracy；
3. test cable, which can be changed position fixture, in the present invention can realize that once mounting is applicable in a variety of line footpath test cable insulation always
Change experiment demand, while ensureing that test cable axis is unified with force snesor dynamometry axial reference by clamp structure.
Description of the drawings
Fig. 1 is a kind of structural schematic diagram of aircraft electrical power supply system cable multi- scenarios method Aging Test device of the present invention；
Fig. 2 is that the test cable in a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device of the present invention can
Position-changing clamp structural schematic diagram；
Fig. 3 is the test cable harness bending stress loader that test cable of the present invention can be changed position fixture；
Wherein, 1-stepper motor；2-installation transfer blocks；3-first bearing seats；4-trapezoidal screw pair of nut；5-lead
To round guide；6-linear bearings；7-mounting plates；8-force snesor holders；9-force snesors；The sliding of 10-pulling force ends pushes
Plate mounting blocks；11-top boards；12-sliding lower platens；13-second bearing seats；14-test cables；15-fixing ends are slided
Lower platen mounting blocks；16-fixing end holders；17-pedestal bottom plates；18-thermal stress load program control type high low temperature cycles test
Case；19-insulation measurement instrument；20-lock nuts；21-end rubber stoppers；22-cable aperture rubber stoppers；23-simulations fly
Machine covering metal tube；24-electric controllers；25-host computer PCs.
Specific implementation mode
The present invention will be further described with reference to the accompanying drawings and examples.
Embodiment 1
This example illustrates a kind of tools of aircraft electrical power supply system cable multi- scenarios method Aging Test device of the present invention
Body is implemented.
Fig. 1 is a kind of structural schematic diagram of aircraft electrical power supply system cable multi- scenarios method Aging Test device of the present invention；
It will be seen from figure 1 that a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device is mainly by locking
Nut (20), end rubber stopper (21), cable aperture rubber stopper (22), simulation aircraft skin metal tube (23), thermal stress load journey
Control formula high low temperature cycles test case (18), pulling force end sliding lower platen mounting blocks (10), top board (11), sliding lower platen
(12), fixing end sliding lower platen mounting blocks (15), stepper motor (1), installation transfer block (2), first bearing seat (3), second
Bearing block (13), is oriented to round guide (5), linear bearing (6), mounting plate (7), force snesor holder at trapezoidal screw pair of nut (4)
(8), fixing end holder (16), pedestal bottom plate (17), insulation measurement instrument (19), force snesor (9), electric controller (24)
Is formed with host computer PC (25)
Fig. 2 is that the test cable in a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device of the present invention can
Position-changing clamp structural schematic diagram；
From figure 2 it can be seen that test cable can be changed position fixture mainly by pulling force end sliding lower platen mounting blocks (10), on
Pressing plate (11), sliding lower platen (12), fixing end sliding lower platen mounting blocks (15), force snesor (9) and test cable
(14) it forms；
Fig. 3 is the test cable harness bending stress loader that test cable of the present invention can be changed position fixture；
From figure 3, it can be seen that test cable harness bending stress loader is by test cable (14), lock nut
(20), end rubber stopper (21), cable aperture rubber stopper (22), simulation aircraft skin metal tube (23) form；
Cable bend stress loading device main analog test cable is coated with the work condition environment in aircraft skin, wherein simulation flies
Machine covering metal tube is hollow cylinder, one group of through-hole of a determining deviation is opened up along central symmetry plane, the spacing of through-hole is according to test
Cable minimum radius bend determines.Through hole is installed with cable aperture rubber stopper, to avoid test cable in action of pulling stress
Under through-hole knee occur mechanical wear.Test cable penetrates inside hollow cylinder side, is worn on one side from first through-hole
Go out, then penetrated on one side by second through-hole and be pierced by from another side, repeat the above process until test cable from the last one
Through-hole is pierced by after penetrating on one side inside hollow cylinder.End rubber stopper is ladder axis structure, and through-hole is equipped with along axial location,
The size of through-hole determines that the present embodiment test cable outer diameter is 5mm according to the line footpath of test cable, and the diameter of through-hole omits in principle
More than the diameter of test cable, therefore determine that through-hole diameter is 5.5mm, end rubber stopper small end journal size and aircraft skin metal
Pipe orifice coordinates, and big end journal size is consistent with aircraft skin metal pipe outside diameter.Aircraft skin metal tube both ends process screw thread, with
Lock nut connects, and test cable is pierced by from lock nut central through hole, and central through hole size is 7mm.With lock nut by
Grade is tightened, and lock nut squeezes end rubber stopper, and radially compressive deformation is shunk end rubber stopper central through hole, will be tested
Cable steps up to position, the fixed effect of simulation test cable harness in aircraft skin.
The test cable can be changed position fixture as standard modular structure from top to bottom, mainly be compatible with different line footpaths tests
Cable positions clamping demand, the applicability of expanding test device.Test cable can be changed position fixture and correspond to dynamometry end and fixing end two
Group, two groups of test cables, which can be changed, to be only different from pulling force end sliding lower platen mounting blocks and is fixed with force snesor dynamometry end in position fixture
Connection, fixing end sliding lower platen mounting blocks are fixedly connected by fixing end holder with pedestal bottom plate, corresponding top board and sliding
Lower platen is consistent.Top board is strip cube, and length direction is evenly distributed with one group of half-round cross hole, aperture be respectively 2.8mm,
4.8mm, 6.8mm, 9.8mm, half-round cross hole run through in the width direction, and half-round cross hole lower boundary is overlapped with top board ground, semicircle
Through-hole both sides symmetrical machining counter sink.The strip cube that lower platen is section inverted T-shaped is slided, length is consistent with top board,
Upper end width and top board equivalent width, lower end width in certain proportion relationship and are more than top board width with top board width.
It slides lower platen upper end with top board to coordinate, corresponding top board countersunk head hole site processes matched threaded hole, corresponds to and presses
The consistent half-round cross hole of plate half-round cross hole position machine direction size.Test cable passes through the sliding lower platen semicircle of correspondingly-sized
Through-hole, test cable are cased with the pyrocondensation protection of pipe of correspondingly-sized, top board and cunning with sliding lower platen half-round cross hole contact position
Dynamic lower platen is connected through a screw thread fastening, and the both ends of test cable are fixedly clamped by top board with sliding lower platen.Top board with
Sliding lower platen cooperation is formed by through-hole center (the present embodiment corresponds to aperture 4.8mm) and force snesor dynamometry axis and test
Cable axis is consistent.The side of the nearly test cable in sliding lower platen lower end corresponds to half-round cross hole both sides and is symmetrily processed with location hole.
Lower platen mounting blocks are slided at pulling force end, fixing end sliding lower platen mounting blocks are rectangular groove structure, nearly test cable one end
Face processes two threaded holes along its length, and sliding lower platen lower end can be slided in rectangular channel.It is true according to test cable line footpath
Determine top board and is formed by with sliding lower platen cooperation logical with position location whole after lower platen combines, corresponding top board is slided
The location hole of hole center both sides is overlapped with pulling force end sliding lower platen mounting blocks, fixing end sliding lower platen mounting blocks threaded hole,
It is then positioned and is fixed by holding screw.
Mounting plate is fixedly connected with feed screw nut and linear bearing in the tensile stress loading device, to realize in trapezoidal silk
It is moved along linear bearing guide direction under the traction of thick stick pair of nut.Force snesor is fixedly installed in peace by force snesor holder
Loading board, host computer PC export control command to electric controller, in electric controller according to tensile stress needed for Aging Test
Stepper motor driver controls stepper motor rotation, and stepper motor output shaft drives screw pair, mounting plate by shaft coupling
It is moved along test cable tensile stress direction under the traction of trapezoidal screw pair of nut, it is axial suffered by force sensor measuring test cable
Tension feedback is to host computer PC, and when reaching nominative testing force value, stepper motor stops operating, and trapezoidal nut pair relies on latching characteristics
Realize that positioning is kept.
The aircraft electrical power supply system cable multi- scenarios method Aging Test device can provide mechanical stress simultaneously, heat is answered
The ambient stress of three kinds of power, electric field coupled fields, wherein mechanical stress include two kinds of tensile stress and bending stress, and tensile stress passes through drawing
Stress loading device generates, and bending stress is generated by cable bend stress loading device；Thermal stress is loaded program-controlled by thermal stress
Formula high low temperature cycles test case generates；Electric field is generated by insulation measurement instrument internal high pressure power supply.Test cable one end is logical
It crosses the variable position fixture of test cable and is fixed on fixing end holder, the other end runs through cable bend stress loading device, by cable bend
Stress loading device penetrates heating in silicon corundum heating tube, insulation ag(e)ing inside thermal stress load program control type high low temperature cycles test case
Test temperature is that thermal stress loads temperature transducer directly measured quantities inside program control type high low temperature cycles test case, thermal stress load
The temperature-rise period of program control type high low temperature cycles test case is directly controlled by host computer PC and acquires real time temperature.Test cable is defeated
Go out one end of heating tube and can be changed position fixture by test cable to be fixed on force snesor dynamometry end, measures Aging Test process
Middle test cable institute tension stress.Insulation measurement instrument includes high voltage power supply, and positive p-wire is connected to the nearly power of test cable
On the test cable interior metal conductor of sensor one end, cathode p-wire is connected on test cable fixing end insulation epidermis.Absolutely
The output of edge resistance measuring instrument test voltage is controlled by host computer PC, and acquires measured test cable in real time in coupling stress ring
Insulating resistance value between border lower conductor and insulation epidermis.When insulating resistance value is reduced to certain resistance value, show test cable
Ageing failure occurs, host computer PC acquires and stores test cable life-cycle Aging Test number under coupling stress environment
According to.Coupling stress field measurement involved in the present embodiment and control accuracy such as table 1, Aging Test data such as table 2.
1 coupling stress field measurement of table and control accuracy
2 test cable Aging Test data of table
The present embodiment is based on similarity principle, establishes the Aging Test dresses being physically coupled to such as heat, machinery, electric field more
It sets, the deviation brought is assessed to aging life-span to reduce single factor test during existing degradation, degradation is the result shows that examination
Experiment device reliably and accurately simulates test cable in aircraft equipment actual condition environment, makes the assessment result of Aging Test
Closer to the practical aging life-span of cable.
The above is presently preferred embodiments of the present invention, and it is public that the present invention should not be limited to embodiment and attached drawing institute
The content opened.It is every not depart from the lower equivalent or modification completed of spirit disclosed in this invention, both fall within the model that the present invention protects
It encloses.
Claims (7)
1. a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device, it is characterised in that：Mainly by cable bend
Stress loading device, thermal stress load program control type high low temperature cycles test case, test cable can be changed position fixture, tensile stress load dress
It sets, insulation measurement instrument, force snesor, electric controller and host computer PC composition；
Test cable is the test specimen of this experimental rig；
Simulation aircraft skin metal tube in cable bend stress loading device is hollow cylinder, between central symmetry plane opens up centainly
Away from one group of through-hole, the spacing of through-hole determines according to test cable minimum radius bend；End rubber stopper is ladder axis structure,
It is equipped with through-hole along axial location, the size of through-hole determines that the diameter of through-hole is slightly larger than survey in principle according to the line footpath of test cable
Try the diameter of cable；End rubber stopper small end journal size and simulation aircraft skin metal tube inner hole, big end journal size
It is consistent with simulation aircraft skin metal pipe outside diameter；It simulates aircraft skin metal tube both ends and processes screw thread；
The tensile stress loading device includes：Stepper motor, installation transfer block, first bearing seat, second bearing seat, trapezoidal silk
Thick stick pair of nut is oriented to round guide, linear bearing, mounting plate, force snesor holder, fixing end holder and pedestal bottom plate；
Wherein, first bearing seat is identical with second bearing seat function, plays a supporting role, but internal structure is somewhat different, and first
Bearing block is to put angular contact ball bearing, and second bearing seat is to put deep groove ball bearing；
It is that standard modular structure, test cable can be changed position fixture and correspond to survey from top to bottom that the test cable, which can be changed position fixture,
Two groups of power end and fixing end, two groups of corresponding top boards and sliding lower platen are consistent；Two groups of test cables can be changed in position fixture
Dynamometry end group be pulling force end slide lower platen mounting blocks be fixedly connected with force snesor dynamometry end；Fixing end group is slided for fixing end
Dynamic lower platen mounting blocks are fixedly connected by fixing end holder with pedestal bottom plate；Slide lower platen mounting blocks and fixation in pulling force end
End sliding lower platen mounting blocks are rectangular groove structure, and nearly test cable one end side processes two threaded holes along its length；
Top board is strip cube, and length direction is evenly distributed with one group of half-round cross hole, and half-round cross hole runs through in the width direction, half-round cross hole
Lower boundary is overlapped with top board ground, and the radius of one group of half-round cross hole is slightly less than the determination of test cable specification line footpath, half-round cross hole
Both sides symmetrical machining counter sink；The strip cube that lower platen is section inverted T-shaped is slided, length is consistent with top board, upper end
Width and top board equivalent width, lower end width in certain proportion relationship and are more than top board width with top board width；
The connection relation of each module is as follows in a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device：
Thermal stress load program control type high low temperature cycles test case is connected with pedestal bottom plate, and test cable can be changed position fixture and tensile stress
Loading device is connected, and cable bend stress loading device is tensioned to thermal stress by test cable and loads program control type high low temperature cycles test
In case, insulation measurement instrument is connect with tensile stress loading device mounting plate, and test cable can be changed position fixture pulling force end and pass through drawing
Power end sliding lower platen mounting blocks are connect with tensile stress loading device mounting plate, and test cable can be changed position fixture fixing end and pass through admittedly
Fixed end sliding lower platen mounting blocks are connect with pedestal bottom plate；
Wherein, the connection relation of each module is as follows in cable bend stress loading device：Cable aperture rubber stopper is connected with test cable,
End rubber stopper is connected with simulation aircraft skin metal tube, and simulation aircraft skin metal tube is connect with lock nut, lock nut
It is connect with end rubber stopper；
The connection relation that test cable can be changed each module in position fixture is as follows：Sliding lower platen is connected with top board, test cable
It is connected respectively with top board and sliding lower platen；Top board is slided respectively with pulling force end with sliding lower platen both sides location hole and is pushed
Plate mounting blocks are connected with fixing end sliding lower platen mounting blocks；
The connection type of each module is as follows in tensile stress loading device：Mounting plate connects with trapezoidal screw pair of nut and linear bearing
It connects；Force snesor is connect with force snesor holder and mounting plate；Stepper motor output end is connect with trapezoidal screw pair of nut；It leads
It is connect to round guide with pedestal bottom plate；Linear bearing is flexibly connected with round guide is oriented to；
The function of each module of this experimental rig is as follows：
The function of cable bend stress loading device is that simulation test cable is coated with the work condition environment in aircraft skin；Test cable can
The function of position-changing clamp is compatible different line footpath test cable positioning clamping demands, the applicability of expanding test device；Power senses
The function of device is to measure axial tension suffered by test cable and feed back to host computer PC, and when reaching nominative testing force value, stepping is electric
Machine is stopped operating by electric controller control, and screw pair realizes that positioning is kept by itself latching characteristics；Electric controller
Function be that stepper motor rotation is controlled by its internal stepper motor driver；The function of host computer PC is to acquire and store
Test cable life-cycle Aging Test data under coupling stress environment.
2. a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device according to claim 1, feature
It is：Cable bend stress loading device includes：Lock nut, end rubber stopper, cable aperture rubber stopper and simulation aircraft skin
Metal tube.
3. a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device according to claim 1, feature
It is：The test cable can be changed position fixture：Lower platen mounting blocks, top board are slided, lower platen is slided, is solid in pulling force end
Slide lower platen mounting blocks in fixed end.
4. a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device according to claim 1, feature
It is：The aircraft electrical power supply system cable multi- scenarios method Aging Test device can provide mechanical stress, thermal stress simultaneously
With the ambient stress of three kinds of coupled fields of electric field；Wherein, mechanical stress includes two kinds of tensile stress and bending stress, and tensile stress passes through drawing
Stress loading device generates, and bending stress is generated by cable bend stress loading device；Thermal stress is loaded program-controlled by thermal stress
Formula high low temperature cycles test case generates；Electric field is generated by insulation measurement instrument internal high pressure power supply；
Test cable one end can be changed position fixture by test cable and be fixed on fixing end holder, and the other end runs through cable bend stress
Cable bend stress loading device is penetrated silicon corundum inside thermal stress load program control type high low temperature cycles test case and heated by loader
Heating in pipe, Aging Test temperature are that temperature transducer is direct inside thermal stress load program control type high low temperature cycles test case
The temperature-rise period of measurement amount, thermal stress load program control type high low temperature cycles test case is directly controlled by host computer PC and acquires reality
Shi Wendu；One end of test cable output heating tube can be changed position fixture by test cable and be fixed on force snesor dynamometry end, survey
Test cable institute tension stress during amount Aging Test；Insulation measurement instrument includes high voltage power supply, positive p-wire
It is connected on the nearly force snesor one end test cable interior metal conductor of test cable, it is solid that cathode p-wire is connected to test cable
It insulate on epidermis fixed end；The output of insulation measurement instrument test voltage is controlled by host computer PC, and the measured survey of acquisition in real time
Try insulating resistance value of the cable between coupling stress environment lower conductor and insulation epidermis；When insulating resistance value is reduced to certain resistance
When value, show that ageing failure occurs for test cable.
5. a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device according to claim 1, feature
It is：The installation of cable bend stress loading device and the course of work are as follows：Cable bend stress loading device is opened along central symmetry plane
If one group of through hole of a determining deviation is installed with cable aperture rubber stopper, to avoid test cable logical under action of pulling stress
Mechanical wear occurs for hole knee；Test cable penetrates inside hollow cylinder side, is pierced by one side from first through-hole, then
Penetrated on one side by second through-hole and be pierced by from another side, repeat the above process until test cable from the last one through-hole on one side
It is pierced by inside hollow cylinder after penetrating；End rubber stopper small end journal size and simulation aircraft skin metal tube inner hole,
Big end journal size is consistent with simulation aircraft skin metal pipe outside diameter；Simulate the screw thread and lock of the processing of aircraft skin metal tube both ends
Tight nut connection, test cable are pierced by from lock nut central through hole, and central through hole size is slightly larger than test cable；With locking
Nut is tightened step by step, and lock nut squeezes end rubber stopper, and radially compressive deformation is shunk end rubber stopper central through hole,
By test cable clamping and positioning, the fixed effect of simulation test cable harness in aircraft skin.
6. a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device according to claim 1, feature
It is：The installation process that test cable can be changed position fixture is as follows：
It slides lower platen upper end with top board to coordinate, corresponding top board countersunk head hole site processes matched threaded hole, corresponding
The consistent half-round cross hole of top board half-round cross hole position machine direction size；Test cable passes through the sliding lower platen of correspondingly-sized
Half-round cross hole, test cable are cased with the pyrocondensation protection of pipe of correspondingly-sized, top board with sliding lower platen half-round cross hole contact position
It is connected through a screw thread fastening with sliding lower platen, the both ends of test cable are fixedly clamped by top board with sliding lower platen；Upper pressure
To be formed by through-hole center consistent with force snesor dynamometry axis and test cable axis with the cooperation of sliding lower platen for plate；Under sliding
The side of the nearly test cable in pressing plate lower end corresponds to half-round cross hole both sides and is symmetrily processed with location hole；Slide lower platen installation in pulling force end
Block, fixing end sliding lower platen mounting blocks are rectangular groove structure, and nearly test cable one end side processes two along its length
Threaded hole, sliding lower platen lower end can be slided in rectangular channel；Top board and sliding lower platen are determined according to test cable line footpath
Whole position location after combination, corresponding top board with slide lower platen cooperation be formed by the location holes of through-hole center both sides with
Lower platen mounting blocks are slided at pulling force end, fixing end sliding lower platen mounting blocks threaded hole overlaps, and are then positioned by holding screw
It is fixed.
7. a kind of aircraft electrical power supply system cable multi- scenarios method Aging Test device according to claim 1, feature
It is：The installation process of the tensile stress loading device is as follows：Mounting plate is fixedly connected with feed screw nut and linear bearing, with reality
It is moved along linear bearing guide direction under the traction of present trapezoidal screw pair of nut；Force snesor is solid by force snesor holder
Dingan County is loaded on mounting plate, and host computer PC exports control command to electric controller, electricity according to tensile stress needed for Aging Test
Stepper motor driver control stepper motor rotation, stepper motor output shaft drive feed screw nut by shaft coupling in airgun controller
Pair, mounting plate move under the traction of trapezoidal screw pair of nut along test cable tensile stress direction, force sensor measuring test electricity
Axial tension suffered by cable feeds back to host computer PC, and when reaching nominative testing force value, stepper motor stops operating, trapezoidal nut pair according to
Realize that positioning is kept by latching characteristics.
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