CN202481325U - Reliability test device for aircraft cabin door lock - Google Patents
Reliability test device for aircraft cabin door lock Download PDFInfo
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- CN202481325U CN202481325U CN2012200486336U CN201220048633U CN202481325U CN 202481325 U CN202481325 U CN 202481325U CN 2012200486336 U CN2012200486336 U CN 2012200486336U CN 201220048633 U CN201220048633 U CN 201220048633U CN 202481325 U CN202481325 U CN 202481325U
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Abstract
Provided is a reliability test device for an aircraft cabin door lock. One ends of cabin door carlings are fixed on the surface of one side of a cabin door beam and the other ends of the cabin door carlings are provided with installation holes of a cabin door rotating shaft. The cabin door rotating shaft penetrates two ends of the installation holes and the two ends of the cabin door rotating shaft are respectively arranged inside the cabin door rotating holes on the simulated cabin door bases. A lock ring lug piece is located in the middle of the cabin door beam. A lock ring is connected with the lock ring lug piece. One end of each spring inside a loading mechanism is hung in each spring installation hole on the cabin door beam, and the other end of each spring is hung in each spring installation hole on a loading beam. The loading beam is fixed on the bottom frame of a clamp through loading bolts. According to the reliability test device for the aircraft cabin door lock, simulated cabin doors are used for replacing real cabin doors, the aerodynamic force loading which the reliability test device bears is passed to the cabin door lock, and a plurality of fault simulation tests are carried out on the cabin door lock. The reliability test device for the aircraft cabin door lock is small in size, simple in structure, low in processing requirement and capable of fitting a high and low temperature test, a salt mist test, a vibrating test and a sand-dust test of a combined environment test box clearance cabin door lock.
Description
Technical field
The present invention relates to a kind of aeroplane structure design field, specifically is a kind of reliability test of aircraft cabin door lock.
Background technology
The landing gear compartment door lock system of certain type aircraft partly is made up of hatch door actuator, hatch door, lock ring and hatch door lock etc.The hatch door actuator is handled the folding and unfolding of hatch door, and the hatch door lock is installed on the fuselage, and lock ring is installed on the hatch door.The hatch door lock is hydraulically powered active lock, is one of critical component of hatch door lock system.When taking off, after the hatch door actuator was packed up hatch door, hatch door lock hydraulic gear was handled latch hook and is closed, and latch hook hooks lock ring and hatch door is locked; Remain at locking state at aircraft flight process middle deck door lock; During aircraft landing, hatch door lock hydraulic gear is handled latch hook and is opened, and latch hook discharges lock ring and with the hatch door release, puts down hatch door by the hatch door actuator then.In above-mentioned hatch door lock working process, the hatch door lock should be able to normally cut out, remain on normal locking state or normally open, otherwise can cause the aircraft mission failure, and influences aircraft flight safety.Especially in the aircraft landing stage,, can cause alighting gear normally not put down, very likely cause major accidents such as air crash if the hatch door lock can not normally be opened.
The reliability of hatch door lock is to be directly connected to flight safety; But at present that is that all right is ripe to the theoretical investigation of Mechanical Product Reliability analysis and assessment; Can not reach the level that replaces actual loading test fully, so, expose the main failure mode and the weak link of hatch door lock in order to assess the reliability index of hatch door lock design plan; Obtain to influence the important environmental factor that the hatch door lock lost efficacy; And the innovative approach that obtains to improve hatch door lock reliability level, realize the reliability growth of hatch door lock, must carry out reliability test to the hatch door lock.
In the aircraft development process, part aircraft subsystem is installed aboard at present, carried out the reliability of products test with the work of taking a flight test of aircraft.But, the hatch door lock makes an experiment as if being installed on the aircraft; There is following point in this test method: one, representative type cycle of operations of hatch door lock comprises locking, remains on the locking state certain hour and unblank; And general aircraft each rise and fall and only comprise a hatch door lock cycle of operations, it is long to cause that so the hatch door lock is carried out the spent time compole of life-cycle period run; Two, aircraft flight is with high costs, causes experimentation cost unacceptable; Three, the risk that breaks down of test itself is bigger, in case the fault that the hatch door lock can not normally be opened occurs, very likely causes the major accident of air crash; Four, the environmental conditions of hatch door lock real work is complicated and can't expect, and the environmental conditions that aircraft faces in flight test can't be expected and control equally, the reliability test that causes hatch door to be locked can not cover the environmental conditions that might run into; Five, because the service conditions of flight test middle deck door lock can not be controlled, cause to carry out the failure mode provocative test; Six, the mode of operation to the hatch door lock is difficult to monitor in real time.
Is the effective way that solves the flight test problem on ground in the face of hatch door lock carries out reliability test, but that is that all right is ripe to the reliability test method of the engineering goods of hatch door lock and so at present, and often only considers the influence of monocycle border factor to product reliability in the test.But the actual working environment complicated condition of hatch door lock; And have coupling between each environmental factor, it is completely different to cause hatch door to be locked in simple superposition and its Performance And Reliability evolution rule under the combined environment condition that Performance And Reliability under each monocycle border condition degenerates.If only consider in test of the influence of monocycle border factor to hatch door lock reliability; Then because the factor of considering is comprehensive inadequately; The environmental conditions of simulation is true inadequately, and reliability evolution rule and service life and the actual conditions deviation that can cause testing the hatch door lock that draws are bigger.Therefore need a kind of reliability test that can load the combined environment factor to the hatch door lock.
Summary of the invention
For overcoming experimental result and the bigger deficiency of actual conditions deviation that exists in the prior art, the present invention proposes a kind of aircraft cabin door lock reliability test.
The present invention includes anchor clamps, load load maintainer, simulation hatch door, spacing crossbeam and lock support.Said lock support is fixed on the upper surface of anchor clamps, and the hatch door lock is installed on the lock support.Said simulation hatch door comprises hatch door crossbeam, 2 hatch door longerons, hatch door rotating shaft, simulation hatch door base, lock ring auricle and lock rings, and said load load maintainer comprises that spring, loading crossbeam, load loading bolt and load load nut.On this hatch door crossbeam, be evenly equipped with the mounting hole of three springs.One end of 2 hatch door longerons all is fixed on the side surface of hatch door crossbeam.The line of centers of 2 hatch door longeron length directions perpendicular to the hatch door crossbeam the surface and lay respectively between 2 adjacent on hatch door crossbeam through holes.The other end of 2 hatch door longerons has the mounting hole of hatch door rotating shaft, and this hatch door rotating shaft mounting hole is passed in the hatch door rotating shaft, and two ends are respectively charged in the hatch door shaft hole on the simulation hatch door base.The lock ring auricle is positioned at the middle part of hatch door crossbeam.Lock ring is connected with the lock ring auricle.Spring one end in the said load load maintainer hangs in the spring mounting hole on the hatch door crossbeam, and the other end hangs in the spring mounting hole that loads on the crossbeam.Said loading crossbeam is fixed on through the load loading bolt and is positioned on the anchor clamps underframe.
On the described simulation hatch door base mounting hole is arranged, the mounting hole of boiler-plate door pivot is arranged at the middle part of simulation hatch door base plate, the mounting hole inside face carries out fine limit work.
Lock support comprises the top board of horizontal support plate, vertical support plate and both sides.Said vertical support plate is " protruding " font, and the mounting hole of hatch door lock is arranged on institute's projection, and the position of mounting hole is corresponding with the position that hatch door is locked bolt hole.Upper surface at horizontal support plate has stay bearing plate, and a limit of this stay bearing plate and the upper surface of horizontal support plate are fixed, and captives joint with the surperficial of vertical support plate projection in another limit.The top board of lock support both sides is separately fixed at horizontal support plate and vertical support plate two ends, and in the angle between horizontal support plate and the vertical support plate.Distance between the outside face of lock support both sides top board is identical with distance between the anchor clamps two side wall panels inside face.
Described anchor clamps comprise wallboard, brace panel and a plurality of horizontal reinforcement of both sides.The underframe of two side wall panels bottom is used for the installed load load maintainer along the outside horizontal-extending of wallboard, and the upper surface of the outside horizontal-extending part of said underframe has the mounting hole of load loading bolt and the oblong concave station rank of matching with the termination of load loading bolt.
The present invention replaces the true hatch door of aircraft with the simulation hatch door, and the simulation hatch door can rotate around its rotation axis, and hatch door rotation axis and latch hook rotation axis are to vertical.The simulation hatch door is connected with two hatch door bases through revolute pair respectively, and the hatch door base is connected with anchor clamps through modes such as bolted connections respectively.Lock ring is installed on the simulation hatch door, mounting means and consistent with the relative position and the actual installation situation of lock.
The present invention installs a spacing crossbeam below hatch door, the position of restriction hatch door before locking.Each overlap joint of the two ends of spacing crossbeam is on spacing beam base, and spacing beam base is cemented on the anchor clamps through modes such as bolts.Before locking, the simulation hatch door can overlap under the effect of gravity and spring tension on spacing crossbeam, and this position is the hatch door retracted position.The influence that needs the different retracted positions of research hatch door that hatch door is locked reliability in the test is installed bearing cap shim between spacing crossbeam and spacing beam base, adjust the position of spacing crossbeam through the quantity of bearing cap shim.Lock in the lock process at hatch door, after latch hook hooks lock ring, lock ring is upwards drawn a segment distance.Since spacing crossbeam be installed in the simulation hatch door below, the simulation hatch door can make progress and freely rotates, and can upwards rotate a segment distance so in hatch door is locked process, simulate hatch door.After locking, simulation hatch door and spacing crossbeam disengage, and all hatch door load are born by lock, and spacing crossbeam should have enough strength and stiffness to bear the load of hatch door.
The present invention adopts spring tension to simulate the suffered aerodynamic force of hatch door.Load the crossbeam two ends and be connected on the anchor clamps through a load loading bolt respectively, and regulate the upper-lower position that loads crossbeam through the nut on the bolt.Bolt hole on the crossbeam is less times greater than the diameter of bolt, and crossbeam is stuck when asynchronous in order to avoid two bolts are regulated.When the loading crossbeam moves down, spring will be elongated and pulling force increases.In the lock open mode, all spring tensions are born by spacing crossbeam; In the lock closed condition, spring tension is delivered on the latch hook and by lock through simulation hatch door and lock ring and bears.
The aerodynamic force load that the technical scheme that the present invention taked receives the simulated aircraft hatch door, and through simulation hatch door and lock ring this aerodynamic force loading transfer is locked to hatch door.Replace actual hatch door through the simulation hatch door, and lock ring is identical with actual conditions with simulation hatch door connection mode, so the hatch door lock is comparatively approaching with the relative motion relation and the actual conditions of latch hook.The present invention utilizes spring force to simulate the aerodynamic force that hatch door receives, and the size through load load maintainer adjustment spring force, so simulation hatch door and the suffered aerodynamic force load of hatch door lock can freely be adjusted as required in the reliability test process.The each several part of anchor clamps is bonded to together, and rigidity is big, and resonance frequency is high, and its transmitting vibrations was effective when the hatch door lock was carried out vibration test.Because volume of the present invention is little, can put in the combined environment test case of finite volume, so in the reliability test process, can utilize the combined environment test case that the hatch door lock is loaded multiple stress such as high low temperature, salt fog, vibration, sand dust.When utilizing the present invention and combined environment test case to carry out reliability test, can hydraulic tubing be connected to hatch door and lock, and the hatch door lock is loaded hydraulic load.Thus, in the reliability test process, through being used of the present invention and other test facilitys, the environmental conditions of intending for the hatch door locked mode is comparatively true.Carry out reliability test owing to utilize experimental set-up and equipment that hatch door is locked on ground, hatch door is locked in environmental conditions suffered in the reliability test process and controls easily, and to compare experimentation cost low with flight test.The present invention can adjust the free position of simulation hatch door through the quantity of bearing cap shim, comes hatch door in the simulating actual conditions to can not receive the failure condition of design attitude thus, with the influence of research hatch door retracted position to hatch door lock reliability; The present invention comes the abnormal situation of hydraulic system pressure in the simulating actual conditions through the delivery pressure in modulated pressure source, with the influence of research hydraulic pressure to hatch door lock reliability; The present invention can be through come the installation error of simulating actual conditions middle deck door lock on the adjustment lock support with the position of hatch door lock bonded assembly bolt hole, with the influence of research hatch door lock installation error to hatch door lock reliability.Thus, the present invention can carry out the various faults analogue test to the hatch door lock, and experimental set-up has stronger commonality.Volume of the present invention is little, and the material that expends is few, and is simple in structure, and processing request is low, so tooling cost of the present invention is low, experimentation cost is low.
Description of drawings
Accompanying drawing 1 is a three-dimensional exploded view of the present invention;
Accompanying drawing 2 is structural representations of the present invention;
Accompanying drawing 3 is block diagrams of lock support;
Accompanying drawing 4 is structural representations of anchor clamps;
Accompanying drawing 5 is structural representations of simulation hatch door;
Accompanying drawing 6a is the structural representation of simulation hatch door base;
Accompanying drawing 6b is that the axle of simulation hatch door base is surveyed scheme drawing;
Accompanying drawing 7 is simulation hatch door and lock ring connection mode scheme drawing;
Accompanying drawing 8 is simulation hatch door and the assembly relation scheme drawing of simulating hatch door base and lock ring;
Accompanying drawing 9a is the structural representation of spacing beam base;
Accompanying drawing 9b is that the axle of spacing beam base is surveyed scheme drawing;
Accompanying drawing 10 is assembly relation scheme drawings of spacing crossbeam, bearing cap shim and spacing beam base;
Accompanying drawing 11 is relative position relation scheme drawings of simulation hatch door and spacing crossbeam;
Accompanying drawing 12 is load loading bolts;
Accompanying drawing 13 is connection mode scheme drawings of load loading bolt and anchor clamps.Among the figure:
1. lock support 2. horizontal reinforcement 3. wallboards 4. are simulated hatch door bases 5. boiler-plate door pivots
6. lock ring 7. simulation hatch door longerons 8. lock ring auricles 9. are simulated hatch door crossbeams 10. brace panels
11. load loads nut 12. load loading bolts 13. and loads crossbeam 14. springs 15. spacing beam base
16. bearing cap shim 17. spacing crossbeam 18. hatch doors lock latch hook 19. hatch doors locks
The specific embodiment
Present embodiment is a kind of aircraft cabin door lock combined environment test device, comprises anchor clamps, load load maintainer, simulation hatch door, spacing crossbeam and lock support 1.Said lock support 1 is fixed on the upper surface of anchor clamps, and hatch door lock 19 is installed on the lock support 1.
The simulation hatch door comprises 9,2 hatch door longerons 7 of hatch door crossbeam, hatch door rotating shaft 5, simulation hatch door base 4, lock ring auricle 8 and lock ring 6.Hatch door crossbeam 9 is a rectangular block, on this hatch door crossbeam 9, is evenly equipped with the mounting hole of three springs 14.One end of 2 hatch door longerons 7 is fixed on the side surface of hatch door crossbeam 9; The line of centers of 2 hatch door longeron 7 length directions perpendicular to hatch door crossbeam 9 the surface and lay respectively between 2 adjacent on the hatch door crossbeam 9 through holes.The other end of 2 hatch door longerons 7 has the mounting hole of hatch door rotating shaft, and this hatch door rotating shaft mounting hole is passed in hatch door rotating shaft 5, and two ends are respectively charged in the hatch door shaft hole on the simulation hatch door base 4; Normal-running fit between the hatch door rotating shaft mounting hole on hatch door rotating shaft 5 and the hatch door longeron 7.Lock ring auricle 8 is positioned at the middle part of hatch door crossbeam 9, between 2 hatch door longerons 7.Lock ring 6 adopts prior art; Be two " U " shape structure; Be that lock ring 6 is made up of 2 " U " shape auricles of being inverted and being parallel to each other, the through hole that hatch door lock latch hook hanging scroll is installed is all arranged at the top of said 2 inversions " U " shape auricle, and 2 through holes be concentric.The side of said 2 inversions " U " shape auricle lower end is connected to each other as a whole, and on the connecting panel of 2 inversions " U " shape auricle lower end side, bolt hole is arranged all, through bolt lock ring 6 is connected with lock ring auricle 8.Spring 14 1 ends in the said load load maintainer hang in the spring mounting hole on the hatch door crossbeam 9, and the other end hangs in the spring mounting hole that loads on the crossbeam 13; Said loading crossbeam 13 is fixed on through load loading bolt 12 and is positioned on the anchor clamps underframe.
In Fig. 5, the simulation hatch door comprises 9,2 simulations of simulation hatch door crossbeam hatch door longeron 7,5,2 simulations of boiler-plate door pivot hatch door base 4, lock ring auricle 8 and lock ring 6.Simulation hatch door longeron 7 is one section square steel tube, and an end has the mounting hole of boiler-plate door pivot 5.Simulation hatch door crossbeam 9 is a rectangular steel plates, on this simulation hatch door crossbeam 9, is evenly equipped with the mounting hole of three springs 14.Boiler-plate door pivot 5 solid drawn pipe section bars process, and the two ends of this boiler-plate door pivot have and simulation hatch door base bonded assembly concave station rank, and the outside face on concave station rank carries out fine limit work respectively, to improve the degree of finish of concave station rank outside face.Lock ring auricle 8 is for machine adds part, and its oad parameter is confirmed according to lock ring actual installation situation aboard.Two simulation hatch door longerons 7 are neck and neck together, and lock ring auricle 8 is positioned at the middle part of simulation hatch door crossbeam 9, between simulation hatch door longeron 7.Boiler-plate door pivot 5 passes the mounting hole of two simulation hatch door longerons 7 and is fixed together with it.Simulation hatch door left-right symmetric.
In Fig. 6, described simulation hatch door base 4 is trapezoidal bulk.There is mounting hole at two ends at simulation hatch door base 4 base plates, and the mounting hole of boiler-plate door pivot 5 is arranged at the middle part of simulation hatch door base plate, and the mounting hole inside face carries out fine limit work.
In Fig. 7 and Fig. 8, lock ring 6 is two " U " shape structures, and promptly lock ring 6 is made up of 2 " U " shape auricles of being inverted and being parallel to each other, for machine adds part, at the top of said 2 inversions " U " shape auricle pin and sleeve is installed.The side of said 2 inversions " U " shape auricle lower end is connected to each other as a whole, and on the connecting panel of 2 inversions " U " shape auricle lower end side, bolt hole is arranged all, through bolt lock ring 6 is connected with lock ring auricle 8.The oad parameter of lock ring 6 according to install on the aircraft material object confirm.
In Fig. 8, the concave station rank at boiler-plate door pivot 5 two ends are inserted into respectively in the boiler-plate door pivot mounting hole on the simulation hatch door base 4, and form revolute pair with it.Lock ring 6 connects together with the lock ring auricle through bolt, and the connection mode of the two is identical with actual connection mode on the aircraft.
The load load maintainer comprises that spring 14, loading crossbeam 13, load loading bolt 12 and load load nut 11.Loading crossbeam 13 is rod member, and the bolt hole of vertical direction is arranged at the two ends of this loading crossbeam 13, is used for installed load loading bolt 12, and diameter is a bit larger tham the diameter of load loading bolt 12; Be evenly equipped with the mounting hole of the spring 14 of three horizontal directions on the centre portion of this loading crossbeam 13.In Figure 12, the termination of load loading bolt is a rectangular shape.
In Fig. 3, lock support 1 comprises the top board of horizontal support plate, vertical support plate and both sides.Said vertical support plate is " protruding " font, and the mounting hole of hatch door lock is arranged on institute's projection, is used for fixing hatch door lock 19 is installed, and the position of mounting hole is corresponding with the position that hatch door is locked 19 upper bolt holes.Upper surface at horizontal support plate has stay bearing plate, and a limit of this stay bearing plate and the upper surface of horizontal support plate are fixed, and captives joint with the surperficial of vertical support plate projection in another limit, through this stay bearing plate horizontal support plate is captiveed joint with vertical support plate; Horizontal support plate is the right angle with angle between the vertical support plate.The top board of lock support 1 both sides is separately fixed at horizontal support plate and vertical support plate two ends, and in the angle between horizontal support plate and the vertical support plate; Distance between the outside face of lock support 1 both sides top board is identical with distance between anchor clamps two side wall panels 3 inside faces.
In Fig. 4, anchor clamps adopt aluminum alloy to process, and comprise wallboard 3, brace panel 10 and a plurality of horizontal reinforcement 2 of both sides.Two side wall panels 3 usefulness aluminium alloy plate integral cutting form, on two side wall panels 3 all symmetry have a two-layer square through hole; The crossbeam that forms between the two-layer square through hole plays booster action, and has formed underframe in the bottom of two side wall panels 3.Have the bolt hole of 3 vertical directions at the underframe upper surface, be used for anchor clamps are installed to joggling table.The underframe of two side wall panels 3 bottoms is along wallboard 3 outside horizontal-extendings; Be used for the installed load load maintainer, the upper surface of the outside horizontal-extending part of said underframe has the mounting hole of load loading bolt 12 and the oblong concave station rank of matching with the termination of load loading bolt 12.The middle part of two side wall panels 3 and top also are distributed with the bolt hole of a plurality of horizontal directions, are used for installing simulation hatch door base 4, spacing beam base 15 and lock support 1 respectively.Laterally reinforcement 2 is processed by the aluminium alloy plate with wallboard 3 same thickness for machine adds part, and its shape of cross section is " U " shape.Brace panel 10 is processed by aluminum alloy equally.Be connected through horizontal reinforcement 2 between the two side wall panels 3 of anchor clamps, formed the anchor clamps of shaped as frame.The anchor clamps both sides are connected with brace panel 10.
In Fig. 1 and Fig. 9, spacing crossbeam 17 is for machine adds part, wherein between thickness the thickest, and reduce gradually to two ends.The seamed edge rounding of its upside.Spacing beam base 15 is for machine adds part, a groove arranged between wherein, in order to overlapping spacing crossbeam 18, and at bottom portion of groove a bolt hole arranged, in order to through the spacing crossbeam of bolted connection 17, bearing cap shim 16 and spacing beam base 15.In its bottom surface two bolts hole are arranged, in order to be fixed on the anchor clamps.Bearing cap shim 16 is the flaky texture of rectangle, and there is bolt hole the centre.
In Figure 10 and Figure 11, the two ends of spacing crossbeam 17 overlap in the groove of spacing beam base 15, are lined with bearing cap shim 16 between the two, and through bolt spacing crossbeam 17, bearing cap shim 16 and spacing beam base 15 are linked together.Simulation hatch door longeron 7 snaps on the spacing crossbeam 17, and it is to there being downward load.
In Fig. 2, during assembling, 2 spacing beam base 15 are fixed between the wallboard 3 of anchor clamps both sides, and the two ends of bearing cap shim 16 and spacing crossbeam 17 are respectively charged in the groove of said spacing beam base 15, and with bolt that the three is affixed; The concave station rank at boiler-plate door pivot 5 two ends of simulation hatch door are fit into respectively in the boiler-plate door pivot mounting hole of simulation hatch door base 4, then 2 simulation hatch door bases 4 are fixed between the wallboard 3 of anchor clamps both sides; Said spacing beam base 15 lays respectively on the front vertical frame and rear vertical frame of anchor clamps two side wall panels 3 with simulation hatch door base 4.Simulation hatch door after the installation is a horizontality, and simulation hatch door longeron 7 overlap joints are on the spacing crossbeam 16 of hatch door.The lower surface of lock support 1 horizontal support plate is installed in the anchor clamps upper surface, and the vertical support plate of lock support 1 and the top board and the anchor clamps two side wall panels of both sides are fitted.Hatch door locking fixes on the vertical support plate outside face of lock support 1, and make hatch door lock latch hook 18 can be positioned at the lock latch hook hanging scroll of ring 6 of simulation hatch door and cooperate.In Figure 13, with two load loading bolts 12 outwards loading bolt mounting hole of horizontal-extendings part of packing into from below respectively below two wallboards 3 of anchor clamps, and the termination of load loading bolt 12 cooperates with wallboard 3 following concave station rank.In Fig. 2, the bolt hole that loads crossbeam 13 two ends is set to respectively on the load loading bolt 12, the load of on load loading bolt 12, screwing on respectively then loads nut 11.3 springs 14 are arranged in the load load maintainer, and the lower end of each spring 14 is installed in respectively in each spring mounting hole that loads on the crossbeam 13, and the upper end of each spring 14 is installed in respectively in each spring mounting hole on the simulation hatch door crossbeam 9 of simulating hatch door.
During use, hatch door lock 19 is installed on the lock support 1 of experimental set-up; Then the whole test device is put into the combined environment test case, and experimental set-up is installed on the joggling table expansion table top of combined environment test case through the bolt hole of wallboard 3 bottom vertical directions; At last with hydraulic pipe on the hatch door interlocking.When making an experiment, load is loaded nut 11 twist downwards, nut 11 drives loading crossbeam 13 and moves down, and spring is elongated, thereby realizes spring load is loaded on the simulation hatch door, comes the suffered aerodynamic force load of hatch door in the simulated aircraft practical flight thus.Control the free position of simulation hatch door through the quantity of control bearing cap shim 16, thereby simulate the different retracted positions of hatch door.
Claims (4)
1. an aircraft cabin door lock reliability test is characterized in that, comprises anchor clamps, load load maintainer, simulation hatch door, spacing crossbeam and lock support; Said lock support is fixed on the upper surface of anchor clamps, and the hatch door lock is installed on the lock support; Said simulation hatch door comprises hatch door crossbeam, 2 hatch door longerons, hatch door rotating shaft, simulation hatch door base, lock ring auricle and lock rings, and said load load maintainer comprises that spring, loading crossbeam, load loading bolt and load load nut; On this hatch door crossbeam, be evenly equipped with the mounting hole of three springs; One end of 2 hatch door longerons all is fixed on the side surface of hatch door crossbeam; The line of centers of 2 hatch door longeron length directions perpendicular to the hatch door crossbeam the surface and lay respectively between 2 adjacent on hatch door crossbeam through holes; The other end of 2 hatch door longerons has the mounting hole of hatch door rotating shaft, and this hatch door rotating shaft mounting hole is passed in the hatch door rotating shaft, and two ends are respectively charged in the hatch door shaft hole on the simulation hatch door base; The lock ring auricle is positioned at the middle part of hatch door crossbeam; Lock ring is connected with the lock ring auricle; Spring one end in the said load load maintainer hangs in the spring mounting hole on the hatch door crossbeam, and the other end hangs in the spring mounting hole that loads on the crossbeam; Said loading crossbeam is fixed on through the load loading bolt and is positioned on the anchor clamps underframe.
2. a kind of according to claim 1 aircraft cabin door lock reliability test is characterized in that, on the described simulation hatch door base mounting hole is arranged, and the mounting hole of boiler-plate door pivot is arranged at the middle part of simulation hatch door base plate, and the mounting hole inside face carries out fine limit work.
3. a kind of according to claim 1 aircraft cabin door lock reliability test is characterized in that, lock support comprises the top board of horizontal support plate, vertical support plate and both sides; Said vertical support plate is " protruding " font, and the mounting hole of hatch door lock is arranged on institute's projection, and the position of mounting hole is corresponding with the position that hatch door is locked bolt hole; Upper surface at horizontal support plate has stay bearing plate, and a limit of this stay bearing plate and the upper surface of horizontal support plate are fixed, and captives joint with the surperficial of vertical support plate projection in another limit; The top board of lock support both sides is separately fixed at horizontal support plate and vertical support plate two ends, and in the angle between horizontal support plate and the vertical support plate; Distance between the outside face of lock support both sides top board is identical with distance between the anchor clamps two side wall panels inside face.
4. a kind of according to claim 1 aircraft cabin door lock reliability test is characterized in that, anchor clamps comprise wallboard, brace panel and a plurality of horizontal reinforcement of both sides; The underframe of two side wall panels bottom is used for the installed load load maintainer along the outside horizontal-extending of wallboard, and the upper surface of the outside horizontal-extending part of said underframe has the mounting hole of load loading bolt and the oblong concave station rank of matching with the termination of load loading bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200486336U CN202481325U (en) | 2012-02-15 | 2012-02-15 | Reliability test device for aircraft cabin door lock |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200486336U CN202481325U (en) | 2012-02-15 | 2012-02-15 | Reliability test device for aircraft cabin door lock |
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| CN202481325U true CN202481325U (en) | 2012-10-10 |
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| CN2012200486336U Withdrawn - After Issue CN202481325U (en) | 2012-02-15 | 2012-02-15 | Reliability test device for aircraft cabin door lock |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530265A (en) * | 2012-02-15 | 2012-07-04 | 西北工业大学 | Device for testing reliability of cabin door lock for aircrafts |
| CN104019983A (en) * | 2014-06-23 | 2014-09-03 | 西北工业大学 | Reliability test device for aircraft cabin door lock |
| CN105818999A (en) * | 2015-01-04 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Helicopter hatch door interchange coordination installation method |
| CN105841951A (en) * | 2016-05-25 | 2016-08-10 | 西北工业大学 | Improved cabin door lock testing apparatus for aircraft undercarriage |
-
2012
- 2012-02-15 CN CN2012200486336U patent/CN202481325U/en not_active Withdrawn - After Issue
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530265A (en) * | 2012-02-15 | 2012-07-04 | 西北工业大学 | Device for testing reliability of cabin door lock for aircrafts |
| CN102530265B (en) * | 2012-02-15 | 2013-12-04 | 西北工业大学 | Device for testing reliability of cabin door lock for aircrafts |
| CN104019983A (en) * | 2014-06-23 | 2014-09-03 | 西北工业大学 | Reliability test device for aircraft cabin door lock |
| CN104019983B (en) * | 2014-06-23 | 2017-01-04 | 西北工业大学 | A kind of device for testing reliability of cabin door lock for aircrafts |
| CN105818999A (en) * | 2015-01-04 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Helicopter hatch door interchange coordination installation method |
| CN105818999B (en) * | 2015-01-04 | 2018-03-02 | 哈尔滨飞机工业集团有限责任公司 | One kind, which is gone straight up to cabin door and exchanged, coordinates installation method |
| CN105841951A (en) * | 2016-05-25 | 2016-08-10 | 西北工业大学 | Improved cabin door lock testing apparatus for aircraft undercarriage |
| CN105841951B (en) * | 2016-05-25 | 2018-07-13 | 西北工业大学 | A kind of improved aircraft landing gear cabin door lock experimental rig |
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