CN108238271A - A kind of avionic device installs stent concentratedly - Google Patents
A kind of avionic device installs stent concentratedly Download PDFInfo
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- CN108238271A CN108238271A CN201711379907.3A CN201711379907A CN108238271A CN 108238271 A CN108238271 A CN 108238271A CN 201711379907 A CN201711379907 A CN 201711379907A CN 108238271 A CN108238271 A CN 108238271A
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- avionic device
- piston rod
- positioning
- pin
- spring
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- 238000009423 ventilation Methods 0.000 claims abstract description 38
- 238000004891 communication Methods 0.000 claims abstract description 24
- 230000007246 mechanism Effects 0.000 claims abstract description 12
- 238000013016 damping Methods 0.000 claims description 29
- 239000006096 absorbing agent Substances 0.000 claims description 16
- 230000008054 signal transmission Effects 0.000 claims description 16
- 229910000831 Steel Inorganic materials 0.000 claims description 14
- 239000010959 steel Substances 0.000 claims description 14
- 230000035939 shock Effects 0.000 claims description 7
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 230000011218 segmentation Effects 0.000 claims description 3
- 238000007789 sealing Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 9
- 239000000203 mixture Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- 239000012141 concentrate Substances 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012856 packing Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000003032 molecular docking Methods 0.000 description 2
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20845—Modifications to facilitate cooling, ventilating, or heating for automotive electronic casings
- H05K7/20863—Forced ventilation, e.g. on heat dissipaters coupled to components
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The present invention proposes that a kind of avionic device installs stent concentratedly, it can be achieved that the concentration quick despatch of multiple avionic devices, including quick assembling/disassembling mechanism, damper mechanism, ventilation and heat pipeline, communication between devices and the communication port of system and interplane.Quick assembling/disassembling mechanism is including installing the latch handle on the strainer on stent, spring holder and avionic device concentratedly.Vibration insulating system is made of 6 dampers, can effectively reduce avionic device vibration level, improves system reliability.Ventilation and heat pipeline includes blast pipe, wind chamber, ventilation duct and sealing ring, and air-cooled condition can be provided for avionic device, effectively adjusts internal electronic component operating temperature, improves functional reliability.The communication port of communication between devices and system and interplane includes installing the rectangular connector on the cylindrical connector and front shroud on stent back casing and left shell concentratedly, realizes the communication connection of equipment room and system and aircraft.
Description
Technical field
The invention belongs to field of mechanical structure design, propose that a kind of avionic device installs stent concentratedly, to meet machine
Upper avionic device concentrates quick despatch, vibration damping, ventilation and heat, the communication connection demand of equipment room.
Background technology
Avionic device use and maintenance process in need Fast Installation and dismounting, internal electronic component will be subjected to
Various oscillating load impacts and thermal shock.The mounting bracket of existing single avionic device, can not realize multiple aviation electronics
Equipment is installed concentratedly, and installing stent concentratedly in contrast can fix on reduction machine in the laying of communication cable, reduce airplane load,
And existing mounting bracket is mostly to use to wave bolt and tightening hook fixation avionic device, operation is loaded down with trivial details can not to realize fast quick-mounting
Unload, requirement can not be met, there is an urgent need for a kind of concentration quick despatch with avionic device, vibration damping, ventilation and heat, can be real
The mounting bracket of the communication connection multi-functional of existing equipment room and system and aircraft.
Invention content
It is more to meet in view of the deficiencies of the prior art, the present invention provides a kind of avionic device installs stent concentratedly
A avionic device concentrates quick despatch, vibration damping, ventilation and heat, the communication connection that equipment room and system and aircraft can be achieved
It is multiple to use functional requirement.
The technical scheme is that：
A kind of avionic device installs stent concentratedly, it is characterised in that：Including install concentratedly stent, back casing,
Side housing, quick assembling/disassembling mechanism, vibration insulating system, ventilation and heat pipeline, communication system；
The stent of installing concentratedly is made of side by side several groups of installing plates；There are segmentation end in the installing plate width direction both sides
Plate, installing plate width dimensions are corresponding with avionic device width, and installing plate length dimension is corresponding with avionic device length；
The quick assembling/disassembling mechanism includes being fixed on the strainer of installing plate bottom outside, on installing plate upper interior end face
Spring holder, the latch handle being fixed on avionic device and the positioning steel bushing on avionic device,
Wherein strainer is corresponded with latch handle, and spring holder is corresponded with positioning steel bushing, when avionic device is placed
On a mounting board in place after, spring holder be inserted into positioning steel bushing in, strainer is in the lock state with latch handle, by aviation
Electronic equipment is fixed on a mounting board；
The vibration insulating system includes supporting plate, damper；Multiple dampers are fixedly mounted on supporting plate, damper upper end and peace
Loading board bottom connects；The threaded hole being connect with aircraft is provided on the supporting plate, it is fixed with aircraft cooperation to there also is provided in supporting plate rear end
The positioning pin of position；
For the ventilation and heat Pipe installing in back casing, the back casing is mounted on installing plate rear end；The ventilation dissipates
Hot channel includes blast pipe, wind chamber and ventilation duct；Blast pipe is connect with aircraft ventilation apparatus；Blast pipe is by being in back casing
Wind chamber connect with ventilation duct, in the air duct set in ventilation duct access avionic device babinet；
The communication system includes several communications mounted on back casing front shroud, upper cover plate and side case top lid plate
Connector forms, and connects composition signal transmission system by inner lead between communications connector, realize avionic device it
Between signal transmission and avionic device and aircraft on signal transmission between other equipment.
Further preferred embodiment, a kind of avionic device install stent concentratedly, it is characterised in that：The damping
Device includes damper housing, radial direction damping piece, is oriented to damping piece, absorber spring and shock absorber piston rod；It is oriented to damping piece edge
It is axially mounted in damper housing, absorber spring, which is sleeved on, to be oriented on the outside of damping piece, and shock absorber piston rod, which is mounted on to be oriented to, to be hindered
In the axial cylindrical bore of damping member, radial direction damping piece is arranged between absorber spring and damper housing and damper piston
Between bar and housing.
Further preferred embodiment, a kind of avionic device install stent concentratedly, it is characterised in that：The locking
Handle includes upswept frame, upper pin, lower bearing pin, hook, torsional spring and pull rod；Upper pin and lower bearing pin are separately mounted to arch frame
Frame back of a bow both ends；It links up with as L-type structure, side is the neck of hook, and opposite side is hook portion, and hook L-type structure corner is provided with pin shaft hole,
For coordinating with upper pin；Torsional spring is also sleeved on upper pin；Drag link sleeve is on lower bearing pin, and pull rod main body is in the back of a bow；It draws
Bar one end groove and the hook portion of hook coordinate, and the pretightning force of torsional spring makes hook hook portion apply constraint to pull rod one end groove；Pull rod
The other end has the crotch face of arc, and crotch face opening direction is identical with groove direction, is constrained when hook hook portion applies groove
When, crotch face can coordinate with the cylindrical pin of the strainer.
Further preferred embodiment, a kind of avionic device install stent concentratedly, it is characterised in that：The tension
Device includes plug-in unit, tenses housing, back-moving spring, tenses piston rod and guide pin；There is opening in the middle part of the plug-in unit, be open interior install
There is cylindrical pin, for coordinating with the crotch face of latch handle；Equipped with piston rod is tensed in the tension housing, piston rod is tensed
One end, which is stretched out, to be tensed housing end face and is fixedly connected with plug-in unit, is tensed the piston rod other end and is fixedly connected with guide pin, tenses piston
Back-moving spring is cased on bar, back-moving spring is in pressured state, and both ends are constrained by tension shell ends face and guide pin.
Further preferred embodiment, a kind of avionic device install stent concentratedly, it is characterised in that：The spring
Positioning pin includes axis pin, retaining spring in positioning piston rod, abutment sleeve, positioning；Positioning piston rod rear end is provided with axial blind hole,
And there is stop bit protrusion in rear end outer；Abutment sleeve is divided into inner sleeve and outer sleeve, and inner sleeve is coaxial nested and fixed with outer sleeve,
Step surface in formation；Inner sleeve both ends are open, the closing of outer sleeve one end, and it is domestic that axial positioning is fixed on blind end
Axis；Positioning piston rod is in abutment sleeve, and positions the stop bit protrusion of piston rod rear end outer and the interior step of abutment sleeve
Face forms constraint, can prevent positioning piston rod abjection abutment sleeve；Retaining spring is in positioning piston rod blind hole and is sleeved on
In positioning on axis pin, retaining spring is in compressive state, both ends by positioning piston rod hole bottom and outer sleeve blind end about
Beam.
Advantageous effect
Advantages of the present invention：Firstth, the concentration quick despatch of multiple avionic devices can be achieved, not by any work
Tool, it is convenient and efficient；Secondth, included vibration insulating system, can effectively reduce system vibration magnitude, improve avionic device signal transmission
Reliability；Third, included ventilation and heat pipeline can provide air-cooled source for avionic device, effectively adjust in avionic device
Portion's electronic component operating temperature, keeps it in optimum range, improves functional reliability；4th, can be achieved equipment room and
System and the reliable communications of aircraft connect, and signal transmission without cable on machine, reduces failure rate between avionic device.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description
It obtains significantly or is recognized by the practice of the present invention.
Description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become in the description from combination accompanying drawings below to embodiment
Significantly and it is readily appreciated that, wherein：
Fig. 1 avionic devices and its install stent assembling schematic diagram concentratedly；(a) side view；(b) front view；
Fig. 2 installs supporting structure schematic diagram concentratedly；
Fig. 3 installs stent concentratedly and mechanical interface schematic diagram is connect with aircraft；
Fig. 4 avionic devices I (2) schematic diagram；(a) front elevation；(b) back view；
Fig. 5 latch handles (4) structure diagram；(a) sectional view；(b) front view；(c) axonometric drawing；
Fig. 6 strainers (22) structure diagram；(a) sectional view；(b) front view；
Fig. 7 spring holders (12) structure diagram；(a) sectional view；(b) front view；
Fig. 8 ventilation and heat channel three-dimensional exploded perspective views；
Fig. 9 dampers (6) structure diagram.
Wherein：1st, stent is installed concentratedly；2nd, avionic device I；3rd, avionic device II；4th, latch handle；5th, it holds in the palm
Plate；6th, damper；7th, back casing；8th, small sealing ring；9th, rectangular connector 1；10th, cylindrical connector 1；11st, cylindrical connector 2；
12nd, spring holder；13rd, rectangular connector 2；14th, large sealing packing ring；15th, cylindrical connector 3；16th, cylindrical connector 4；17th, circle
Shape connector 5；18th, cylindrical connector 6；19th, cylindrical connector 7,20, left shell；21st, installing plate 1；22nd, strainer；23rd, pacify
Loading board 2；24th, chamfered edge pin；25th, straight pin；26th, air duct；27th, ventilation opening；28th, steel bushing is positioned；29th, rectangular connector；30th, it hangs
Hook；31st, axis pin 1；32nd, frame；33rd, torsional spring；34th, axis pin 2；35th, pull rod；36th, plug-in unit；37th, housing is tensed；38th, back-moving spring
1；39th, back-moving spring 2；40th, guide pin；41st, piston rod is tensed；42nd, nut；43rd, cylindrical pin；44th, piston rod is positioned；45、
Retaining spring；46th, inner sleeve；47th, outer sleeve；48th, gasket；49th, axis pin in positioning；50th, round nut；51st, back shroud；52nd, wind
Chamber；53rd, blast pipe；54th, small air hose；55th, front shroud；56th, big air hose；57th, damper housing；58th, bottom cover；59th, it rivets
Steel bushing；60th, absorber spring；61st, it is oriented to damping piece；62nd, piston lever of reducer；63rd, radial direction damping piece 1；64th, radial direction damping piece
2。
Specific embodiment
The embodiment of the present invention is described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning to end
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and is not considered as limiting the invention.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer ", " up time
The orientation or position relationship of the instructions such as needle ", " counterclockwise " are based on orientation shown in the drawings or position relationship, are for only for ease of
The description present invention and simplified description rather than instruction imply that signified device or element must be with specific orientation, Yi Te
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
In addition, term " first ", " second " are only used for description purpose, and it is not intended that instruction or hint relative importance
Or the implicit quantity for indicating indicated technical characteristic.Therefore, define " first ", the feature of " second " can be expressed or
Implicitly include one or more this feature.In the description of the present invention, " multiple " are meant that two or more,
Unless otherwise specifically defined.
Avionic device in the present embodiment installs stent concentratedly, including installing stent, back casing, side shell concentratedly
Body, quick assembling/disassembling mechanism, vibration insulating system, ventilation and heat pipeline, communication system.
The stent of installing concentratedly is made of side by side several groups of installing plates；There are segmentation end in the installing plate width direction both sides
Plate, installing plate width dimensions are corresponding with avionic device width, and installing plate length dimension is corresponding with avionic device length.
The quick assembling/disassembling mechanism includes being fixed on the strainer of installing plate bottom outside, on installing plate upper interior end face
Spring holder, the latch handle being fixed on avionic device and the positioning steel bushing on avionic device,
Wherein strainer is corresponded with latch handle, and spring holder is corresponded with positioning steel bushing, when avionic device is placed
On a mounting board in place after, spring holder be inserted into positioning steel bushing in, strainer is in the lock state with latch handle, by aviation
Electronic equipment is fixed on a mounting board；
The vibration insulating system includes supporting plate, damper；Multiple dampers are fixedly mounted on supporting plate, damper upper end and peace
Loading board bottom connects；The threaded hole being connect with aircraft is provided on the supporting plate, it is fixed with aircraft cooperation to there also is provided in supporting plate rear end
The positioning pin of position；
For the ventilation and heat Pipe installing in back casing, the back casing is mounted on installing plate rear end；The ventilation dissipates
Hot channel includes blast pipe, wind chamber and ventilation duct；Blast pipe is connect with aircraft ventilation apparatus；Blast pipe is by being in back casing
Wind chamber connect with ventilation duct, in the air duct set in ventilation duct access avionic device babinet；
The communication system includes several communications mounted on back casing front shroud, upper cover plate and side case top lid plate
Connector forms, and connects composition signal transmission system by inner lead between communications connector, realize avionic device it
Between signal transmission and avionic device and aircraft on signal transmission between other equipment.
The damper includes damper housing, radial direction damping piece, is oriented to damping piece, absorber spring and damper piston
Bar；It is oriented to damping piece to be axially mounted in damper housing, absorber spring, which is sleeved on, to be oriented on the outside of damping piece, damper piston
Bar is mounted in the axial cylindrical bore for being oriented to damping piece, and radial direction damping piece is arranged between absorber spring and damper housing,
And between shock absorber piston rod and housing.
The latch handle includes upswept frame, upper pin, lower bearing pin, hook, torsional spring and pull rod；Upper pin and lower bearing pin
It is separately mounted to upswept frame back of a bow both ends；It links up with as L-type structure, side is the neck of hook, and opposite side is hook portion, links up with L-type structure
Corner is provided with pin shaft hole, for coordinating with upper pin；Torsional spring is also sleeved on upper pin；Drag link sleeve is on lower bearing pin, and pull rod
Main body is in the back of a bow；Pull rod one end groove and the hook portion of hook coordinate, and the pretightning force of torsional spring makes hook hook portion to pull rod one end
Groove applies constraint；The pull rod other end has the crotch face of arc, and crotch face opening direction is identical with groove direction, when hook hook
When portion applies constraint to groove, crotch face can coordinate with the cylindrical pin of the strainer.
The strainer includes plug-in unit, tenses housing, back-moving spring, tenses piston rod and guide pin；In the middle part of the plug-in unit
There is opening, cylindrical pin is installed in opening, for coordinating with the crotch face of latch handle；Equipped with tension in the tension housing
Piston rod tenses piston rod one end and stretches out tension housing end face and be fixedly connected with plug-in unit, tenses the fixation of the piston rod other end and connects
Guide pin is connect, tensing upper cover of piston rod has back-moving spring, and back-moving spring is in pressured state, and both ends are by tension shell ends face and lead
Constraint to piece.
The spring holder includes axis pin, retaining spring in positioning piston rod, abutment sleeve, positioning；Position piston rod
Rear end is provided with axial blind hole, and there is stop bit protrusion in rear end outer；Abutment sleeve is divided into inner sleeve and outer sleeve, inner sleeve and housing
Cylinder is coaxial nested and fixed, step surface in formation；Inner sleeve both ends are open, the closing of outer sleeve one end, and fixed on blind end
There is axis pin in axial positioning；Positioning piston rod be in abutment sleeve, and position piston rod rear end outer stop bit protrusion and
The interior step surface of abutment sleeve forms constraint, can prevent positioning piston rod abjection abutment sleeve；Retaining spring is in positioning and lives
In stopper rod blind hole and be sleeved in positioning on axis pin, retaining spring be in compressive state, both ends by position piston rod hole bottom with
And outer sleeve blind end constraint.
In the present embodiment, the locking hand on strainer on stent, spring holder and avionic device is installed concentratedly
Handle forms the quick assembling/disassembling mechanism of avionic device, is not needed in cargo handling process by any tool, easy to operate；With
6 dampers form vibration insulating system, effectively reduce avionic device vibration level, improve system reliability；Blast pipe, ventilation
Chamber, ventilation duct and sealing ring form ventilation and heat pipeline, and air-cooled source is provided for avionic device, make electric in avionic device
Sub- component operating temperature is maintained in optimum range；Install the rectangular connector set on stent back casing and left shell concentratedly
Communication and the communication port of system and interplane between cylindrical connector constitution equipment realize the logical of equipment room and system and aircraft
Letter is reliably connected.
As illustrated in fig. 1 and 2, avionic device I (2) and avionic device II (3) pass through latch handle (4) thereon
Collection is fixed to the quick assembling/disassembling mechanism installation of strainer (22), spring holder (12) composition concentrated in mounting bracket (1)
In middle mounting bracket.It installs one avionic device of installation on stent concentratedly and needs to configure 2 strainers and 2 spring positionings
Pin, this example only assemble 2 avionic devices.It installs stent concentratedly mechanical interface schematic diagram is connect with aircraft and see Fig. 3, aviation
Electronic equipment installs 3 supporting plates (5) of stent concentratedly, and totally 3 chamfered edge pins (24), 3 straight pins (25) and 6 screw holes fix peace
It is attached on aircraft.
When avionic device is installed to and installs concentratedly on stent, aviation electronics as shown in Figure 4 and Figure 5 is pulled first
Hook (30) in equipment in latch handle (4), links up with and is rotated clockwise around axis pin 1 (31), and pull rod (35) is unclamped.Then
Avionic device is put into and is installed concentratedly on stent, the crotch face a of pull rod (35) lower end is allowed to catch on circle on strainer (22)
Axis pin of column (43), positioning steel bushing (28) on avionic device can contact spring positioning pin (12), press latch handle with hand
(4) upper connecting rod (35) top allows it to be rotated clockwise around axis pin 2 (34), and avionic device further can install stent concentratedly
On moved afterwards along installing plate 1 (21), while further force piston rod (44) in spring holder axial along sleeve 2 (47)
It slides, treats that pull rod (35) top turns to plumbness along axis pin 2 (34), unclamp hook (30), torsional spring (33) can force extension
Hook (30) is rotated counterclockwise around axis pin 1 (31), and the left side of hook (30) can catch on pull rod (35) top, the work in torsional spring (33)
Pull rod (35) can be locked with lower.Piston rod (44) in installation process in spring holder (12) can be deep into avionic device
It positions in steel bushing (28) cylinder pin hole, piston rod (44) can be forced to slide backward certain distance along sleeve 2 (47) after bottoming out.
Simultaneously the plug-in unit (36) in strainer (22) can drive piston rod (41) and guide pin (40) along housing (37) interior cylindrical hole to
It moves left, and then compressed spring 1 (38) and spring 2 (39).Spring (45) and the strainer being installed in place in rear spring holder
(22) spring 1 (38) and spring 2 (39) in can be to a reaction forces each before and after avionic device, at the two by compression
Pull rod (35) and hook (30) will not detach avionic device under the active force of torsional spring (33) in reaction force and latch handle
It is locked on stent is installed concentratedly.
During dismounting, the hook (30) of avionic device latch handle (4) is pulled first, allows it around axis pin 1 (31) up time
Needle rotates and then releasing lever (35), and the crotch that pull rod (35) rotates lower end around axis pin 2 (34) counterclockwise can be with strainer (22)
On cylindrical pin (43) disengage, push avionic device under the reaction force of spring holder (12) spring (45) at this time
A distance is slided along carriage mounting plate 1 (21) is installed concentratedly, at this time latch handle (4) pull rod (35) face b and strainer
(22) the plane b fittings of cylindrical pin (43), pull latch handle (4) upper connecting rod (35) and allow it around axis pin 2 (34) inverse time
Needle rotate, at this time using install concentratedly strainer on stent (22) cylindrical pin (43) plane b as fulcrum, further force boat
Empty electronic equipment treats to position steel bushing (28) on avionic device with living on spring holder (12) with installing stent disengaging concentratedly
Stopper rod (44) completely disengages, you can holds up avionic device from installing concentratedly and is disassembled on stent.
It installs stent concentratedly and Quick-dismantling mechanism quantity is adjusted according to avionic device quantity, realize multiple aviation electronics
The dress of single avionic device can be realized without any tool in the concentration quick despatch of equipment, overall process in 10s
It unloads, it is convenient and efficient.
Setting ventilation and heat pipeline on stent is installed concentratedly, including blast pipe (53), wind chamber (52), ventilation duct (54,56)
With sealing ring (8,14).It installs concentratedly after stent is installed on aircraft, the meeting of aircraft ventilation apparatus and concentrates mounting bracket blast pipe
(53) it is connected by pipeline, wind regime can enter closed logical between wind chamber (52) and back shroud (51) along blast pipe (53)
Then road enters avionic device 8 (2) along big air hose (56), large sealing packing ring (14), along small air hose (54), small close
Seal (8) enters avionic device II (3).Large sealing packing ring (14) can be bonded with the ventilation opening (27) of avionic device,
Wind is entered by ventilation opening (27) in the air duct (26) of avionic device babinet both sides setting, before avionic device
Plate comes out, and the heat that internal electronic component generates when avionic device is worked quickly is taken away, and can effectively prevent component
The excessively high signal transmission reliability of temperature, which reduces, influences flight safety.
It installs stent lower part concentratedly and is provided with 3 supporting plates (5), arrange 2 dampers (6) on each supporting plate, structure is shown
Intention is shown in Fig. 9.According to avionic device and 6 damper positions of system gravity position rational deployment that mounting bracket is concentrated to form
It puts, vibration is had during aircraft flight, landing etc. and is generated, exciting force can be transmitted to the piston rod (62) on damper (6)
On, piston rod (62) can slide drawing-pressing spring (60) simultaneously being oriented in damping piece (61) interior cylindrical hole during axial vibration, by bullet
Spring (60), damping piece 1 (63) absorb vibrational energy, and damping piece (61) is oriented to during radial vibration and damping piece 2 (64) is absorbed and vibrated
Energy effectively reduces the vibration of avionic device, improves system signal transmission reliability.
After avionic device is centrally mounted in mounting bracket, the rectangular connector (29) on avionic device 9 (2)
Rectangular connector 2 (13) docking in meeting and concentration mounting bracket, the rectangular connector meeting of avionic device II (3) and concentration
Rectangular connector 1 (9) docking in mounting bracket, and rectangular connector 1 (9), rectangular connector 2 (13) and cylindrical connector
(10,11,15,16,17,18,19) composition signal transmission system can be connected with inner lead, realize avionic device it
Between signal transmission and avionic device and aircraft on signal transmission between other equipment.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, those of ordinary skill in the art are not departing from the principle of the present invention and objective
In the case of can make changes, modifications, substitutions and variations to the above described embodiments within the scope of the invention.
Claims (5)
1. a kind of avionic device installs stent concentratedly, it is characterised in that：Including installing stent, back casing, side shell concentratedly
Body, quick assembling/disassembling mechanism, vibration insulating system, ventilation and heat pipeline, communication system；
The stent of installing concentratedly is made of side by side several groups of installing plates；There are segmentation end plate in the installing plate width direction both sides,
Installing plate width dimensions are corresponding with avionic device width, and installing plate length dimension is corresponding with avionic device length；
The quick assembling/disassembling mechanism includes being fixed on the strainer of installing plate bottom outside, the spring on installing plate upper interior end face
Positioning pin, the latch handle being fixed on avionic device and the positioning steel bushing on avionic device, wherein
Strainer is corresponded with latch handle, and spring holder is corresponded with positioning steel bushing, when avionic device is placed on peace
In loading board in place after, spring holder be inserted into positioning steel bushing in, strainer is in the lock state with latch handle, by aviation electronics
Equipment is fixed on a mounting board；
The vibration insulating system includes supporting plate, damper；Multiple dampers are fixedly mounted on supporting plate, damper upper end and installing plate
Bottom connects；The threaded hole being connect with aircraft is provided on the supporting plate, there also is provided in supporting plate rear end and aircraft cooperation positioning
Positioning pin；
For the ventilation and heat Pipe installing in back casing, the back casing is mounted on installing plate rear end；The ventilation and heat pipe
Road includes blast pipe, wind chamber and ventilation duct；Blast pipe is connect with aircraft ventilation apparatus；Blast pipe passes through the wind that is in back casing
Chamber is connect with ventilation duct, in the air duct set in ventilation duct access avionic device babinet；
The communication system includes several communication connections mounted on back casing front shroud, upper cover plate and side case top lid plate
Device forms, and is connected between communications connector by inner lead and forms signal transmission system, between realization avionic device
Signal transmission in signal transmission and avionic device and aircraft between other equipment.
2. a kind of avionic device installs stent concentratedly according to claim 1, it is characterised in that：The damper includes
Damper housing, is oriented to damping piece, absorber spring and shock absorber piston rod at radial direction damping piece；Damping piece is oriented in an axial direction to pacify
In damper housing, absorber spring, which is sleeved on, to be oriented on the outside of damping piece, and shock absorber piston rod, which is mounted on, is oriented to damping piece
In axial cylindrical bore, radial direction damping piece is arranged between absorber spring and damper housing and shock absorber piston rod and shell
Between body.
3. a kind of avionic device installs stent concentratedly according to claim 1, it is characterised in that：The latch handle packet
Include upswept frame, upper pin, lower bearing pin, hook, torsional spring and pull rod；Upper pin and lower bearing pin are separately mounted to the upswept frame back of a bow
Both ends；Link up with as L-type structure, side is the neck of hook, and opposite side is hook portion, and hook L-type structure corner is provided with pin shaft hole, for
Upper pin coordinates；Torsional spring is also sleeved on upper pin；Drag link sleeve is on lower bearing pin, and pull rod main body is in the back of a bow；Pull rod one end
The hook portion of groove and hook coordinates, and the pretightning force of torsional spring makes hook hook portion apply constraint to pull rod one end groove；The pull rod other end
Crotch face with arc, crotch face opening direction is identical with groove direction, when linking up with hook portion to groove application constraint, crotch
Face can coordinate with the cylindrical pin of the strainer.
4. a kind of avionic device installs stent concentratedly according to claim 3, it is characterised in that：The strainer includes
Plug-in unit tenses housing, back-moving spring, tenses piston rod and guide pin；There is opening in the middle part of the plug-in unit, cylinder is installed in opening
Axis pin, for coordinating with the crotch face of latch handle；Equipped with piston rod is tensed in the tension housing, tense piston rod one end and stretch
Go out to tense housing end face and be fixedly connected with plug-in unit, tense the piston rod other end and be fixedly connected with guide pin, tense upper cover of piston rod
There is back-moving spring, back-moving spring is in pressured state, and both ends are constrained by tension shell ends face and guide pin.
5. a kind of avionic device installs stent concentratedly according to claim 3, it is characterised in that：The spring holder
Including axis pin, retaining spring in positioning piston rod, abutment sleeve, positioning；Positioning piston rod rear end is provided with axial blind hole, and rear end
There is stop bit protrusion in outer；Abutment sleeve is divided into inner sleeve and outer sleeve, and inner sleeve is coaxial nested and fixed with outer sleeve, in formation
Step surface；Inner sleeve both ends are open, the closing of outer sleeve one end, and axis pin in axial positioning is fixed on blind end；Positioning
Piston rod is in abutment sleeve, and the stop bit protrusion of positioning piston rod rear end outer and the interior step surface of abutment sleeve are formed about
Beam can prevent positioning piston rod abjection abutment sleeve；Retaining spring is domestic in positioning in piston rod blind hole and being sleeved on positioning
On axis, retaining spring is in compressive state, and both ends are constrained by positioning piston rod hole bottom and outer sleeve blind end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711379907.3A CN108238271A (en) | 2017-12-20 | 2017-12-20 | A kind of avionic device installs stent concentratedly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711379907.3A CN108238271A (en) | 2017-12-20 | 2017-12-20 | A kind of avionic device installs stent concentratedly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108238271A true CN108238271A (en) | 2018-07-03 |
Family
ID=62701040
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711379907.3A Pending CN108238271A (en) | 2017-12-20 | 2017-12-20 | A kind of avionic device installs stent concentratedly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108238271A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109578756A (en) * | 2018-12-07 | 2019-04-05 | 江西洪都航空工业集团有限责任公司 | It is a kind of for installing the bracket of electronic control unit |
| CN109665112A (en) * | 2019-01-31 | 2019-04-23 | 江苏恒铭达航空设备有限公司 | Helicopter electronic self-defence component mounting bracket and helicopter |
| CN112498657A (en) * | 2020-12-18 | 2021-03-16 | 常州宇翔圆航空科技有限公司 | Front radome for aircraft with telescopic turnover mechanism |
| CN113148221A (en) * | 2021-03-04 | 2021-07-23 | 中国航空工业集团公司西安航空计算技术研究所 | Weight reduction optimization method and structure for mounting rack of avionic device |
| CN113795111A (en) * | 2021-11-12 | 2021-12-14 | 四川省安道速博科技有限公司 | Carry on LRM's avionics equipment cabin |
| CN114165508A (en) * | 2021-11-16 | 2022-03-11 | 中国航空工业集团公司洛阳电光设备研究所 | Spring positioning pin |
| CN114286575A (en) * | 2021-12-10 | 2022-04-05 | 西安现代控制技术研究所 | Tool for rear plugging of electronic box |
| CN114352886A (en) * | 2022-01-29 | 2022-04-15 | 中国航空无线电电子研究所 | Airborne equipment multiplexing type mounting structure |
| CN114727534A (en) * | 2022-02-25 | 2022-07-08 | 中航光电科技股份有限公司 | Top sealing device for sealing top of electronic equipment and sealing element thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109578756A (en) * | 2018-12-07 | 2019-04-05 | 江西洪都航空工业集团有限责任公司 | It is a kind of for installing the bracket of electronic control unit |
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| CN112498657A (en) * | 2020-12-18 | 2021-03-16 | 常州宇翔圆航空科技有限公司 | Front radome for aircraft with telescopic turnover mechanism |
| CN113148221A (en) * | 2021-03-04 | 2021-07-23 | 中国航空工业集团公司西安航空计算技术研究所 | Weight reduction optimization method and structure for mounting rack of avionic device |
| CN113795111A (en) * | 2021-11-12 | 2021-12-14 | 四川省安道速博科技有限公司 | Carry on LRM's avionics equipment cabin |
| CN114165508A (en) * | 2021-11-16 | 2022-03-11 | 中国航空工业集团公司洛阳电光设备研究所 | Spring positioning pin |
| CN114286575A (en) * | 2021-12-10 | 2022-04-05 | 西安现代控制技术研究所 | Tool for rear plugging of electronic box |
| CN114352886A (en) * | 2022-01-29 | 2022-04-15 | 中国航空无线电电子研究所 | Airborne equipment multiplexing type mounting structure |
| CN114727534A (en) * | 2022-02-25 | 2022-07-08 | 中航光电科技股份有限公司 | Top sealing device for sealing top of electronic equipment and sealing element thereof |
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Application publication date: 20180703 |