CN102390519A - Novel unit in-air emergency hatchdoor - Google Patents
Novel unit in-air emergency hatchdoor Download PDFInfo
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- CN102390519A CN102390519A CN2011102727623A CN201110272762A CN102390519A CN 102390519 A CN102390519 A CN 102390519A CN 2011102727623 A CN2011102727623 A CN 2011102727623A CN 201110272762 A CN201110272762 A CN 201110272762A CN 102390519 A CN102390519 A CN 102390519A
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- fuselage
- cable wire
- pulley
- access door
- wind blocking
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Abstract
The invention belongs to a design technology of an emergency hatchdoor of an aircraft and provides a brand new design scheme of an in-air parachute jumping emergency hatchdoor. The emergency hatchdoor is characterized in that an access door is arranged on the outer side of a fuselage, wherein the access door comprises a mouth cover of the access door, two lock holes of bolt locks are respectively arranged on the two sides of the mouth cover of the access door, two spring bolt locks are respectively arranged on each of fuselage door frames corresponding to the two sides of the mouth cover of the access door, and the spring bolt locks and the lock holes are correspondingly matched and mounted for fixing the mouth cover of the access door on the fuselage; and four steel cables are connected at the tail ends of the four spring bolt locks, each of the four steel cables is respectively connected with one end of a fan-shaped wheel fixed on the fuselage, the other ends of the four fan-shaped wheels are further connected with the four steel cables and connected with two pulley blocks, the pulley blocks comprise three pulleys and five pulleys respectively, and the pulley blocks are connected on a handle through the steel cables. The emergency hatchdoor can almost meet emergency opening of the hatchdoor in various flight attitudes at high speed and low speed; the pure mechanical manual operation is safe and reliable; the mechanism principle is clear and concise; and the scheme has very strong expansibility.
Description
Technical field
The invention belongs to aircraft emergency exit designing technique, proposed parachute jumping emergency exit design plan in a kind of brand new.
Background technology
At a high speed (speed per hour is greater than 400 kilometers) aerial parachute jumping all adopts both at home and abroad at present for the crew is to drive the hatch door pressurized strut method of opened door as wind shield of facining the wind with the aircraft main hydraulic system; Belong to the electric-controlled hydraulic maneuverability pattern; Representative type has Ilyushin 76-MD, empty alert 2000 aircrafts; This kind emergency exit is strict for aerial parachute jumping limiting condition, at first requires system not allow to lose efficacy, and can not satisfy high reliability lifesaving requirement; Secondly under the prerequisite that system does not have to lose efficacy, being limited in scope of lifesaving must keep aircraft rectilinear flight, that is to say, limits aircraft basically and under the situation about can't put out of catching fire, uses.
Summary of the invention
The object of the invention: design the aerial bailout hatch door of airframe sidewall unit that uses in a kind of full speed degree envelope curve, this hatch door does not use the extra power system, pure mechanical manual operation; Under the normal flight situation, hatch door must positive lock, prevents that accident from opening; Must be in being not more than 10s under the emergency condition smooth opening do not take and withdraw passage; And can effectively stop the windblast crew, simultaneously, armstrong's patent operating handle power will meet relevant criterion, code requirement.
Technical scheme of the present invention is:
The aerial emergency exit of a kind of novel unit is characterized in that, at fuselage outer side an access door is set, and access door comprises an access door flap, and access door flap both sides respectively are provided with two latch lock lockholes 1; 2,3,4, the cooresponding fuselage doorframe in access door flap both sides place respectively is provided with two spring tongue locks 5,6; 7,8, spring tongue lock 5,6,7; 8 install with lockhole 1,2,3,4 corresponding matching the access door flap are fixed on the fuselage; On spring tongue lock 5,6,7,8 tail ends, connect four cable wires 9,10,11,12, four cable wires 9; 10,11,12, respectively with a sectional wheel 13,14 that is fixed on the fuselage, 15,16 one ends connect; Four sectional wheel other ends connect cable wire 17,18 again, and 19,20 and two assembly pulleys 21,22 connect, and assembly pulley 21 is by three pulleys 23,24; 25 form, and assembly pulley 22 is by pulley 26,27, and 28,29,30 form, and cable wire 17,18 is connected on the pulley 23,24; Cable wire 19,20 is connected on the pulley 26,27, connects a cable wire 31 from pulley 25, and cable wire 31 is connected with pulley 28, connects a cable wire 32 from pulley 29, and cable wire 32 is fixedly connected on the handle 33.
A wind blocking door is set in the front of said fuselage outer side access door, and the wind blocking door flap is connected with the fuselage doorframe through the hinge near access door one side, at wind blocking door flap opposite side two latch lock lockholes 34 is set; 35; Two spring tongue locks 36,37, spring tongue lock 36 are set at the cooresponding doorframe of wind blocking door flap place; 37 lock the installation of lockhole 34,35 corresponding matching with latch is fixed on the wind blocking door flap on the fuselage;
On spring tongue lock 36,37 tail ends, connect 38,39, two cable wires 38 of two cable wires; 39 connect with sectional wheel 40,41 one ends that are fixed on the fuselage respectively, and two sectional wheel other ends connect cable wire 42,43 again and are connected with an assembly pulley 44; Assembly pulley 44 is formed cable wire 42 by three pulleys 45,46,47; 43 are connected on the pulley 45,46, connect a cable wire 48 from pulley 47, and cable wire 48 is connected on the pulley 49.
Said cable wire 17,18,19,20,31 walk around deflection sheave 50,51,52,53,54 respectively.
Said cable wire 42,43 is walked around deflection sheave 55,56 respectively.
The initial opener of wind blocking door is installed on fuselage, and this initial opener comprises extension spring, push rod, and extension spring one end is fixed on the fuselage, and the other end is fixed on push rod one end, and the push rod other end withstands on wind blocking door flap inside face.
The said push rod other end is installed a roller.
Said initial opener quantity is one or more sets.
One or more spring pins are installed at the lintel place on access door, and this spring pin passes lintel and is fixed on the lintel.
Be connected with one or more cable wire between said wind blocking door flap inside face and the fuselage.
According to actual conditions one or more turnbuckles or tension link can be set in the middle of the said cable wire.
Principle of work of the present invention: its principle of work is:
Under the normal flight situation; Access door and wind blocking door are locked on the fuselage sidewall by the spring tongue latch mechanism; Wherein access door respectively arranges up and down that in both sides, back in front of the door 1 locks latch; Wind blocking door arranges respectively up and down that in the front side 1 locks spring tongue, and portion installs 2 hinges up and down behind the door, is connected with the doorframe hinge seat.Two doors are actual to be non-airtight not load flap.
When unit bailout is used; Emergency opening handle in the pilot operator driving compartment; Handle action drives the pulley rope arrangement and synchronously the lock pin of 6 place's spring tongue latch mechanisms of access door and wind blocking door is extracted from access door and wind blocking door lockhole; Access door has just been removed constraint fully, fly in the air, during have and be arranged on the access door 2 spring pin mechanism springs at lintel place and yearn for the application of forces and help access doors to break away from aircrafts; After wind blocking door spring tongue lock lock pin is extracted; The extension spring action pulling push rod of the initial opener of wind blocking door rotates around the fuselage shaft seating; Promote wind blocking door and outwards rotate about 6 ° around main hinge; Air-flow gets into the wind blocking door zone, under the effect of wind-force head-on, door is raised, and wind blocking door is opened after about 90 ° by being arranged in two cable wires between wind blocking door inside face and the doorframe and door is remained on opened the position and keep out the wind.Like this, access door will fly away from aircraft, and wind blocking door facings the wind under the windage effect and opens the effect of playing the fender guard that keeps out the wind against the course, and the crew can jump out from passage and flee from aircraft.
Beneficial effect of the present invention is: the outside tunnel escape door of wind blocking door and fuselage splits, and is independent of each other, and almost satisfies the various flight attitude hatch door of high low speed emergency opening; Pure manipulator dynamic formula operation, safe and reliable, need not other energy resource system; Mechanism principle is short and sweet, and technology maturation can guarantee the firm locking of hatch door under the normal flight condition; Scheme has very strong extendability, and for the aerial bailout demand of low speed, the anterior wind blocking door of cancellation can form new scheme.
Description of drawings
Fig. 1: unit emergency exit fuselage surface distribution schematic diagram
Fig. 2: wind blocking door is opened a scheme drawing
Fig. 3: hatch door mechanism general picture
Fig. 4: wind blocking door is anterior
Fig. 5: wind blocking door assembly pulley
Fig. 6: access door is anterior
Fig. 7: access door rear portion
Fig. 8: access door assembly pulley
Fig. 9: intermediate pulley group
Figure 10: access door power-assisted opener scheme drawing
Figure 11: the initial opener scheme drawing of wind blocking door
Figure 12: pulley cable wire and spring tongue latch mechanism canonical schema
Wherein, 100: fuselage lower wall 101: wind blocking door 102: access door 103: access door opening 104: upper hinge 105: go up cable wire 106: following hinge 107: wind blocking door opening 108: following cable wire 109: wind blocking door 110: assistant's door-opening mechanism 111: stage clip 112: access door 113: bearing 114: push rod 115: extension spring seat 116: extension spring hanging point 117: push rod shaft seating 118: wind blocking door 119: roller 120: push rod 121: extension spring 122: latch 123: stage clip 124: lock 125: cable connector 126: cable wire 127: sectional wheel bearing 128: sectional wheel 129: deflection sheave 130: pulley base 34: upper latch lock lockhole 35: bottom latch lock lockhole
5,6,7,8,36,37: the spring tongue lock; 13,14,15,16,40,41: sectional wheel; 33: handle mechanism; 19,20,31,32,42,43,48: cable wire; 21,22,44: assembly pulley; 54: deflection sheave 38,39: cable wire; 55,56: deflection sheave 45,46,47: pulley 3,4: lockhole; 11,12,19,20: cable wire; 52,53: deflection sheave 1,2: spring tongue lock lockhole; 9,10: cable wire; 50,51: deflection sheave 23,24,25: pulley 26,27,28:, 29,30: pulley
The specific embodiment
Through the specific embodiment the present invention is further described below:
The aerial emergency exit of aircraft crewmember according to the invention; Tunnel escape door and anterior wind blocking door and steering unit, locking mechanism etc. by being positioned on the fuselage one side lower wall constitute; Mechanism is that pulley cable wire and spring tongue lock are the main soft steering unit of forming, the aerial pure manual unlocking of hatch door, and access door independently is arranged on after the wind blocking door; To break away from aircraft after access door is unblanked, will be under the effect of contrary wind air-flow after wind blocking door is unblanked outwards open towards the airplane tail group moving hinge that rotates.
Access door comprises an access door flap, and the access door flap is made up of aluminum alloy materials covering and blanked part skeleton, and the both sides upper-lower position has 4 bearings of captive joint altogether before and after flap, has a through hole 1 on the bearing; 2,3,4, through hole locks 5 with spring tongue respectively; 6,7,8 latch cooperates. Spring tongue lock 5,6,7; 8 are made up of latch, compression spring, lock, trip ring shown in accompanying drawing 12, and wherein lock is corresponding with support position on the access door flap, is fixedly connected on the airframe structure; Be the aluminium alloy hollow box-like structure; Latch passes the mounting hole on the lock front/rear end, and compression spring is enclosed within on the latch, and trip ring is fixedly mounted on the latch between lock front end face and compression spring.The latch tail end of spring tongue lock 5,6,7,8 connects cable wire 9,10,11 through cable connector; 12, cable wire 9,10,11,12 other ends equally through cable connector be installed in the sectional wheel 13 on the airframe structure; 14,15,16 1 ends connect, and two arc section radiuses of sectional wheel are different, and 2 times of last arc section radiuses are to descending the arc section radius; Four sectional wheel other ends connect cable wire 17,18,19,20 again through cable connector, and these four cable wires are respectively through being fixed on the pulley 50 on the airframe structure; 51,52 (2), 53 turn to, and turn to back and two assembly pulleys 21,22 to connect.Assembly pulley 21 is made up of three pulleys 23,24,25; Be installed on the assembly pulley bearing that is fixed on the fuselage pulley 23,24; 25 are fixed on the sheave shaft that passes the assembly pulley bearing, and sheave shaft is a compound type step axle, and pulley is fixedly mounted between each step to avoid cable wire to interfere.Assembly pulley 22 is by pulley 26,27, and 28,29,30 form, and assembly pulley form and assembly pulley 21 are similar.Cable wire 17,18 is connected on the pulley 23,24 through cable connector; Cable wire 19,20 is connected on the pulley 26,27 through cable connector; Connect a cable wire 31 from pulley 25; Cable wire 31 is connected with pulley 28, connects a cable wire 32 from pulley 29, and cable wire 32 turns to the back to be connected with handle mechanism 33 through pulley 54.Pulley 54 is installed in the pulley base that is fixed on the driving compartment floor.
The lintel place installs 2 spring pin on access door, and spring pin passes lintel and is fixed on the lintel.Shown in figure 10, spring pin is through in the ears formula bearing that is fixed on the fuselage, for ladder bar-shaped.A compression spring is enclosed within on the spring pin, before spring pin front end and bearing between the auricle.When access door was closed, door body extrusion spring pin overcame the compression spring resistance and moves energy reserve inwards; When access door four locks 5 to spring tongue; After 6,7,8 latch is pulled out and unblanks; Access door loses that help breaks away from doorframe as early as possible under the bounce effect that constrains in 2 spring pins, makes the in time aerial parachute jumping of aviator thereby abdicate tunnel escape.
Simultaneously, the front of above-mentioned fuselage outer side access door (towards heading) is provided with a wind blocking door, and wind blocking door comprises a wind blocking door flap; The wind blocking door flap adds part by aluminum alloy exterior skin and whole machine and forms, and is connected with the fuselage doorframe through two hinges up and down near access door one side, and two latch lock lockholes 34 are set on wind blocking door flap opposite side end face; 35; Two spring tongue locks 36,37, spring tongue lock 36 are set at the cooresponding doorframe of wind blocking door flap place; 37 lock the installation of lockhole 34,35 corresponding matching with latch is fixed on the wind blocking door flap on the fuselage; On spring tongue lock 36,37 tail ends, connect 38,39, two cable wires 38,39 of two cable wires respectively with a sectional wheel 40 that is fixed on the fuselage; 41 1 ends connect, and two sectional wheel other ends connect cable wire 42,43 again and turn to the back to be connected with an assembly pulley 44 through pulley 55,56 separately; Assembly pulley 44 is formed cable wire 42 by three pulleys 45,46,47; 43 are connected on the pulley 45,46, connect a cable wire 48 from pulley 47, and cable wire 48 is connected on the pulley 29 of assembly pulley 22.
The motion principle of above-mentioned spring tongue lock 36,37, sectional wheel 40,41, assembly pulley 44, size relationship, installation relation etc. and aforementioned channels doorway lid spring latch lock, sectional wheel, assembly pulley are identical.
The initial opener of two cover wind blocking doors is installed on fuselage, and shown in figure 11, this initial opener comprises extension spring, push rod; Extension spring one end hook ring is connected on the fuselage hook base; The other end is connected on the hook on the push rod, and push rod is installed in the fuselage bearing shaft hole, and it is inboard that shaft hole is positioned at the extension spring hook; At double in the distance apart from the push rod front end, install a roller and withstand on the wind blocking door flap inside face by the push rod front end apart from extension spring hook hole distance for the push rod shaft hole.Utilize lever principle like this; The moment that extension spring produces is several times as much as wind blocking door when closing to the moment of push rod; After the release of wind blocking door flap latch lock; Even aerodynamic loading compresses the wind blocking door flap, thereby can confirm fully that through anatomizing calculating suitable lever arm of force relation and extension spring rigidity overcome aerodynamic loading and wind blocking door is opened a suitable angle lets air-flow act on the flap inside face door is outwards opened around hinge through fully.Like this, the door shield that keeps out the wind plays the effect of barrier air in access door opening front, and when aircraft at high speed (air speed surpasses 400Km/h) flight, when the aviator parachuted from passage, it was injured blown by high velocity air.
For being remained on, wind blocking door opens the position; Between wind blocking door flap inside face and fuselage, be connected with 2 tension cable wires; Correspondingly, on wind blocking door flap inside face and fuselage, be fixed with the cable wire bearing, the length of cable wire is confirmed according to the wind blocking door open angle; Cable wire is external outside wind blocking door flap inside face is fixed on partially, and apportion is two up and down.
One or more turnbuckles or tension link can be set in the middle of above-mentioned each root cable wire according to actual needs reduce the motion transmission error that the cable wire elastic deformation brings to regulate the cable wire tightness.
In order to eliminate many asynchronisms with the cable wire motion, the length that the length that must back extract according to the spring tongue locking plug must be inserted access door flap or wind blocking door flap greater than reality is 15mm at least.
When not having high-speed bailout to need, cancellation wind blocking door and hinge thereof, latch latch mechanism, initial opener, tension cable wire get final product, and a reserve channel doorway is covered and associated mechanisms can satisfy the unit escape and rescue trunk demand of parachuting in the air.
The aerial emergency exit of aircraft crewmember according to the invention; Its operating process is when unit bailout is used: the handle mechanism in the pilot operator driving compartment; Handle action drives the pulley rope arrangement and synchronously the latch of 6 place's spring tongue latch mechanisms of access door and wind blocking door is extracted from access door and wind blocking door lockhole; Access door has just been removed constraint fully, fly in the air, during be arranged on the access door 2 spring pin mechanism springs at lintel place and yearn for the application of forces and help access doors to break away from aircrafts; After wind blocking door spring tongue lock lock pin is extracted; The extension spring action pulling push rod of the initial opener of wind blocking door rotates around the fuselage shaft seating; Promote wind blocking door and outwards rotate about 6 ° around main hinge; Air-flow gets into the wind blocking door zone, under the effect of wind-force head-on, door is raised, and wind blocking door is opened after about 108 ° by being arranged in two tension cable wires between wind blocking door inside face and the doorframe and door is remained on opened the position and keep out the wind.Like this, access door will fly away from aircraft, and wind blocking door facings the wind under the windage effect and opens the effect of playing the fender guard that keeps out the wind against the course, and the crew can jump out from passage and flee from aircraft.
Claims (10)
1. aerial emergency exit of novel unit; It is characterized in that; At fuselage outer side an access door is set; Access door comprises an access door flap; Access door flap both sides respectively are provided with two latch lock lockholes (1), (2), (3), (4), and the cooresponding fuselage doorframe in access door flap both sides place respectively is provided with two spring tongue locks (5), (6), (7), (8), and spring tongue lock (5), (6), (7), (8) are installed the access door flap is fixed on the fuselage with lockhole (1), (2), (3), (4) corresponding matching; On spring tongue lock (5), (6), (7), (8) tail end, connect four cable wires (9), (10), (11), (12); Four cable wires (9), (10), (11), (12); Be connected with sectional wheel (13), (14), (15), (16) one ends that are fixed on the fuselage respectively; Four sectional wheel other ends connect cable wire (17), (18), (19), (20) again and are connected with two assembly pulleys (21), (22), and assembly pulley (21) is made up of three pulleys (23), (24), (25), and assembly pulley (22) is made up of pulley (26), (27), (28), (29), (30); Cable wire (17), (18) are connected on pulley (23), (24); Cable wire (19), (20) are connected on pulley (26), (27), connect a cable wire (31) from pulley (25), and cable wire (31) is connected with pulley (28); Connect a cable wire (32) from pulley (29), cable wire (32) is fixedly connected on the handle (33).
2. the aerial emergency exit of novel unit according to claim 1 is characterized in that, a wind blocking door is set in the front of said fuselage outer side access door; The wind blocking door flap is connected with the fuselage doorframe through the hinge near access door one side; At wind blocking door flap opposite side two latch lock lockholes (34) are set, (35) are provided with two spring tongue locks (36) at the cooresponding doorframe of wind blocking door flap place; (37); Spring tongue lock (36), (37) and latch lock lockhole (34), (35) corresponding matching is installed the wind blocking door flap is fixed on the fuselage; At spring tongue lock (36), connect two cable wires (38), (39), two cable wires (38) on (37) tail end; (39) respectively with a sectional wheel (40) that is fixed on the fuselage, (41) one ends connect, two sectional wheel other ends connect cable wire (42) again, (43) are connected with an assembly pulley (44); Assembly pulley (44) is by three pulleys (45), and (46), (47) are formed, cable wire (42); (43) be connected pulley (45), on (46), connect a cable wire (48) from pulley (47), cable wire (48) is connected on the pulley (49).
3. the aerial emergency exit of novel unit according to claim 1 is characterized in that, said cable wire (17), (18), and (19), (20), (31) are walked around deflection sheave (50), (51), (52), (53), (54) respectively.
4. the aerial emergency exit of novel unit according to claim 2 is characterized in that, said cable wire (42), and (43) are walked around deflection sheave (55), (56) respectively.
5. the aerial emergency exit of novel unit according to claim 2; It is characterized in that; The initial opener of wind blocking door is installed on fuselage, and this initial opener comprises extension spring, push rod, and extension spring one end is fixed on the fuselage; The other end is fixed on push rod one end, and the push rod other end withstands on wind blocking door flap inside face.
6. the aerial emergency exit of novel unit according to claim 5 is characterized in that, the said push rod other end is installed a roller.
7. the aerial emergency exit of novel unit according to claim 5 is characterized in that, said initial opener quantity is one or more sets.
8. the aerial emergency exit of novel unit according to claim 1 is characterized in that one or more spring pins are installed at the lintel place on access door, and this spring pin passes lintel and is fixed on the lintel.
9. the aerial emergency exit of novel unit according to claim 2 is characterized in that, is connected with one or more cable wire between said wind blocking door flap inside face and the fuselage.
10. according to claim 1 and the aerial emergency exit of 2 described novel units, it is characterized in that, according to actual conditions one or more turnbuckles or tension link can be set in the middle of the said cable wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110272762.3A CN102390519B (en) | 2011-09-14 | A kind of aerial emergency hatch of novel unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110272762.3A CN102390519B (en) | 2011-09-14 | A kind of aerial emergency hatch of novel unit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102390519A true CN102390519A (en) | 2012-03-28 |
| CN102390519B CN102390519B (en) | 2016-12-14 |
Family
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104058087A (en) * | 2014-07-03 | 2014-09-24 | 天津曙光敬业科技有限公司 | Case opening and closing system of unmanned helicopter |
| CN106043663A (en) * | 2016-06-02 | 2016-10-26 | 江西洪都航空工业集团有限责任公司 | Glass quick-release access cover |
| CN106628196A (en) * | 2017-02-14 | 2017-05-10 | 成都飞机工业（集团）有限责任公司 | Drag parachute housing with combined rear cover for aircraft |
| CN107444607A (en) * | 2017-08-14 | 2017-12-08 | 北京奇正数元科技股份有限公司 | The rotation fast-open type hatchcover of small-sized unmanned plane |
| CN107965218A (en) * | 2017-10-27 | 2018-04-27 | 中航通飞研究院有限公司 | A kind of hatch door quick-release latch mechanism |
| CN108583843A (en) * | 2018-06-21 | 2018-09-28 | 西安飞机工业（集团）有限责任公司 | A kind of Aircraft life-saving Cover of cabin locking mechanism |
| CN109878694A (en) * | 2019-04-03 | 2019-06-14 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft escape hatch baffle device for water and water blocking method |
| CN111502457A (en) * | 2020-04-22 | 2020-08-07 | 中国直升机设计研究所 | Device is put in throwing of hinged door |
| CN113562154A (en) * | 2021-08-25 | 2021-10-29 | 成都飞机工业（集团）有限责任公司 | Opening and closing mechanism of aircraft cabin cover, aircraft cabin mechanism and opening and closing method of aircraft cabin cover |
| CN113607559A (en) * | 2021-07-14 | 2021-11-05 | 武汉航达航空科技发展有限公司 | Static test platform for cockpit door |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104058087B (en) * | 2014-07-03 | 2016-07-06 | 天津曙光敬业科技有限公司 | The casing open-close system of depopulated helicopter |
| CN104058087A (en) * | 2014-07-03 | 2014-09-24 | 天津曙光敬业科技有限公司 | Case opening and closing system of unmanned helicopter |
| CN106043663A (en) * | 2016-06-02 | 2016-10-26 | 江西洪都航空工业集团有限责任公司 | Glass quick-release access cover |
| CN106628196A (en) * | 2017-02-14 | 2017-05-10 | 成都飞机工业（集团）有限责任公司 | Drag parachute housing with combined rear cover for aircraft |
| CN106628196B (en) * | 2017-02-14 | 2023-05-09 | 成都飞机工业（集团）有限责任公司 | Aircraft drag parachute cabin with combined rear cover |
| CN107444607A (en) * | 2017-08-14 | 2017-12-08 | 北京奇正数元科技股份有限公司 | The rotation fast-open type hatchcover of small-sized unmanned plane |
| CN107965218B (en) * | 2017-10-27 | 2022-03-15 | 中航通飞研究院有限公司 | Cabin door quick-release mechanism |
| CN107965218A (en) * | 2017-10-27 | 2018-04-27 | 中航通飞研究院有限公司 | A kind of hatch door quick-release latch mechanism |
| CN108583843A (en) * | 2018-06-21 | 2018-09-28 | 西安飞机工业（集团）有限责任公司 | A kind of Aircraft life-saving Cover of cabin locking mechanism |
| CN108583843B (en) * | 2018-06-21 | 2021-04-20 | 西安飞机工业（集团）有限责任公司 | Aircraft lifeboat hatch cover locking mechanism |
| CN109878694A (en) * | 2019-04-03 | 2019-06-14 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft escape hatch baffle device for water and water blocking method |
| CN111502457A (en) * | 2020-04-22 | 2020-08-07 | 中国直升机设计研究所 | Device is put in throwing of hinged door |
| CN111502457B (en) * | 2020-04-22 | 2021-12-03 | 中国直升机设计研究所 | Device is put in throwing of hinged door |
| CN113607559A (en) * | 2021-07-14 | 2021-11-05 | 武汉航达航空科技发展有限公司 | Static test platform for cockpit door |
| CN113562154A (en) * | 2021-08-25 | 2021-10-29 | 成都飞机工业（集团）有限责任公司 | Opening and closing mechanism of aircraft cabin cover, aircraft cabin mechanism and opening and closing method of aircraft cabin cover |
| CN113562154B (en) * | 2021-08-25 | 2024-03-15 | 成都飞机工业（集团）有限责任公司 | Opening and closing mechanism of aircraft cabin cover, aircraft cabin mechanism and opening and closing method of aircraft cabin cover |
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