CN106081127B - Airplane crash escape aircraft - Google Patents
Airplane crash escape aircraft Download PDFInfo
- Publication number
- CN106081127B CN106081127B CN201610605202.8A CN201610605202A CN106081127B CN 106081127 B CN106081127 B CN 106081127B CN 201610605202 A CN201610605202 A CN 201610605202A CN 106081127 B CN106081127 B CN 106081127B
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- aircraft
- fuselage
- jet engine
- end cap
- engine
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- 230000007246 mechanism Effects 0.000 claims description 15
- 230000001154 acute effect Effects 0.000 claims description 4
- 230000003139 buffering effect Effects 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims 1
- 230000007423 decrease Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 230000009471 action Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 210000004209 hair Anatomy 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 238000013475 authorization Methods 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000010485 coping Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000008034 disappearance Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008569 process Effects 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Emergency Lowering Means (AREA)
Abstract
The invention discloses a kind of airplane crash escape aircrafts, its key points of the technical solution are that including fuselage and the wing that is set at left and right sides of fuselage, sustainer is symmetrically arranged on the wing, the tail end of the fuselage is provided with the jet engine opened after the sustainer is flame-out, and the jet engine provides thrust for aircraft.The present invention solves existing aircraft after engine misses due to being short of power or unpowered, causes aircraft flight attitude unstable, it is difficult to the problem of operating forced landing, jeopardizing the precious life of crew member and passenger.
Description
Technical field
The present invention relates to a kind of aircrafts, more specifically, it is related to a kind of airplane crash escape aircraft.
Background technique
Aircraft, be it is mostly important, a kind of in the modern means of communication, from structurally analyzing, aircraft itself
It should be a kind of highest vehicles of safety coefficient.However, since the operation area of aircraft is high-altitude, unpredictable factor
Very much, it even if all carrying out comprehensively careful detection to aircraft before flight every time, not can avoid still since many factors cause
Airplane crash.And since aircraft runs on high-altitude, once airplane crash occurs, the personnel in aircraft, the especially revenue passenger in passenger plane,
Dredging, pacify and instructing for flight attendant is relied on, can not still make passenger that there is self-saving ability, therefore, once aviation accident, several
Mean that the disappearance of hundreds and thousands of life.
It since invention, has been removed from aircraft to aircraft manufacturing, outside the research that controls and drive flight simulator, for aircraft
The research for how coping with airplane crash also emerges one after another, wherein more mainstream is such as http://www.le.com/ptv/vplay/
Mode disclosed in 24777237.html ch=360_kandsp web video, it may be assumed that in such a way that aircraft is seperated by main cabin with
The other positions of aircraft separate, and to parachute, jet deceleration device is equipped at the top of main cabin, give main cabin bottom setting buffering gas
Capsule, so that main cabin can save the life of the passenger in main cabin in road surface or sea safe falling.For another example Authorization Notice No. is
In technical solution disclosed in the invention patent mandate text of CN1148306C, core concept and video mentioned above
Scheme is approximate, i.e., by aircraft body be made into can be seperated form, seperated scheme is that main body is made into mutually independent shell
It with several cabin units, when causing danger, is blown when the head of aircraft and fuselage, to form a cabin unit in main body
The outlet skidded off, cabin unit skids off main body under the control of brake apparatus with controllable sliding speed, and regards according to being similar to
The mode demonstrated in frequency releases a parachute, buffer air bag etc., so that cabin unit safe landing.
Although above-mentioned technical proposal can be separated by main cabin, and be gradually reduced, if the speed of fuselage flight is larger,
The location status of fuselage can be changed using parachute so that fuselage is unstable, the life of passenger and crew member can be injured
Safety.
The generation of air accident of plane is mostly due to engine misses, stops working in aircraft engine single-shot or double hairs are flame-out,
Engine loses partial power or whole power and causes aircraft flight attitude disorder, it is difficult to control, cause aircraft to fall and make
At.Therefore, if the power slided can be provided for aircraft after aircraft engine is flame-out, aircraft is enable to carry out by sliding
Forced landing, it is thus possible to a possibility that providing existence for birdman and crew member.
Summary of the invention
In view of the deficiencies of the prior art, the present invention intends to provide a kind of airplane crash escape aircraft, starting
After machine is flame-out, additional flying power can be provided for aircraft, stablize aircraft flight attitude, so that forced landing, so that
Passenger and crew member are rescued.
To achieve the above object, the aircraft the present invention provides the following technical scheme that a kind of airplane crash is escaped includes fuselage with
And it is set to the wing at left and right sides of fuselage, sustainer is symmetrically arranged on the wing, spy is: the tail of the fuselage
End is provided with the jet engine opened after the sustainer is flame-out, and the jet engine provides thrust for aircraft.
By using above-mentioned technical proposal, air crash is typically due to sustainer single-shot on wing and double
Hair is flame-out, and aircraft is made to lose whole power or partial power suddenly, and due to losing flying power, aircraft flies
Row becomes uncontrollable, and therefore, it is difficult to control aircraft to force-land.Therefore the jet engine that setting is met an urgent need in the tail portion of aircraft, when
When sustainer loses whole or partial power, the jet engine of emergency is opened, jet engine can provide for aircraft
The power of flight forward can provide certain liter when aircraft flight forward is due to the aerodynamic action of wing for aircraft
Power can ensure slow decline under the action of lift, and the emergency of aircraft is carried out when aircraft can be as regular flight condition at this time
Operation, pilot can be reached by controlling the flight attitude of aircraft and the flying power of jet engine so that forced landing
Purpose, to ensure the precious life of passenger and crew member.
The present invention is further arranged to: the jet engine is located at the inside of the fuselage tail end, sets in the fuselage
It is equipped with the inlet plenum being connected to the jet engine, being evenly arranged on the inlet plenum can be before jet engine starting
The end cap of opening, the end cap close to one end of the tail end of fuselage rotation even fuselage, the end cap be connected with by
In the control mechanism of end cap opening and closing, setting opposite and at an acute angle with the aircraft flight direction after the end cap is opened.
By using above-mentioned technical proposal, jet engine is arranged in the inside of airframe tail end, in order to jet
Engine carries out good gas supply on startup, and inlet plenum is arranged with jet plane, while setting rotation connects on inlet plenum
The end cap connect.When sustainer stops working, end cap is opened by control mechanism, after end cap is opened and is fixed and fuselage side
To setting at an acute angle, end cap can provide guiding role to air-flow at this time, and then air-flow is directed in inlet plenum, into starting
Machine, to ensure that aircraft engine is normally run.
The present invention is further arranged to: the control mechanism includes the connecting rod of the inner surface rotation connection of the end cap, institute
It states link rotatable and is connected with sliding block, the slide bar being arranged in the middle part of the sliding block and the inlet plenum, which slides, to be connected, the sliding block connection
Have for controlling the mobile hydraulic mechanism of the sliding block.
By using above-mentioned technical proposal, hydraulic mechanism is that the movement of sliding block provides power, so that sliding block is mobile, is slided
Block is mobile while driving connecting rod, and then drives end cap mobile, and since end cap and fuselage are rotatablely connected, the movement of connecting rod can
The rotation of end cap is driven, to achieve the purpose that control end cap opening and closing.
The present invention is further arranged to: the inlet plenum is in the fuselage in contraction setting on from head to tail end direction.
By using above-mentioned technical proposal, inlet plenum is arranged to collapsed shape from the head of airframe to tail end, is received
The inlet plenum of contracting shape can generate guiding role to air, so that the air into inlet plenum all enters jet and starts
In machine, be conducive to the normal work of aircraft.
The present invention is further arranged to: the engine is located at below the fuselage, and the jet engine is connected with peace
Bracket is filled, the mounting bracket is connected to the lower section of the fuselage tail end.
By using above-mentioned technical proposal, jet engine is arranged in the lower section of fuselage tail end, and will by bracket
Jet engine is connected on fuselage, and jet engine can not only provide forward power at this time for fuselage, while can produce
Raw certain torque, so that the head of aircraft is upward, head can be avoided aircraft upward and quickly decline, while pass through wing
Adjusting is capable of increasing the falling speed that lift further slows down aircraft.
The present invention is further arranged to: the jet engine is replaced by rocket engine.
By using above-mentioned technical proposal, jet engine is changed to rocket engine, rocket motor can be shorter
Time in, provide biggish power, it is thus possible to high thrust is provided while aircraft sustainer is flame-out, to guarantee to fly
The stabilization of machine state of flight, after losing the power of rocket engine, since flight status is stablized, thus pilot can
By further adjusting the flight attitude of aircraft, aircraft is slided and is force-landed.
The present invention is further arranged to: the rocket engine is connected to the end of the fuselage tail end.
By using above-mentioned technical proposal, since rocket engine does not need the participation of air on startup, because without
The similar structures of air inlet are provided for rocket engine, therefore the installation requirement of rocket engine is smaller, it therefore, can will be fiery
Arrow start frame be mounted on fuselage tail end end inside, not only save space, while the thrust provided for fuselage more collects
In.
The present invention is further arranged to: it is normal for reducing that the front end of the jet engine is connected with streamlined setting
The pod of resistance when flight, the pod are needing to open the jet engine front opening.
By using above-mentioned technical proposal, engine due to jet engine as Emergency use, in normal aircraft
It does not need to be opened or worked during flight, therefore leading for streamlined setting is set in the front end of jet engine
Stream cover, avoids air from entering in jet engine, can not only change the placement environment of jet engine, while streamlined setting
Pod can further decrease jet engine bring drag losses, thus achieve the purpose that save aircraft fuel oil.
The present invention is further arranged to: the bottom of the fuselage is additionally provided at least one for the buffering in forced landing
The inflation unit of the fuselage impact force.
By using above-mentioned technical proposal, when aircraft is when force-land and without good landing environment, pass through setting
Inflation unit is buffered when aircraft is contacted with ground, and aircraft and ground is avoided to generate the collision of hardness, thus bigger
The life security of passenger and crew member are ensured in degree.
The present invention is further arranged to: several drops for hiding setting are also evenly arranged on the fuselage and/or the wing
Fall umbrella.
By using above-mentioned technical proposal, when fuselage flight is to the place with drop conditions, the height of aircraft is controlled
Afterwards, jet engine is closed, the parachute on fuselage and wing is opened simultaneously, so that fuselage freedom of entry falling state, landing
Umbrella can be improved the opposite resistance of aircraft and air, thus into the decrease speed of airframe was once reduced, to ensure machine
Body drops to level point with a lower speed, improves the success rate of landing.
In conclusion the invention has the following advantages: the present invention stops working in aircraft engine single-shot or all puts out
When fiery, power can be provided for the flight of aircraft by starting jet engine or rocket engine, to be the forced landing of aircraft
Offer condition ensures the life security of passenger and crew member to the full extent, avoids the generation of air crash.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of embodiment one；
Fig. 2 is the structural schematic diagram after a dozen beginnings of embodiment lid；
Fig. 3 is the structural schematic diagram of the control mechanism of embodiment one；
Fig. 4 is the structural schematic diagram of embodiment two；
Fig. 5 is the structural schematic diagram that two parachute of embodiment is opened；
Fig. 6 is the structural schematic diagram of embodiment three.
In figure: 1, fuselage；2, wing；3, sustainer；4, jet engine；5, rocket engine；6, tailplane；7,
Vertical tail；8, mounting bracket；9, pod；10, inflation unit；11, parachute；12, elevator；13, rudder；14, it holds
Lid；15, control mechanism；151, connecting rod；152, sliding block；153, slide bar；154, hydraulic mechanism.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
Embodiment one: a kind of airplane crash escape aircraft, as shown in Figure 1, Figure 2 and Figure 3, including fuselage 1, in the two sides of fuselage 1
Wing 2 symmetrically is installed, promising aircraft is symmetrically installed on wing 2, the sustainer 3 of power is provided.While the tail portion of aircraft is also
It is provided with tailplane 6 and vertical tail 7, is respectively arranged with elevator 12 and rudder on tailplane 6 and vertical tail 7
13.Wherein elevator 12 is used to adjust the pitch attitude of aircraft, and rudder 13 is used to adjust the heading of aircraft.
The tail end of airframe 1 is provided with jet engine 4, and jet direction, that is, jet engine 4 of jet engine 4 mentions
The thrust direction of confession is parallel with the direction of fuselage 1.The inside of 1 tail end of fuselage is arranged in jet engine 4, in order to enable engine
It is able to carry out normal gas supply at work, the front end setting of jet engine 4 connects with jet engine 4 in the fuselage 1 of aircraft
Logical inlet plenum is uniformly arranged end cap 14, the one end and fuselage of end cap 14 close to the tail end of fuselage 1 on the outer wall on inlet plenum
1 rotation connection, end cap 14 can be completed to open and close by control mechanism 15 by pilot operator, and control mechanism 15 includes end
The connecting rod 151 of the inner surface rotation connection of lid, connecting rod 151 and sliding block 152 are rotatablely connected, are arranged in the middle part of sliding block 152 and inlet plenum
Slide bar 153 slide connection, sliding block is connected with for controlling the mobile hydraulic mechanism 154 of the sliding block.It will by hydraulic mechanism
End cap 14 open after with the setting at an acute angle of aircraft flight direction, while the inner surface of end cap 14 air-flow can be played guiding make
With entering air-flow in inlet plenum.Simultaneously in order to which the air-flow that will go into inlet plenum is preferably directed to jet engine
In 4, inlet plenum is arranged to contraction-like along air-flow approach axis, to provide guiding role, is being conducive to jet engine 4 just
Often work.
When aircraft engine stops working suddenly, pilot manually controls aircraft, and adjusts the flight attitude of aircraft,
The jet engine 4 of aircraft is opened at the same time, and aircraft engine can provide the power of flight at this time for aircraft, fly at this time
Member's control wing 2 enables wing 2 to provide lift for aircraft is as much as possible, so as to slow down the falling speed of aircraft.
Aircraft is in mover runner state under the power effect of jet engine 44 at this time.In flight course at this moment, pilot's energy
Enough pitch attitudes and heading that aircraft is adjusted by the elevator 12 or rudder 13 of control aircraft.Pilot may be selected
Land place, when aircraft flight to landing place, aircraft can force-land, when aircraft will be beaten when being contacted with ground when forced landing
Inflation unit 10 is opened, to further ensure that the life security of passenger is complete, avoids when reducing forced landing and the impact force on ground
The generation of airplane crash.
Embodiment two: a kind of airplane crash escape aircraft, as shown in Figure 4 and Figure 5, including fuselage 1, it is symmetrical in the two sides of fuselage 1
Wing 2 is installed, promising aircraft is symmetrically installed on wing 2, the sustainer 3 of power is provided.It is also uniform on fuselage 1 and wing 2
It is provided with several parachutes 11 for hiding setting.The tail portion of aircraft is additionally provided with tailplane 6 and vertical tail 7 simultaneously, horizontal
Elevator 12 and rudder 13 are respectively arranged on empennage 6 and vertical tail 7.Wherein elevator 12 is used to adjust the pitching of aircraft
State, rudder 13 are used to adjust the heading of aircraft.
Mounting bracket 8 is installed below the tail end of airframe 1, jet engine 4 is installed in mounting bracket 8, is sprayed
The thrust direction that jet direction, that is, jet engine 4 of gas engine 4 provides is parallel with the direction of fuselage 1.By jet engine 4
The lower section of 1 tail end of fuselage is arranged in, and is connected jet engine 4 on the fuselage 1 by bracket, at this time jet engine 4
Forward power can not only be provided for fuselage 1, while certain torque can be generated, so that the head of aircraft is upward, head
It can be avoided aircraft upward quickly to decline, while lift be capable of increasing by the adjusting of wing 2 and is further slowed down under aircraft
Terminal-velocity degree.In addition, in order to reduce jet engine 4 to the influence with aircraft under regular flight condition, in jet engine 4
Pod 9, the streamlined setting of pod 9, it is thus possible to reduce the resistance of flight so as to save aircraft is arranged in front end
Fuel oil, which can be manually controlled by pilot before jet engine 4 is opened and be opened.It can fly simultaneously
The bottom of machine fuselage 1 is additionally provided in forced landing, the inflation unit 10 for cushion impact forces.
When aircraft engine stops working suddenly, pilot manually controls aircraft, and adjusts the flight attitude of aircraft,
The jet engine 4 that pod 9 opens aircraft at the same time is opened, aircraft engine can provide the dynamic of flight at this time for aircraft
Power, the wing 2 of pilot's control at this time enables wing 2 to provide lift for aircraft is as much as possible, so as to slow down aircraft
Falling speed.Aircraft is in mover runner state under the power effect of jet engine 4 at this time.Flight course at this moment
In, pilot can adjust the pitch attitude and heading of aircraft by the elevator 12 or rudder 13 for controlling aircraft.
Landing place may be selected in pilot, and when aircraft flight to landing place, aircraft can force-land, and opening is hidden in fuselage 1 and machine
Parachute 11 on the wing 2 is used to further decrease the speed of aircraft, when aircraft will open inflation unit 10 when being contacted with ground,
When to reduce forced landing and the impact force on ground, further ensure that the life security of passenger is complete, avoids the generation of airplane crash.
Embodiment three: a kind of airplane crash escape aircraft, as shown in fig. 6, difference is, by jet compared with embodiment two
Engine 4 is changed to rocket engine 5, and rocket engine 5 is connected to the end position of aircraft tail end.
Jet engine 4 is changed to rocket engine 5, rocket motor can provide biggish in a relatively short period of time
Power provides high thrust while aircraft sustainer 3 stops working, and has ensured that aircraft will not reduce suddenly in instantaneous time thrust,
To guarantee the stabilization of flight status, since the working time of rocket engine 5 is shorter, main function is exactly to keep away
Exempt from the flame-out influence for aircraft flight attitude of sustainer 3, after aircraft flight attitude is stablized, pilot can pass through control
Aircraft taxi completes the process of forced landing, to avoid the generation of airplane crash.
The above is only a preferred embodiment of the present invention, protection scope of the present invention is not limited merely to above-mentioned implementation
Example, all technical solutions belonged under thinking of the present invention all belong to the scope of protection of the present invention.It should be pointed out that for the art
Those of ordinary skill for, several improvements and modifications without departing from the principles of the present invention, these improvements and modifications
It should be regarded as protection scope of the present invention.
Claims (7)
- The aircraft 1. a kind of airplane crash is escaped, includes fuselage (1) and the wing (2) being set at left and right sides of fuselage (1), the machine Sustainer (3) are symmetrically arranged on the wing (2), it is characterised in that: the tail end of the fuselage (1) is provided in the sustainer (3) jet engine (4) opened after stopping working, the jet engine (4) provide thrust, the jet engine for aircraft (4) it is located at the inside of the fuselage (1) tail end, is provided with the inlet plenum being connected to the jet engine in the fuselage (1), The end cap (14) of front opening can be started in jet engine (4) by being evenly arranged on the inlet plenum, and the end cap (14) is leaned on One end of the tail end of the nearly fuselage (1) is rotatablely connected the fuselage (1), and the end cap (14) is connected with for the end cap (14) control mechanism (15) opened and closed, setting opposite and at an acute angle with aircraft flight direction after the end cap (14) is opened are described Control mechanism (15) includes the connecting rod (151) with the rotation connection of the inner surface of the end cap (14), and the link rotatable is connected with The slide bar (153) being arranged in the middle part of sliding block (152), the sliding block (152) and the inlet plenum, which slides, to be connected, the sliding block (152) It is connected with for controlling the mobile hydraulic mechanism (154) of the sliding block, end cap (14) has muti-piece and circumferentially uniform along fuselage Distribution forms gap between adjacent end cap (14) after muti-piece end cap (14) is opened.
- The aircraft 2. airplane crash according to claim 1 is escaped, it is characterised in that: the jet engine is located at the fuselage (1) lower section, the jet engine (4) are connected with mounting bracket (8), and the mounting bracket (8) is connected to the fuselage (1) tail The lower section at end.
- The aircraft 3. airplane crash according to claim 1 is escaped, it is characterised in that: the jet engine (4) is replaced by fire Arrow engine (5).
- The aircraft 4. airplane crash according to claim 3 is escaped, it is characterised in that: the rocket engine (5) is connected to described The end of fuselage (1) tail end.
- The aircraft 5. airplane crash according to claim 1 is escaped, it is characterised in that: the front end of the jet engine (4) connects There is the streamlined pod (9) that resistance when for reducing normal flight is set, the pod (9) is needing to open the spray Gas engine (4) front opening.
- The aircraft 6. airplane crash according to claim 1 is escaped, it is characterised in that: the bottom of the fuselage (1) be additionally provided with to Few one for buffering the inflation unit (10) of the fuselage (1) impact force in forced landing.
- The aircraft 7. airplane crash according to claim 1 is escaped, it is characterised in that: on the fuselage (1) and/or the wing (2) Also it is evenly arranged with several parachutes (11) for hiding setting.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610605202.8A CN106081127B (en) | 2016-07-27 | 2016-07-27 | Airplane crash escape aircraft |
| PCT/CN2017/090452 WO2018019074A1 (en) | 2016-07-27 | 2017-06-28 | Escape aircraft in air crash |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610605202.8A CN106081127B (en) | 2016-07-27 | 2016-07-27 | Airplane crash escape aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106081127A CN106081127A (en) | 2016-11-09 |
| CN106081127B true CN106081127B (en) | 2018-12-25 |
Family
ID=57478744
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610605202.8A Expired - Fee Related CN106081127B (en) | 2016-07-27 | 2016-07-27 | Airplane crash escape aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN106081127B (en) |
| WO (1) | WO2018019074A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081127B (en) * | 2016-07-27 | 2018-12-25 | 冯政尧 | Airplane crash escape aircraft |
| CN108974332A (en) * | 2018-08-08 | 2018-12-11 | 张延林 | The emergency method of air accident of plane |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB924078A (en) * | 1961-12-22 | 1963-04-24 | Rolls Royce | Aircraft |
| FR1499853A (en) * | 1963-06-04 | 1967-11-03 | Matra Engins | Mixed propulsion aircraft |
| US5480107A (en) * | 1994-04-11 | 1996-01-02 | Bacon; Richard J. | 3x multi-engine jet configuration |
| CN2375561Y (en) * | 1998-04-23 | 2000-04-26 | 王秉琨 | Aircraft falling protector |
| FR2943039B1 (en) * | 2009-03-12 | 2012-09-28 | Airbus France | PLANE TANK-TAIL AND REVERSE ENGINE. |
| CN102582836A (en) * | 2012-03-02 | 2012-07-18 | 浙江金中机电科技有限公司 | Airplane with emergency landing device in fault |
| CN103910060A (en) * | 2013-01-09 | 2014-07-09 | 赵润生 | Combined-type push/lift airplane |
| CN203612198U (en) * | 2013-11-05 | 2014-05-28 | 桂林鑫鹰电子科技有限公司 | Front-pull rear-push type multifunctional fixed-wing unmanned aerial vehicle |
| CN105620764A (en) * | 2016-02-16 | 2016-06-01 | 李和坤 | Aircraft with rocket thruster |
| CN106081127B (en) * | 2016-07-27 | 2018-12-25 | 冯政尧 | Airplane crash escape aircraft |
-
2016
- 2016-07-27 CN CN201610605202.8A patent/CN106081127B/en not_active Expired - Fee Related
-
2017
- 2017-06-28 WO PCT/CN2017/090452 patent/WO2018019074A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| WO2018019074A1 (en) | 2018-02-01 |
| CN106081127A (en) | 2016-11-09 |
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