CN105947223A - Split airplane - Google Patents
Split airplane Download PDFInfo
- Publication number
- CN105947223A CN105947223A CN201610288565.3A CN201610288565A CN105947223A CN 105947223 A CN105947223 A CN 105947223A CN 201610288565 A CN201610288565 A CN 201610288565A CN 105947223 A CN105947223 A CN 105947223A
- Authority
- CN
- China
- Prior art keywords
- security module
- split type
- cabin
- safety
- type aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/18—Flotation gear
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/32—Severable or jettisonable parts of fuselage facilitating emergency escape
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/12—Ejectable capsules
Abstract
The invention provides a split airplane, and relates to the field of an aircraft. The split airplane comprises an airplane body and a safety cabin, wherein the safety cabin is positioned in the airplane body, and comprises a cabin body; the cabin body is hollow; the airplane body is detachably connected with the cabin body of the safety cabin; the tail part of the airplane body is provided with a safety cabin ejecting opening; an ejecting device is also arranged in the airplane body, and is used for ejecting the safety cabin; chairs are arranged inside the cabin body; and parachutes are arranged on the top of the safety cabin. The split airplane provided by the invention has the advantage that the technical problem of great casualties after aircraft accidents in the prior art is solved.
Description
Technical field
The present invention relates to vehicle technology field, especially relate to a kind of split type aircraft.
Background technology
Passenger plane broad sense i.e. civil aircraft.Civil aircraft refers to the aircraft of all non-military uses.The people
It is also referred to as aircarrier aircraft with aircraft.By respective purposes, civil aircraft is divided into again execution commercial airliners
The airline aircraft flown and the big class of general aviation aircraft two being used for General Aviation.Propeller is had to fly
Machine and jet plane point.Propeller history aircraft, including piston-propeller driver aircraft and turbine
Propellor aircraft, aeroengine is piston-propeller, and this is the most original power form.
It utilizes the rotation of propeller to be promoted after machine by air, before promoting aircraft by means of its counteracting force
Enter.Revolution speed of propeller is the highest, then flight speed is the fastest.Jet plane, including turbojet
Formula and fanjet plane.The advantage of this type is simple in construction, and speed is fast, one
As time scooter 500-600 mile；Fuel cost is saved, and useful load is big, typically can carrying
400-500 people or 100 tons of goods.
Passenger plane narrow sense refers to airline carriers of passengers, is that build is compared with collective's airline big, that handling capacity of passengers is more
Instrument, and international business flight domestic for dealing.Airline carriers of passengers is typically runed by airline.
The airline carriers of passengers of handling capacity of passengers maximum is the A380 that Airbus SAS produces, three grades of main cabins of standard
Layout is 555.
The general handling capacity of passengers of existing passenger plane is the biggest, once has an accident, such as Ma Hang
The air crash that MH370 etc. are famous, often results in substantial amounts of casualties.Passenger's most cases
Under cannot survive.
Based on this, the invention provides a kind of split type aircraft to solve above-mentioned technical problem.
Summary of the invention
It is an object of the invention to provide a kind of split type aircraft, to solve prior art exists
Aviation accident after the bigger technical problem of casualties.
The split type aircraft that the present invention provides, including fuselage and Security Module, described Security Module is positioned at
In described fuselage；Described fuselage removably connects with described Security Module；Described afterbody is arranged
There is Security Module ejection door；Being additionally provided with device for ejecting in described fuselage, described device for ejecting is used for
Eject described Security Module；
Described Security Module is internally provided with seat；
Described Security Module top is provided with parachute.
Optionally, described Security Module both sides are provided with air bag.
It is provided with air bag, is in order to when described Security Module falls into nautical mile, Security Module can float over
On sea, seabed will not be sunk to.So, the passenger in Security Module and crew member just can be hard
Hold the arrival of rescue personnel.Described air bag preferably uses automatic inflatable air sac, Security Module bullet
After going out, air bag automatic inflating expands, and holds up by Security Module.
Optionally, described Security Module be provided around buffer unit.
It is provided around buffer unit at described Security Module, be described in order to further slow down
The Security Module impact when landing, is greatly reduced impact force, thus more effectively
The safety of personnel in protection cabin.
Optionally, described buffer unit uses and expands resistance to compression air bag.
Expand resistance to compression air bag lighter in weight, it is possible to alleviate the overall burden of aircraft, and, bullet
Property relatively big, anti-pressure ability is strong, not cracky, the most durable, thus, it is possible to bear
The pressure that described Security Module is bigger, also will not bring heavier burden.
Optionally, it is additionally provided with spring and sponge bottom described Security Module.
It is provided around spring and sponge at described Security Module, is to further slow down institute
State the Security Module impact when landing, impact force be greatly reduced, thus more effectively
The safety of personnel in protection cabin, ground.Preferably, sponge and spring are arranged on inside Security Module, peace
Full bilge portion is provided with cavity, fills cushion, so do not interfere with the bullet of Security Module in cavity
Going out, sponge and spring etc. do not come off yet.
Optionally, it is additionally provided with luggage storeroom in described Security Module.
In described Security Module, also set up luggage storeroom, be the wealth such as luggage in order to protect passenger
Produce safety, it is to avoid passenger loses carry-on valuables etc..
Optionally, it is provided with safety door at described Security Module ejection door.
Safety door is in closed state usually, just opens when aviation accident, is used for ejecting safety
Cabin.Described safety door can use the most all with the rear opening safety door of transporter, passes through circuit
Controlled by the central processing system of aircraft, automatically open up.
Optionally, described device for ejecting is stage clip, and described stage clip is positioned at described fuselage and described
Between the front end of Security Module；Described Security Module and described fuselage are fixed by electric magnet.
Substantial amounts of big elastic force stage clip can be set between the top of Security Module and fuselage, usually locate
In compressive state, when aviation accident, electric magnet is controlled automatically to disconnect by central processing unit, peace
Full cabin disconnects with the connection of fuselage, and at this moment, Security Module is ejected by a large amount of stage clips.Certainly, it is possible to
To use device for ejecting otherwise, such as, the aircraft device for ejecting being applied on aircraft carrier,
Just can be applicable to this, it is provided that bigger elastic force, Security Module is ejected.
Optionally, it is provided with oxygen survival kit in described Security Module.
Oxygen survival kit provides oxygen when aviation accident, prevents passenger from phenomenon of suffocating occur,
Life threatening safety.
Optionally, luminaire and power supply, described power supply and photograph it are provided with in described Security Module
Bright equipment electrically connects.
By described luminaire, it is ensured that the illumination in Security Module, bring light and the heart for passenger
In comfort.
The described split type aircraft that the present invention provides, including fuselage and Security Module, airframe structure with
Existing fuselage is roughly the same, but is changed over by cab portion split type, described safe freight space
In described fuselage；Described fuselage removably connects with described Security Module；Fuselage interior arranges solid
Determine device, fix Security Module.Being additionally provided with device for ejecting in described fuselage, described ejection fills
Put for ejecting described Security Module, and described Security Module top is provided with parachute.To fly
The passenger cabin of machine and fuselage are designed to split type, safety problem occurs in aircraft when, individually set
Vertical Security Module can eject from fuselage interior.Seat it is provided with in Security Module, intact at aircraft
Time, passenger is in Security Module, normally completes flight journey；When aviation accident, Cheng Kesui
Security Module to eject together outside aircraft, ensure passenger and the safety of crew member to greatest extent.
Parachute is set at the top of described Security Module, after Security Module ejects, is positioned at described Security Module
The parachute at top is opened, make Security Module slowly from airborne, thus avoid because falling
The shock caused soon, it is to avoid accident occur in passenger and crew member.
The described split type aircraft that the present invention provides, changes intrinsic airplane design thinking, will
The passenger cabin of passenger and whole fuselage design in split, when there is accident in aircraft, the most just
Aircraft ejects, and farthest ensure that the safety of passenger and crew member.
Based on this, the present invention, than original technology, has and farthest protects passenger and take advantage of
The advantage of business personal security.
Accompanying drawing explanation
In order to be illustrated more clearly that the specific embodiment of the invention or technical side of the prior art
Case, will make letter to the accompanying drawing used required in detailed description of the invention or description of the prior art below
Singly introduce, it should be apparent that, the accompanying drawing in describing below is some embodiments of the present invention,
For those of ordinary skill in the art, on the premise of not paying creative work, also may be used
To obtain other accompanying drawing according to these accompanying drawings.
The structural representation front view of the split type aircraft that Fig. 1 provides for the embodiment of the present invention；
Schematic diagram after the Security Module ejection of the split type aircraft that Fig. 2 provides for the embodiment of the present invention.
Reference:
1-fuselage；2-Security Module；3-Security Module ejection door；
4-parachute；5-air bag.
Detailed description of the invention
Below in conjunction with accompanying drawing, technical scheme is clearly and completely described, aobvious
So, described embodiment is a part of embodiment of the present invention rather than whole embodiments.
Based on the embodiment in the present invention, those of ordinary skill in the art are not making creative work
The every other embodiment obtained under premise, broadly falls into the scope of protection of the invention.
In describing the invention, it should be noted that term " " center ", " on ", D score,
Orientation or the position of the instruction such as "left", "right", " vertically ", " level ", " interior ", " outward " are closed
System, for based on orientation shown in the drawings or position relationship, is for only for ease of the description present invention and Jian
Change describe rather than instruction or the hint device of indication or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.Additionally,
Term " first ", " second ", " the 3rd " are only used for describing purpose, and it is not intended that indicate
Or hint relative importance.
In describing the invention, it should be noted that unless otherwise clearly defined and limited,
Term " is installed ", " being connected ", " connection " should be interpreted broadly, for example, it may be fixing even
Connect, it is also possible to be to removably connect, or be integrally connected；Can be to be mechanically connected, it is also possible to
It it is electrical connection；Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, can concrete feelings
Condition understands above-mentioned term concrete meaning in the present invention.
Embodiment one
The structural representation front view of the split type aircraft that Fig. 1 provides for the embodiment of the present invention；Fig. 2
For the schematic diagram after the Security Module ejection of the split type aircraft of embodiment of the present invention offer.Such as figure
Shown in 1-2, provide a kind of split type aircraft, described split type aircraft bag in the present embodiment
Including fuselage 1 and Security Module 2, described Security Module 2 is positioned at described fuselage 1；Described Security Module
2 include nacelle, described nacelle hollow；Described fuselage 1 afterbody is provided with Security Module ejection door 3；
Being additionally provided with device for ejecting in described fuselage 1, described device for ejecting is used for ejecting described Security Module
2；Described nacelle is preferably cylindrical shape, and columnar nacelle sidewall is provided with landing gate,
For passenger's boarding；The front end of nacelle is provided with captain room door, connects with captain room；The two
Men Junke is airtight；Described fuselage 1 removably connects with the nacelle of described Security Module 2；Usually shape
It is in stationary state under state, disconnects when aircraft meets accident；
Described nacelle is internally provided with seat；
Described Security Module 2 top is provided with parachute 4.
The described split type aircraft that the present invention provides, designs composition by passenger cabin and the fuselage 1 of aircraft
Body formula, safety problem occurs in aircraft when, the Security Module 2 individually set up can be from fuselage
1 internal ejection.Being provided with seat in Security Module 2, when aircraft is intact, passenger is in safety
In cabin 2, normally complete flight journey；When aviation accident, passenger is along with Security Module 2 together
Outside ejection aircraft, ensure passenger and the safety of crew member to greatest extent.At described Security Module
The top of 2 arranges parachute 4, after Security Module 2 ejects, is positioned at described Security Module 2 top
Parachute 4 open, make Security Module 2 slowly from airborne, from
The described split type aircraft that the present invention provides, changes intrinsic airplane design thinking, will
The passenger cabin of passenger and whole fuselage 1 design in split, when accident occurs in aircraft, the most just
Aircraft is ejected, farthest ensure that the safety of passenger and crew member.
Based on this, the present invention, than original technology, has and farthest protects passenger and take advantage of
The advantage of business personal security.
After the Security Module of the split type aircraft provided for the embodiment of the present invention such as Fig. 2, Fig. 2 ejects
Schematic diagram.In the alternative of the present embodiment, described Security Module 2 both sides are provided with air bag 5.
It is provided with air bag 5, is in order to when described Security Module 2 falls into nautical mile, Security Module 2 energy
Enough float across the sea, seabed will not be sunk to.So, the passenger in Security Module 2 and crew member
Just can adhere to the arrival of rescue personnel.Described air bag 5 preferably uses automatic inflating gas
Capsule, after Security Module 2 ejects, air bag 5 automatic inflating expands, and is held up by Security Module 2.From
Move aerating gasbag response speed quickly, while the chemical reaction of intimate blast quickly occurs,
The most harmless gas based on nitrogen can be produced, by airbag aeration to full state.
In the alternative of embodiment, described Security Module 2 be provided around buffer unit.
It is provided around buffer unit at described Security Module 2, is to further slow down institute
State the Security Module 2 impact when landing, impact force is greatly reduced, thus more has
The safety of personnel in protection cabin, effect ground.
Further, described buffer unit uses and expands resistance to compression air bag.
Expand resistance to compression air bag lighter in weight, it is possible to alleviate the overall burden of aircraft, and, bullet
Property relatively big, anti-pressure ability is strong, not cracky, the most durable, thus, it is possible to bear
The pressure that described Security Module 2 is bigger, also will not bring heavier burden.And, air bag energy
Enough cost-effective, custom-made by size, process relatively simple, make protection more perfect.
Further, it is additionally provided with spring and sponge bottom described Security Module 2.
It is provided around spring and sponge at described Security Module 2, is to further slow down
The described Security Module 2 impact when landing, is greatly reduced impact force, thus more
The safety of personnel in protection cabin effectively.Preferably, sponge and spring are arranged on Security Module 2
Inside, is provided with cavity bottom Security Module 2, fill cushion, so do not interfere with in cavity
The ejection of Security Module 2, sponge and spring etc. do not come off yet.
In the alternative of the present embodiment, in described Security Module 2, it is additionally provided with luggage storeroom.
In described Security Module 2, also set up luggage storeroom, be the luggage etc. in order to protect passenger
Property safety, it is to avoid passenger loses carry-on valuables etc..
In the alternative of the present embodiment, at described Security Module ejection door 3, it is provided with safety door.
Safety door is in closed state usually, just opens when aviation accident, is used for ejecting safety
Cabin 2.Described safety door can use the most all with the rear opening safety door of transporter, by electricity
Road is controlled by the central processing system of aircraft, automatically opens up.
In the alternative of the present embodiment, described device for ejecting is stage clip, and described stage clip is positioned at institute
State between the front end of fuselage 1 and described Security Module 2；Described Security Module 2 and described fuselage 1
Fixed by electric magnet.These electric magnet are preferably mounted at the inside of fuselage, around described peace
All sides in full cabin, arrange multi-turn battery ferrum.These battery ferrum are electrically connected with the center processor of aircraft
Connecing, acceptor center processor controls, it is possible to when aviation accident, automatically disconnect.
Substantial amounts of big elastic force stage clip can be set between the top of Security Module 2 and fuselage 1, flat
Often being in compressive state, when aviation accident, electric magnet is controlled automatically to disconnect by central processing unit,
Security Module 2 disconnects with the connection of fuselage 1, and at this moment, Security Module 2 is ejected by a large amount of stage clips.When
So, it would however also be possible to employ device for ejecting otherwise, such as, the aircraft bullet being applied on aircraft carrier
Go out device, so that it may Security Module 2, here, provide bigger elastic force, is ejected by application.Certainly,
Can also use other device for ejecting being suitable for, these designs are all at the protection domain of the application
In.
In the alternative of the present embodiment, in described Security Module 2, it is provided with oxygen survival kit.
Oxygen survival kit provides oxygen when aviation accident, prevents passenger from phenomenon of suffocating occur,
Life threatening safety.
In the alternative of the present embodiment, in described Security Module 2, it is provided with luminaire and electricity
Source, described power supply and luminaire electrical connection.
By described luminaire, it is ensured that the illumination in Security Module 2, for passenger bring bright and
Comfort at heart.
It is last it is noted that various embodiments above is only in order to illustrate technical scheme,
It is not intended to limit；Although the present invention being described in detail with reference to foregoing embodiments,
It will be understood by those within the art that: it still can be to described in foregoing embodiments
Technical scheme modify, or the most some or all of technical characteristic carried out equivalent replace
Change；And these amendments or replacement, do not make the essence of appropriate technical solution depart from the present invention each
The scope of embodiment technical scheme.
Claims (10)
1. a split type aircraft, it is characterised in that include fuselage and Security Module, described peace
Full freight space is in described fuselage；Described Security Module includes nacelle, described nacelle hollow；Described machine
Body removably connects with the nacelle of described Security Module；Described afterbody is provided with Security Module and ejects
Mouthful；Being additionally provided with device for ejecting in described fuselage, described device for ejecting is used for ejecting described safety
Cabin；Described nacelle is internally provided with seat；
Described Security Module top is provided with parachute.
Split type aircraft the most according to claim 1, it is characterised in that described safety
Both sides, cabin are provided with air bag.
Split type aircraft the most according to claim 1, it is characterised in that described safety
Cabin be provided around buffer unit.
Split type aircraft the most according to claim 3, it is characterised in that described buffering
Device uses and expands resistance to compression air bag.
Split type aircraft the most according to claim 3, it is characterised in that described safety
Bilge portion is additionally provided with spring and sponge.
Split type aircraft the most according to claim 1, it is characterised in that described safety
Luggage storeroom it is additionally provided with in cabin.
Split type aircraft the most according to claim 1, it is characterised in that described safety
It is provided with safety door at the ejection door of cabin.
Split type aircraft the most according to claim 1, it is characterised in that described ejection
Device is stage clip, and described stage clip is between the front end of described fuselage and described Security Module；Described
Security Module and described fuselage are fixed by electric magnet.
Split type aircraft the most according to claim 1, it is characterised in that described safety
Oxygen survival kit it is provided with in cabin.
10. according to the split type aircraft described in any one of claim 1-9, it is characterised in that
Luminaire and power supply, described power supply and luminaire electrical connection it is provided with in described Security Module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610288565.3A CN105947223A (en) | 2016-05-05 | 2016-05-05 | Split airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610288565.3A CN105947223A (en) | 2016-05-05 | 2016-05-05 | Split airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105947223A true CN105947223A (en) | 2016-09-21 |
Family
ID=56913806
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610288565.3A Pending CN105947223A (en) | 2016-05-05 | 2016-05-05 | Split airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105947223A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910056A (en) * | 2018-08-09 | 2018-11-30 | 雷子墨 | A kind of aircraft with separable pressurized cabin |
| IT202100005921A1 (en) * | 2021-03-12 | 2022-09-12 | Alessandro Cornali | AIRPLANE INCLUDING A PASSENGER CAPSULE |
| EP4098558A1 (en) * | 2021-06-02 | 2022-12-07 | Du, Di | Aircraft safety lifesaving system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2177441C2 (en) * | 2000-03-22 | 2001-12-27 | Халидов Гамид Юсупович | Method of emergency evacuation of passengers from aircraft |
| DE20301271U1 (en) * | 2003-01-28 | 2003-05-08 | Meyer Michael | Passenger aircraft interchange section has an inner area which is constructed separately and a passenger interchange cabin |
| US20090072077A1 (en) * | 2007-09-18 | 2009-03-19 | Chui Wen Chiu | High passenger capacity airplane |
| CN202400290U (en) * | 2011-10-14 | 2012-08-29 | 王晓进 | Plane distress separate cabin escape device |
| CN205098484U (en) * | 2015-10-26 | 2016-03-23 | 王雅馨 | Aircraft launches system of fleing |
-
2016
- 2016-05-05 CN CN201610288565.3A patent/CN105947223A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2177441C2 (en) * | 2000-03-22 | 2001-12-27 | Халидов Гамид Юсупович | Method of emergency evacuation of passengers from aircraft |
| DE20301271U1 (en) * | 2003-01-28 | 2003-05-08 | Meyer Michael | Passenger aircraft interchange section has an inner area which is constructed separately and a passenger interchange cabin |
| US20090072077A1 (en) * | 2007-09-18 | 2009-03-19 | Chui Wen Chiu | High passenger capacity airplane |
| CN202400290U (en) * | 2011-10-14 | 2012-08-29 | 王晓进 | Plane distress separate cabin escape device |
| CN205098484U (en) * | 2015-10-26 | 2016-03-23 | 王雅馨 | Aircraft launches system of fleing |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910056A (en) * | 2018-08-09 | 2018-11-30 | 雷子墨 | A kind of aircraft with separable pressurized cabin |
| IT202100005921A1 (en) * | 2021-03-12 | 2022-09-12 | Alessandro Cornali | AIRPLANE INCLUDING A PASSENGER CAPSULE |
| WO2022189877A1 (en) * | 2021-03-12 | 2022-09-15 | Cornali Alessandro | Airplane comprising a passenger pod |
| EP4098558A1 (en) * | 2021-06-02 | 2022-12-07 | Du, Di | Aircraft safety lifesaving system |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160921 |
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| RJ01 | Rejection of invention patent application after publication |