CN115027679A

CN115027679A - Safe landing aircraft

Info

Publication number: CN115027679A
Application number: CN202210715770.9A
Authority: CN
Inventors: 宋学恭
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-06-23
Filing date: 2022-06-23
Publication date: 2022-09-09

Abstract

The invention relates to a safe landing airplane, which is characterized in that: the aircraft comprises an aircraft nose, a first passenger cabin and a second passenger cabin, wherein the economic passenger cabin and the aircraft tail are designed into a whole, the rear end of the first passenger cabin, the front end of the business passenger cabin, the rear end of the business passenger cabin and the front end of the economic passenger cabin are designed to be connected in a clamping manner, a cockpit fixing frame is in a circular sphere shape, cockpit gyroscope balancers are symmetrically arranged and installed on the upper part, the lower part, the front part, the rear part, the left part and the right part of the inner side wall of the circular sphere, a parachute catapult and a parachute are arranged on the aircraft, the electric propeller thruster catapult comprises an electric propeller thruster, an air bag bin and an air bag, wherein an operating system display screen, a remote controller, a pedal type safe electric sound alarm power button and an impact electric shock rod power button are arranged and installed in a cockpit, the impact electric shock rod catapult and the impact electric shock rod are arranged and installed on the left side, the right side and the back of a driver seat, and an electric sound alarm, an operating system remote controller and a display screen are arranged and installed in a passenger cabin.

Description

Safe landing aircraft

Technical Field

The invention belongs to the technical field of airplanes, and particularly relates to a safe landing airplane.

Background

The airplane is a carrier flying at high altitude, and does not stick to the sky and the ground, but the airplane has accidents in the actual flying process, and once the accidents happen, the tragic consequence of death and death of the airplane can be caused. The invention relates to a safe landing airplane, which is technically improved on the basis of the existing airplane to achieve the purpose of safe landing of the airplane and is applied to air transportation airplanes.

Disclosure of Invention

A safe landing aircraft comprises an aircraft nose, aircraft-head and other cabins, an aircraft commercial cabin, an aircraft economic cabin, an aircraft tail, an aircraft cockpit fixing frame, an aircraft cockpit gyroscope balancer sliding ball, an aircraft cockpit guide rail, an aircraft cockpit door, an aircraft operating system display screen, an aircraft operating system keyboard, an aircraft parachute ejector, an aircraft parachute, an aircraft electric propeller ejector, an aircraft airbag bin, an aircraft airbag, an aircraft pedal type safe electroacoustic alarm power button, an aircraft safe electroacoustic alarm, an aircraft pedal type counterattack electric shock rod power button, an aircraft counterattack electric shock rod ejector, an aircraft counterattack electric shock rod, an aircraft cabin operating system remote controller and an aircraft cabin display screen.

The rear end of the aircraft nose of the safe landing aircraft and the front end of the passenger cabin such as the aircraft nose are designed to be fixedly connected integrally. The aircraft comprises an aircraft cabin, an aircraft commercial cabin, an aircraft tail, a front end of the aircraft commercial cabin, a rear end of the aircraft commercial cabin and the aircraft tail are designed to be connected in a locking mode, and the rear end of the aircraft commercial cabin and the aircraft tail are designed to be fixedly connected into a whole.

The fixed frame of the safe landing aircraft cockpit is arranged at the upper part in front of an aircraft nose and is in a circular sphere shape, an aircraft cockpit gyroscope balancer is arranged and mounted at the symmetrical part of the upper part, the lower part, the front part, the rear part, the left part and the right part of the inner side wall of the circular sphere, an aircraft cockpit gyroscope balancer sliding ball is arranged and mounted on the aircraft cockpit gyroscope balancer, an aircraft cockpit guide rail is arranged and mounted around the outer side of the aircraft cockpit, the aircraft cockpit gyroscope balancer sliding ball is buckled and connected with an aircraft cockpit guide rail guide groove, and the aircraft cockpit can be always kept in a parallel state under the action of the aircraft cockpit gyroscope balancer.

According to the safe landing aircraft in the technical scheme, the cabin door of the cockpit is arranged at the lower position on the left side of the cockpit of the aircraft, so that an aircraft pilot and a crew member can get in and out of the cockpit.

The display screen of the safe landing aircraft operating system and the keyboard of the aircraft operating system are arranged in an aircraft cockpit, and the aircraft operating system acquires information through an external multi-directional camera of the aircraft and an external multi-directional camera of the aircraft cockpit, and the aircraft pilot operates the keyboard of the aircraft operating system to execute flight tasks after the information is displayed on the display screen of the aircraft operating system.

The safe parachute catapult and the airplane parachute in the technical scheme are used for the airplane to carry out flight tasks in the air, when accidents happen and the airplane cannot fly normally, in order to avoid airplane crash, airplane pilots, crew members, cabin crew members and passenger casualties, the airplane pilots operate the keyboard of an airplane operating system, and the airplane parachute catapult is popped out and opened to support the airplane to land safely.

In the technical scheme of the safe landing aircraft, the aircraft electric propeller thruster catapult and the aircraft electric propeller thruster meet high buildings and densely populated areas in the process of landing the aircraft by supporting an aircraft parachute, and an aircraft driver pops the aircraft electric propeller thruster by the aircraft electric propeller thruster catapult through an aircraft operating system keyboard to open and rotate to generate thrust to push the aircraft to a safe zone for landing.

According to the safe landing aircraft in the technical scheme, the aircraft airbag bin and the aircraft airbag are used for preventing aircraft submergence accidents caused by the fact that aircraft drivers, crew members, cabin crew members and passengers are injured and killed when meeting sea, river, lake and water areas in the process that the aircraft parachute supports the aircraft to land, and the aircraft airbag bin and the aircraft airbag are popped up to generate buoyancy so that the aircraft can float on the water surface and cannot sink. Meanwhile, the airplane driver operates the keyboard of the airplane operating system to enable the ejector of the electric propeller of the airplane to eject the electric propeller of the airplane to open and rotate to generate thrust to push the airplane to drive to the shore and wait for rescue. The aircraft airbag in the technical scheme of the invention generates buoyancy when the aircraft lands in the water areas of the sea, the river, the lake and the river, so that the aircraft is not submerged, and simultaneously, the airbag can play a role in buffering when the landing gear of the aircraft breaks down.

The pedal type safe electroacoustic alarm power button for safe landing aircraft and the safe electroacoustic alarm for aircraft in the technical proposal of the invention are characterized in that under the condition that the aircraft pilot is hijacked by illegal criminals and terrorists, the upper part of the body of the airplane pilot is controlled, the upper part of the body can not be used for pushing the keyboard of the airplane operating system by hands to send alarms to each passenger cabin of the airplane, the airplane pilot tramples the power button of the pedal type safety electroacoustic alarm arranged below the keyboard of the airplane operating system to send alarms to each passenger of the airplane, so that crew members of the airplane, crew members of each passenger cabin of the airplane and passengers are ready for coping, meanwhile, the plane pilot tramples the pedal type electric shock rod power button, the counterattack electric shock rod ejectors arranged on the left side, the right side and the back of the plane pilot seat eject the counterattack electric shock rod, and the electric shock criminals and terrorists hijacking the plane catch the electric shock rod.

The invention relates to a safe landing airplane which is designed to land in three landing modes.

The invention is applicable to air transport aircraft.

Drawings

FIG. 1 is a schematic view of the overall structure of a safe landing aircraft

FIG. 2 schematic cross-sectional view of an aircraft cockpit

FIG. 3 schematic illustration of an interior arrangement of an aircraft passenger cabin

FIG. 4 is a schematic diagram of the aircraft parachute catapult ejecting and opening the parachute when the aircraft is in the air to perform the flight mission and meets the accident aircraft integral landing

FIG. 5 is a schematic diagram of an aircraft electric propeller ejector popping up and opening an electric propeller when an aircraft performs a flight mission in the air and meets an accident aircraft integral landing

FIG. 6 is a schematic diagram of the airbag cabin of the airplane to open the airbag to pop up when the airplane is in integral landing in case of accident when the airplane is in flight

FIG. 7 is a schematic diagram of an aircraft nose, an aircraft nose and other cabin parachute ejectors ejecting and opening a parachute when the aircraft performs a flight task in the air and meets an accident aircraft split type landing

FIG. 8 is a schematic diagram of an aircraft nose, an aircraft nose and other cabin electric propeller ejectors ejecting and opening electric propeller ejectors when an aircraft performs a flight task in the air and meets an accident aircraft split landing

FIG. 9 is a schematic diagram of airbag popping-up after airbag opening in airbag bins of passenger cabins such as aircraft heads and aircraft heads when an aircraft is subjected to split landing in case of accident when the aircraft performs flight task in the air

FIG. 10 is a schematic diagram of an aircraft commercial cabin parachute catapult popping up and opening a parachute when the aircraft performs a flight task in the air and meets an accident aircraft split type landing

FIG. 11 is a schematic diagram of an aircraft commercial cabin electric propeller ejector popping up and opening an electric propeller when an aircraft performs a flight task in the air and meets an accident aircraft split landing

FIG. 12 is a schematic diagram of airbag popping-up of airbag cabin of commercial cabin of airplane when the airplane performs flight task in the air and meets accident airplane split landing

FIG. 13 is a schematic diagram of an aircraft economic cabin and an aircraft tail parachute catapult ejecting and opening a parachute when the aircraft performs a flight task in the air and meets an accident aircraft split type landing

FIG. 14 is a schematic diagram of an economic cabin of an airplane and an electric propeller ejector of the tail of the airplane ejecting and opening the electric propeller when the airplane performs a flight task in the air and meets an accident and the airplane is in split landing

FIG. 15 is a schematic diagram of the economic passenger cabin of the airplane and the airbag popping-up of the airbag after the airbag cabin of the tail of the airplane when the airplane performs the flight task in the air and meets the accident and the airplane is in split landing

In the figure, 1, an aircraft nose, 2, an aircraft head and other cabins, 3, an aircraft business cabin, 4, an aircraft economic cabin, 5, an aircraft tail, 6, an aircraft cockpit fixing frame, 7, an aircraft cockpit gyroscope balancer, 8, an aircraft cockpit gyroscope balancer sliding ball, 9, an aircraft cockpit, 10, an aircraft cockpit guide rail, 11, an aircraft cockpit door, 12, an aircraft operating system display screen, 13, an aircraft operating system keyboard, 14, an aircraft parachute catapult, 15, an aircraft parachute, 16, an aircraft electric propeller thruster, 17, an aircraft electric propeller thruster, 18, an aircraft airbag cabin, 19, an aircraft airbag, 20, an aircraft pedal type safety electroacoustic alarm power button, 21, an aircraft safety electroacoustic alarm, 22, an aircraft pedal type counterattack electric shock rod power button, 23, an aircraft counterattack electric shock rod catapult, 23, a aircraft counterattack electric shock rod catapult, a vehicle air bag cabin, 19, an aircraft airbag, 20, an aircraft pedal type safety electroacoustic alarm power button, 21, an aircraft safety electroacoustic alarm, 22, an aircraft pedal type counterattack electric shock rod power button, 23, a vehicle and a vehicle, 24. The airplane is used for counterattack electric shock rods 25, airplane cabin operation system remote controllers 26 and airplane cabin display screens.

Detailed Description

The first form of landing is: the airplane normally performs flying tasks in the air and can land at a destination airport according to the existing landing form.

The second form of landing is: when the airplane carries out flying tasks in the air, the airplane can not land at a destination airport according to the existing landing form after an accident happens, and the airplane can land integrally by adopting a second landing form under the condition that the integral weight of the airplane does not exceed the supporting weight limit of a parachute.

The invention will be further described with reference to the accompanying drawings.

Fig. 1 to 5 illustrate the present invention. In the figure, 1, an airplane head and 2. an airplane head and other cabins are designed to be fixedly connected integrally, 2. an airplane head and other cabins and rear ends of the airplane head and other cabins and 3. an airplane business cabin front end is designed to be in locking connection, 3. an airplane business cabin rear end and 4. an airplane economy cabin front end is designed to be in locking connection, and the airplane economy cabin and an airplane tail are designed to be fixedly connected integrally. Fig. 1 to 5 constitute an aircraft as a whole.

6. the fixed frame of the airplane cockpit is arranged in the upper part in front of the airplane head and is in a circular sphere shape, the upper part, the lower part, the front part, the rear part, the left part and the right part of the inner side wall of the circular sphere are symmetrically provided with 7. the gyro balancer of the airplane cockpit is arranged and installed on the 7. the gyro balancer of the airplane cockpit is provided with 8 sliding balls of the gyro balancer of the airplane cockpit, 9. the periphery of the outer side of the airplane cockpit is provided with 10 guide rails of the airplane cockpit, 8 sliding balls of the gyro balancer of the airplane cockpit are buckled and connected with 10 guide rails of the airplane cockpit, 8 sliding balls of the gyro balancer of the airplane cockpit are buckled and installed on 10 peripheries of the outer side of the airplane cockpit, and when the airplane carries out a flight task in the air, the airplane can bump and roll in the air due to extreme severe weather and vortex airflow, And 9. changing the flight attitude, and keeping the parallel state of the aircraft cockpit under the action of 7. the gyroscope balancer of the aircraft cockpit. When the posture of the airplane is changed due to bumping, rolling and turning, the airplane driver also rolls along with the airplane to transversely, vertically, inversely and vertically cause the rise of the blood pressure of the airplane driver, the confusion and the head and eye splash, and the dislocation of the visual angle, so that the situation that the airplane driver mistakenly takes the sea as the blue sky to operate the airplane to continuously descend and fall into the sea to cause tragedy under the emergency condition is avoided, and the accidents of airplane crew members, airplane cabin crew members and passengers can not happen only by tying safety belts.

The cabin door of the airplane cockpit is arranged at the lower position on the left side of the airplane cockpit for an airplane pilot and an airplane crew member to get in and out of the cockpit.

The airplane operating system in the technical scheme of the invention is characterized in that an airplane external multi-directional camera and an airplane cockpit external multi-directional camera form a device for collecting information 12, an airplane pilot operates 13 after the display of the airplane operating system display screen, and an airplane operating system keyboard executes a flight task.

14, aircraft parachute catapult, 15, aircraft parachute, used as the aircraft to carry out the flight task in the air, when the aircraft can not fly normally in case of accident, the aircraft driver, the aircraft crew member, the aircraft cabin crew member and the passenger casualty, the aircraft driver passes 13, the aircraft operation system keyboard lets 14, the aircraft parachute catapult ejects and opens the aircraft to support the aircraft to land, when the aircraft parachute supports the aircraft to land 15, if the aircraft parachute meets the high building and the dense population area, the aircraft accident and the aircraft driver, the aircraft crew member, the aircraft cabin crew member and the passenger casualty are avoided to be caused for the wall, when the aircraft pilot operates 13, the aircraft operation system keyboard lets 16, the aircraft electric propeller catapult ejects 17, the aircraft electric propeller ejects and opens and rotates to generate the thrust to push the aircraft to drift away from the high building and the population Dense areas, landing in safety zones. In 15, if the airplane parachute holds the airplane to land, and if the airplane encounters sea, river, lake water areas, the airplane pilot is prevented from accidents caused by submergence of the airplane and injuries and deaths of the airplane pilot, airplane crew members, airplane cabin crew members and passengers, at the moment, the airplane pilot passes through 13, an airplane operating system keyboard opens 18, an airplane air bag bin is opened, and 19, the airplane air bag is popped up to generate buoyancy so that the airplane can float on the water surface and cannot sink. And meanwhile, the aircraft pilot passes through 13. an aircraft operating system operates a keyboard to let 16. an aircraft electric propeller thruster ejector ejects 17. the aircraft electric propeller thruster is ejected to be opened and rotated to generate thrust to push the aircraft to drive to the shore and wait for rescue. The aircraft airbag in the technical scheme of the invention not only can generate buoyancy when the aircraft lands in the water areas of the sea, the river, the lake and the river, but also can prevent the aircraft from sinking in water, and simultaneously can play a role in buffering when the landing gear of the aircraft breaks down.

The 20. the power supply button of the pedal type safe electroacoustic alarm of the airplane in the technical proposal of the invention is that under the condition that the pilot of the airplane is hijacked by illegal criminals or terrorists, the pilot's upper body is controlled and cannot be manually pressed 13. in the event that the aircraft operating system keypad sends an alert to each cabin of the aircraft, the aircraft pilot steps on 20. the power button of the pedal type safety electroacoustic alarm sends an alarm to each cabin of the aircraft to make each cabin crew member and passengers ready for response, the aircraft pilot steps on 22. the aircraft pedal type counterattack electric shock rod power button allows the setting to be installed on the left side, the right side and the back of the aircraft pilot seat 23. the aircraft counterattack electric shock rod ejector will 24. the aircraft counterattack electric shock rod ejects and catches the criminal who has hit the law of electric shock criminals or hijacked the aircraft (the merchant should pay attention to the use of the counterattack electric shock rod by law).

The third landing mode is that when the airplane performs the flying task in the air, after an accident happens, the whole weight of the airplane exceeds the landing weight limit, in this case, the pilot can operate 13. after the keyboard of the airplane operating system sends out an alarm to each cabin of the airplane, each cabin crew of the airplane passes 25. the remote controller of the airplane cabin sends out an instruction to let 2. the rear end of the cabin of the airplane head and the rear end of the other cabin of the airplane and the front end of the business cabin of the airplane, 3. the rear end of the business cabin of the airplane and the rear end of the business cabin of the airplane 4. the electromagnetic push-pull rod at the joint of the latch of the front end of the economic cabin of the airplane opens the latch to let 2. the rear end of the cabin of the airplane head and the rear end of the other cabin of the airplane are split to let 3. the rear end of the business cabin of the airplane and the front end of the other cabin of the airplane are split, after the split of the airplane, the cabin doors of the aircraft are closed, the power supply and the air pressure of each cabin of the airplane are all the airplane are normal, and each cabin crew of the airplane will operate 25. the remote controller of the cabin of the aircraft allows the parachute of the aircraft to let the aircraft parachute catapulter of the aircraft to push the aircraft to operate the aircraft to let 25 The parachutes in each passenger cabin of the airplane are popped up and opened, passengers in each passenger cabin of the airplane can not blindly open the parachutes in each passenger cabin of the airplane at the same time, because the parachutes in each cabin of the airplane can be intertwined and cannot be opened when the parachutes in each cabin of the airplane are opened simultaneously when the parts of each cabin of the airplane land on the same parallel line after the airplane is just split, the aim of safe landing can not be achieved, the crew members in each cabin of the airplane can open the parachutes in each cabin of the airplane after the display screen of each cabin of the airplane observes the safe distance for landing of each cabin of the airplane, because the weight of each cabin part of the airplane is different, the landing speed is also different, each cabin crew member of the airplane should operate 25 after knowing the safe distance for landing of each cabin of the airplane in advance, the keyboard of the operation system of the airplane cabin allows 14, the ejector of the airplane parachute ejects 15, the parachute is ejected to be opened to support the safe landing of each cabin part of the airplane. If the plane is separated and each cabin part of the plane is landed at a parallel speed, the parachutes at the two cabin parts of the plane can be opened first and then the parachutes at the middle cabin part of the plane are opened, if each cabin part of the plane is landed at an up-down vertical speed, each cabin crew of the plane should operate a remote controller keyboard of an operation system of the plane cabin to ensure that the cabin part of the plane at the top is 14, a parachute catapult is used for ejecting and opening 15, the parachutes are ejected and opened to support the cabin part of the plane to be pulled away from other cabin parts of the plane for safe landing, and then the parachutes at each cabin part of the plane are opened from top to bottom in sequence. When the parachute holds each cabin part of the airplane to land, if the parachute meets a high building and a dense population area, each cabin crew member of the airplane operates 25 to avoid accidents and casualties of airplane drivers, airplane crew members, airplane cabin crew members and passengers, the airplane cabin operation system remote controller keyboard gives 16, the airplane electric propeller ejector ejects the airplane electric propeller to open and rotate to generate thrust to push each cabin part of the airplane to float away from the high building and the dense population area, and the airplane arrives at a safety zone to land. When the aircraft parachute holds each cabin part of the aircraft to land, if the aircraft parachute meets sea, river, lake water areas, all the cabin parts of the aircraft sink in water, accidents are avoided, aircraft drivers, aircraft crew members, all the cabin crew members of the aircraft and passengers are injured and killed, at the moment, all the cabin crew members of the aircraft operate 25, the keyboard of the aircraft cabin operation system remote controller allows 18, the air bag bin of the aircraft is opened, and 19, the air bag of the aircraft pops out to generate buoyancy, so that all the cabin parts of the aircraft float on the water surface and cannot sink. Meanwhile, each cabin attendant operates 25. 16. the electric propeller thruster of the airplane cabin pops out 17 electric propeller thrusters of the airplane to open and rotate to generate thrust to push each cabin part of the airplane to drive to the shore and wait for rescue.

Claims

1. A safe-landing aircraft comprising: the aircraft comprises an aircraft head (1), cabins (2) such as the aircraft head and the like, an aircraft business cabin (3), an aircraft economic cabin (4), an aircraft tail (5), an aircraft cockpit fixing frame (6), an aircraft cockpit gyroscope balancer (7), an aircraft cockpit gyroscope balancer sliding ball (8), an aircraft cockpit (9), an aircraft cockpit guide rail (10), an aircraft cockpit door (11), an aircraft operating system display screen (12), an aircraft operating system keyboard (13), an aircraft parachute catapult (14), an aircraft parachute (15), an aircraft electric propeller thruster (16), an aircraft electric propeller thruster (17), an aircraft airbag cabin (18), an aircraft airbag (19), an aircraft pedal type safety electroacoustic alarm power button (20), an aircraft safety alarm (21), an aircraft pedal type counterattack electric shock rod power button (22), The airplane back-striking electric shock rod comprises an airplane back-striking electric shock rod ejector (23), an airplane back-striking electric shock rod (24) (the merchant should pay attention to the fact that the back-striking electric shock rod is used legally), an airplane cabin operating system remote controller (25) and an airplane cabin display screen (26).

2. A safety-landing aircraft as claimed in claim 1, configured for landing in three landing modes.

The first landing form is that when the aircraft is in the air to perform a flight mission, it can be landed at the destination airport in the existing landing form under all normal conditions.

The second landing form is that when the aircraft carries out the flight task in the air, after meeting the accident, the aircraft can not land at the destination airport according to the existing landing form, under the condition that the whole weight of the aircraft does not exceed the supporting weight limit of the parachute, the aircraft can land in the whole by adopting the second landing form, and the second landing form is characterized in that: the aircraft nose (1) rear end and the first equal main cabin (2) front end of aircraft design fixed connection as an organic whole, and first equal main cabin (2) rear end and aircraft commercial main cabin (3) front end of aircraft design for the kayser is connected, and aircraft commercial main cabin (3) rear end and aircraft economy main cabin (4) front end design are connected for the kayser, and aircraft economy main cabin (4) rear end and aircraft tail (5) design fixed connection as an organic whole have constituteed the aircraft wholly.

3. A safety landing aircraft as claimed in claim 2, wherein: the aircraft cockpit fixing frame (6) is arranged at the upper part in front of an aircraft nose (1) and is in a circular sphere shape, an aircraft cockpit gyroscope balancer (7) is arranged and installed at the symmetrical part of the upper part, the lower part, the front part, the rear part, the left part and the right part of the inner side wall of the circular sphere, aircraft cockpit gyroscope balancer sliding balls (8) are arranged and installed on the aircraft cockpit gyroscope balancer (7), an aircraft cockpit guide rail (10) is arranged and installed around the outer side of an aircraft cockpit (9), and the aircraft cockpit gyroscope balancer sliding balls (8) are connected with the aircraft cockpit guide rail (10) in a buckling mode.

4. A safety landing aircraft as claimed in claim 3, wherein: the cabin door (11) of the aircraft cockpit is arranged at the lower position of the left side of the aircraft cockpit.

5. A safety landing aircraft as claimed in claim 4, wherein: the display screen (12) of the airplane operating system and the keyboard (13) of the airplane operating system are arranged and installed in the airplane cockpit (9).

6. A safety landing aircraft as claimed in claim 5, wherein: a parachute catapult (14) and a parachute (15) are respectively arranged at the upper part of the aircraft nose (1), the wingtips of the front left wing of the aircraft, the wingtips of the front right wing of the aircraft, the upper edge right-angle position of the commercial passenger cabin (3) of the aircraft, the wingtips of the rear left wing of the aircraft, the wingtips of the rear right wing of the aircraft and the upper part of the aircraft tail (5), an electric propeller thruster catapult (16) and an electric propeller thruster (17) are respectively arranged at the front middle position of the aircraft nose (1), the central position of the upper part of the front end of the aircraft commercial cabin (3) and the central position of the upper part of the front end of the aircraft economic cabin (4), an air bag bin (18) and an air bag (19) are respectively arranged and mounted at the bottom of the aircraft nose (1), the bottoms of the passenger cabins (2) such as the aircraft nose, the bottoms of the aircraft commercial passenger cabins (3), the bottoms of the aircraft economic passenger cabins (4) and the bottoms of the aircraft tail (5).

7. A safety landing aircraft as claimed in claim 6, wherein: the lower part of an operation keyboard (13) of the aircraft cockpit is provided with an aircraft pedal type safety electroacoustic alarm power button (20) and an aircraft pedal type counterattack electric shock rod power button (22), and the left side, the right side and the back of a seat of an aircraft pilot are provided with a counterattack electric shock rod ejector (23) and a counterattack electric shock rod (24).

8. A safety landing aircraft as claimed in claim 7, wherein: each cabin of the airplane is provided with a safety electroacoustic alarm (21), a cabin operating system remote controller (25) and a cabin display screen (26).

The third form of landing is: when the aircraft is in the aerial mission of carrying out the flight, the back of the accident appears, when the whole weight of aircraft surpassed parachute support weight limit, can adopt the third kind to land the form and let the aircraft divide whole landing, characterized by: aircraft nose (1) rear end and aircraft first class main cabin (2) front end design fixed connection as an organic whole, aircraft first class main cabin (2) rear end and aircraft commercial cabin (3) front end design are connected for the kayser, open the kayser through the electromagnetism push-and-pull rod and can realize the aircraft components of a whole that can function independently, aircraft commercial cabin (3) rear end and aircraft economy main cabin (4) front end design are connected for the kayser, open the kayser through the electromagnetism push-and-pull rod and can realize the aircraft components of a whole that can function independently, aircraft economy main cabin (4) rear end and aircraft tail (5) design fixed connection as an organic whole.