WO2018019075A1

WO2018019075A1 - Aircraft having air crash lifesaving function

Info

Publication number: WO2018019075A1
Application number: PCT/CN2017/090454
Authority: WO
Inventors: 冯政尧
Original assignee: 冯政尧
Priority date: 2016-07-27
Filing date: 2017-06-28
Publication date: 2018-02-01
Also published as: CN106005363A; CN106005363B

Abstract

Disclosed in the present invention is an aircraft having an air crash lifesaving function. The aircraft comprises a nose, a passenger cabin and wings disposed on the left side and the right side of the passenger cabin. The wings and the passenger cabin are detachably connected by means of a plug connector assembly, and the plug connector assembly comprises a pair of jaws, a clamping groove cooperating with the jaws, and a driving member for driving the jaws to be opened to press against the clamping groove or driving the jaws to folded to separate the jaws from the clamping groove. Parachutes capable of being unfolded after the wings are separated and reverse jet devices for reducing the falling speeds of the nose and the passenger cabin are disposed on the passenger cabin; at least one inflation unit for buffering the falling impact force of the passenger cabin and the nose is also disposed at the bottom of the passenger cabin. When an accident happens to the aircraft, the wings are separated from the other positions of the aircraft in the first place to save pilots and important control elements in the nose on the basis that passengers in the passenger cabin are saved, so that the passengers on the aircraft with such an accident and most of important components of the aircraft are safely landed, and air crash loss is reduced.

Description

Aircraft with air rescue function

Technical field

The present invention relates to an aircraft structure having an air rescue function that can rescue all personnel on an aircraft during an air crash.

Background technique

Aircraft is the most important and fastest type of modern transportation. From the structural analysis, the aircraft itself should also be the vehicle with the highest safety factor. However, since the operating area of the aircraft is high, there are many unpredictable factors. Even if the aircraft is thoroughly and thoroughly tested before each flight, it is still impossible to avoid the air disaster caused by many factors. Because the aircraft is running at high altitude, once the air crash occurs, the personnel inside the aircraft, especially the ordinary passengers in the passenger aircraft, rely on the guidance, comfort and guidance of the flight attendants, and still cannot make the passengers self-rescue. Therefore, once the plane crashes, almost It means the demise of hundreds of lives.

Since the invention of the aircraft, in addition to the research on aircraft manufacturing, control and driving simulators, research on how aircraft respond to air crashes has emerged. The more mainstream ones are http://www.le.com/ptv/vplay. /24777237.htmlch=360_kandsp The method disclosed in the website video is to separate the cabin from other positions of the aircraft by means of aircraft separation, and to equip the top of the cabin with a parachute, jet deceleration device, and to provide a buffer airbag to the bottom of the cabin to Allows the cabin to land safely on the road or on the sea, saving the lives of passengers in the cabin. Another example is the technical solution disclosed in the invention patent authorization text of CN1148306C. The core idea is similar to the scheme in the video mentioned above, that is, the aircraft body is made into a separable form, and the split solution is The main body is made into a separate outer casing and a plurality of cabin units. When a danger occurs, the head of the aircraft and the fuselage are blasted to form an exit of the cabin unit on the main body, and the cabin unit is controlled by the brake device. Controllable The sliding speed slides out of the main body and opens the parachute, cushioning airbag, etc. in a manner similar to that demonstrated in the video to allow the cabin unit to land safely.

However, the nose of the aircraft is where the people and equipment controlling the flight of the aircraft are located, and it is unreasonable to directly waive this part and only save the passenger cabin and the passengers therein.

Summary of the invention

SUMMARY OF THE INVENTION It is an object of the present invention to provide an aircraft having an air rescue function that saves the nose and the passenger cabin together in a plane crash to minimize the loss of the aircraft crash and to preserve the personal safety of the pilot.

The above object of the present invention is achieved by the following technical solutions: an aircraft having an air rescue function, including an organic head, a passenger cabin, and a wing disposed on the left and right sides of the passenger cabin, the wing and the passenger cabin being docked The assembly is detachably connected, and the plug assembly includes a pair of claws, a slot engaged with the claw, and driving the claw to open against the slot or to close the claw to disengage the slot from the slot. a drive member having a parachute that can be deployed after the wing is disengaged and a reverse jet device for slowing down the speed of the nose and the cabin, the bottom of the passenger cabin being provided with at least one cushioning cabin and An inflatable unit with a falling impact on the nose.

By adopting the above technical solution, a detachable connection relationship is established between the wing and the passenger cabin, and when the aircraft is in danger, the driving member drives the pair of claws to be gathered to be detached from the card slot, thereby achieving the wing and With the departure of the cabin, the cabin gradually landed under the protection of the parachute, the reverse jet and the inflatable unit, thus achieving the purpose of protecting the passengers in the cabin as well as the pilots and important aircraft parts within the nose.

Preferably, the card slot is disposed in a dovetail slot.

By adopting the above technical solution, the dovetail groove is more precise with respect to the general chute structure, and the engagement between the dovetail and the jaws ensures a tight and reliable cooperation between the wing and the passenger cabin during normal flight.

Further, the card slot is arranged in a front-rear direction along a side of the wing that is engaged with the passenger cabin, and the claw is slidably disposed in the card slot, when the driving member drives a pair of the claws to be gathered The claw can slide out of the card slot along the extending direction of the card slot.

By adopting the above technical solution, the claw slides out of the card slot form, and when the aircraft fails, the pair of claws are first gathered by the driving member, and the quality of the wing and the cabin is different, so the inertia of the two is different, the wing When the engine can continue to work, the wing will be forwarded to disengage it from the passenger cabin. When the engine fails, the inertia between the wing cabins will be used, and the wing will stop flying forward before the passenger cabin. Therefore, two After the claws are gathered, the positional relationship during the original flight is released and the sliding position is released, which can effectively prevent the disengaged wing from colliding with the passenger cabin.

Preferably, a pair of the claws are arranged along a width direction of the wing, and when the driving member drives a pair of the claws to be gathered, the claws can be released from the card slot.

By adopting the above technical solution, when the aircraft is in normal flight, the wing needs to drive the passenger cabin. Therefore, the joint strength between the two is very important. When the above arrangement is adopted, the wing of the aircraft moves the direction of movement of the passenger cabin, which is exactly the claw Close to the direction of the card slot, it can ensure the reliable connection between the wing and the cabin during the flight; and when the aircraft needs to take off the wing when there is an accident, gather a pair of claws to take it out of the slot, and quickly realize the air resistance. The wing is separated from the cabin.

Further, the claw and the card slot are arranged along the extending direction of the wing to both sides of the passenger cabin.

By adopting the above technical solution, in the process of removing the card slot after the claws are gathered, the wing will rotate toward the tail direction along the point where the clamping component is located, and the claws and the card slot are arranged in the above direction, thereby preventing the wing from being The claws hinder the detachment of the wing during the rotation of the passenger compartment.

Preferably, the drive member employs a hydraulic cylinder.

By adopting the above technical solution, the hydraulic pressure outputted by the hydraulic cylinder can ensure the reliable abutment between the claw and the card slot, so as to ensure the fixing of the wing and the passenger cabin is reliable, and the hydraulic cylinder cooperates with a reasonable external hydraulic control system, such as double Control hydraulic locks, quick reversing circuits, etc., can easily achieve the purpose of reliably abutting the jaws and quickly gathering the jaws when needed.

Preferably, the jaws are linked to the piston rod of the hydraulic cylinder to be gathered or opened.

By adopting the above technical solution, the movement of the claws is directly driven by the piston rod, the structure reliability is high, and the link relationship is simple and easy to implement.

Preferably, a gap is formed between the pair of claws, and the piston rod of the hydraulic cylinder extends into or out of the gap to drive the claw to open against the card slot or to gather and exit the card slot.

By adopting the above technical solution, the opening of the claw can be made more reliable by pushing the pair of claws in the piston rod insertion gap, and even if the piston rod is slightly retracted due to leakage of the hydraulic cylinder or the like, a guarantee can be ensured. The jaws are reliably pressed against the slot to ensure reliable engagement of the wing with the passenger compartment.

Preferably, a spring is disposed between the pair of claws in a tension state. By adopting the above technical solution, the spring can gather a pair of claws with an elastic force after the piston rod exits the gap, so as to make it fast and reliable. The cabin is separated.

Preferably, the top of the passenger cabin is provided with a plurality of sunroofs, and the lower side of the sunroof is correspondingly provided with a storage body for accommodating the parachute.

By adopting the above technical solution, a storage body for accommodating a parachute is arranged on the sunroof, and the skylight is spread out for a period of time after the wing is detached, and the parachute in the storage body is released to be deployed, thereby ensuring the normal flight of the aircraft. The up and down direction of the time gradually descends.

In summary, the present invention has the following beneficial effects: the wing can be separated from the passenger compartment and the nose, and when the aircraft is in an accident, the wing is disengaged from the other positions of the aircraft in the first time. On the basis of the passengers in the cabin, the pilots in the nose and the important control components in the nose are simultaneously rescued, and the descending and landing control of the cabin and the nose are carried out by the parachute, the reverse jet and the inflating unit, so that the aircraft on the accident occurs. The passengers and most of the important parts of the aircraft landed safely, reducing the loss of both human and property caused by air crashes.

DRAWINGS

Figure 1 is a schematic view showing the structure after the parachute is opened;

Figure 2 is a partial cross-sectional view of the wing portion for showing the wing and the docking assembly;

Figure 3 is a partial enlarged view A of Figure 2;

Figure 4 is a partial enlarged view of the driving member of Figure 3 after changing the fixed position;

Figure 5 is a partial cross-sectional view of the docking device after the parachute is removed for another arrangement of the docking assembly;

Figure 6 is a partial enlarged view B of Figure 5;

Figure 7 is a partial enlarged view of the driving member of Figure 6 after changing the fixed position;

Figure 8 is a cross-sectional view showing the overall landing structure;

Figure 9 is a schematic diagram of the lock loop of the drive member.

In the figure, 1, the machine head; 11, the traction rope; 12, the damper; 2, the passenger cabin; 20, the skylight; 21, the warehouse body; 3, the wing; 4, the parachute; 5, the reverse jet device; Assembly; 60, claw; 61, card slot; 62, drive member; 63, spring; 64, hydraulic lock; 7, inflatable unit.

detailed description

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

Example 1

An aircraft with a space-saving and life-saving function, as shown in FIG. 1 , has the same structure as a general aircraft, and includes an organic head 1 , a passenger cabin 2 integrally formed with the head 1 , and a machine symmetrically disposed on both sides of the passenger cabin 2 . Wing 3.

A docking assembly 6 is disposed between the wing 3 and the passenger cabin 2 to form a detachable connection. During normal flight, the docking assembly 6 connects the wing 3 and the passenger cabin 2, and the wing 3 normally drives the aircraft to fly; when the aircraft fails, the aircraft needs to take off. When the wing 3 is removed, the docking assembly 6 is opened to disengage the wing 3 and the passenger cabin 2 from each other by an external force.

Specifically, as shown in FIGS. 2 to 3, the plug assembly 6 includes a pair of claws 60, a latching groove 61 engaged therewith, and a driving member 62 disposed between the pair of claws 60, wherein the driving member 62 can be a hydraulic cylinder or a cylinder, etc., taking the hydraulic cylinder as the driving member 62 as an example, the piston rod is fixed to the claw 60. When a single hydraulic cylinder is used, the cylinder and the piston rod of the hydraulic cylinder are respectively disposed on a pair of cards. When the hydraulic cylinder is extended on the claw 60, the cylinder tube and the piston rod generate a pair of force and reaction force between the pair of claws 60, and pushes the pair of claws 60 to each other to make the two abut against the card. In the groove 61, the wing 3 and the passenger cabin 2 are reliably connected; when the piston rod of the hydraulic cylinder is retracted into the cylinder, the pair of claws 60 lose tension with each other and gather to abut each other, thereby clamping the jaws The 60 and the card slot 61 lose their mutual abutment relationship, and at this time, the wing 3 and the passenger cabin 2 are in a detachable state.

In the form of the two hydraulic cylinders shown in Fig. 3, the principle is similar to the above process, except that each of the claws 60 corresponds to a driving member 62, and the force in the abutment and the slot 61 is larger, and the connection is more reliable.

As shown in FIG. 2, the cross-sectional shape of the card slot 61 is a dovetail type, and the card slot 61 is disposed in the width direction of the wing 3, and the claws 60 are gathered from each other. In the state, it can be slid into the card slot 61 to connect the wing 3 and the passenger cabin 2. In the emergency state in which the wing 3 needs to be disengaged, the driving member 62 drives the two claws 60 to be close to each other to loosen the clamping state of the card and the slot 61. At this time, the pair of claws 60 and the slot 61 are engaged. There is a gap between them, and the difference between the weight of the wing 3 and the cabin 2 itself will cause the inertia between the two parts to be different. The original wing 3 and the passenger cabin 2 are separated from each other before the same speed, the moment of disengagement, the initial two The speed is the same and the inertia is different, so after a short flight, the passenger cabin 2 will slide away from the wing 3 in the direction of the distribution of the slot 61, thereby achieving the disengagement of the wing 3 from the passenger cabin 2.

In order to securely lock the hydraulic cylinder in the extended position when it is extended, as shown in Figure 9, an embodiment of a locking circuit for the locking hydraulic cylinder is given. The extension and retraction of the hydraulic cylinder are controlled by the electromagnetic reversing valve, and the positioner can adopt the H-type neutral function, and the hydraulic lock 64 is connected between the rod cavity and the rodless cavity of the hydraulic cylinder as the driving member 62, so that When the hydraulic cylinder is extended to a position where the pair of claws 60 are tightened, the two electromagnets of the electromagnetic reversing valve are de-energized, the spool is operated at the neutral position, and the two ends of the hydraulic lock 64 are connected to each other. The cavity is connected so that there is no pressure difference at both ends of the piston rod to achieve its fixed point locking.

As shown in Fig. 8, the top of the passenger cabin 2 is provided with an openable sunroof 20, and below it is provided with a magazine body 21 in which a parachute 4 is stored for ensuring the slow landing of the passenger cabin 2. The form of the parachute 4 is not limited An umbrella structure shown in the figure can also adopt the tower-shaped parachute structure in the prior patent, and, according to the rated load of the aircraft, one or more cartridge bodies 21 for storing the parachute 4, and a plurality of cartridge bodies 21 are provided. It is distributed along the direction from the head 1 to the tail to provide sufficient lift for the aircraft with a large weight to ensure its slow fall. The parachute 4 has multiple groups and is sequentially ejected in a plane-flat curve to control the slow landing of the cabin 2 and the nose 1. To the ground.

A traction rope 11 connecting the two and transferring the lift of the parachute 4 to the passenger cabin 2 is further disposed between the parachute 4 and the magazine body 21, and the traction rope 11 is provided with a buffer damper 12 for buffering the traction rope 11 sudden moments of sudden tension on the passenger cabin 2, one protects the traction rope 11 from being interrupted by an instantaneous impulse, and the other prevents the sudden tension of the traction rope 11 from causing the passengers in the passenger cabin 2 to feel the shaking worrying and nervous.

Regardless of how the cabin 2 is controlled to fall, at the moment when the cabin 2 is in contact with the ground, the huge momentum still has the potential to injure the personnel inside the aircraft. Therefore, the bottom of the cabin 2 and the two sides are provided with the

inflatable units

7, 7 at the right time. Inflate. The structure of the inflator unit 7 is the same as that of the airbag mentioned in the prior patent.

In order to further buffer the descending speed of the passenger cabin 2 and the nose 1 so that the aircraft can land as smoothly as possible, a reverse jet device 5 is also arranged on the bottom of the passenger cabin 2 or on the traction rope 11, and after the cabin 2 descends to a certain distance, it is opened. The reverse jet device 5 causes the compressor body therein to release an upward recoil force to slow the landing speed of the passenger cabin 2.

Example 2

An aircraft having a space-saving and life-saving function differs from that in Embodiment 1 in that a gap is formed between the claws 60 when a pair of claws 60 are in contact with each other in the card slot 61 as a hydraulic pressure of the driving member 62. When the piston rod of the cylinder projects into this gap, the gap between the pair of jaws 60 will be filled. At this time, since the gap is filled by the piston rod, the two claws 60 abut against the card slot 61.

Example 3

An aircraft having a space-saving rescue function differs from that in Embodiment 1 in that, as shown in FIGS. 5 to 6, the cross-sectional shape of the card slot 61 is a dovetail type as viewed along the top surface of the wing 3. With this connection structure, when the driving members 62 between the pair of claws 60 are to be joined together, the pair of claws 60 must be able to exit the card slot 61 so that the wing 3 is placed along the point of the insertion assembly 6. After the rotation, it is separated from the cabin 2.

In order to prevent the claw 60 from interfering with the card slot 61 during the backward rotation of the wing 3, the claw 60 and the card slot 61 are respectively arranged along the extending direction of the wing 3 from the passenger cabin 2 to both sides thereof, so as to make the card The claw 60 can be smoothly disengaged from the card slot 61.

Due to the process of the rearward rotation of the wing 3 and the disengagement of the passenger cabin 2, in order to prevent the disengaged wing 3 from reaching the tail of the passenger cabin 2, a parachute can also be added to the wing 3 to pull the disengagement direction of the wing 3 to prevent it. Reached on cabin 2.

Example 4

An aircraft having a space-saving rescue function differs from that in Embodiment 3 in that the driving member 62 controls the opening or closing of the pair of claws 60 in the manner shown in Embodiment 2.

Further, as shown in FIG. 7, one or more sets of springs 63 may be tensionably disposed between the pair of claws 60, particularly when a pair of claws 60 are inserted into the card slot 61 by the piston rod insertion, the spring 63. At the moment when the piston rod is withdrawn from the gap between the claws 60, the two claws 60 are brought closer to each other by the elastic force to accelerate the detachment speed of the wing 3 from the passenger cabin 2.

The present invention is only an explanation of the present invention, and is not intended to limit the present invention. Those skilled in the art can make modifications without innovating the present embodiment as needed after reading the present specification, but as long as the present invention is in the right of the present invention. All requirements are protected by patent law.

Claims

An aircraft having an air rescue function, comprising an organic head (1), a passenger cabin (2) and a wing (3) disposed on the left and right sides of the passenger cabin (2), characterized in that: the wing (3) and the passenger cabin (2) being detachably connected by a plug assembly (6), the plug assembly (6) comprising a pair of claws (60), a card slot (61) cooperating with the claw (60), And a driving member (62) for driving the claw (60) to open against the card slot (61) or to be separated to disengage the claw (60) from the card slot (61), the passenger cabin (2) is mounted thereon a parachute (4) that can be deployed after the wing (3) is disengaged and a reverse jet (5) for slowing the falling speed of the handpiece (1) and the passenger cabin (2), the bottom of the passenger cabin (2) At least one inflating unit (7) for buffering the falling impact of the passenger cabin (2) and the handpiece (1) is provided.
The aircraft with air crash rescue function according to claim 1, wherein the card slot (61) is disposed in a dovetail slot.
The aircraft with a space-saving and life-saving function according to claim 2, wherein the card slot (61) is arranged in a front-rear direction along a side of the wing (3) that engages with the passenger compartment (2), the card The claw (60) is slidably disposed in the card slot (61), and when the driving member (62) drives a pair of the claws (60) to be gathered, the claw (60) can be along the card slot The extending direction of (61) slides out of the card slot (61).
An aircraft having a lifesaving function according to claim 2, wherein a pair of said claws (60) are arranged along a width direction of said wing (3), and said driving member (62) drives a When the claw (60) is gathered, the claw (60) can be released from the card slot (61).
The aircraft with air crash rescue function according to claim 4, characterized in that: the claw (60) and the card slot (61) extend along the wing (3) to both sides of the passenger cabin (2). Directional arrangement.
An aircraft having a lifesaving function according to claim 3 or 4 or 5, wherein said driving member (62) is a hydraulic cylinder.
The aircraft with air crash rescue function according to claim 6, wherein the claw (60) is interlocked with the piston rod of the hydraulic cylinder to be gathered or opened.
The aircraft with air crash rescue function according to claim 6, wherein a gap is formed between a pair of said claws (60), and a piston rod of said hydraulic cylinder extends into or out of said gap to drive said The claw (60) is opened to the card slot (61) or is folded out of the card slot (61).
The aircraft having a lifesaving function according to claim 8, wherein a pair of said claws (60) is further provided with a spring (63) in a tensioned state.
The aircraft with the air rescue function according to claim 1, characterized in that: the top of the passenger cabin (2) is provided with a plurality of sunroofs (20), and the lower portion of the sunroof (20) is correspondingly provided with a parachute (4) for receiving. Warehouse body (21).