Aircraft and landing method of aircraft

Abstract

The invention relates to the technical field of aircrafts, in particular to an aircraft and a landing method of the aircraft. The aircraft provided by the invention comprises a cabin, a parachute and a jet device, the cabin is in butt joint with the flight mechanism; the parachute is arranged in the cabin; the spraying device comprises a spraying opening, and the spraying opening faces the parachute; when the cabin is separated from the flight mechanism, the jet orifice jets high-pressure airflow to rush out the parachute, so that the parachute can be normally opened under the condition that the low altitude is not enough, the landing speed of the cabin can be slowed down after the parachute is jetted upwards, and the safety during landing is improved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft, and in particular, to an aircraft and a landing method thereof. Background Art

[0002] With the progress of urban three-dimensional transportation technology, low-altitude aircraft with a carrying function have become a development trend. A split-type aircraft generally includes a flight mechanism and a cockpit. In an emergency, the flight mechanism and the cockpit need to be separated. How to ensure the safe landing of the passengers in the cockpit and avoid damage to other objects by the cockpit has become an important research content. Summary of the Invention

[0003] The present disclosure provides an aircraft and a landing method thereof to at least solve the above technical problems existing in the prior art.

[0004] In a first aspect of the present disclosure, an aircraft is provided, including:

[0005] A cockpit, docked with a flight mechanism:

[0006] A parachute, provided in the cockpit;

[0007] A jet device, including a jet port, the jet port facing the parachute;

[0008] Wherein, when the cockpit is separated from the flight mechanism, the jet port ejects high-pressure air to eject the parachute.

[0009] Further, the number of the jet ports is multiple, and the multiple jet ports eject gas towards the parachute in different directions.

[0010] Further, the aircraft further includes a first airbag located in the cockpit, and the first airbag is used for inflating when the cockpit is separated from the flight mechanism.

[0011] Further, the aircraft further includes a first detection member, and the first detection member is used for detecting whether the cockpit is separated from the flight mechanism and transmitting the detected information on whether the cockpit is separated from the flight mechanism to a controller;

[0012] When the first detection member detects that the cockpit is separated from the flight mechanism, the controller controls the first airbag to automatically inflate.

[0013] Further, a second airbag is provided at the bottom of the cockpit, and the second airbag is used for inflating when the distance from the cockpit to the ground reaches a threshold.

[0014] Further, the cockpit is provided with a height sensor for detecting the height information of the cockpit and transmitting the detected height information to the controller;

[0015] The controller is configured to control the second airbag according to the height information, so that when the distance between the cockpit and the ground reaches a threshold value, the controller controls the second airbag to automatically inflate.

[0016] Further, the cockpit is provided with an attitude adjustment mechanism for adjusting the attitude of the cockpit.

[0017] Further, the attitude adjustment mechanism includes a first drainage plate and a second drainage plate, which are respectively arranged on both sides of the cockpit;

[0018] The upper surface of the first drainage plate is an upwardly convex arc surface, and the lower surface of the first drainage plate is a flat surface;

[0019] The upper surface of the second drainage plate is an upwardly convex arc surface, and the lower surface of the second drainage plate is a flat surface.

[0020] Further, the angle of attack of the first drainage plate and the angle of attack of the second drainage plate are both adjustable.

[0021] The second aspect of the present disclosure provides a landing method for an aircraft, including

[0022] After the cockpit detaches from the flight mechanism, the first airbag is opened;

[0023] The injection device ejects high-pressure air flow to eject the parachute;

[0024] When the distance between the cockpit and the ground reaches a threshold value, the second airbag is opened.

[0025] The technical solutions provided by the embodiments of the present disclosure have the following advantages compared with the prior art:

[0026] The aircraft provided by the embodiments of the present disclosure includes a cockpit, a parachute, and an injection device. The cockpit is docked with the flight mechanism. The parachute is arranged in the cockpit; the injection device includes an injection port facing the parachute; wherein, when the cockpit is separated from the flight mechanism, the injection port ejects high-pressure air flow to eject the parachute, so that it can ensure normal parachute opening even when the altitude is insufficient at low altitude. After the parachute is ejected upward, it can slow down the landing speed of the cockpit and improve the safety during landing.

[0027] It should be understood that the content described in this part is not intended to identify the key or important features of the embodiments of the present disclosure, nor is it used to limit the scope of the present disclosure. Other features of the present disclosure will become easily understood through the following description. Brief Description of the Drawings

[0028] By reading the following detailed description with reference to the accompanying drawings, the above and other objects, features, and advantages of the exemplary embodiments of the present disclosure will become readily understandable. In the drawings, several embodiments of the present disclosure are shown in an exemplary rather than restrictive manner, where:

[0029] In the drawings, the same or corresponding reference numerals denote the same or corresponding parts.

[0030] Figure 1 A schematic structural diagram of an aircraft provided by an embodiment of the present disclosure is shown;

[0031] Figure 2 A schematic structural diagram of a first drainage plate or a second drainage plate in the aircraft provided by an embodiment of the present disclosure is shown;

[0032] Figure 3 A flowchart of a landing method of an aircraft provided by an embodiment of the present disclosure is shown.

[0033] Description of reference numerals in the figure: 1, cockpit; 2, parachute; 3, ejection port; 4, second airbag; 5, attitude adjustment mechanism; 51, first drainage plate; 511, upper surface; 512, lower surface. Detailed implementation manners

[0034] To make the objects, features, and advantages of the present disclosure more obvious and understandable, the technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present disclosure. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments. Based on the embodiments of the present disclosure, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present disclosure.

[0035] Combined with Figure 1 and Figure 2 As shown, the aircraft provided by an embodiment of the present disclosure includes a cockpit 1, a parachute 2, a flight mechanism, and an ejection device. The cockpit 1 is docked with the flight mechanism. Optionally, the cockpit 1 and the flight mechanism can be connected through a docking mechanism. When the docking mechanism is in a locked state, the cockpit 1 and the flight mechanism are integrated; when the docking mechanism is in a disengaged state, the cockpit 1 and the flight mechanism are separated; the cockpit 1 can carry passengers or materials. When the cockpit 1 needs to land in the air, the docking mechanism is in a disengaged state so that the cockpit 1 is separated from the flight mechanism. The parachute 2 provided on the cockpit 1 can provide an upward pulling force during the landing process of the cockpit 1 to ensure the safe landing of the cockpit 1. Optionally, since the cockpit 1 and the flight mechanism can be designed as a separable type, the cockpit 1 can achieve independent landing.

[0036] An aircraft can include a fuselage, wings, a tail, landing gear, a power system, an avionics system, etc., and is a device that can fly within the atmosphere or in outer space (space).

[0037] When operating on the ground, the cockpit 1 can be set on the vehicle chassis. When there is a traffic jam on the ground or when it is necessary to quickly reach the destination, the cockpit 1 can be detached from the vehicle chassis, and the cockpit 1 can be connected to the aircraft through a docking mechanism, and the aircraft can carry the cockpit 1 to reach the destination.

[0038] Optionally, the locking and unlocking states of the docking mechanism can be controlled manually by a button or automatically by the controller receiving an instruction.

[0039] In this embodiment, the parachute 2 is arranged in the cockpit 1; the ejection device includes an ejection port 3, and the ejection port 3 faces the parachute 2; wherein, when the cockpit 1 is separated from the aircraft, the ejection port 3 ejects high-pressure air to push out the parachute 2, so as to ensure that the parachute can be normally opened even when the altitude is not enough at low altitude. After the parachute 2 is ejected upward, it can slow down the landing speed of the cockpit 1 and improve the safety during landing.

[0040] The ejection device can include an air launcher, which compresses air through the air launcher and ejects the air upward from the ejection port 3 to push the parachute 2 to deploy quickly. Optionally, the number of ejection ports 3 can be multiple, and by ejecting gas at multiple points, the opening speed of the parachute 2 can be increased.

[0041] Optionally, the ejection device can include a gas source and a gas chamber. The gas source can generate deflagration gas in the gas chamber to eject air flow from the ejection port 3, and the air flow ejected from the ejection port 3 directly ejects the parachute 2, so that the parachute 2 can be quickly released. Optionally, the gas chamber can be spherical, and multiple ejection ports 3 are arranged on the spherical surface, and the parachute 2 covers the outside of the gas chamber. When the multiple ejection ports 3 eject high-pressure air from different directions, the parachute 2 can be quickly ejected.

[0042] Optionally, the jet device can include a controller, a gas storage cylinder and a valve. High-pressure gas is stored in the gas storage cylinder. The intake end of the valve is communicated with the bottle mouth of the gas storage cylinder to form an intake channel. The outlet end of the valve is located below the ejection port 3. The valve is used to open or close the intake channel. The valve can be an electromagnetic valve. The valve is connected to the controller. When the controller controls the valve to open the intake channel, the outlet end of the valve ejects high-pressure gas to push the parachute 2 out of the shell cover.

[0043] In some specific embodiments, the number of the ejection ports 3 is multiple, and the multiple ejection ports 3 eject gas towards the parachute 2 in different directions, so that the part of the parachute 2 corresponding to the ejection port 3 can be quickly opened. The multiple ejection ports 3 eject gas towards the parachute 2 in different directions, which can quickly open the whole parachute 2, enabling the parachute 2 to quickly expand to the fully opened state, thus achieving the purpose of being opened within a short time and shortening the time delay for the parachute 2 to open.

[0044] Optionally, the ejection device is connected to the controller, and the controller controls the ejection device to eject high-pressure gas to push out the parachute 2.

[0045] In some specific embodiments, the aircraft further includes a first airbag located in the cockpit 1, and the first airbag is used for inflating when the cockpit 1 is separated from the flight mechanism. The first airbag is used to support the passengers and ensure the safety of the passengers during a collision.

[0046] The number of the first airbags can be set according to requirements, and can be set to one, or two or more.

[0047] Optionally, the first airbag can be connected to an ejection port 3 of the ejection device, and by ejecting gas through the ejection port 3, the first airbag can be opened.

[0048] Optionally, the aircraft further includes a first gas generating device, the first gas generating device is connected to the first airbag to inflate the first airbag, and the controller is electrically connected to the first gas generating device. A start switch is provided on the first gas generating device. When the start switch is manually or controlled by the controller to be turned on to make the first gas generating device inflate the inside of the first airbag, the first airbag quickly expands. The first gas generating device can be selected from a hydrogen generating device, a helium generating device, and a nitrogen generating device.

[0049] The first gas generating device can also adopt a hybrid gas generator combining a compressed gas type or an ignition type.

[0050] In some specific embodiments, the aircraft further includes a first detection member, and the first detection member is used for detecting whether the cockpit 1 is separated from the flight mechanism and transmitting the detected information on whether the cockpit 1 is separated from the flight mechanism to the controller; when the first detection member detects that the cockpit 1 is separated from the flight mechanism, the controller controls the first airbag to automatically inflate, which can ensure the safety of the passengers.

[0051] The first detection member can be an electromagnetic sensor: the electromagnetic sensor is used for real-time feedback on the docking and separation states of the cockpit 1 and the flight mechanism.

[0052] The first detection component can be an electromagnetic sensor and a separation sensor. When the cockpit 1 is combined with the flight mechanism, the electromagnetic sensor continuously monitors the current signal of the docking mechanism; when the cockpit 1 is separated from the flight mechanism, the separation sensor will detect the interruption of mechanical contact and send an alarm signal to the controller.

[0053] Optionally, the cockpit 1 and the flight mechanism are rigidly connected through a mechanical clamping part and a limiting structure, and the locking / unlocking state of the docking lock system is real-time feedback through an electromagnetic locking device.

[0054] In some specific embodiments, a second airbag 4 is provided at the bottom of the cockpit 1. The second airbag 4 is used to inflate when the distance between the cockpit 1 and the ground reaches a threshold, so that the second airbag 4 opens when the cockpit 1 is about to land, cushioning the impact and preventing greater damage to external objects at the same time.

[0055] Optionally, the number of the second airbags 4 can be set according to requirements, and can be set to one, or two or more. Optionally, the second airbag 4 can be connected to a spray port 3 of a spraying device, and gas is sprayed into the first airbag through the spray port 3 to open the second airbag 4. Optionally, the aircraft further includes a second gas generating device connected to the second airbag 4 to inflate the second airbag 4, and the controller is electrically connected to the second gas generating device. A start switch is provided on the second gas generating device. When the start switch is manually or controlled by the controller to open and the second gas generating device inflates the inside of the second airbag 4, the second airbag 4 expands rapidly. The second gas generating device can be selected from a hydrogen generating device, a helium generating device, and a nitrogen generating device. The second gas generating device can also adopt a hybrid gas generator combining a compressed gas type or an ignition type.

[0056] In some specific embodiments, the cockpit 1 is provided with a height sensor for detecting the height information of the cockpit 1 and transmitting the detected height information to the controller; the controller is used to control the second airbag 4 according to the height information, so that when the distance between the cockpit 1 and the ground position reaches the threshold, the controller controls the second airbag 4 to automatically inflate. The second airbag 4 opens when the cockpit 1 is about to land, cushioning the impact and preventing greater damage to external objects at the same time.

[0057] By inflating and deploying the second airbag 4, the impact force received when the cockpit 1 lands can be reduced, thereby protecting the lives of passengers. The second airbag 4 can be arranged at the bottom and side surfaces of the outer surface of the cockpit 1, so as to provide buffer protection for the cockpit 1 when it touches the ground during landing, and can effectively reduce the damage to the cockpit 1 caused by the impact force. Optionally, the second airbag 4 can include a bottom airbag located at the bottom of the cockpit 1 and a side airbag located at the side of the cockpit 1. The bottom airbag and the side airbag can protect the cockpit 1 from multiple directions when the cockpit 1 lands, thereby reducing the impact load transmitted to the cockpit 1 by the collision and reducing the injury of the occupants.

[0058] It should be noted that the first airbag is an inner airbag (not shown in the figure) arranged inside the cockpit 1. The second airbag 4 is an outer airbag.

[0059] In some specific embodiments, the cockpit 1 is provided with a posture adjusting mechanism 5 for adjusting the posture of the cockpit 1. The posture adjusting mechanism 5 is used to guide the flow direction of the air flow, ensure the stability of the posture of the cockpit 1 during the landing process, and reduce the impact on the safety of the passengers.

[0060] The posture adjusting mechanism 5 can make a posture adjustment for the cockpit 1 in time through the counterweight effect, or can adjust the posture of the cockpit 1 by changing the aerodynamic shape.

[0061] In some specific embodiments, the posture adjusting mechanism 5 includes a first flow guiding plate 51 and a second flow guiding plate. The first flow guiding plate 51 and the second flow guiding plate are respectively arranged on both sides of the cockpit 1; by arranging the first flow guiding plate 51 and the second flow guiding plate on both sides of the cockpit 1, the lateral stability of the cockpit 1 can be increased. The first flow guiding plate 51 and the second flow guiding plate can reduce the influence of the crosswind on the flight mechanism and keep the posture of the cockpit 1 stable. The upper surface 511 of the first flow guiding plate 51 is an upwardly convex arc surface, and the lower surface 512 of the first flow guiding plate 51 is a flat surface; the upper surface 511 of the second flow guiding plate is an upwardly convex arc surface, and the lower surface 512 of the second flow guiding plate is a flat surface. The design of the arc surfaces of the upper surface 511 of the first flow guiding plate 51 and the upper surface 511 of the second flow guiding plate helps to guide the air flow to flow more smoothly through the first flow guiding plate 51 and the second flow guiding plate, reducing turbulence and resistance. The lower surface 512 of the first flow guiding plate 51 and the lower surface 512 of the second flow guiding plate are flat surfaces, which can reduce turbulence and resistance, and help to keep the air flow velocity relatively stable when flowing through this surface.

[0062] In some specific embodiments, the angle of attack of the first flow guiding plate 51 and the angle of attack of the second flow guiding plate are both adjustable. By adjusting the angle of attack of the first flow guiding plate 51 and the second flow guiding plate, the cockpit 1 can adjust its posture more flexibly. The stability of the posture of the cockpit 1 during the falling process is improved, and the impact on the safety of the passengers is reduced.

[0063] Such as Figure 3As shown, the landing method of the aircraft provided by the embodiments of the present disclosure includes that after the cockpit 1 detaches from the flight mechanism, the first airbag is opened to support the passengers and ensure the safety of the passengers during a collision; the ejection device ejects high-pressure air to push out the parachute 2 to slow down the landing speed. At this time, the attitude adjustment mechanism 5 and the parachute 2 work together to maintain the stability of the cockpit 1; when the distance from the cockpit 1 to the ground position reaches a threshold value, the second airbag 4 is opened; when the cockpit 1 is about to land, the second airbag 4 is opened, which can cushion the impact and prevent greater damage to external objects at the same time.

[0064] In summary, the embodiments of the present disclosure have the following advantages:

[0065] 1. Improve passenger safety: By combining multiple protection measures such as the parachute 2, the first drainage plate 51, the second drainage plate, the first airbag and the second airbag 4, the descending speed of the cockpit 1 can be effectively slowed down to ensure the safety of the passengers.

[0066] 2. Use the airflow through the first drainage plate 51 and the second drainage plate to maintain the attitude of the cockpit 1 and prevent the passengers from being injured due to the drastic change in the pose of the cockpit 1.

[0067] 3. The second airbag 4 is opened when the cockpit 1 is about to land, which can reduce the damage to ground objects, effectively slow down the impact force during landing, reduce the damage of the cockpit 1 to ground objects, and ensure the safety of the landing area.

[0068] It should be understood that various forms of the processes shown above can be used, reordering, adding or deleting steps. For example, the steps described in the disclosure of the present invention can be executed in parallel, sequentially, or in a different order, as long as the desired results of the technical solutions disclosed in the embodiments can be achieved. This is not limited herein.

[0069] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present disclosure, "a plurality" means two or more unless otherwise specifically defined.

[0070] The above is only the specific implementation manner of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present disclosure can easily think of changes or substitutions, which should be covered within the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be subject to the protection scope of the claims.

Claims

1. An aircraft, characterized in that: include: Cockpit (1), docking with the flight mechanism: A parachute (2) is arranged on the cockpit (1); A jet device, comprising a jet port (3), wherein the jet port (3) faces the parachute (2); When the cabin (1) is separated from the flight mechanism, the jet port (3) ejects a high-pressure airflow to flush the parachute (2) out.

2. The aircraft according to claim 1, characterized in that There are a plurality of injection ports (3), and the plurality of injection ports (3) inject gas toward the parachute (2) in different directions.

3. The aircraft according to claim 1, characterized in that: It also comprises a first airbag located in the cockpit (1), the first airbag being used for being inflated when the cockpit (1) is separated from the flying mechanism.

4. The aircraft according to claim 3, characterized in that It also includes a first detection component, which is used to detect whether the cockpit (1) is separated from the flying mechanism, and transmit the detected information of whether the cockpit (1) is separated from the flying mechanism to a controller; When the first detection member detects that the cabin (1) is separated from the flight mechanism, the controller controls the first airbag to automatically inflate the first airbag.

5. The aircraft according to claim 1, characterized in that: A second airbag (4) is provided at the bottom of the cabin (1), and the second airbag (4) is used to inflate when the distance between the cabin (1) and the ground reaches a threshold value.

6. The aircraft according to claim 5, characterized in that The cabin (1) is provided with an altitude sensor, which is used to detect altitude information of the cabin (1) and transmit the detected altitude information to a controller; The controller is used to control the second airbag (4) according to the altitude information, so that when the distance from the cabin (1) to the ground position reaches a threshold, the controller controls the second airbag (4) to automatically inflate the second airbag (4).

7. The aircraft according to claim 1, characterized in that: The cockpit (1) is provided with a posture adjustment mechanism (5) for adjusting the posture of the cockpit (1).

8. The aircraft according to claim 7, characterized in that The posture adjustment mechanism (5) comprises a first deflector plate (51) and a second deflector plate, wherein the first deflector plate (51) and the second deflector plate are respectively arranged on two sides of the cabin (1); The upper surface (511) of the first guide plate (51) is an upwardly convex arc surface, and the lower surface (512) of the first guide plate (51) is a flat surface; The upper surface (511) of the second flow guide plate is an arc-shaped surface convex upward, and the lower surface (512) of the second flow guide plate is a flat surface.

9. The aircraft according to claim 8, characterized in that The angle of attack of the first guide plate (51) and the angle of attack of the second guide plate are both adjustable.

10. A method for landing an aircraft, characterized in that: include After the cockpit (1) is detached from the flight mechanism, the first airbag is opened; The jet device ejects high-pressure airflow to push the parachute (2) out; When the distance from the cabin (1) to the ground reaches a threshold, the second airbag (4) is opened.

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