Water low-altitude manned aircraft
By using components such as plexiglass shells, cushioned seats, airbags, and inflatable air cushions in low-altitude aircraft, safety issues during aircraft crashes and water landings have been resolved, enabling passenger protection and rescue.
Patent Information
- Application Number
- CN202520309318.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-25
- Publication Date
- 2026-01-23
- Estimated Expiration
- 2035-02-25
AI Technical Summary
Existing low-altitude aircraft are prone to crashing in case of malfunction, causing injury to personnel inside, and are not safe enough when making emergency landings on water.
It uses components such as an acrylic glass shell, cushioned seats, internal and external airbags, a control console, a satellite positioning device, and inflatable air cushions. The airbags inflate to protect passengers, ensuring a smooth landing and facilitating rescue.
It improves passenger safety during aircraft crashes and water landings, ensuring smooth landings and timely rescue.
Smart Images
Figure CN223822026U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to the technical field of low altitude aircraft, especially to a water low altitude manned aircraft. BACKGROUND
[0002] With the social development, the vehicle on the ground is more and more, and the traffic pressure is more and more big, and the traffic jam time greatly increases, and the traffic accident also increases, and such present situation brings inconvenience to people's life, and the life safety is seriously affected, in order to alleviate the ground traffic pressure, the traffic tool should gradually enter the flight field.
[0003] Low altitude aircraft refers to the aircraft mainly operating in the relatively low airspace. Relative to the conventional land surface, the air space above the river, sea surface and other water areas has low complexity and flat undulation, so the probability of collision of the low altitude aircraft flying on the water surface is low. However, if some failure or aircraft collision accident occurs, the aircraft may still fall, causing serious injury to the internal personnel. UTILITY MODEL CONTENT
[0004] In order to improve the problem that the existing aircraft mentioned above causes impact when the aircraft falls due to failure in the low altitude flight process, and further causes injury to the personnel inside the aircraft, the utility model provides a water low altitude manned aircraft.
[0005] The utility model provides a water low altitude manned aircraft, adopts the following technical scheme:
[0006] A water low altitude manned aircraft, comprising a manned cabin, the top of the manned cabin is provided with a quadcopter assembly, the bottom of the manned cabin is provided with a support assembly, the manned cabin comprises a plexiglass shell, a buffer seat is installed in the inside of the plexiglass shell, a console is installed at one end of the inside of the plexiglass shell close to the buffer seat, and an inner safety airbag and an outer safety airbag are respectively installed on the inside and the outside of the plexiglass shell.
[0007] By adopting the above technical scheme, when the aircraft normally flies, the personnel sit on the buffer seat in the plexiglass shell, four propellers on the quadcopter assembly rotate to provide upward lift, when the lift is greater than the overall gravity of the aircraft, the aircraft takes off, the rotation speed of each propeller on the quadcopter assembly is adjusted to form a resultant force to drive the aircraft to move horizontally or vertically in the air, when the aircraft falls due to failure during normal operation of the aircraft, the console controls the inflation and expansion of the inner safety airbag and the outer safety airbag to protect the safety of the personnel in the plexiglass shell.
[0008] Optionally, the plexiglass shell adopts a spherical structure.
[0009] By adopting the technical scheme, the field of view of the flight personnel can be expanded.
[0010] Optionally, the inner wall of the organic glass shell is connected with a plurality of high-strength structural members.
[0011] By adopting the technical scheme, the high-strength structural members can provide structural strength for the organic glass shell to cope with self-load and external impact.
[0012] Optionally, an acceleration sensor is installed at one end of the organic glass shell close to the buffer seat, and an output end of the acceleration sensor is electrically connected with an input end of the control console.
[0013] By adopting the technical scheme, when the aircraft fails and falls, the acceleration sensor sends an emergency signal, and the control console inflates the inner and outer safety airbags according to the emergency signal.
[0014] Optionally, a satellite positioning device and a satellite communication device are installed on the top of the control console.
[0015] By adopting the technical scheme, the control console obtains position information of the manned cabin through the satellite positioning device, and contacts the ground through the satellite communication device to obtain rescue.
[0016] Optionally, the support assembly comprises a landing support, the landing support is installed at the bottom of the organic glass shell, a plurality of inflatable air cushions are connected to one side of the landing support away from the organic glass shell, and the number of the inflatable air cushions is four.
[0017] By adopting the technical scheme, the inflatable air cushions are inflated to form air cushions, so that the aircraft can land stably on the water surface in a normal posture.
[0018] Optionally, a height sensor is installed on the landing support, and an output end of the height sensor is electrically connected with an input end of the control console.
[0019] By adopting the technical scheme, the height of the aircraft is measured by the height sensor, so that the aircraft can be constrained to fly within a specific height range, and the effectiveness of safety measures of the aircraft in the case of failure can be improved.
[0020] In summary, the utility model has at least one of the following beneficial effects:
[0021] By the organic glass shell, the buffer seat, the control console, the inner safety airbag and the outer safety airbag, when the aircraft fails and falls during low-altitude flight, the inner safety airbag and the outer safety airbag on the organic glass shell and the buffer seat can be used to protect the personnel by shock absorption, and the safety of the personnel is improved.
[0022] By adopting the spherical plexiglass shell and high-strength structural member as the main frame of the manned cabin, the strength of the whole manned cabin can be improved to cope with self-load and external impact, and the spherical structure helps the pilot to expand the visual field.
[0023] By cooperating the landing support and the inflatable air cushion, the inflatable air cushion on the landing support is inflated to form the air cushion, so that the aircraft can land on the water surface in a normal posture and float on the water surface.
[0024] By cooperating the console, the satellite positioning device and the satellite communication device, when the aircraft crashes or makes an emergency landing on the water surface, the satellite positioning device and the satellite communication device are used to contact the ground and obtain rescue. BRIEF DESCRIPTION OF DRAWINGS
[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment or the prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.
[0026] Figure 1 It is a three-dimensional structure schematic diagram of the present application;
[0027] Figure 2 It is a sectional structure schematic diagram of the manned cabin of the present application;
[0028] Figure 3 It is a structure schematic diagram of the support assembly of the present application.
[0029] In the figure: 1, four-rotor aircraft assembly; 2, manned cabin; 21, plexiglass shell; 22, high-strength structural member; 23, acceleration sensor; 24, buffer seat; 25, console; 26, satellite positioning device; 27, satellite communication device; 28, inner safety airbag; 29, outer safety airbag; 3, support assembly; 31, landing support; 32, height sensor; 33, inflatable air cushion. DETAILED DESCRIPTION
[0030] The following will be further described in combination with the drawings Figures 1-3 The present application will be further described in detail.
[0031] Please refer to the drawings in the specification Figure 1 and Figure 3The utility model provides an embodiment: a water low empty manned aircraft, manned cabin 2 is provided with four rotor aircraft subassembly 1 on the top of manned cabin 2, the bottom of manned cabin 2 is provided with support subassembly 3, support subassembly 3 includes landing support 31, landing support 31 is installed at the bottom of organic glass shell 21, landing support 31 is connected with a plurality of inflatable air cushion 33 on the side away from organic glass shell 21, and the number of inflatable air cushion 33 is provided with four. Through the inflation of inflatable air cushion 33, air cushion can be expanded to ensure that the aircraft lands steadily on the water surface in normal posture.
[0032] Please refer to the drawing of the specification Figure 1 And Figure 3 Height sensor 32 is installed on landing support 31, and the output end of height sensor 32 is electrically connected with the input end of control console 25. The height of the aircraft is measured by height sensor 32, the aircraft can be constrained to fly within a specific height range, and the effectiveness of safety measures of the aircraft in the event of failure can be improved.
[0033] Please refer to the drawing of the specification Figure 1 And Figure 2 Manned cabin 2 includes organic glass shell 21, and the organic glass shell 21 adopts spherical structure. Thus the field of view of the flight personnel can be expanded. The inner wall of organic glass shell 21 is fixedly connected with a plurality of high-strength structural members 22. The high-strength structural members 22 can provide structural strength for the organic glass shell 21 to cope with its own load and external impact.
[0034] Please refer to the drawing of the specification Figure 2 Buffer seat 24 is installed in the inside of organic glass shell 21, control console 25 is installed at one end of the inside of organic glass shell 21 close to buffer seat 24, satellite positioning device 26 and satellite communication device 27 are respectively installed on the top of control console 25. The position information of manned cabin 2 is obtained by control console 25 through satellite positioning device 26, and the ground is contacted through satellite communication device 27 to obtain rescue.
[0035] Please refer to the drawing of the specification Figure 2 Inner safety airbag 28 and outer safety airbag 29 are respectively installed on the inside and outside of organic glass shell 21, acceleration sensor 23 is installed at one end of the inside of organic glass shell 21 close to buffer seat 24, and the output end of acceleration sensor 23 is electrically connected with the input end of control console 25. After the failure of the aircraft, acceleration sensor 23 sends an emergency signal, and control console 25 controls inflatable expansion of inner safety airbag 28 and outer safety airbag 29 according to the emergency signal.
[0036] Working principle: when the aircraft is flying normally, the personnel sits on the buffer seat 24 in the plexiglass shell 21, the four propellers on the quadcopter assembly 1 rotate to provide upward lift, when the lift is greater than the overall weight of the aircraft, the aircraft takes off, by adjusting the rotating speed of each propeller on the quadcopter assembly 1, the resultant force is formed to control the horizontal or vertical movement of the aircraft in the air, when the aircraft is running normally, the height sensor 32 obtains the height of the aircraft from the water surface in real time, the maximum flight height of the aircraft can be set to ensure flight safety.
[0037] When the aircraft fails and falls, the acceleration sensor 23 sends an emergency signal, the console 25 controls the inflation of the inner safety air bag 28 and the outer safety air bag 29 according to the emergency signal, protects the safety of the personnel in the plexiglass shell 21, at the same time, the console 25 obtains the position information of the manned cabin 2 through the satellite positioning device 26, and contacts the ground through the satellite communication device 27 to obtain rescue.
[0038] When the aircraft is insufficient in power or needs to implement forced landing on the water surface due to other reasons, the console 25 sends the inflation instruction to the inflatable air cushion 33 to form the inflated air cushion, the aircraft lands on the water surface in a normal posture, and the aircraft floats on the water surface, at the same time, the console 25 obtains the position information of the manned cabin 2 through the satellite positioning device 26, and contacts the ground through the satellite communication device 27 to obtain rescue, thereby improving the safety of the aircraft during landing.
[0039] The above are preferred embodiments of the utility model, and do not limit the protection scope of the utility model, so that: equivalent changes made according to the structure, shape and principle of the utility model should be covered in the protection scope of the utility model.
Claims
1. A low-altitude manned watercraft, comprising a manned cabin (2), characterized in that: The top of the manned cabin (2) is provided with a quadcopter assembly (1), the bottom of the manned cabin (2) is provided with a support assembly (3), the manned cabin (2) includes an plexiglass shell (21), a cushioned seat (24) is installed inside the plexiglass shell (21), a console (25) is installed inside the plexiglass shell (21) near the cushioned seat (24), and an inner airbag (28) and an outer airbag (29) are installed on the inner and outer sides of the plexiglass shell (21), respectively.
2. The low-altitude manned watercraft according to claim 1, characterized in that: The plexiglass shell (21) has a spherical structure.
3. The low-altitude manned watercraft according to claim 1, characterized in that: The inner wall of the plexiglass shell (21) is connected to several high-strength structural components (22).
4. A low-altitude manned watercraft according to claim 1, characterized in that: An accelerometer (23) is installed inside the plexiglass shell (21) near the end of the cushion seat (24), and the output of the accelerometer (23) is electrically connected to the input of the console (25).
5. A low-altitude manned watercraft according to claim 1, characterized in that: The top of the console (25) is equipped with a satellite positioning device (26) and a satellite communication device (27).
6. A low-altitude manned watercraft according to claim 1, characterized in that: The support assembly (3) includes a landing support (31), which is installed at the bottom of the plexiglass shell (21). The landing support (31) has several inflatable air cushions (33) connected to the side of the landing support (31) away from the plexiglass shell (21). The number of inflatable air cushions (33) is four.
7. A low-altitude manned watercraft according to claim 6, characterized in that: A height sensor (32) is installed on the landing support (31), and the output of the height sensor (32) is electrically connected to the input of the control console (25).