WO2023246948A1

WO2023246948A1 - A new folding convenient manned aircraft

Info

Publication number: WO2023246948A1
Application number: PCT/CN2023/107631
Authority: WO
Inventors: Hengzhi SU
Original assignee: SU, Wu
Priority date: 2022-06-24
Filing date: 2023-07-17
Publication date: 2023-12-28
Also published as: CN114954896A

Abstract

A new foldable convenient manned aircraft comprises a fuselage, four arms arranged on the fuselage, a rotor motor, a rotor and an anti-collision radar which are symmetrically arranged on the outer end of each arm, four anti-collision airbags and four support legs fitted with stress spring sensors which are provided at the bottom of the fuselage, a control system and a micro laser ranging radar which are provided in front of the fuselage, a seat box and a plastic film hood which are located on the fuselage, a battery box which is in the seat box and a parachute which is on top of the canopy.

Description

a new folding convenient manned aircraft

Technical Field

The invention relates to the technical field of manned aircraft, in particular to a new folding convenient manned aircraft.

Background Art

With the continuous progress of science and technology, people's living standards are also constantly improving, so people have a higher pursuit of the quality of leisure life, manned aircraft travel, flight experience and aerial photography have always been a pursuit of high-quality leisure life. The existing manned aircraft models are large, occupy a large area, loud noise, low maneuverability, high risk factor, low intelligence, and expensive, which not only affects the quality of travel and aerial photography, but also is not easy to transport and promote.

Content of invention

The invention mainly aims at providing a convenient folding type, small volume, light weight, high controllability, low risk factor, high intelligence and low cost manned aircraft in view of the shortcomings of the existing manned aircraft.

In order to realize the purpose of the invention, the invention provides a new folding convenient manned aircraft, which comprises four arms arranged on the fuselage, and a rotor motor, a rotor and an anti-collision radar are symmatically arranged on the outer end of each arm. The bottom of the fuselage is provided with four anti-collision airbags and four support legs, which are equipped with stress spring sensors; The front of the fuselage is equipped with a control system and a micro laser ranging radar; The body is provided with a seat box and a plastic film hood; A battery box is provided in the seat box; The canopy is topped with a parachute.

Preferably, the arms, rotors, support legs, seat box frame and canopy frame of the new folding convenient manned aircraft are all made of carbon fiber materials to reduce the weight of the whole machine.

Preferably, the canopy of the new folding convenient manned aircraft adopts a plastic film, and the plastic film canopy is provided with a zipper.

Preferably, the connection between the four arms and the fuselage and the connection between the four support legs and the fuselage of the new folding convenient manned aircraft is hinged, and the hinged is provided with an upper limit positioner and a spring clip positioner.

Preferably, the seat box frame and canopy frame of the new folding convenient manned aircraft can be shrunk and folded through the spring buckle to reduce the space occupied by the whole machine.

Preferably, the control system (9) of the novel folding convenient manned aircraft consists of a control terminal, a lighting device, a GPS (Beidou) positioning device, a safety control system, a collision avoidance control system, an intelligent driving system and a cabin environmental control system.

Advantageous Effects

The invention has the advantages of reasonable structure, strong practicability, convenient folding, small volume, light weight, high controllability, low cost, and safe and reliable use;

There is a parachute on the top of the aircraft, and when the system detects abnormal wing work, the parachute will automatically pop out. At the same time, the four support legs at the bottom of the aircraft are equipped with a force spring sensor. When the pressure is greater than the normal value, the four anti-collision airbags at the bottom of the fuselage will pop out within 0.1 seconds to prevent personnel injury;

The invention provides a wing anti-collision radar and a front micro-laser ranging radar to improve the automatic avoidance anti-collision system during flight;

The invention provides an intelligent driving system such as automatic rise, automatic driving, automatic cruise, automatic landing, one-click return, etc.

Description of Drawings

In order to more clearly state the technical scheme in the embodiment of the invention or the prior art, the following is a brief introduction of the drawings required to be used in the description of the embodiment or the prior art. It is obvious that the drawings described below are only some embodiments of the invention. For ordinary technicians in the field, without creative labor, Other drawings can also be obtained according to the structure shown in these drawings;

FIG. 1 is a schematic diagram of the overall main view structure of the invention;

Figure 2 is a schematic diagram of the carbon fiber skeleton structure of the invention;

FIG. 3 is the structure diagram of the fuselage, arm and rotor of the invention;

FIG. 4 shows the structure diagram of the fuselage and the articulating detail of the arm of the invention;

FIG. 5 is the detailed structure diagram of the fuselage skeleton spring buckle of the invention;

FIG. 6 is a schematic diagram of the safety control system of the invention;

FIG. 7 is the structure diagram of the anti-collision control system of the invention;

Figure 8 is the structure diagram of the intelligent driving system of the invention;

The realization of the purpose, functional characteristics and advantages of the invention will be further explained in conjunction with embodiments and with reference to the attached drawings.

Best Mode

The following is a clear and complete description of the technical scheme in the embodiment of the invention in combination with the drawings attached to the embodiment of the invention. Obviously, the embodiment described is only a part of the embodiment of the invention, but not the whole embodiment. Based on the embodiments of the invention, all other embodiments obtained by ordinary technicians in the field without creative labor fall within the scope of protection of the invention.

It should be noted that all directional indications in embodiments of the invention (such as up, down, left, right, front, back...) It is only used to explain the relative position relationship and motion between the components in a specific attitude (as shown in the attached figure). If the specific attitude changes, the directional indication will also change accordingly.

In the present invention, unless otherwise expressly specified and limited, the terms "connection", "fixed", etc. shall be understood in a broad sense, for example, "fixed" may be a fixed connection, a detachable connection, or a whole; Can be mechanical connection, can also be electrical connection; It can be directly connected, it can be indirectly connected through an intermediate medium, it can be a connection within two components or an interaction between two components, unless otherwise explicitly defined. For ordinary skilled persons in the art, the specific meaning of the above terms in the present invention can be understood according to the specific circumstances.

In addition, descriptions in the present invention that refer to "first", "second", etc., are used for descriptive purposes only and are not to be understood as indicating or implying their relative importance or as implicitly indicating the quantity of the technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the features. In addition, the technical schemes between the embodiments can be combined with each other, but must be based on the realization of ordinary technical personnel in the field. When the combination of technical schemes is contradictory or cannot be realized, it shall be considered that such combination of technical schemes does not exist and is not within the scope of protection required by the invention.

Industrial Applicability 1

The invention provides a new folding convenient manned aircraft.

Referring to FIG. 1, FIG. 2 and FIG. 3, in embodiments of the invention, the new folding convenient manned aircraft comprises four arms 2 arranged on the fuselage 1, and the outer ends of each arm are symmetrically provided with rotor motor 3, rotor 4 and anti-collision radar 5 respectively. The bottom of the fuselage is provided with four anti-collision airbags 6 and four support legs 7, the support legs are equipped with a force spring sensor 8; The front of the fuselage is equipped with a control system 9 and a micro laser ranging radar 10; The body is provided with a seat box 11 and a plastic film hood 12; The seat box is equipped with a battery box 13; The canopy is topped with a parachute 14.

In this embodiment, preferably, the said new folding convenient manned aircraft is characterized by the use of carbon fiber materials for arms 2, rotors 4, support legs 7, seat boxes 11 and canopy 12, reducing the weight of the whole machine.

In this embodiment, further, and preferably, the novel folding convenient manned aircraft is characterized in that the canopy 12 adopts a plastic film and the plastic film canopy 12 is provided with a zipper 15.

In the present embodiment, further, and optimally, the novel folding convenient manned aircraft is characterized in that the connection of four arms 2 with the fuselage 1 and the connection of four support legs 7 with the fuselage 1 are connected by an hinged 16, and the hinged 16 is provided with an upper limit positioner 17 and a spring snap-snap positioner 18.

In this embodiment, further, preferably, the novel folding convenient manned aircraft is characterized in that the seat box frame 11 and the canopy frame 12 can be shrunk and folded through the spring buckle 19-25 to reduce the space occupied by the whole machine.

In this embodiment, preferably, the new folding convenient manned aircraft is characterized in that the control system 9 consists of a control terminal, a lighting device, a GPS (Beidou) positioning device, a safety control system, a collision avoidance control system, an intelligent driving system and a cabin environmental control system.

Industrial Applicability 2

Referring to FIG. 2, FIG. 3, FIG. 4 and FIG. 5, the invention provides a new folding convenient manned aircraft, and the folding process comprises the following steps:

Step 1) Take out the battery box 13 from the sitting box 11. The battery box consists of 3-5 cells and is equipped with 3-5 battery packs;

Step 2), hold down the spring buckle 19 and 23, and shrink the carbon fiber frame of fuselage 1 to the left, narrowing the length by 30cm;

Step 3), hold down the spring buckle 22 and 25, shrink the carbon fiber frame of the fuselage 1 downward, and reduce the height by 40cm;

Step 4), hold down the spring buckle 20, 21 and 24, shrink the carbon fiber frame of the fuselage 1 downward, and reduce the height by 40cm;

Step 5), turn the top and bottom of the manned aircraft fuselage 1, and fix the aircraft rotor 4 with a rubber band;

Step 6), hold down the spring buckle 18 of the four arms 2, turn the four arms 2 upward to the chassis of the fuselage 1;

Step 7), hold down the spring buckle 18 of the four support legs 7, turn the four support legs 7 upward to the chassis of the fuselage 1;

Step 8) Lift the aircraft into the trunk of the car and transport it to the destination;

In this embodiment, the steps for opening the aircraft are preferably the opposite of the steps for folding.

Industrial Applicability 3

As shown in FIG. 1 and FIG. 6, the invention also provides a new folding convenient manned aircraft safety control system, including the following steps.

In this embodiment, preferably, step 1), the control system 6000 monitors the data returned by each sensor at any time, and when the aircraft rotor 4 is abnormal, the aircraft rotor sensor 6002 sends a signal back, and the control system 6000 treats it as an anomaly and sends a parachute ejection signal to the parachute system 14, ejecting the parachute 6004.

In this embodiment, further, preferably, step 2), if there is an abnormal ejection of parachute 6004, it can be controlled manually, and the emergency button for ejection of parachute is set on the control panel, and the control system 6000 handles it and sends the ejection signal to the parachute system 14, ejecting parachute 6004.

In this embodiment, further, and optimally, step 3), the control system 6000 monitors the data returned by each sensor at any time. When the four supporting legs 7 of the aircraft land, the force sensor of the supporting leg spring (6001) sends the force data back to the control system 6000. In case of a fall, the force data will be too large, and the control system 6000 will judge it as abnormal. Send out the anti-collision airbag signal, the anti-collision airbag system receives the signal, the anti-collision airbag signal 6003 will pop up in 0.1 seconds.

Industrial Applicability 4

As shown in Figure 7, the invention also provides a novel folding convenient manned aircraft automatic collision avoidance control system, which comprises the following steps:

In this embodiment, preferably, step 1), the control system 7000 monitors the data returned by each aircraft rotor anti-collision radar 7002 at any time. When there is an abnormal distance between the aircraft rotor 4 and the obstacle, the aircraft rotor anti-collision radar 7002 sends back a signal, and the control system 7000 processes it as an anomaly. According to the distance data of the four aircraft rotor anti-collision radars, Make the best avoidance plan, send a signal to avoid collision 7004.

In this embodiment, further, preferably, step 2), the control system 7000 monitors the data returned by the micro laser ranging radar 7001 in the forward direction at any time, and the range of the micro laser ranging radar 7001 is greater than 500 meters to ensure the safety avoidance distance of high-speed movement collision avoidance. Based on the data, determine whether the obstacle ahead is stationary or moving. If it is a moving object, advance collision avoidance 7003 according to the speed of movement and the size of the object. If it is a stationary object, it will carry out forward collision avoidance 7003 according to GPS, Beidou positioning and three-dimensional map data to make the optimal flight path.

Industrial Applicability 5

As shown in Figure 8, the invention also provides a new folding convenient manned aircraft, which is equipped with an intelligent driving system such as automatic lifting, automatic driving, automatic cruise, automatic landing and one-click return, including the following steps:

In this embodiment, preferably, step 1), function module 8001 of intelligent driving system 8000 contains functions such as automatic lifting 8002, automatic driving 8003, automatic cruise 8004, automatic landing 8005, one-click return 8006, etc.

In this embodiment, further, preferably, step 2), automatic raising 8002 consists of three steps, the first step is to set a raising height 8007, the default is 1 meter, set to 3 meters; Step 2 Set the number of raises to 8011, the default is 1, set to 2. After the third step is set, if the aircraft stops on the ground, click the automatic raise 8002 button, then the rotor of the aircraft will automatically start, slowly raise 3 meters ×2=6 meters, hover after reaching the target height, and set the raise frequency 8011 to restore to the default once. If you feel that the height is not enough, click the automatic rise 8002 once to raise 3 meters, and click many times to raise 3 meters.

In this embodiment, further, preferably, step 3), automatic driving 8003 consists of three steps, the first step is set to pass through point A 8008; Step 2 Set the end point B 8012. In theory, the take-off point, passing through point A and the straight flight route of point B will be selected, but due to the difference in altitude, the intelligent driving system 8000 will calculate according to GPS, Beidou positioning and three-dimensional map data to select the optimal flight height and route. After the third step is set, you only need to click automatic pilot 8003, if the aircraft does not take off, the aircraft slowly rises from the take-off point to the flight height; If it is hovering, it passes through point A according to the optimal flight height and route, reaches the end point B, and then hovers.

In this embodiment, further, preferably, step 4), automatic cruise 8004 consists of three steps, the first step is to set the cruise radius 8009, the default is 5 meters, set to 10 meters; Step 2 Set the cruise speed 8013, the default is slow, set to medium speed. After the third step is set up, you only need to click automatic cruise 8004, the aircraft from the hover of 10 meters radius, moderate speed cruise one circle, return to the original hover point to continue to hover.

In this embodiment, further, preferably, step 5), automatic landing 8005 consists of three steps, the first step is set a landing height 8010, the default is 1 meter, set to 3 meters; Step 2 Set the number of landings to 8014, the default is 1, set to 2. After the third step is set, click the automatic landing 8005 button, then the plane will land 3 meters ×2=6 meters, hover after reaching the target altitude, and set the number of landings 8014 to restore to the default once. If the ground height is less than 6 meters, the intelligent driving system 8000 controls the descent speed according to GPS, Beidou positioning and three-dimensional map data, then the force sensor 8 of the support leg spring will contact the ground and send the force data back to the intelligent driving system 8000. The intelligent driving system 8000 will automatically adjust the flight attitude and land smoothly. If you feel that the altitude still needs to drop, drop 3 meters every time you click the automatic landing 8005 until you reach the target hovering altitude or a smooth landing.

In this embodiment, further, preferably, step 6), if you click the one-button to return to the 8006 button, the intelligent driving system 8000 will retrieve the take-off point and flight data according to the historical records stored in this flight, make calculations with reference to GPS, Beidou positioning and three-dimensional map data, select the fastest and optimal flight altitude and route, return to the take-off point and land smoothly.

The above is only the preferred embodiment of the invention, and does not therefore limit the scope of the patent of the invention. Under the premise of not deviating from the spirit and scope of the invention, the invention will also have various changes and improvements. Under the invention idea, the equivalent structure transformation made by the specification of the invention and the content of the drawings is used. Or directly/indirectly used in other related technical fields are included in the scope of patent protection of the invention.

Claims

A new folding convenient manned aircraft is characterized in that it comprises four arms (2) arranged uniformly on the fuselage (1), and a rotor motor (3), a rotor (4) and an anti-collision radar (5) are symmatically arranged at the outer end of each arm; The bottom of the fuselage is provided with four anti-collision airbags (6) and four support legs (7), which are equipped with a force spring sensor (8); The front of the fuselage is provided with a control system (9) and a micro laser ranging radar (10); The body is provided with a seating box (11) and a plastic film hood (12); A battery box is provided in the cushion case (13); The canopy is topped with a parachute (14).
According to claim 1, a new folding convenient manned aircraft is characterized in that the arms (2), rotors (4), support legs (7), seat box (11) and canopy (12) are made of carbon fiber materials to reduce the weight of the whole machine.
A new folding convenient manned aircraft described in claim 1 is characterized in that the canopy (12) is made of plastic film and the plastic film canopy (12) is provided with a zipper (15).
A new folding convenient manned aircraft described in claim 1 is characterized in that four arms (2) are connected to the fuselage (1), and four support legs (7) are connected to the fuselage (1), all connected by a hinge (16), and the hinge (16) is provided with an upper limit (17) and a spring-snap snap locator (18).
According to claim 1, a new folding convenient manned aircraft is characterized in that the seat box (11) and the canopy (12) can be shrunk and folded through the spring buckle (19-25) to reduce the space occupied by the whole machine.
A new folding convenient manned aircraft described in claim 1 is characterized in that the control system (9) consists of a control terminal, a lighting device, GPS, a Beidou positioning device, a safety control system, a collision avoidance control system, an intelligent driving system and a cabin environmental control system.
A new folding convenient manned aircraft safety control system described in claim 6 comprises a control system (6000), an aircraft rotor sensor (6002), an ejection parachute (6004), a support leg spring force sensor (6001), and an ejection anti-collision airbag signal (6003).
According to claim 6, a new folding convenient automatic collision avoidance control system for manned aircraft, including package control system (7000), rotor collision avoidance radar (7002), collision avoidance left and right (7004), micro laser ranging radar (7001), and forward collision avoidance (7003).
A new foldable and convenient manned aircraft described in claim 6 includes the function module (8001) of the intelligent piloting system (8000), which includes automatic lifting (8002), automatic piloting (8003), automatic cruise (8004), automatic landing (8005), one-click return (8006), etc.