A multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft

Abstract

A multi-rotor aircraft arm is designed as a fold-able fixed-wing aircraft, which comprises a multi-rotor flight system, a folded fixed-wing flight system, a cabin (10), a chassis, etc. Multi-rotor aircraft arm which the cabin is connected with both sides also is a folded fixed-wing (2). The chassis includes the frame (1), the rotor flight system and the ground walking system. The top of the machine adopts an inflatable low cost parachute, the bottom adopts an anti-fall safety facility, the wing is provided with an anti-collision radar, and the front is provided with a micro laser ranging radar, and the use is safe and reliable. The structure of the invention adopts carbon fiber material, which makes the weight light. The aircraft has the characteristics of reasonable structure, shrinkage and folding, small volume, light weight, high controllability, low cost, safety and reliability, and high intelligence degree.

Description

A multi-rotor aircraft arm is designed as a foldable fixed-wing aircraftTechnical Field

[0001] The invention relates to the technical field of a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft.Background Art

[0002] The traditional means of family travel are generally public transportation and family cars, and congestion and traffic jams have become the norm in cities, especially in big cities. With the continuous progress of science and technology, people's living standards are also constantly improving, so people have a higher pursuit of leisure life and travel quality, manned plane travel, flight experience, special scenic spots flight sightseeing and aerial photography, etc., have always been a pursuit of high-quality life. In recent years, with the rapid development of aircraft technology, various types of aircraft continue to emerge, especially the application of small manned aircraft, more and more become the focus of research.

[0003] The existing aircraft are mainly divided into two categories: fixed-wing and rotary-wing. The traditional fixed-wing aircraft has the advantages of high speed and low energy consumption, but the wing structure is not strong enough to be damaged easily, the take-off and landing requirements are high, and the landing distance is long. Rotary-wing aircraft has the advantages of convenient take-off and landing, but it has some disadvantages such as high energy consumption, low safety factor, poor load capacity, slow horizontal flight speed and easy crash. The traditional manned aircraft is expensive and has high takeoff and landing requirements. When flying at high altitude, if an emergency occurs, the safety of the crew cannot be guaranteed, and manned aircraft are not being promoted to replace the family car.Technical Solution

[0004] The main purpose of the invention is to propose a household small manned aircraft with retraction and folding, high intelligence, small size, light weight, high maneuverability, low risk factor, safety and reliability, and low cost. In order to realize the purpose of the invention, the invention provides a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft, including multi-rotor flight system, folding fixed-wing flight system, cabin, chassis, etc. The cabin is provided with a battery module, a seat and an intelligent control system. The cabin is provided with an upper opening door or a window in front of the cabin , an inflatable low-cost parachute in the cabin, and a reserve door, a rear window or an upper opening door behind the cabin. The cabin is symmetrically equipped with a multi-rotor flight system and a folded fixed-wing flight system on both sides, Multi-rotor aircraft arm which the cabin is connected with both side also is a folded fixed-wing; The folded fixed-wing flight system comprises a folded fixed wing, a telescopic rod, a horizontally propelled rotor motor and a rotor; The multi-rotor flight system comprises a multi-rotor arm, a motorand a rotor. The chassis is under the cabin, including the frame, the rotor flight system and the ground driving system. The rotor flight system comprises four arm , four motor and rotor .The bottom of the frame is provided with anti-fall safety facilities and tire support legs, and tire support legs are equipped with spring buffer and force spring sensor; The front of the frame is provided with a miniature laser ranging radar.

[0005] Preferably, a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft is characterized by retractable folding, specifically:

[0006] The contraction of the telescopic rod  can make the fixed wing and the arm move up or down, can make the fixed wing and the rotor fold up or down, and the expansion process is opposite to the contraction process;

[0007] Preferably, a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft adopts a small manned aircraft inflatable low-cost parachute on the top, a small manned aircraft anti-fall safety facilities on the bottom, the wing is provided with an anti-collision radar, and the front is provided with a miniature laser ranging radar, making the use of safety more reliable.

[0008] Preferably, most of the structural parts of a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft frame, fixed wing, cabin and other manned aircraft are made of carbon fiber materials, and the structural parts are hollow structures, the compressive end of the carbon fiber material is thicker, the tension end of the carbon fiber material is thinner, reducing the material used to reduce the weight of the whole machine. Manned aircraft as a whole has the characteristics of light weight.

[0009] Preferably, the base of a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft frame is provided with a tire support leg, which is equipped with a spring buffer device and a force spring sensor. When a manned aircraft lands, the tire and spring buffer device can reduce the impact force on the ground, and transmit the force data of the loaded spring sensor to the control center to control the rotation speed and descent speed of the rotor flight system, so as to make the landing more stable. After landing, the ground driving motor drives the tire rotation, which makes the small manned aircraft drive to the indoor hangar and park, and the manned aircraft has the characteristics of stronger applicability.

[0010] Preferably, the ground driving and flight process of a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft is as follows: start the ground driving system to drive from the underground airport to the empty square where it can take off; The fixed-wing and rotary-wing arms are extended respectively. Start the rotor flight system to take off vertically; After rising to a certain height, the rotor motor of the fixed wing flight system is started for horizontal flight, and the rotor flight system properly starts the auxiliary lifting and turning, and provides flight stability; After flying over the destination, start the rotor flight system and stop the rotor motor of the fixed wing flight system; And then we land; After landing on the ground, the retracted fixed-wing and rotary-wing arms are folded; Start the ground driving system and drive to the stop position.

[0011] Preferably, a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft intelligent control system comprises a control terminal, a start-up test system, a safety system, an intelligent driving system, an air management system, a camera system, and other components.

[0012] Preferably, a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft air traffic management system comprises a hardware system and a software system, wherein the hardware system comprises a mobile phone communication card or satellite communication card system to realize real-time data communication between the small manned aircraft and the air traffic management center through the mobile phone communication system or satellite communication system; The software system includes air application, emergency application and accident declaration. The air application refers to the application of the data obtained by the intelligent driving system to the air traffic management center before takeoff, the approval of the air channel or the air field, and the monitoring at any time; Emergency application refers to the small manned aircraft in the flight process of abnormal weather, change the flight destination and other circumstances need to change the flight route, to the air traffic management center to re-apply for air access or air field approval, and to monitor at any time; Accident declaration refers to the situation in which a small manned aircraft accidentally crashes and opens its parachute during flight. The small manned aircraft will intelligently send the affected airspace location to the air traffic management Center at any time, and the air traffic management center will control the aircraft in this field and adjust the aircraft routes that affect the flight. The control of manned aircraft by the air traffic management center is more intelligent and simple.Advantageous Effects

[0013] The invention has the characteristics of reasonable structure, retractable folding, high maneuverability and low cost, and fills the gap of domestic manned aircraft;

[0014] The top of the aircraft is provided with a parachute, the bottom of the aircraft is provided with anti-fall safety facilities, the wing is provided with anti-collision radar, the front is provided with a micro laser ranging radar, safe and reliable use;

[0015] Most of the structure of the invention adopts carbon fiber material, which has the characteristics of small volume and light weight;

[0016] The rotor arm of the invention is shared with the fixed wing, which makes the structure simpler and the weight lighter;

[0017] The invention is composed of a control terminal, a start-up test system, a safety system, an intelligent driving system, an air management system, a camera system, and other components, and has a very high degree of intelligence.Description of Drawings

[0018] 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;

[0019] FIG. 1 is a schematic diagram of the overall main view structure of the invention;

[0020] FIG. 2 is a schematic diagram of the rear-view structure of the invention;

[0021] FIG. 3 is a folding diagram of the rear-view fixed wing of the invention;

[0022] Figure 4 is a schematic diagram of the tire leg structure of the invention;

[0023] FIG. 5 is a schematic diagram of ground driving, flight and lifting operation of the invention;

[0024] FIG. 6 is a schematic diagram of the control system structure of the invention;

[0025] 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

[0026] 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.

[0027] 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.

[0028] 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.

[0029] 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 Applicability1

[0030] Referring to FIG. 1, FIG. 2, FIG. 3 industrial application of the invention provide a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft, which comprises multi-rotor flight system, folding fixed-wing flight system, cabin, chassis, etc. The cabin 10 is provided with a battery module, a seat 8 and an intelligent control system. The cabin 10 is provided with an upper opening door 7 or a window 11 in front of the cabin 10, an inflatable low-cost parachute 9 in the cabin 10, and a reserve door 4, a rear window 11 or an upper opening door 7 behind the cabin 10. The cabin10 is symmetrically equipped with a multi-rotor flight system and a folded fixed-wing flight system on both sides, Multi-rotor aircraft arm2 which the cabin10 is connected with both side also is a folded fixed-wing2; The folded fixed-wing flight system comprises a folded fixed wing2, a telescopic rod13, a horizontally propelled rotor motor and a rotor12; The multi-rotor flight system comprises a multi-rotor arm2, a motor3 and a rotor4.

[0031] The chassis is under the cabin 10, including the frame 1, the rotor flight system 2 and the ground driving system. The bottom of the frame 1 is provided with anti-fall safety facilities and tire support legs 5, and tire support legs 5 are equipped with spring buffer and force spring sensor 6; The front of the frame 1 is provided with a miniature laser ranging radar.

[0032] Preferably, a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft, which is characterized by retractable folding, specifically: The contraction of the telescopic rod13 can make the fixed wing and the arm2 move up or down, can make the fixed wing2 and the rotor4 fold up or down, and the expansion process is opposite to the contraction process;

[0033] Preferably, a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft inflatable low-cost parachute 9, which has the characteristics of short opening time, high temperature resistance, high strength, light weight and low cost. The bottom of the aircraft adopts a small manned aircraft anti-fall safety facilities. The manned aircraft falls from a height of 5 meters due to accidental failure, the parachute can not fully play a role, and the speed of reaching the ground is 35.64 km / h, which prevent to cause personnel injury and aircraft damage; Fall from a height of 50 meters, reach the ground speed of 112.7 km / h, prevent to cause serious injury or death. The wing is equipped with anti-collision radar, and the front is equipped with a micro laser ranging radar, which is safer and more reliable.

[0034] Preferably, most of the structural parts of a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft frame 1, fixed wing2, cabin 10 and other manned aircraft are made of carbon fiber materials, and the structural parts are hollow structures, the compressive end of the carbon fiber material is thicker, the tension end of the carbon fiber material is thinner, and the material is reduced to reduce the weight of the whole machine. Manned aircraft as a whole has the characteristics of light weight.

[0035] Referring to FIG. 1,FIG.4,Preferably, a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft frame 1 is provided with a tire leg 6001 at the bottom, and the tire leg 6001 is provided with a spring buffer device and a force spring sensor 6002. When the manned aircraft lands, the tire 6001 and the spring buffer device 6002 can reduce the impact force on the ground, and at the same time transmit the force data of the stress spring sensor 6002 to the control center to control the rotation speed and descent speed of the rotor flight system 2, so as to make the landing more stable; After landing, the ground driving motor drives the tire 6001 to rotate, so that the small manned aircraft can drive to the indoor hangar and park, and the manned aircraft has the characteristics of stronger applicability.Industrial Applicability2

[0036] As shown in Figure 5, the invention also provides a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft for ground driving and flight process including the following steps:

[0037] In this embodiment, preferably, step 1), start the ground driving system 8001 to drive from the underground airport to the empty plaza where takeoff is possible;

[0038] In this embodiment, further, preferably, step 2), respectively extend the fixed-wing and rotary-wing arms in an extended state;

[0039] In this embodiment, further, and optimally, step 3), start the rotor flight system 8002 for vertical takeoff;

[0040] In this embodiment, further, preferably, step 4), after a certain altitude, start the rotor motor of the fixed wing flight system 8003 for horizontal flight, and the rotor flight system 8002 appropriately starts the auxiliary lifting and turning, and provides flight stability;

[0041] In this embodiment, further, and optimally, step 5), start the rotor flight system 8002 and stop the rotor motor of the fixed wing flight system 8003 after flying over the destination;

[0042] In this embodiment, further, preferably, step 6), the landing is carried out;

[0043] In this embodiment, further, preferably, step 7), after landing on the ground, the fixed wing is contracted to a folded state, and then the rotary wing arm is contracted to a folded state;

[0044] In this embodiment, further, preferably, step 8), start the ground driving system 8001 to drive to the stop position.Industrial Applicability3

[0045] As shown in Figure 6, the invention also provides a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft intelligent control system 9000, which comprises a control terminal, a start-up test system 9100, a safety system 9200, an intelligent driving system 9300, an air management system 9400, a camera system 9500, and other 9600. The start-up test system 9100 includes extended rotor system 9101, extended fixed wing 9102, test rotary arm motor 9103 and test horizontal motor 9104; The safety system 9200 includes ejection parachute 9201, ejection anti-fall safety setting 9202, collision avoidance 9203; The intelligent driving system 9300 includes automatic lifting 9301, automatic driving 9302, automatic cruise 9303, automatic landing 9304, ground driving 9305, one-button return 9306 and other intelligent driving systems; The camera system 9500 includes switching lens 9501, designated video 9502, automatic video 9503; The other 9600 includes lighting 9601, positioning 9602, environmental control 9603, etc. The manned aircraft has the characteristics of a high degree of intelligence.

[0046] The present industrial application further, preferably, a multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft air traffic management system 9400 comprises a hardware system and a software system, wherein the hardware system comprises a mobile phone communication card or satellite communication card system. To realize the small manned aircraft real-time data communication with the air traffic management center through the mobile phone communication system or satellite communication system; The software system includes air application 9401, emergency application 9402, accident declaration 9403. The air application 9401 refers to the application of the data obtained by the intelligent driving system to the air traffic management center before takeoff, the approval of the air channel or the air field, and the monitoring at any time; Emergency application 9402 refers to the small manned aircraft in the course of flight weather anomalies, change the flight destination and other circumstances need to change the flight path, to the air traffic management center to re-apply for air access or air field approval, and to monitor at any time; Accident declaration 9403 refers to the situation in which a small manned aircraft accidentally crashes and opens its parachute during flight. The small manned aircraft will intelligently send the affected airspace location to the air traffic management Center at any time, and the air traffic management center will control the aircraft in this field and adjust the aircraft routes that affect the flight. The control of manned aircraft by the air traffic management center is more intelligent and simple.

[0047] 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

1. A multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft, which is characterized in that the cabin (10) is symmetrically equipped with a multi-rotor flight system and a folded fixed-wing flight system on both sides, Multi-rotor aircraft arm(2) which the cabin(10) is connected with both side also is a folded fixed-wing(2).

2. A multi-rotor aircraft arm is designed as a foldable fixed-wing aircraft can be contracted and folded, specifically: the contraction of the telescopic rod (13) can make the fixed wing and the aircraft arm (2) move up or down, can make the fixed wing and the rotor fold up or down, the expansion process is opposite to the contraction process.

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