Aircraft with multi-rotor arms designed into foldable fixed wings

Abstract

The invention discloses an aircraft with a multi-rotor arm designed into a foldable fixed wing, which comprises a multi-rotor flight system, a foldable fixed wing flight system, a cabin, a chassis and the like, and the multi-rotor arm and the foldable fixed wing are connected with the cabin; the chassis comprises a rack, a rotor wing flight system and a ground walking system. The top of the aircraft adopts an inflatable low-cost parachute, the bottom of the aircraft adopts an anti-falling safety facility, the wings are provided with anti-collision radars, and the front is provided with a miniature laser ranging radar, so that the aircraft is safe and reliable to use. The structural part is made of the carbon fiber material, so that the weight is light. The retractable folding electric vehicle has the characteristics of reasonable structure, retractable folding, small size, light weight, high controllability, low cost, safety, reliability and high intelligent degree.

Description

Technical Field

[0001] The invention relates to the technical field of domestic manned aircraft, and more specifically to an aircraft in which a multi-rotor aircraft arm is designed to be a foldable fixed-wing aircraft. Background Art

[0002] Traditional family travel tools are generally public transportation and family cars. Crowding and traffic jams have become the norm in cities, especially in large cities. With the continuous advancement of science and technology, people's living standards are also constantly improving, so people have higher pursuits for the quality of leisure life and travel. Manned aircraft travel, flight experience, special scenic spot flight sightseeing and aerial photography have always been a pursuit of high-quality life. In recent years, aircraft technology has developed rapidly, and various types of aircraft have continued to emerge, especially the application of small manned aircraft, which has become more and more a hot topic of research.

[0003] Existing aircraft are mainly divided into two categories: fixed-wing and rotary-wing. Traditional fixed-wing aircraft have advantages such as high speed and low energy consumption, but the wing structure is not strong and easy to damage, high take-off and landing requirements, long take-off and landing distance and other disadvantages; rotary-wing aircraft have the advantage of convenient take-off and landing, but have disadvantages such as high energy consumption, low safety factor, poor load capacity, slow horizontal flight speed, and easy crash. Traditional manned aircraft are expensive and have high take-off and landing requirements. When flying at high altitudes, if there is an emergency, the safety of passengers cannot be guaranteed, and they cannot replace the full promotion of family cars. Summary of the invention

[0004] The main purpose of the present invention is to address the shortcomings of existing manned aircraft and to propose a small manned aircraft for household use that is retractable and foldable, highly intelligent, small in size, light in weight, highly maneuverable, low in risk, safe and reliable, and low in cost. In order to achieve the above-mentioned invention purpose, the present invention proposes an aircraft in which a multi-rotor arm is designed as a foldable fixed-wing aircraft, including a multi-rotor flight system, a foldable fixed-wing flight system, a cabin, a chassis, etc. A battery module, a seat (8) and an intelligent control system are arranged in the cabin (10); an upper opening door (7) or a window (11) is arranged in front of the cabin (10); an inflatable low-cost parachute (9) is installed on the cabin (10); a trunk door (4), a rear window (11) or an upper opening door (7) is arranged at the rear of the cabin (10); a multi-rotor flight system and a foldable fixed-wing flight system are symmetrically arranged on both sides of the cabin (10); both the multi-rotor arm (2) and the foldable fixed wing (2) are connected to the cabin (10); The multi-rotor flight system comprises a folding fixed wing (2), a telescopic rod (13), a horizontal propulsion rotor motor and a rotor (12); the multi-rotor flight system comprises a multi-rotor arm (2), a motor (3) and a rotor (4); a chassis is provided under the cabin (10), comprising a frame (1), a rotor flight system (2) and a ground walking system; an anti-fall safety facility and a tire support leg (5) are provided at the bottom of the frame (1); the tire support leg (5) is provided with a spring buffer and a force spring sensor (6); and a micro laser ranging radar is provided in front of the frame (1).

[0005] Preferably, the multi-rotor aircraft with a foldable fixed-wing designed as an aircraft arm is retractable and foldable, specifically: the telescopic rod (13) is retracted to move the fixed wing and the aircraft arm (2) upward or downward, so that the fixed wing and the rotor can be folded upward or downward, and the unfolding process is opposite to the retracting process; Preferably, the aircraft in which the multi-rotor arms are designed as foldable fixed-wing aircraft has a small manned aircraft inflatable low-cost parachute on the top, a small manned aircraft anti-fall safety facility on the bottom, anti-collision radars on the wings, and a micro laser ranging radar in the front, which is safer and more reliable to use.

[0006] Preferably, most of the structural parts of the manned aircraft such as the frame, fixed wing, and cabin of the multi-rotor aircraft in which the arms of the multi-rotor are designed to be foldable fixed-wing aircraft are made of carbon fiber materials, and the structural parts adopt a hollow structure, the carbon fiber material at the compression end is relatively thick, and the carbon fiber material at the tension end is relatively thin, so that the material usage is reduced to reduce the weight of the whole aircraft, and the manned aircraft as a whole has the characteristics of light weight.

[0007] Preferably, the aircraft frame of the multi-rotor aircraft with foldable fixed-wing arms is provided with tire legs at the bottom, and the tire legs are equipped with spring buffer devices and force spring sensors. When the manned aircraft lands, the tires and spring buffer devices can reduce the impact force on the ground, and at the same time transmit the force data of the force spring sensor to the control center to control the rotation speed and descent speed of the rotor flight system to make the landing smoother; after landing, the ground driving motor drives the tires to rotate, so that the small manned aircraft drives to the indoor hangar for parking, and the manned aircraft has the characteristics of stronger applicability.

[0008] Preferably, the ground driving and flight process of the aircraft in which the multi-rotor arms are designed to be foldable fixed-wings is as follows: start the ground walking system to drive from the underground parking lot to an open space where takeoff is possible; extend the fixed-wing and rotary-wing arms respectively to an unfolded state; start the rotary-wing flight system to take off vertically; after rising to a certain height, start the rotor motor of the fixed-wing flight system to fly horizontally, and the rotary-wing flight system appropriately starts to assist in lifting and turning, and provides flight stability; after flying over the destination, start the rotary-wing flight system and stop the rotor motor of the fixed-wing flight system; then land; after landing on the ground, retract the fixed-wing and rotary-wing arms to a folded state; start the ground walking system to drive to the parking position.

[0009] Preferably, the intelligent control system for an aircraft in which the multi-rotor arms are designed to be foldable fixed-wings comprises a control terminal, a startup test system, a safety system, an intelligent driving system, an air management system, a camera system, and other components.

[0010] Preferably, the air traffic management system for aircraft with multi-rotor arms designed as foldable fixed wings includes a hardware system and a software system, wherein the hardware system includes a mobile phone communication card or a satellite communication card system to enable the small manned aircraft to communicate data with the air traffic management center in real time through the mobile phone communication system or the satellite communication system; the software system includes air application, emergency application, and accident declaration. The air application refers to the data obtained by the intelligent driving system being applied to the air traffic management center before takeoff, obtaining approval of the air channel or air field, and monitoring at any time; the emergency application refers to the small manned aircraft requiring change of flight route due to abnormal weather, change of flight destination, etc. during flight, and re-applying for approval of the air channel or air field from the air traffic management center, and monitoring at any time; the accident declaration refers to the situation where the small manned aircraft accidentally crashes and opens the parachute during flight, and the small manned aircraft will intelligently send the airspace location that may be affected to the air traffic management center at any time, and the air traffic management center will control the aircraft in the field and adjust the aircraft route that affects the flight. The air traffic management center has the characteristics of being more intelligent and simple to control manned aircraft.

[0011] The beneficial effects of the technical solution provided by the present invention are: 1) The present invention has the characteristics of reasonable structure, retractable and foldable, high maneuverability and low cost, and fills the gap of domestic manned aircraft; 2) There is a parachute on the top of the aircraft, anti-fall safety facilities on the bottom of the aircraft, anti-collision radars on the wings, and a micro laser ranging radar in the front, which is safe and reliable to use; 3) Most of the structures of the present invention are made of carbon fiber materials, which are small in size and light in weight; 4) The rotorcraft arm of the present invention is shared with the fixed wing, making the structure simpler and lighter; 5) The present invention is equipped with 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. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained according to the structures shown in these drawings without creative work. Figure 1 It is a schematic diagram of the overall main structure of the present invention; Figure 2 It is a rear view structural schematic diagram of the present invention; Figure 3 This is a rear view schematic diagram of the fixed wing folding of the present invention; Figure 4 This is a schematic diagram of the tire outrigger structure of the present invention; Figure 5 This is a schematic diagram of the ground driving, flying and lifting operation of the present invention; Figure 6 It is a schematic diagram of the structure of the control system of the present invention; The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0013] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0014] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0015] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0016] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention. Example 1

[0017] Reference Figure 1 , Figure 2 , Figure 3In an embodiment of the present invention, a multi-rotor aircraft with a multi-rotor arm designed as a foldable fixed-wing aircraft comprises a multi-rotor flight system, a foldable fixed-wing flight system, a cabin, a chassis, etc. A battery module, a seat (8) and an intelligent control system are arranged in the cabin (10); an upward opening door (7) or a window (11) is arranged in front of the cabin (10); an inflatable low-cost parachute (9) is installed on the cabin (10); a trunk door (4), a rear window (11) or an upward opening door (7) is arranged at the rear of the cabin (10); a multi-rotor flight system and a foldable fixed-wing flight system are symmetrically arranged on both sides of the cabin (10); both the multi-rotor arm (2) and the foldable fixed wing (2) are connected to the cabin (10); The multi-rotor flight system comprises a folding fixed wing (2), a telescopic rod (13), a horizontal propulsion rotor motor and a rotor (12); the multi-rotor flight system comprises a multi-rotor arm (2), a motor (3) and a rotor (4); a chassis is provided under the cabin (10), comprising a frame (1), a rotor flight system (2) and a ground walking system; an anti-fall safety facility and a tire support leg (5) are provided at the bottom of the frame (1); the tire support leg (5) is provided with a spring buffer and a force spring sensor (6); and a micro laser ranging radar is provided in front of the frame (1).

[0018] Reference Figure 3 , Figure 4 Preferably, the multi-rotor aircraft with a foldable fixed-wing designed as the multi-rotor arm is retractable and foldable, specifically: the telescopic rod (13) is retracted to move the fixed wing and the arm (2) upward or downward, so that the fixed wing and the rotor can be folded upward or downward, and the unfolding process is opposite to the retracting process; Preferably, the top of the aircraft with a multi-rotor arm designed as a foldable fixed-wing aircraft adopts a small manned 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 facility. If the manned aircraft falls from a height of 5 meters due to an unexpected malfunction, the parachute cannot fully function and the speed of reaching the ground is 35.64 kilometers per hour. No personal injury or damage to the aircraft will occur; if it falls from a height of 50 meters, the speed of reaching the ground is 112.7 kilometers per hour, and no serious personal injury or death will occur. The wings are equipped with anti-collision radars and the front is equipped with a micro laser ranging radar, which is safer and more reliable to use.

[0019] Preferably, in the manned aircraft in which the arms of the multi-rotor aircraft are designed to be foldable fixed-wing aircraft, most of the structural parts such as the frame (1), fixed wings (13) (15), cabin (10) are made of carbon fiber materials, and the structural parts are hollow structures. The carbon fiber material at the compression end is relatively thick, and the carbon fiber material at the tension end is relatively thin, so that the material usage is reduced to reduce the weight of the whole aircraft, and the manned aircraft as a whole has the characteristics of light weight.

[0020] See also Figure 1 and Figure 4 Preferably, the bottom of the aircraft frame 1 in which the multi-rotor arm is designed as a foldable fixed-wing aircraft is provided with a tire leg 6001, and the tire leg 6001 is equipped 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 force spring sensor 6002 to the control center to control the rotation speed and descent speed of the rotor flight system 2, so that the landing is more stable; after landing, the ground driving motor drives the tire 6001 to rotate, so that the small manned aircraft drives to the indoor hangar for parking, and the manned aircraft has the characteristics of stronger applicability. Example 2

[0021] See also Figure 5 The present invention also proposes a ground driving and flying process of an aircraft in which the arms of a multi-rotor are designed to be foldable fixed-wing aircraft, comprising the following steps: In this embodiment, preferably, in step 1), the ground walking system 8001 is started to travel from the underground parking area to an empty square where take-off is possible; In this embodiment, further, preferably, in step 2), the fixed wing and the rotary wing arms are respectively extended to be in an unfolded state; In this embodiment, further, preferably, step 3), starting the rotor flight system 8002 for vertical takeoff; In this embodiment, further, preferably, in step 4), after ascending to a certain height, the rotor motor of the fixed-wing flight system 8003 is started for horizontal flight, and the rotor flight system 8002 is appropriately started to assist in lifting and turning, and provide flight stability; In this embodiment, further, preferably, in step 5), after flying over the destination, the rotor flight system 8002 is started, and the rotor motor of the fixed-wing flight system 8003 is stopped; In this embodiment, further, preferably, step 6), landing; In this embodiment, further, preferably, in step 7), after landing on the ground, the fixed wing is retracted to a folded state, and then the rotary wing arm is retracted to a folded state; In this embodiment, further, preferably, in step 8), the ground travel system 8001 is started to travel to the parking position. Example 3

[0022] See also Figure 6The present invention also proposes an aircraft intelligent control system 9000 that designs a multi-rotor arm into a foldable fixed-wing aircraft, including a control terminal, a startup test system 9100, a safety system 9200, an intelligent driving system 9300, an air management system 9400, a camera system 9500, and other components 9600. The startup test system 9100 includes extending the rotor system 9101, extending the fixed wing 9102, testing the swing arm motor 9103, and testing the horizontal wing motor 9104; the safety system 9200 includes popping up a parachute 9201, popping up an anti-fall safety setting 9202, and anti-collision avoidance 9203; the intelligent driving system 9300 includes automatic lifting 9301, automatic driving 9302, automatic cruising 9303, automatic landing 9304, ground driving 9305, one-key return 9306 and other intelligent driving systems; the camera system 9500 includes switching lenses 9501, designated recording 9502, and automatic recording 9503; others 9600 include lighting 9601, positioning 9602, environmental control 9603, etc. The manned aircraft has the characteristics of a high degree of intelligence.

[0023] In this embodiment, further, preferably, the aircraft air traffic management system 9400 in which the multi-rotor arms are designed to be foldable fixed-wings includes a hardware system and a software system, wherein the hardware system includes a mobile phone communication card or a satellite communication card system to enable small manned aircraft to communicate data with the air traffic management center in real time through the mobile phone communication system or the satellite communication system; the software system includes an air application 9401, an emergency application 9402, and an accident declaration 9403. The air application 9401 refers to the data obtained by the intelligent driving system being applied to the air traffic control center before takeoff, obtaining approval for the air channel or air area, and monitoring at any time; the emergency application 9402 refers to the small manned aircraft requiring a change of flight route due to abnormal weather or change of flight destination during flight, and re-applying to the air traffic control center for approval of the air channel or air area, and monitoring at any time; the accident declaration 9403 refers to the situation where a small manned aircraft unexpectedly crashes and opens a parachute during flight. The small manned aircraft will intelligently send the airspace location that may be affected to the air traffic control center at any time, and the air traffic control center will control the aircraft in the area and adjust the aircraft routes that affect the flight. The air traffic control center has the characteristics of being more intelligent and simple to control manned aircraft.

[0024] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements. All equivalent structural changes made by using the contents of the present invention specification and drawings under the inventive concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. An aircraft with a multi-rotor arm designed as a foldable fixed-wing aircraft, characterized in that A multi-rotor flight system and a folding fixed-wing flight system are symmetrically arranged on both sides of the cabin (10), and connected to the cabin (10) are both the multi-rotor aircraft arm (2) and the folding fixed wing (2).

2. An aircraft in which a multi-rotor machine arm is designed to be foldable and fixed-wing, which is retractable and foldable, specifically: the telescopic rod (13) is retracted to make the fixed wing and the machine arm (2) move upward or downward, and the fixed wing and the rotor are folded upward or downward, and the unfolding process is opposite to the retracting process.

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