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WO2024017420A1 - Petit aéronef piloté à voilure fixe ovale pliable pour particuliers - Google Patents

Petit aéronef piloté à voilure fixe ovale pliable pour particuliers Download PDF

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Publication number
WO2024017420A1
WO2024017420A1 PCT/CN2023/130677 CN2023130677W WO2024017420A1 WO 2024017420 A1 WO2024017420 A1 WO 2024017420A1 CN 2023130677 W CN2023130677 W CN 2023130677W WO 2024017420 A1 WO2024017420 A1 WO 2024017420A1
Authority
WO
WIPO (PCT)
Prior art keywords
manned aircraft
oval
fixed wing
flight
wing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
PCT/CN2023/130677
Other languages
English (en)
Inventor
Wu SU
Hengzhi SU
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to PCT/CN2023/130677 priority Critical patent/WO2024017420A1/fr
Priority to CN202311709032.4A priority patent/CN117602058A/zh
Publication of WO2024017420A1 publication Critical patent/WO2024017420A1/fr
Pending legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/28—Collapsible or foldable blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/06—Undercarriages fixed
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
    • B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B64C25/62—Spring shock-absorbers; Springs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/16—Frontal aspect
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/44—Varying camber
    • B64C3/48—Varying camber by relatively-movable parts of wing structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/54—Varying in area
    • B64C3/546—Varying in area by foldable elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/068—Aircraft not otherwise provided for having disc- or ring-shaped wings having multiple wings joined at the tips
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/08—Arrangements of cameras
    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft
    • G08G5/50—Navigation or guidance aids
    • G08G5/51—Navigation or guidance aids for control when on the ground, e.g. taxiing or rolling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials

Definitions

  • the invention relates to the technical field of a household manned aircraft, in particular to an oval folding fixed wing household small manned aircraft.
  • 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.
  • 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.
  • the invention provides an oval folding fixed wing household small manned aircraft, including oval 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 an oval fixed wing system on both sides, including an oval fixed wing lower edge, a lower edge telescopic rod, an oval fixed wing upper edge, an upper edge telescopic rod, a horizontal propeller rotor motor and a rotor;
  • the chassis is under the cabin, including the frame, the rotor flight system and the ground driving system.
  • 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.
  • the oval folding fixed wing household small manned aircraft is characterized by retractable folding, specifically:
  • the contraction of the upper edge telescopic rod can make the upper edge of the oval fixed wing move vertically downward, and the contraction of the lower edge telescopic rod can make the lower edge of the oval fixed wing fold upward, and the expansion process is opposite to the contraction process;
  • the oval folding fixed wing household small manned 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.
  • most of the structural parts of the oval folding fixed wing household small manned aircraft frame, Oval 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.
  • the base of the oval folding fixed wing household small manned aircraft frame is provided with a tire support leg, which is equipped with a spring buffer device and a force spring sensor.
  • 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.
  • 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.
  • the ground driving and flight process of the oval folding fixed wing household small manned 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.
  • the oval folding fixed wing household small manned 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.
  • the oval folding fixed wing household small manned 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.
  • the invention has the characteristics of reasonable structure, retractable folding, high maneuverability and low cost, and fills the gap of household manned aircraft;
  • 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;
  • Most of the structure of the invention adopts carbon fiber material, which has the characteristics of small volume and light weight
  • 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.
  • FIG. 1 is a schematic diagram of the overall main view structure of the invention
  • FIG. 2 is a schematic diagram of the rear-view structure of the invention.
  • FIG. 3 is a folding diagram of the rear-view fixed wing of the invention.
  • FIG. 4 is a folding diagram of the rotary wing system of the invention.
  • Figure 5 is a schematic diagram of the tire leg structure of the invention.
  • FIG. 6 is a schematic diagram of ground driving, flight and lifting operation of the invention.
  • FIG. 7 is a schematic diagram of the control system structure of the invention.
  • connection 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.
  • connection 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.
  • FIG. 1 FIG. 2, FIG. 3, FIG. 4, industrial application of the invention provide an oval folding fixed wing household small manned aircraft, which comprises oval 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 cabin 10 is symmetrically equipped with an oval fixed wing system on both sides, including an oval fixed wing lower edge 13, a lower edge telescopic rod 12, an oval fixed wing upper edge 15, an upper edge telescopic rod 14, a horizontal propeller rotor motor and a rotor 3;
  • 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.
  • the oval folding fixed wing household small manned aircraft which is characterized by retractable folding, specifically:
  • the contraction of the upper edge telescopic rod 14 can make the upper edge of the oval fixed wing 15 move vertically downward, and the contraction of the lower edge telescopic rod 12 can make the lower edge of the oval fixed wing 13 fold upward, and the expansion process is opposite to the contraction process;
  • the oval folding fixed wing household small manned 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 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.
  • most of the structural parts of the oval folding fixed wing household small manned aircraft frame 1, Oval fixed wing 13,15, 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.
  • the oval folding fixed wing household small manned 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.
  • 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;
  • 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.
  • the invention also provides an oval folding fixed wing household small manned aircraft for ground driving and flight process including the following steps:
  • step 1) start the ground driving system 8001 to drive from the underground airport to the empty plaza where takeoff is possible;
  • step 2) respectively extend the fixed-wing and rotary-wing arms in an extended state
  • step 3 start the rotor flight system 8002 for vertical takeoff;
  • 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;
  • 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;
  • step 6 the landing is carried out
  • 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;
  • step 8 start the ground driving system 8001 to drive to the stop position.
  • the invention also provides an oval folding fixed wing household small manned 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.
  • the oval folding fixed wing household small manned 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.
  • the hardware system comprises a mobile phone communication card or satellite communication card 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.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Tires In General (AREA)

Abstract

L'invention concerne un petit aéronef piloté à voilure fixe ovale pliable pour particuliers, qui comprend un système de vol à voilure fixe ovale pliable, une cabine, un châssis, etc. Le système à voilure fixe ovale pliable comprend un bord inférieur de voilure fixe ovale, une tige télescopique de bord inférieur, un bord supérieur de voilure fixe ovale, une tige télescopique de bord supérieur, un moteur de rotor de poussée horizontale et un rotor. Le châssis comprend le cadre, le système de vol de rotor et le système d'entraînement au sol. La partie supérieure de la machine adopte un parachute de faible coût gonflable, la partie inférieure adopte une installation de sécurité anti-chute, la voilure est pourvue d'un radar anti-collision, l'avant est pourvu d'un micro-radar télémétrique laser, et l'utilisation est sûre et fiable. La structure de l'invention fait appel à un matériau de fibre de carbone, ce qui réduit le poids. L'invention présente les caractéristiques suivantes : structure raisonnable, rétraction et pliage, petit volume, faible poids, contrôlabilité élevée, faible coût, sécurité et fiabilité, et haut degré d'intelligence.
PCT/CN2023/130677 2023-11-09 2023-11-09 Petit aéronef piloté à voilure fixe ovale pliable pour particuliers Pending WO2024017420A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/CN2023/130677 WO2024017420A1 (fr) 2023-11-09 2023-11-09 Petit aéronef piloté à voilure fixe ovale pliable pour particuliers
CN202311709032.4A CN117602058A (zh) 2023-11-09 2023-12-13 一种椭圆形翼可折叠轻质的家用小型载人飞机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2023/130677 WO2024017420A1 (fr) 2023-11-09 2023-11-09 Petit aéronef piloté à voilure fixe ovale pliable pour particuliers

Publications (1)

Publication Number Publication Date
WO2024017420A1 true WO2024017420A1 (fr) 2024-01-25

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ID=89617174

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2023/130677 Pending WO2024017420A1 (fr) 2023-11-09 2023-11-09 Petit aéronef piloté à voilure fixe ovale pliable pour particuliers

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Country Link
CN (1) CN117602058A (fr)
WO (1) WO2024017420A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2025184836A1 (fr) * 2024-03-06 2025-09-12 Wu SU Bras d'aéronef à rotors multiples conçu comme aéronef à voilure fixe pliable

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160318609A1 (en) * 2015-05-01 2016-11-03 Other Lab, Llc System and method for flying trucks
CN109070989A (zh) * 2016-05-28 2018-12-21 深圳市大疆创新科技有限公司 可折叠无人飞行器
US20190106209A1 (en) * 2017-10-11 2019-04-11 Hangzhou Zero Zero Technology Co., Ltd. Aerial system including foldable frame architecture
CN111152611A (zh) * 2020-03-02 2020-05-15 朱幕松 折叠式飞行汽车
US20220169380A1 (en) * 2018-06-23 2022-06-02 Behrang Mehrgan Vtol tail sitting aircraft with rotor blown nonplanar wing configuration
CN114954896A (zh) * 2022-06-24 2022-08-30 苏武 一种新型折叠便捷式载人飞机
WO2023109114A1 (fr) * 2021-12-14 2023-06-22 吴斌 Voiture volante reconstructible et procédé de commande de voiture volante
CN116353855A (zh) * 2023-04-03 2023-06-30 河南工业大学 一种光电混合动力多用途消防无人机

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160318609A1 (en) * 2015-05-01 2016-11-03 Other Lab, Llc System and method for flying trucks
CN109070989A (zh) * 2016-05-28 2018-12-21 深圳市大疆创新科技有限公司 可折叠无人飞行器
US20190106209A1 (en) * 2017-10-11 2019-04-11 Hangzhou Zero Zero Technology Co., Ltd. Aerial system including foldable frame architecture
US20220169380A1 (en) * 2018-06-23 2022-06-02 Behrang Mehrgan Vtol tail sitting aircraft with rotor blown nonplanar wing configuration
CN111152611A (zh) * 2020-03-02 2020-05-15 朱幕松 折叠式飞行汽车
WO2023109114A1 (fr) * 2021-12-14 2023-06-22 吴斌 Voiture volante reconstructible et procédé de commande de voiture volante
CN114954896A (zh) * 2022-06-24 2022-08-30 苏武 一种新型折叠便捷式载人飞机
CN116353855A (zh) * 2023-04-03 2023-06-30 河南工业大学 一种光电混合动力多用途消防无人机

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