CN112208751A - A design method and system for a dual-release bureau autogyro - Google Patents
A design method and system for a dual-release bureau autogyro Download PDFInfo
- Publication number
- CN112208751A CN112208751A CN202011208561.2A CN202011208561A CN112208751A CN 112208751 A CN112208751 A CN 112208751A CN 202011208561 A CN202011208561 A CN 202011208561A CN 112208751 A CN112208751 A CN 112208751A
- Authority
- CN
- China
- Prior art keywords
- engine
- layout
- autogyro
- ground
- dual
- 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
Links
- 238000013461 design Methods 0.000 title claims abstract description 50
- 230000009977 dual effect Effects 0.000 title claims abstract description 11
- 238000000034 method Methods 0.000 title claims abstract description 9
- 238000009987 spinning Methods 0.000 claims description 11
- 238000009434 installation Methods 0.000 claims description 9
- 238000007726 management method Methods 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 5
- 230000007246 mechanism Effects 0.000 claims description 5
- 239000000446 fuel Substances 0.000 claims description 4
- 239000007858 starting material Substances 0.000 claims description 4
- 238000013523 data management Methods 0.000 claims description 3
- 238000012549 training Methods 0.000 claims description 3
- 230000009471 action Effects 0.000 claims description 2
- 238000007689 inspection Methods 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 claims description 2
- 238000005259 measurement Methods 0.000 claims description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract description 4
- 230000005484 gravity Effects 0.000 abstract description 4
- 238000005457 optimization Methods 0.000 abstract 1
- 239000000575 pesticide Substances 0.000 description 7
- 239000007921 spray Substances 0.000 description 7
- 238000005507 spraying Methods 0.000 description 6
- 238000012384 transportation and delivery Methods 0.000 description 5
- 238000004891 communication Methods 0.000 description 4
- 230000006978 adaptation Effects 0.000 description 3
- 238000012857 repacking Methods 0.000 description 3
- 230000003044 adaptive effect Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000002146 bilateral effect Effects 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010612 desalination reaction Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000002905 metal composite material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000011218 segmentation Effects 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- 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
- B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pest Control & Pesticides (AREA)
- Toys (AREA)
Abstract
本发明公开了一种双发布局自旋翼机的设计方法及系统，通过双发布局的设计提高自旋翼机的安全性和装载能力，优化自旋翼机的总体布局设计，以此为基础可采用有人驾驶状态和无人驾驶状态两种设计方案。本发明提出双发串列布局的设计方案是多发布局的一种优化，可减轻自旋翼与发动机的气动力干扰，解决单发布局对重心设计的局限，可克服单发停车后的飞行控制难度。本发明设计的双发布局自旋翼机可在通用航空领域扩展应用。The invention discloses a design method and system for a dual-release station autogyro. The safety and loading capacity of the autogyro are improved through the design of the dual-release stations, and the overall layout design of the autogyro is optimized. There are two design schemes of manned state and unmanned state. The design scheme of the double-engine tandem layout proposed by the present invention is an optimization of the multi-engine, which can reduce the aerodynamic interference between the rotor and the engine, solve the limitation of the center of gravity design of the single-engine, and overcome the flight control after the single-engine is stopped. difficulty. The dual-release bureau autogyro designed by the invention can be extended and applied in the field of general aviation.
Description
Technical Field
The invention belongs to the technology of designing and controlling an aircraft, in particular to the field of design of an unmanned aircraft and general aviation application.
Background
Autogyroplanes are aircraft that rely on rotorcraft lift, the safety of their flight principle being of interest for general aviation applications. At present, autogiro is popularized and applied in civil or military fields, the total amount is not large, but the market attention is still promoted by the advantages of low-altitude flight application, low cost, safety and the like. The main limitation of the spread application of the spinning wing aircraft is that the loading capacity is relatively small. A single-shot double-seat self-rotary wing aircraft with double seats is used for teaching or sightseeing flight, and a teacher occupies one seat and can only carry 1 passenger. Flight verification has been completed on single-engine three-seat spinning-wing aircraft designed by replacing a high-power engine, but the three-seat layout of a coach seat and a student seat layout and a passenger seat layout are inconvenient to provide good observation visual field for students or passengers or comfortable riding experience.
Disclosure of Invention
The invention aims to provide a design method and a system of a dual-engine layout autogyro, and in order to achieve the aim, the technical scheme adopted by the invention is as follows:
a design method of a dual-engine layout autogyro is characterized in that the autogyro adopts a dual-engine layout, and a serial layout design scheme that dual engines are respectively arranged at the front end and the rear end of a fuselage in the installation of 2 engines and comprises a design scheme of a manned state or an unmanned state; the piloting system is arranged on the fuselage and is used for piloting flight and for action control and data management of the airborne system; the engine is stopped in the air, the driving system can restart in the air through the starter, the air double-engine running state is maintained to improve the safety, and when the restarting fails, the driving system can land nearby through a single engine.
A self-rotary wing aircraft adopting a double-engine layout comprises an aircraft body, an engine, a passenger cabin, a driving system and a ground system. The fuselage is made of mixed materials and comprises a bearing structure made of metal or non-metal composite materials, a structure for mounting an engine or equipment, a pneumatic appearance fairing structure, a channel cabin door structure and a skin structure; the self-rotary wing arm and the self-rotary wing are arranged at the upper part of the aircraft body, the self-rotary wing arm and the self-rotary wing provide connection of a bearing structure for the rotary lift force of the self-rotary wing, and an auxiliary transmission shaft or independent power equipment can be arranged for accelerating the spin-off of the self-rotary wing in the take-off stage, wherein the transmission shaft is a transmission mechanism for connecting the self-rotary wing arm with an engine, the independent power equipment is power rotary equipment arranged and connected at the lower end of the self-rotary wing arm, such as an electric motor with a battery, and according to the design scheme, the independent power equipment can be thrown; the tail wing structure is arranged on the fuselage and comprises a tail stay bar, a rudder and an elevator, wherein the rudder is used for yaw control, and the elevator is used for assisting pitching control; the aircraft body is provided with two engines, and the optimized design scheme is that 1 engine is respectively arranged at the front end and the rear end of the axis of the aircraft body, so that the gravity center of the whole aircraft is convenient to arrange or adjust, single-shot flight control of the self-rotary wing aircraft configuration is facilitated, and the interference of self-rotary wing downwash airflow and the engines is reduced; a passenger cabin is designed on the machine body, the passenger cabin comprises passenger seats, passenger windows and passenger cabin doors, and the upper and lower passages of passengers are arranged on the two sides of the machine body and are optimized; a piloting system mounted from the rotorcraft.
The engine is mounted on the fuselage structure. The two engines can be mounted in a series arrangement at the front and rear ends of the fuselage axis, and aerodynamic fairings are designed, see fig. 1-3. The other layout is arranged on the short wing of the side wing of the fuselage in a left-right symmetrical mode, and the defects of performance and use are obvious. Conventional design methods provide an engine with an automatic parameter detector (ECU), engine starter and generator. The layout of the engine can select a plurality of oil engines or motors to replace a double-engine layout, for example, 4 engines are adopted to replace 2 engines, and the installation layout is the left-right layout at the installation positions of 2 engines; the method selects a plurality of motors to replace two fuel engines which are arranged in series, and also replaces the arrangement layout of the position where 2 fuel engines are arranged in series in a bilateral symmetry way, or the arrangement layout of a plurality of motors which are arranged on the short wing structures at the two sides of the machine body in a bilateral symmetry way.
The passenger cabin is designed on the fuselage structure and comprises seats, passenger windows and passenger cabin doors, and a driving system selected by a user. The channels of the passenger cabin are designed on the left side and the right side of the machine body, and the symmetrical structure is convenient for design and manufacture, is convenient for passengers to quickly move up and down, and is convenient for the passengers to sightseeing. The top of the passenger compartment can be designed with a fuselage ridge structure which can be used for bearing force and protecting passengers and can be used for installing passenger windows. The passenger's position of taking is in the corner of fuselage upper portion both sides, and to the compact curved surface structure in corner, simple and convenient passenger cabin structure can adopt the segmentation design scheme, and passenger's window design is installed on fuselage dorsal bar structure promptly, can adopt full transparent structure and upper and lower switch and waterproof design, and passenger hatch door and safety lock mechanism design on the fuselage lateral wall. When the passenger opens the window in the air for ventilation, the passenger cabin door is still safely locked.
The piloting system is mounted on the fuselage and is used for piloting flight and for motion control and data management of the airborne system. The engine is stopped in the air, the driving system can restart in the air through the starter, the safety can be improved by maintaining the double-engine running state in the air, and when the restarting fails, the engine can land nearby through the driving system by means of single engine. The driving system comprises a controller and a servo mechanism which are manually operated or electrically operated or automatically driven, resolving and displaying functions of flight parameters and navigation information, onboard power supply and power utilization management, and control and management required by connection and operation with other onboard systems, particularly the control system is connected with a ground system through a connecting onboard data chain.
The ground system is arranged on the ground and is used for linking the airborne control system and carrying out remote measurement and remote control and information transmission on the flight of the spinning wing aircraft. The ground system comprises a ground station, ground inspection or maintenance equipment, ground training equipment and other ground system equipment required by matching use, such as a differential station, a communication terminal such as 5G communication, ADS-B ground equipment, aviation voice equipment and an optical fiber network. The ground station can be in a vehicle-mounted mobile type or a portable type, and can be in a portable type, and the detailed design scheme is selected according to the use requirement.
The dual-engine spinning wing aircraft can be designed to be in a manned state and can be designed to be in an unmanned state. When the unmanned aerial vehicle system is designed to be in an unmanned state, the driving system is designed to be an unmanned aerial vehicle flight control and task management system, other airborne systems and ground stations carry out conventional adaptive detailed design according to the operation of the unmanned state required by a user, wherein the conventional adaptive detailed design comprises the replacement of electrical interfaces and equipment required by adaptation, so that the data adaptation of the whole set of unmanned aerial vehicle system is perfected. The autogyro is designed to be in an unmanned state, the structural design of the autogyro can be simplified, and the installation of an engine and the loading of cargos are mainly met.
Compared with the prior art, the invention has the following effects: the invention adopts double-engine layout, solves the requirement of improving the loading capacity of the autogyro, and provides a more suitable overall layout scheme for the design of the weight center of gravity of the whole autogyro. The double-engine layout is adopted, various layouts can be selected for the installation of 2 engines, the optimized installation layout is a serial layout design scheme that double engines are respectively installed at the front end and the rear end of a machine body, firstly, the interference of the downwash airflow of a spinning wing is small, secondly, the control cost of converting the downwash airflow into single-engine flight is small, namely, the single-engine flight control of the self-rotor structure is facilitated, thirdly, the channels of the upper passenger compartment and the lower passenger compartment of a passenger and the observation visual field are wide, or the loading and unloading structure design of goods is simple, convenient and rapid.
The self-rotary wing aircraft adopting the double-engine layout keeps the advantage of low cost, supports the design scheme of selecting the manned state or the unmanned state, and can support various navigation operation applications of short take-off and landing and low-altitude low-speed flight, including passenger seats of up to 6 passengers in the manned state, spacious sightseeing experience, cargo tail end express delivery in the unmanned state, emergency rescue such as forest fire extinguishment or stretcher transportation, pesticide spraying operation in agriculture and forestry plant protection and the like.
Drawings
FIG. 1 is a side view of a dual-hair layout spinning wing aircraft;
FIG. 2 is a top view of the autogiro in a dual-launch configuration;
FIG. 3 is a front view of the autogyro in a dual-launch configuration;
FIG. 4 is a schematic view of the sprinkler nozzle installation, from a top view;
FIG. 5 is a schematic view of the sprinkler nozzle installation, front view;
FIG. 6 is a schematic view of a sprinkler with a nozzle tip mounted within an airfoil nozzle tube.
The labels in the figures are: 1-passenger cabin door, 2-fuselage, 3-landing gear, 4-light carving nacelle, 5-engine, 6-autogyro, 7-passenger window, 8-autogyro arm, 9-fuselage ridge, 10-upper tail stay, 11-lower tail stay, 12-rudder, 13-engine fairing, 14-elevator, 15-nozzle draw arm, 16-outer nozzle, 17-front wheel, 18-connecting pipe supporting plate, 19-connecting pipe, 20-front pull rope, 21-rear pull rope, 22-pesticide spraying container, 23-inner nozzle, 24-front fuselage, 25-rear wheel, 26-folding outer nozzle, 27-upper pull rope, 28-nozzle, 29-airfoil structure.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Example 1 sightseeing manned aircraft on ride status
A double-hair layout spinning wing aircraft is designed. The engine 5 selects 135Hp and is provided with a generator. The main technical indexes are as follows: the maximum takeoff weight is 1500kg, the empty weight is 525kg, the fuel weight is 370kg, 6 passengers can carry 20kg of articles, the cruising speed is 140km/h, the maximum time of flight is 9h, and the maximum range is 1200 km.
The passenger seats are arranged on both sides of the fuselage 2, and the passenger windows 7 and the passenger hatches 1 can be designed integrally or separately. The split design scheme is that the horizontal sight of eyes of passengers is slightly higher than that of an engine fairing 13, the passenger window 7 of each seat is designed into an arc structure and is opened upwards, the passenger cabin door 1 is designed into a plane structure and is opened on the side wall of the machine body 2, and the passenger upper and lower channels are designed on the side surface of the machine body 2, so that the split design scheme is also suitable for parachute jumping training or application of airdrop personnel. See figure 1. The pilot system of the pilot or instructor seat may be conventionally arranged on the left side of the nose, or on the right side, as per the design of the navigable aircraft, and the pilot system is specifically designed at each seat so that more occupants can allocate the pilot experience.
To enhance the occupant experience, relevant parameters or charts of the flight process, including engine parameters, flight parameters, navigational situation, airline maps, may be displayed to the occupant.
The state of the single flight belongs to a risk state, is automatically converted by an onboard driving system or an authorized onboard driving instructor, and can also be designed to be converted by ground personnel. The single-shot flight is mainly used for single-shot air parking, and after the single-shot air parking fails to restart, another engine flies to an airport to land in a single-shot state.
To shorten the takeoff-to-ground distance from the rotorcraft, takeoff assist mechanisms or devices designed or configured for use during ground takeoff phases may be designed for use by automatic control of an onboard steering system, or by ground personnel assisted operations.
A double-hair layout spinning wing aircraft is designed according to the scheme in the example 1. The design scheme of this embodiment is, the repacking design is the self rotary wing machine of the dedicated unmanned state of agriculture and forestry plant protection, sprays unmanned aerial vehicle for short, or the sprinkler.
Spraying unmanned aerial vehicle is flown by the control of driving system, ground personnel use ground station to keep watch on the operation flight and spray the operation, need the long-time operation of ultralow altitude to the autogyro that is used for agriculture and forestry plant protection, can meet the interference of gale or indiscriminate wind, can not dangerously touch to the ground for guaranteeing the ultralow altitude flight, can increase in airborne driving system like height finding radar, or height finding lidar, or height finding ultrasonic radar, so that the control deviation of flying height can keep within the air route safety deviation, or carry out unilateral deviation control, and avoid touching to the ground dangerous. The control rate of the detailed design should refine the desalination process of the height variation to avoid hard height fluctuations.
The design scheme of the body structure of the autogyro can be simplified, the pesticide spraying container 22 for loading pesticide is designed on the body 2, and the pesticide spraying container 22 can be simply and conveniently replaced and fastened, so that the pesticide loading preparation time is saved. The interior of the spray container 22 is designed with a partition plate for preventing the center of gravity of the pesticide from shaking rapidly and a communication structure for controlled circulation. The design scheme is provided with pressure spraying power and a spray pipe 28 and a spray head. The design scheme is that the spray pipe 28 is installed inside the airfoil structure 29, so that the flight resistance can be reduced, and the rigidity of the spray pipe 28 can be improved. See fig. 6.
Design details of the spout 28 include, front and rear drawstrings 20, 21 that increase the rigidity of the spout 28; to reduce the parking area, the folding of the connecting tube 19 of the outer nozzle 16 is facilitated. See fig. 4 and 5. The economical and simple design of the connecting tube 19 can be a flexible tube with an elastic element inside, while the complicated design can be a connecting tube with a rotary joint and a control valve.
A double-hair layout spinning wing aircraft is designed according to the scheme in the example 1. The design of this embodiment is, the special autogyro of goods express delivery, express delivery unmanned aerial vehicle for short, or cargo airplane of repacking design for unmanned state. According to example 1, the cargo transportation weight can reach 600 kg. The system is suitable for the fixed-point flight-based express operation of fresh goods, medicines, interplant parts and the like at the tail end of logistics.
From gyroplane repacking design for unmanned aerial vehicle, can be used to the goods express delivery, to the express delivery application, the loading and unloading of structural design scheme adaptation goods is conveniently designed, can select to arrange the goods loading and unloading passageway in 2 both sides of fuselage, increases the goods hatch door rate of opening. The container can be quickly loaded and unloaded by adopting a special container, and both military and civil fusion scenes are applicable, such as loading weapons and ammunition or launching and throwing weapons.
The refitting design of the driving system is mainly aimed at freight transportation, monitoring and communication equipment of whole-course flight information and voice equipment for contacting with a navigation management are added, and an airborne photoelectric pod is added to monitor the conditions of a navigation line and a take-off and landing field. Through the interface design and connection of the equipment, the added or cut subsystem can normally run in the driving system.
Of course, the above is only a specific application example of the present invention, and other embodiments of the present invention are also within the scope of the present invention.
Claims (7)
1. A design method of a dual-engine layout autogyro is characterized by comprising the following steps: the self-rotary wing aircraft adopts a double-engine layout, and a serial layout design scheme that double engines are respectively installed at the front end and the rear end of the aircraft body (2) in the installation of 2 engines (5) comprises a design scheme of a manned state or an unmanned state; the piloting system is arranged on the fuselage (2) and is used for piloting flight and for action control and data management of the airborne system; the engine (5) can be stopped in the air, the air restarting can be implemented by the driving system through the starter, the air double-engine running state is maintained to improve the safety, and when the restarting fails, the engine can be landed nearby through the driving system through the single engine.
2. A dual launch layout autogyro system characterized in that: the self-rotary wing aircraft with the double-engine layout comprises an aircraft body (2), an engine (5), a passenger cabin, a driving system and a ground system; a spinning wing arm (8) and a spinning wing (6) are arranged on the machine body (2); the fuselage (2) is provided with an empennage structure and a corresponding pneumatic control surface; an engine fairing (13) is also arranged on the machine body (2); designing a passenger cabin on a fuselage (2), wherein the passenger cabin comprises seats, passenger windows (7) and a passenger cabin door (1) and corresponding structures; the body (2) is also provided with a driving system.
3. The dual launch layout autogyro system according to claim 2, wherein: the engines (5) are arranged at the front end and the rear end of the machine body (2) in a series arrangement, and a plurality of fuel engines or motors are selected for the arrangement of the engines (5) to replace a double-engine arrangement.
4. The dual launch layout autogyro system according to claim 2, wherein: the top of the passenger compartment is designed with a fuselage ridge (9) structure.
5. The dual launch layout autogyro system according to claim 2, wherein: the driving system comprises a controller and a servo mechanism which are manually operated or electrically operated or automatically driven, resolving and displaying functions of flight parameters and navigation information, onboard power supply and power management, and control and management required by connection and operation with other onboard systems; the ground system is arranged on the ground and is used for linking the airborne control system and carrying out remote measurement and remote control and information transmission on the flight of the spinning wing aircraft; the ground system comprises a ground station, ground inspection or maintenance equipment, ground training equipment and other ground system equipment required by matched use.
6. The dual launch layout autogiro system according to claim 5, wherein: the control system is linked with the ground system by connecting an airborne data chain.
7. The dual launch layout autogiro system according to claim 6, wherein: the self-rotary wing aircraft with the double-engine layout comprises three states of taking a sightseeing piloting plane, an agricultural and forestry plant protection unmanned aerial vehicle and a cargo express unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011208561.2A CN112208751A (en) | 2020-11-03 | 2020-11-03 | A design method and system for a dual-release bureau autogyro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011208561.2A CN112208751A (en) | 2020-11-03 | 2020-11-03 | A design method and system for a dual-release bureau autogyro |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112208751A true CN112208751A (en) | 2021-01-12 |
Family
ID=74058066
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011208561.2A Pending CN112208751A (en) | 2020-11-03 | 2020-11-03 | A design method and system for a dual-release bureau autogyro |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112208751A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU119324U1 (en) * | 2012-04-27 | 2012-08-20 | Валерий Александрович Белов | AUTO FAT AMPHIBIA |
| CN204660028U (en) * | 2015-02-09 | 2015-09-23 | 徐斌 | A kind of two-engined autogiro |
| CN109353495A (en) * | 2018-11-30 | 2019-02-19 | 南京航空航天大学 | An unmanned autogyro that can take off and land vertically |
| CN209581860U (en) * | 2019-01-29 | 2019-11-05 | 黄鹏 | A kind of hairdo autogiros double side by side |
| CN213473505U (en) * | 2020-11-03 | 2021-06-18 | 陶文英 | Dual-engine layout self-gyroplane system |
-
2020
- 2020-11-03 CN CN202011208561.2A patent/CN112208751A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU119324U1 (en) * | 2012-04-27 | 2012-08-20 | Валерий Александрович Белов | AUTO FAT AMPHIBIA |
| CN204660028U (en) * | 2015-02-09 | 2015-09-23 | 徐斌 | A kind of two-engined autogiro |
| CN109353495A (en) * | 2018-11-30 | 2019-02-19 | 南京航空航天大学 | An unmanned autogyro that can take off and land vertically |
| CN209581860U (en) * | 2019-01-29 | 2019-11-05 | 黄鹏 | A kind of hairdo autogiros double side by side |
| CN213473505U (en) * | 2020-11-03 | 2021-06-18 | 陶文英 | Dual-engine layout self-gyroplane system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11518505B1 (en) | Vertical take-off and landing (VTOL) tilt-wing passenger aircraft | |
| US11273911B2 (en) | Detachable power tethering systems for aircraft | |
| US10384796B2 (en) | Aerospace plane system | |
| US8967526B2 (en) | Multi-role aircraft with interchangeable mission modules | |
| US9139299B2 (en) | Vertical takeoff and landing roadable vehicle | |
| US11292585B2 (en) | STOL aircraft | |
| CA2870808C (en) | An aerospace plane system | |
| CN201362362Y (en) | Composite power multipurpose unmanned aerial vehicle | |
| AU2014302220A1 (en) | Hybrid VTOL vehicle | |
| RU2370414C1 (en) | Multipurpose helicopter airplane with remote control | |
| EP2799335B1 (en) | A modular aircraft | |
| CN213473505U (en) | Dual-engine layout self-gyroplane system | |
| CN205293099U (en) | Use coaxial tandem twin engine's fixed wing uavs | |
| RU2380286C1 (en) | Pilotless aircraft | |
| WO2002070342A1 (en) | Circular vertical take-off and landing aircraft | |
| CN205615699U (en) | General type fixed wing uavs | |
| CN108583868B (en) | Ground effect type ducted fan aircraft | |
| CN108033025B (en) | Thrust control system of aircraft engine | |
| Martı́nez-Val et al. | Preliminary design of a low speed, long endurance remote piloted vehicles (RPV) for civil applications | |
| CN112208751A (en) | A design method and system for a dual-release bureau autogyro | |
| Khoury | 19 Unconventional Designs | |
| RU2466061C2 (en) | Flight vehicle (versions), flight vehicles parts, method of exploiting flight vehicle and its parts | |
| US20240294277A1 (en) | Electric autonomous aircraft | |
| Free | Russian Helicopters | |
| RU45361U1 (en) | EDUCATIONAL TRAINING PLANE YAK-152 |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |