CN114856854A - Single-engine aircraft based on vectoring nozzle and method thereof - Google Patents

Single-engine aircraft based on vectoring nozzle and method thereof Download PDF

Info

Publication number
CN114856854A
CN114856854A CN202210392992.1A CN202210392992A CN114856854A CN 114856854 A CN114856854 A CN 114856854A CN 202210392992 A CN202210392992 A CN 202210392992A CN 114856854 A CN114856854 A CN 114856854A
Authority
CN
China
Prior art keywords
engine
aircraft
nozzle
mounting frame
tail
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
CN202210392992.1A
Other languages
Chinese (zh)
Inventor
叶尚军
董钰玲
黎军
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.)
Zhejiang University ZJU
Original Assignee
Zhejiang University ZJU
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 Zhejiang University ZJU filed Critical Zhejiang University ZJU
Priority to CN202210392992.1A priority Critical patent/CN114856854A/en
Publication of CN114856854A publication Critical patent/CN114856854A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • B64C15/12—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets the power plant being tiltable
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

The invention discloses a vector nozzle-based single-engine aircraft and a method thereof, wherein the aircraft comprises an engine and a mounting frame; the mounting frame is of an annular frame structure, an engine is coaxially and vertically mounted in the center, and a tail spray pipe of the engine is positioned below the mounting frame; the tail nozzle can freely rotate within the included angle of 20 degrees and the circumferential 360 degrees of the axis of the engine and is used for changing the thrust direction. Compared with the prior art, the single engine is adopted to provide lift force, and the steering engine is used for controlling the tail spray pipe to rotate, so that the thrust vector control is realized by guiding airflow. The invention has the advantages of simple structure, light structure weight, low manufacturing cost, economy and convenience.

Description

Single-engine aircraft based on vectoring nozzle and method thereof
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a single-engine aircraft based on a vectoring nozzle and a method thereof.
Background
The unmanned aerial vehicle generally has the advantages of small volume, low manufacturing cost, convenience in use, low maintenance cost and the like, and is widely applied to disaster rescue and material transportation. The thrust vector technology can provide vertical take-off and landing capability and extra maneuvering performance for the aircraft, and the capability of the unmanned aircraft in responding to flight tasks with small space and more obstacles, such as small-scale air transportation, urban carrying and the like, is improved.
Most of the current unmanned aerial vehicles controlled by thrust vectoring technology combine a vectoring nozzle with a fixed wing, the lift force is provided by the fixed wing, and the vectoring nozzle is only used for providing part (or all) of the force required for changing direction, and cannot fly in narrow space, such as between trees or under a crown. Chinese patent CN113277079A adopts four turbojet engines, and utilizes the rotatable arc-shaped nozzle to guide the wake flow of the engine, and converts the horizontal force into the vertical force, thereby realizing the flight, and generating the lateral force by rotating the arc-shaped nozzle. However, the use of four engines increases the structural weight, reduces the utilization efficiency of thrust, and also increases the manufacturing cost. The curved nozzle conductance results in thrust loss. In addition, in order to ensure that air intake is not interfered, the aircraft is large in size due to the symmetrical installation mode of the engines, and the requirement that the aircraft flies in a narrow space is conflicted.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a single-engine aircraft based on a vectoring nozzle and a method thereof. The invention adopts the single engine for propulsion, reduces the size of the unmanned aerial vehicle, lightens the structural weight and reduces the manufacturing cost on the basis of meeting the load requirement and the endurance requirement. In the future, the device can exert important influence on fixed-point delivery of rescue materials and rapid transfer of the materials in the rescue process.
The invention adopts the following specific technical scheme:
in a first aspect, the invention provides a vectoring nozzle-based single engine aircraft comprising an engine and a mount; the mounting frame is of an annular frame structure, an engine is coaxially and vertically mounted in the center, and a tail spray pipe of the engine is positioned below the mounting frame; the tail nozzle can freely rotate within the included angle of 20 degrees and the circumferential direction of 360 degrees of the axis of the engine and is used for changing the thrust direction.
Preferably, a plurality of aircraft support frames capable of axially stretching along the engine are uniformly fixed at the bottom of the mounting frame in the circumferential direction; the bottom of the aircraft support frame exceeds the port of the tail nozzle when the aircraft support frame is at the stretching limit position, and the aircraft support frame is used for landing support.
Furthermore, the aircraft support frame comprises a first support rod, a second support rod, a third connecting rod and a transmission block; one end of the first supporting rod is fixed at the bottom of the mounting rack, the other end of the first supporting rod is coaxially sleeved and connected with the second supporting rod, and the first supporting rod and the second supporting rod can slide along the axial direction; the telescopic third connecting rod is fixed on the outer sides of the first supporting rod and the second supporting rod, and a transmission block for controlling the telescopic third connecting rod is arranged on the third connecting rod; the third connecting rod is controlled by the transmission block to stretch and retract so as to drive the first supporting rod and the second supporting rod to slide relatively.
Furthermore, the bottom of the aircraft support frame is provided with a flexible block for playing a role in landing buffering.
Preferably, the jet nozzle is connected to the engine by an annular first connecting rod hinged to the outer periphery of the upper portion of the jet nozzle.
Preferably, the periphery of the tail nozzle is connected with different steering engines through a plurality of second connecting rods, and the second connecting rods can be driven by the steering engines to deflect the tail nozzle so as to change the thrust direction;
furthermore, the number of the second connecting rods is four, the second connecting rods are uniformly distributed on the periphery of the tail nozzle, and one end of each second connecting rod, which is connected with the tail nozzle, is located on the same radial cross section; all the second connecting rods can respectively control the deflection angle of the tail nozzle in the orthogonal direction, so that the tail nozzle has the circumferential motion capability of 360 degrees.
Preferably, the mounting bracket outer ring is provided with an oil tank, a control unit and a communication device for oil supply, flight control and ground communication.
Preferably, the engine includes, but is not limited to, a turbojet engine, a piston engine, or a ducted engine.
In a second aspect, the present invention provides a flight landing method for a single-engine aircraft based on a vectoring nozzle according to any one of the first aspects, specifically as follows:
before the aircraft takes off, suspending the engine through a telescopic aircraft support frame arranged at the bottom of the mounting frame, wherein the axial direction of the engine is vertical to the ground, and the direction of a nozzle of the tail spray pipe is controlled to be vertical downwards; then, carrying out ignition operation, starting the engine, gradually increasing the rotating speed and vertically lifting the aircraft; after the aircraft is at a certain height above the ground, the aircraft support frame is folded, and the thrust direction of the nozzle is changed by changing the rotation condition of the tail nozzle, so that the hovering and lifting movement of the aircraft is realized; when the aircraft is required to land, the aircraft is in a hovering state firstly, and then the oil supply of an engine is gradually reduced, so that the aircraft slowly descends; and after the aircraft lands stably, the engine is turned off.
Compared with the prior art, the invention has the following beneficial effects:
firstly, the invention adopts a single engine to provide the lifting force required by flight and the lateral force required by direction change, and compared with an aircraft with a plurality of engines, the invention has low production cost. Meanwhile, only one engine is needed, the structure is additionally designed without considering the problem of mutual interference among the engines, a simpler structure can be adopted, the weight of the structure can be effectively reduced, and the size of the structure is reduced. The engine adopts the mode of vertical installation, can effectively reduce thrust loss.
The steering engine pulls the connecting rod to drive the thrust vectoring nozzle to rotate, the direction of thrust is changed, the direction of flight can be directly changed without changing the flight attitude, and the design of a control system is simpler. Meanwhile, the steering engine has high corresponding speed, and can quickly and accurately complete thrust direction change.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the rear portion of the engine according to the present invention;
FIG. 3 is a schematic structural view of a strut portion of an aircraft according to the present invention;
the notation in the figure is: 1. the aircraft comprises an engine, 2, a tail nozzle, 3, a first connecting rod, 4, a steering engine, 5, a second connecting rod, 6, an installation frame, 7, an aircraft support frame, 8, a first support rod, 9, a second support rod, 10, a third connecting rod, 11, a transmission block, 12 and a flexible block.
Detailed Description
The invention will be further elucidated and described with reference to the drawings and the detailed description. The technical features of the embodiments of the present invention can be combined correspondingly without mutual conflict.
Examples
As shown in FIG. 1, the invention provides a single-engine aircraft based on a vectoring nozzle, which mainly comprises an engine 1 and a mounting frame 6. The mounting bracket 6 is an annular frame structure, the engine 1 is vertically arranged at the central ring, and the engine 1 and the mounting bracket 6 are coaxially arranged. The nozzle of the tail nozzle 2 of the engine 1 is downward and positioned below the mounting frame 6, so that the mounting frame 6 can prevent the thrust generated by the tail nozzle 2 from being influenced by the blocking of the mounting frame 6 during the flight process. In this embodiment, the mounting bracket 6 is formed by splicing sectional materials, and is made of an aluminum alloy material, and the engine 1 and the mounting bracket 6 are fixedly connected in a connecting mode.
In this embodiment, a plurality of aircraft support frames 7 are uniformly fixed to the bottom of the mounting frame 6 in the circumferential direction, the aircraft support frames 7 can stretch out and draw back along the axial direction of the engine 1, and the bottom of the aircraft support frames 7 at the stretching limit position exceeds the port of the tail pipe 2, so that the aircraft can support the aircraft when landing, the engine 1 including the tail pipe 2 can be integrally erected in the air, and the engine 1 is prevented from being damaged due to contact, collision and friction with the ground. The aircraft support frame 7 can be made of aluminum alloy materials and is fixedly connected with the mounting frame 6. An oil tank, a control unit, a communication device and the like are arranged on the outer ring of the mounting frame 6 and are used for oil supply of the engine, flight control and ground communication.
As shown in fig. 3, the present embodiment provides a structure of an aircraft support frame 7, which is as follows:
the aircraft support frame 7 comprises a first support bar 8, a second support bar 9, a third link 10 and a transmission block 12. One end of the first supporting rod 8 is fixed at the bottom of the mounting frame 6, and the other end of the first supporting rod is coaxially sleeved with the second supporting rod 9. The first support bar 8 and the second support bar 9 can slide axially relative to each other to change the length of the entire aircraft support frame 7. The telescopic third connecting rod 10 is fixed on the outer sides of the first supporting rod 8 and the second supporting rod 9, and a transmission block 12 for controlling the telescopic of the third connecting rod 10 is arranged on the third connecting rod. The third connecting rod 10 is controlled to extend and contract through the transmission block 12 so as to drive the first supporting rod 8 and the second supporting rod 9 to slide relatively. In practical applications, the transmission block 12 can be remotely controlled by a remote controller. In addition, a flexible block 12 is arranged at the bottom of the aircraft support frame 7, and the flexible block 12 can play a role in buffering when the aircraft lands. The flexible blocks 12 may be made of rubber material to achieve soft landing and adaptation to the ground.
As shown in figure 2, the tail part of the engine 1 is provided with a tail nozzle 2 which can rotate freely within an angle of 20 degrees and 360 degrees in the circumferential direction with the axis of the engine and is used for providing thrust required by direction change. The tail nozzle 2 is connected with the engine 1 through an annular first connecting rod 3 hinged to the periphery of the upper portion of the tail nozzle, the first connecting rod 3 can drive the tail nozzle 2 to rotate, and the tail nozzle 2 can rotate relative to the first connecting rod 3.
The periphery of the tail spray pipe 2 is connected with different steering engines 4 through a plurality of second connecting rods 5, the steering engines 4 are located on the periphery of the lower portion of the engine 1 and move through the different steering engines 4 to drive the corresponding second connecting rods 5 to move, the second connecting rods 5 pull the tail spray pipe 2 to deflect, the angle of the cross section where the nozzle is located is changed, and then the thrust direction is changed. When the exhaust nozzle 2 is directed vertically downwards, the connecting rod 5 should be in an unrelaxed and unstressed state.
In this embodiment, the number of the second connecting rods 5 is four, and the second connecting rods are uniformly distributed on the periphery of the exhaust nozzle 2, and one end of each second connecting rod 5 connected with the exhaust nozzle 2 is located on the same radial cross section. All the second connecting rods 5 can respectively control the deflection angle of the tail nozzle 2 in the orthogonal direction, so that the tail nozzle 2 has 360-degree circumferential motion capability. The engine 1 includes, but is not limited to, a turbojet engine, a piston engine, or a ducted engine.
The movement positions of the steering engines 4 correspond to the deflection angles of the tail spray pipes 2 one by one, and the positions of the steering engines 4 strictly correspond to the directions of the tail spray pipes 2. The direction of the angular velocity of the deflection of the jet 2 should be opposite to the direction of the lodging moment caused by the equilibrium disturbance.
The main working states of the unmanned aerial vehicle provided by the invention are as follows:
(1) operating conditions at takeoff
Step I: and (5) checking that the states of all the systems are normal, finishing fuel oil filling, and enabling the battery to be in a full-charge state.
Step II: the remote control is started through the remote controller, the direction of the nozzle of the tail nozzle is controlled to be downward through the remote controller, then the ignition operation is carried out, the engine is started, the rotating speed is gradually increased, and the aircraft slowly and vertically rises.
Step III: after the aircraft is at a certain height from the ground, the aircraft support frame is controlled to be shortened through the remote controller.
(2) Operating conditions in flight
The method comprises the following steps: the steering engine is controlled to rotate through a remote controller or a controller, the direction of the nozzle is changed by pulling the connecting rod, and hovering and lifting movement of the aircraft is achieved.
(3) Working condition at landing
Step I: when the aircraft is in a non-hovering state, the remote controller is used for controlling the aircraft support frame to extend, and meanwhile, the accelerator is controlled, so that the aircraft hovers in the air.
Step II: the oil supply of the engine is gradually reduced, so that the aircraft slowly descends.
Step III: and finally, the aircraft stably lands and the engine is shut down.
In conclusion, the invention meets the load requirement of the aircraft by designing materials, structures, power and the like, and simultaneously lightens the structure weight and reduces the production cost as much as possible. The mounting frame and the aircraft support frame are made of aluminum alloy materials or composite materials with high strength and light weight, and the weight of the aircraft is reduced as much as possible on the premise of ensuring reliability. The power system of the single engine not only reduces the complexity of the structure, but also effectively reduces the cost of the aircraft and improves the economy of the aircraft.
The invention is not the best known technology.
The above-described embodiments are merely preferred embodiments of the present invention, which should not be construed as limiting the invention. Various changes and modifications may be made by one of ordinary skill in the pertinent art without departing from the spirit and scope of the present invention. Therefore, the technical scheme obtained by adopting the mode of equivalent replacement or equivalent transformation is within the protection scope of the invention.

Claims (10)

1. A vectoring nozzle based mono-engine aircraft, characterized in that it comprises an engine (1) and a mounting frame (6); the mounting frame (6) is of an annular frame structure, an engine (1) is coaxially and vertically mounted in the center, and a tail nozzle (2) of the engine (1) is positioned below the mounting frame (6); the tail nozzle (2) can rotate freely within the axial included angle of 20 degrees and the circumferential 360 degrees of the engine (1) and is used for changing the thrust direction.
2. The thrust vectoring nozzle-based mono-engine aircraft according to claim 1, characterized in that a plurality of aircraft supports (7) capable of extending and retracting axially along the engine (1) are fixed uniformly on the bottom of the mounting frame (6) in the circumferential direction; the bottom of the aircraft support frame (7) in the stretching limit position exceeds the port of the tail nozzle (2) for landing support.
3. The vectoring nozzle based single engine aircraft according to claim 2, characterized in that the aircraft support frame (7) comprises a first support bar (8), a second support bar (9), a third link (10) and a transmission block (12); one end of the first support rod (8) is fixed at the bottom of the mounting frame (6), the other end of the first support rod is coaxially sleeved and connected with the second support rod (9), and the first support rod and the second support rod can slide along the axial direction; a telescopic third connecting rod (10) is fixed on the outer sides of the first supporting rod (8) and the second supporting rod (9), and a transmission block (12) for controlling the telescopic movement of the third connecting rod (10) is arranged on the third connecting rod; the third connecting rod (10) is controlled to stretch and retract through the transmission block (12) so as to drive the first supporting rod (8) and the second supporting rod (9) to slide relatively.
4. The single-engine aircraft based on a vectoring nozzle according to claim 2, characterized in that the bottom of the aircraft support frame (7) is provided with a flexible block (12) for damping the landing.
5. The single-engine aircraft based on the vectoring nozzle according to claim 1, characterized in that said nozzle (2) is connected to the engine (1) by means of a first annular link (3) hinged to the upper periphery thereof.
6. The single-engine aircraft based on the vectoring nozzle according to claim 1, characterized in that the periphery of the nozzle (2) is connected with different steering engines (4) through a plurality of second connecting rods (5), and the steering engines (4) can drive the second connecting rods (5) to deflect the nozzle (2) so as to change the thrust direction.
7. The vectoring nozzle-based mono-engine aircraft according to claim 6, characterized in that said second links (5) are four in number, evenly distributed around the periphery of the nozzle (2), and the end of each second link (5) connected to the nozzle (2) is located on the same radial cross-section; all the second connecting rods (5) can respectively control the deflection angle of the tail nozzle (2) in the orthogonal direction, so that the tail nozzle (2) has 360-degree circumferential motion capability.
8. Single-engine aircraft based on vectoring nozzle according to claim 1, characterized in that the mounting frame (6) is provided with oil tanks, control units and communication means on the outer periphery for oil supply, flight control and ground communication.
9. The single-engine aircraft based on a vectoring nozzle according to claim 1, characterized in that said engine (1) comprises, but is not limited to, a turbojet engine, a piston engine or a ducted engine.
10. A flight landing method using the vectoring nozzle-based single-engine aircraft according to any one of claims 1 to 9, characterized in that it comprises:
before the aircraft takes off, the engine (1) is suspended through a telescopic aircraft support frame (7) arranged at the bottom of the mounting frame (6), the axial direction of the engine (1) is vertical to the ground, and the nozzle direction of the tail nozzle (2) is controlled to be vertical downwards; then, ignition operation is carried out, the engine (1) is started, and the rotating speed is gradually increased, so that the aircraft is vertically lifted; after the aircraft is at a certain height from the ground, the aircraft support frame (7) is retracted, the thrust direction of the nozzle is changed by changing the rotation condition of the tail nozzle (2), and the hovering and lifting movement of the aircraft is realized; when the aircraft is required to land, the aircraft is firstly in a hovering state, and then the oil supply of the engine (1) is gradually reduced, so that the aircraft slowly descends; and after the aircraft lands stably, the engine (1) is turned off.
CN202210392992.1A 2022-04-14 2022-04-14 Single-engine aircraft based on vectoring nozzle and method thereof Pending CN114856854A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210392992.1A CN114856854A (en) 2022-04-14 2022-04-14 Single-engine aircraft based on vectoring nozzle and method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210392992.1A CN114856854A (en) 2022-04-14 2022-04-14 Single-engine aircraft based on vectoring nozzle and method thereof

Publications (1)

Publication Number Publication Date
CN114856854A true CN114856854A (en) 2022-08-05

Family

ID=82632048

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210392992.1A Pending CN114856854A (en) 2022-04-14 2022-04-14 Single-engine aircraft based on vectoring nozzle and method thereof

Country Status (1)

Country Link
CN (1) CN114856854A (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107745811A (en) * 2017-10-21 2018-03-02 雷安静 A kind of VTOL becomes rotor wing unmanned aerial vehicle
CN208021717U (en) * 2018-02-02 2018-10-30 中国航空工业集团公司沈阳飞机设计研究所 A kind of aircraft thrust vector spout
CN110615092A (en) * 2019-10-08 2019-12-27 孙海馥 Forestry is unmanned aerial vehicle undercarriage for fire prevention
CN112555049A (en) * 2020-12-03 2021-03-26 北方工业大学 Outer sleeve type vectoring nozzle structure of micro turbojet engine
CN113277079A (en) * 2021-05-12 2021-08-20 上海工程技术大学 Jet-propelled vertical take-off and landing unmanned aerial vehicle capable of realizing thrust vector control
CN113879546A (en) * 2021-11-16 2022-01-04 西安觉天动力科技有限责任公司 Aerial adjustable spray angle vortex spraying system
CN114234929A (en) * 2021-11-19 2022-03-25 三门峡职业技术学院 Automatic deviation correcting device for oblique photogrammetry yaw angle of unmanned aerial vehicle

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107745811A (en) * 2017-10-21 2018-03-02 雷安静 A kind of VTOL becomes rotor wing unmanned aerial vehicle
CN208021717U (en) * 2018-02-02 2018-10-30 中国航空工业集团公司沈阳飞机设计研究所 A kind of aircraft thrust vector spout
CN110615092A (en) * 2019-10-08 2019-12-27 孙海馥 Forestry is unmanned aerial vehicle undercarriage for fire prevention
CN112555049A (en) * 2020-12-03 2021-03-26 北方工业大学 Outer sleeve type vectoring nozzle structure of micro turbojet engine
CN113277079A (en) * 2021-05-12 2021-08-20 上海工程技术大学 Jet-propelled vertical take-off and landing unmanned aerial vehicle capable of realizing thrust vector control
CN113879546A (en) * 2021-11-16 2022-01-04 西安觉天动力科技有限责任公司 Aerial adjustable spray angle vortex spraying system
CN114234929A (en) * 2021-11-19 2022-03-25 三门峡职业技术学院 Automatic deviation correcting device for oblique photogrammetry yaw angle of unmanned aerial vehicle

Similar Documents

Publication Publication Date Title
JP7197177B2 (en) Free-wing multirotor with vertical and horizontal rotors
US3135481A (en) Ducted rotor aircraft
CN102133926B (en) Tailstock type vertical take-off and landing unmanned aerial vehicle
CN103144769B (en) Pneumatic layout of vertical taking-off and landing aircraft with tilted duct
CN103552686B (en) A kind of compound type duct aerial reconnaissance machine people
RU2250181C2 (en) Aircraft and method of its operation
CN113277079A (en) Jet-propelled vertical take-off and landing unmanned aerial vehicle capable of realizing thrust vector control
CN105882970B (en) Fuel power independently drives large-scale plant protection drone
RU2513352C1 (en) Balloon-borne hoisting gear
RU141669U1 (en) VERTICAL TAKEOFF AND LANDING FLIGHT
US20220055740A1 (en) Landing Support Assembly For Aerial Vehicles
CN210555581U (en) Small-size carrier-borne unmanned aerial vehicle suitable for catapult-assisted take-off hangs rope and retrieves
CN107176298B (en) Aircraft flight control method and aircraft
CN107225925B (en) A kind of rolling wing VTOL is dwelt aircraft more
CN104260873B (en) A kind of delta-wing aircraft
CN113636073A (en) Triphibian aircraft
CN114856854A (en) Single-engine aircraft based on vectoring nozzle and method thereof
CN206871356U (en) Dish-shaped flying machine
CN114408201A (en) Fixed-wing unmanned aerial vehicle recovery system and method
CN101875397B (en) Duct structure for airship
CN112124589B (en) Two rotor vector unmanned aerial vehicle that verts
CN113562172A (en) Freight transport unmanned aerial vehicle with wing verts
CN114180046A (en) Electric vertical take-off and landing unmanned aerial vehicle
CN107685856A (en) Dish-shaped flying machine
RU2214945C1 (en) Flying vehicle

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
RJ01 Rejection of invention patent application after publication

Application publication date: 20220805

RJ01 Rejection of invention patent application after publication