CN110562448A - Tailstock type unmanned aerial vehicle - Google Patents
Tailstock type unmanned aerial vehicle Download PDFInfo
- Publication number
- CN110562448A CN110562448A CN201910871429.0A CN201910871429A CN110562448A CN 110562448 A CN110562448 A CN 110562448A CN 201910871429 A CN201910871429 A CN 201910871429A CN 110562448 A CN110562448 A CN 110562448A
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- wing
- unmanned aerial
- vertical
- aerial vehicle
- tailstock
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Classifications
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- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention provides a tailstock type unmanned aerial vehicle. The tailstock type unmanned aerial vehicle comprises a body; two wing subassemblies, two the wing subassembly is located on the fuselage, the wing subassembly includes wing, motor, propeller blade, aileron, signal reception antenna and vortex generator, wing fixed mounting is in on the fuselage, the motor the aileron signal reception antenna with vortex generator all installs on the wing, propeller blade installs on the motor. The tailstock type unmanned aerial vehicle has the characteristics of both a fixed-wing aircraft and a four-rotor aircraft, and has vertical take-off and landing capacity; the body adopts a stealth design, so that the radar cross section is reduced, and the reflection of radar waves is reduced; the wings are designed in a high aspect ratio, and have the characteristic of large load; the vertical fin can rotate 90 degrees around the central axis of the aircraft body, thereby effectively reducing the air resistance attached to the vertical fin during horizontal flight and improving the flight speed.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a tailstock type unmanned aerial vehicle.
Background
Conventional fixed wing aircraft require a relatively long runway to achieve take-off and landing. Not only does this mean that large amounts of manpower, material resources and financial resources are required to build the airport, but also in wartime, the airport will become the first target of attack for enemy troops. Once an airport is destroyed, even powerful B2, F22, heroes have no practical place to use. The horizontal flight speed of a helicopter or a multi-rotor aircraft is much slower than that of a fixed-wing aircraft. In order to make an airplane break through the limitation of a runway and realize free take-off and landing, a vertical take-off and landing aircraft VTOL (vertical take-off and landing) is created in the middle of the 20 th century, which is a revolutionary idea.
the tail seat type unmanned aerial vehicle is a vertical take-off and landing unmanned aerial vehicle, is an aircraft integrating the advantages of a four-rotor aircraft and a fixed-wing aircraft, can realize vertical take-off and landing at zero horizontal speed, can hover, can fly horizontally at high speed in the flight mode of the fixed-wing aircraft, has the advantage of large range of the fixed-wing aircraft, and is an aircraft with great development prospect. The aircraft has a complex structure, and the characteristics of multiple inputs, multiple outputs and nonlinearity make the flight control of the aircraft difficult. At present, domestic and foreign research on VTOL unmanned aerial vehicles mainly focuses on tilting rotor unmanned aerial vehicles, ducted fan unmanned aerial vehicles, T-wing unmanned aerial vehicles, tailstock unmanned aerial vehicles and the like, and the tailstock unmanned aerial vehicles are invented in the middle of the 20 th century as an American military, and relatively few domestic and foreign research on the aircrafts which are going to the horse due to too high technical difficulty is carried out later.
Therefore, it is necessary to provide a new tailstock type unmanned aerial vehicle to solve the above technical problems.
disclosure of Invention
the invention aims to provide a tailstock type unmanned aerial vehicle of an aircraft, which can take off and land vertically and fly horizontally at a high speed.
In order to solve the technical problem, the tailstock type unmanned aerial vehicle provided by the invention comprises: a body; the two wing components are arranged on the fuselage and comprise wings, a motor, a propeller blade, an aileron, a signal receiving antenna and a vortex generator, the wings are fixedly arranged on the fuselage, the motor, the aileron, the signal receiving antenna and the vortex generator are all arranged on the wings, and the propeller blade is arranged on the motor; the vertical fin assembly is arranged at one end of the machine body and comprises a vertical fin deformation mechanism, a vertical fin and a vertical fin control surface, the vertical fin deformation mechanism is arranged at one end of the machine body, the vertical fin is arranged on the vertical fin deformation mechanism, and the vertical fin control surface is arranged on the vertical fin; the image sensor is arranged in the machine body; the four motors are respectively arranged on the wing and the vertical tail; the four propeller blades are respectively arranged on the output shafts of the corresponding motors; the four tailstocks are respectively arranged on the wings and the vertical tails, and the machine body can stand on the ground through the four tailstocks.
Preferably, run through first carbon-point and second carbon-point on the fuselage, the wing passes through first carbon-point with the second carbon-point with the fuselage is connected, wing and corresponding motor, corresponding tailstock body coupling, the wing with all be equipped with hinge structure on the vertical fin, the aileron through corresponding the hinge mechanism with the wing is connected, the vertical fin control surface through corresponding the hinge mechanism with the vertical fin is connected, the wing is kept away from the one end of fuselage is equipped with the ABS pole, be equipped with the wingtip on the ABS pole, the diameter of second carbon-point is 6 mm.
Preferably, the machine body is provided with a holder, a hatch cover and a shooting device.
preferably, the vertical tail deformation device is provided with a third carbon rod, the vertical tail is connected with the vertical tail deformation device through the third carbon rod, the vertical tail is integrally connected with the corresponding tailstock, and the diameters of the first carbon rod and the third carbon rod are 10 mm.
Preferably, the wingtip is integrally formed by additive manufacturing, and the wingtip material is polylactic acid.
Preferably, the airfoil of the wing is S-shaped.
preferably, the vertical fin can rotate 90 degrees through the vertical fin deformation mechanism.
Preferably, the body has a stealthy aerodynamic shape.
Preferably, the wing has an aspect ratio of 9.3: 1.
Preferably, a steering engine is arranged on the vertical tail deformation mechanism, and the torque of the steering engine is 20 KG.
Compared with the prior art, the tailstock type unmanned aerial vehicle provided by the invention has the following beneficial effects:
The invention provides a tailstock type unmanned aerial vehicle, which has the characteristics of a fixed wing aircraft and a multi-rotor aircraft and is a tailstock type aircraft; the flying mode is vertical take-off, landing and horizontal flying; as a multi-rotor drone, having a control surface: ailerons and vertical fin control surfaces; the vertical tail can be erected on the ground through the four tailstocks, when a task is executed, the vertical tail can be adjusted to the position which is as horizontal as the wings through the vertical tail deformation mechanism, so that the air resistance is reduced, and the flight performance is excellent and the posture is stable through the arrangement of a large aspect ratio of the wings, a vortex generator, an image sensor, an S-shaped wing section, a control surface, the vertical tail deformation mechanism and the like; the body adopts a stealth design, so that the radar cross section is reduced, and the reflection of radar waves is reduced; the wings are designed in a high aspect ratio, and have the characteristic of large load; the vertical fin can rotate 90 degrees around the central axis of the aircraft body, thereby effectively reducing the air resistance attached to the vertical fin during horizontal flight and improving the flight speed.
drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an overall perspective view of the present invention;
FIG. 3 is a schematic view of the connection between the wing and the fuselage of the present invention;
FIG. 4 is a schematic view of a wing configuration of the present invention;
FIG. 5 is a schematic view of the fuselage, vertical tail and tail structure of the invention;
FIG. 6 is a schematic view of the angle of rotation of the vertical fin of the present invention;
FIG. 7 is a schematic view of the present invention in a flight mode;
FIG. 8 is a schematic view of the invention before deformation of the vertical fin;
FIG. 9 is a schematic view of the invention after deformation of the vertical tails;
FIG. 10 is a front view of the present invention;
FIG. 11 is a left side view of the present invention;
fig. 12 is a top view of the present invention.
Reference numbers in the figures: 1. the airplane comprises a fuselage, 2, a motor, 3, a propeller blade, 4, a holder, 5, wings, 6, ailerons, 7, a signal receiving antenna, 8, a vortex generator, 9, a vertical tail deformation mechanism, 10, a vertical tail, 11, a hatch cover, 12, an image sensor, 13, a vertical tail control surface, 14, a tailstock, 15, a steering engine, 161, a first carbon rod, 162, a second carbon rod, 163, a third carbon rod, 17, a wingtip, 18 and an ABS rod.
Detailed Description
in order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
it should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
in the description of the present invention, it should be noted that the terms "upper", "vertical", "horizontal", "inner", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships conventionally found to be used in products of the present invention, and are only used for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.
Furthermore, the terms "horizontal", "vertical", "hovering", etc. do not imply that the components are required to be absolutely horizontal or overhanging, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed" and "connected" are to be interpreted broadly, e.g., as being either fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, it should be noted that, in the present invention, if the specific structures, connection relationships, position relationships, power source relationships, and the like are not written in particular, the structures, connection relationships, position relationships, power source relationships, and the like related to the present invention can be known by those skilled in the art without creative work on the basis of the prior art.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
The unmanned aerial vehicle of the invention is explained in detail below with reference to the accompanying drawings. The features of the following examples and embodiments may be combined with each other without conflict.
Please refer to fig. 1-12, wherein fig. 1 is a schematic structural diagram of the present invention; FIG. 2 is an overall perspective view of the present invention; FIG. 3 is a schematic view of the connection between the wing and the fuselage of the present invention; FIG. 4 is a schematic view of a wing configuration of the present invention; FIG. 5 is a schematic view of the fuselage, vertical tail and tail structure of the invention; FIG. 6 is a schematic view of the angle of rotation of the vertical fin of the present invention; FIG. 7 is a schematic view of the present invention in a flight mode; FIG. 8 is a schematic view of the invention before deformation of the vertical fin; FIG. 9 is a schematic view of the invention after deformation of the vertical tails; FIG. 10 is a front view of the present invention; FIG. 11 is a left side view of the present invention; fig. 12 is a top view of the present invention. Tailstock formula unmanned aerial vehicle includes: a body 1; the two wing components are arranged on the fuselage 1 and comprise a wing 5, a motor 2, a propeller blade 3, an aileron 6, a signal receiving antenna 7 and a vortex generator 8, the wing 5 is fixedly arranged on the fuselage 1, the motor 2, the aileron 6, the signal receiving antenna 7 and the vortex generator 8 are all arranged on the wing 5, and the propeller blade 3 is arranged on the motor 2; the vertical fin assembly is arranged at one end of the machine body 1 and comprises a vertical fin deformation mechanism 9, a vertical fin 10 and a vertical fin control surface 13, the vertical fin deformation mechanism 9 is arranged at one end of the machine body 1, the vertical fin 10 is arranged on the vertical fin deformation mechanism 9, and the vertical fin control surface 13 is arranged on the vertical fin 10; the image sensor 12 is arranged inside the machine body 1 and is positioned at the tail part of the machine body 1; the four motors 2 are respectively arranged on the wing 5 and the vertical tail 10; the four propeller blades 3 are respectively arranged on the output shafts of the corresponding motors 2; the four tailstocks 14 are respectively arranged on the wing 5 and the vertical fin 10, and the fuselage 1 can stand on the ground through the four tailstocks 14.
the wing 5 is connected with the fuselage 1 through a first carbon rod 161 and a second carbon rod 162 with the diameters of 10mm and 6mm respectively; the airplane wing comprises a vortex generator 8, a signal receiving antenna 7, a tailstock 14, an aileron 6, a motor 2 and a propeller blade 3, wherein the vortex generator 8 is arranged at the fusion position of a wing body, the signal receiving antenna 7 is arranged at one side of the vortex generator 8, the propeller blade 3 is arranged at the motor 2, the motor 2 and the tailstock 14 are integrally connected with a wing 5, the aileron 6 is connected with the wing 5 through a hinge mechanism hinge, and a wing tip 17 is connected with the wing 5 through an ABS rod (18) with the diameter of 10 mm; be equipped with cloud platform 4, hatch board 11, shooting ware, vertical tail deformation mechanism 9 on the fuselage 1, vertical tail deformation mechanism 9 is provided with 20KG big moment of torsion steering wheel 15, and vertical tail deformation mechanism 9 sets up at 1 afterbody of fuselage, and vertical tail 10 is connected with vertical tail deformation mechanism 9 through diameter 10 mm's third carbon-point pole 163, tailstock 14 and vertical tail 10 body coupling, and vertical tail control surface 13 passes through the hinge mechanism hinge and is connected with vertical tail 10, and image sensor 12 sets up inside 1 afterbody of fuselage, and image sensor 12 is for keeping away the barrier device, the quantity of keeping away the barrier device is one, keep away the barrier device set up in within 1 afterbody of tailstock formula unmanned aerial vehicle's fuselage, it still is equipped with the camera lens to keep away the barrier device, image sensor 12 set up in the camera lens.
The vertical tail deformation mechanism 9 is provided with a third carbon rod 163, the vertical tail 10 is connected with the vertical tail deformation mechanism 9 through the third carbon rod 163, the vertical tail 10 is integrally connected with the corresponding tailstock 14, and the diameters of the first carbon rod 161 and the third carbon rod 163 are 10 mm.
The wingtip 17 is manufactured and integrally formed in an additive mode, and the wingtip 17 is made of polylactic acid.
The airfoil profile of the wing 5 is S-shaped.
the vertical fin 10 can rotate 90 degrees through the vertical fin deformation mechanism 9.
the appearance of the machine body 1 is a stealthy aerodynamic appearance.
The aspect ratio of the wing 5 is 9.3: 1.
The device has the characteristics of a fixed-wing aircraft and a multi-rotor aircraft, and is a tailstock type aircraft; the flying mode is vertical take-off, landing and horizontal flying; as a multi-rotor drone, having a control surface: ailerons 6 and vertical fin control surfaces 13; four tailstocks 14 of accessible stand on ground, when carrying out the task, earlier with four tailstocks 14 on this device stand with ground, make this device perpendicular and ground, start four motors 2 through the controller, four motors 2 rotate, make four propeller blades 3 rotate, when four propeller blades 3 rotated certain speed, unmanned aerial vehicle takes off, treat that unmanned aerial vehicle takes off when certain height, through the controller, draw up climbing with unmanned aerial vehicle, when unmanned aerial vehicle climbs predetermined height, adjust vertical fin 10 to with wing 5 with the position of level through vertical fin deformation mechanism 9, thereby reduce the resistance of air, through wing 5 high aspect ratio, vortex generator 8, image sensor 12, S type wing section, the control surface, the setting of vertical fin deformation mechanism 9 etc., make flight performance excellent, the gesture is stable.
Compared with the prior art, the tailstock type unmanned aerial vehicle provided by the invention has the following beneficial effects:
The invention provides a tailstock type unmanned aerial vehicle, which has the characteristics of a fixed wing aircraft and a multi-rotor aircraft and is a tailstock type aircraft; the flying mode is vertical take-off, landing and horizontal flying; as a multi-rotor drone, having a control surface: ailerons 6 and vertical fin control surfaces 13; the vertical tail 10 can be adjusted to the position which is horizontal to the wing 5 through the vertical tail deformation mechanism 9 when a task is executed, so that the air resistance is reduced, the flight performance is excellent and the posture is stable through the arrangement of the large aspect ratio of the wing 5, the vortex generator 8, the image sensor 12, the S-shaped wing section, the control surface, the vertical tail deformation mechanism 9 and the like, and the device has the characteristics of a fixed wing aircraft and a four-rotor aircraft and has the vertical take-off and landing capability; the body adopts a stealth design, so that the radar cross section is reduced, and the reflection of radar waves is reduced; the wings are designed in a high aspect ratio, and have the characteristic of large load; the vertical fin can rotate 90 degrees around the central axis of the aircraft body, thereby effectively reducing the air resistance attached to the vertical fin during horizontal flight and improving the flight speed.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. A tailstock formula unmanned aerial vehicle, its characterized in that includes:
A body;
The two wing components are arranged on the fuselage and comprise wings, a motor, a propeller blade, an aileron, a signal receiving antenna and a vortex generator, the wings are fixedly arranged on the fuselage, the motor, the aileron, the signal receiving antenna and the vortex generator are all arranged on the wings, and the propeller blade is arranged on the motor;
the vertical fin assembly is arranged at one end of the machine body and comprises a vertical fin deformation mechanism, a vertical fin and a vertical fin control surface, the vertical fin deformation mechanism is arranged at one end of the machine body, the vertical fin is arranged on the vertical fin deformation mechanism, and the vertical fin control surface is arranged on the vertical fin;
the image sensor is arranged in the machine body;
The four motors are respectively arranged on the wing and the vertical tail;
the four propeller blades are respectively arranged on the output shafts of the corresponding motors;
The four tailstocks are respectively arranged on the wings and the vertical tails, and the machine body can stand on the ground through the four tailstocks.
2. The tailstock type unmanned aerial vehicle of claim, wherein a first carbon rod and a second carbon rod penetrate through the body, the wing is connected with the body through the first carbon rod and the second carbon rod, the wing is integrally connected with a corresponding motor and a corresponding tailstock, hinge structures are arranged on the wing and the vertical tail, the aileron is connected with the wing through a corresponding hinge mechanism, a vertical tail control surface is connected with the vertical tail through a corresponding hinge mechanism, an ABS (anti-lock brake system) rod is arranged at one end, far away from the body, of the wing, a wing tip is arranged on the ABS rod, and the diameter of the second carbon rod is 6 mm.
3. The tailstock type unmanned aerial vehicle of claim 1, wherein the fuselage is provided with a cradle head, a hatch cover and a camera.
4. The tailstock type unmanned aerial vehicle according to claim 2, wherein a third carbon rod is arranged on the vertical tail deforming device, the vertical tail is connected with the vertical tail deforming device through the third carbon rod, the vertical tail is integrally connected with the corresponding tailstock, and the first carbon rod and the third carbon rod 163 are 10mm in diameter.
5. The tailstock unmanned aerial vehicle of claim 2, wherein the wingtip is integrally formed by additive manufacturing, and the wingtip material is polylactic acid.
6. The tailstock unmanned aerial vehicle of claim 1, wherein the wing profile is S-shaped.
7. The tailstock unmanned aerial vehicle of claim 1, wherein the vertical fin is rotatable 90 degrees by a vertical fin deformation mechanism.
8. The tailstock type unmanned aerial vehicle of claim 1, wherein the body 1 is a stealth aerodynamic shape.
9. The tailstock unmanned aerial vehicle of claim 1, wherein the wing has an aspect ratio of 9.3: 1.
10. the tailstock type unmanned aerial vehicle of claim 1, wherein a steering engine is arranged on the vertical tail deformation mechanism, and the torque of the steering engine is 20 KG.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910871429.0A CN110562448A (en) | 2019-09-16 | 2019-09-16 | Tailstock type unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910871429.0A CN110562448A (en) | 2019-09-16 | 2019-09-16 | Tailstock type unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110562448A true CN110562448A (en) | 2019-12-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910871429.0A Pending CN110562448A (en) | 2019-09-16 | 2019-09-16 | Tailstock type unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN110562448A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722264A (en) * | 2021-01-12 | 2021-04-30 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
| CN114932972A (en) * | 2022-04-28 | 2022-08-23 | 中国民航大学 | Ground effect and hydrofoil combined carrying speedboat |
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| CN109733599A (en) * | 2019-02-27 | 2019-05-10 | 广西翼界科技有限公司 | A kind of combined dual-purpose unmanned plane |
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| CN103693194A (en) * | 2013-12-17 | 2014-04-02 | 南京航空航天大学 | Tilting four-rotor-wing aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112722264A (en) * | 2021-01-12 | 2021-04-30 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
| CN112722264B (en) * | 2021-01-12 | 2023-02-28 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
| CN114932972A (en) * | 2022-04-28 | 2022-08-23 | 中国民航大学 | Ground effect and hydrofoil combined carrying speedboat |
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Application publication date: 20191213 |
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| RJ01 | Rejection of invention patent application after publication |