CN214824040U - Long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle - Google Patents
Long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle Download PDFInfo
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Abstract
The utility model discloses a duck formula overall arrangement two-stage propulsion unmanned aerial vehicle during long voyage, including organism structural component, two-stage propulsion system, mixed stabilizer part, control rudder face part, organism structural component is used for producing lift, payload carry or loads, and two-stage propulsion system realizes that unmanned aerial vehicle impels in grades, accomplishes VTOL, the horizontal flight function switch, mixes stabilizer part and provides unmanned aerial vehicle flight stability, and control rudder face part is used for the aircraft vertically, transversely manipulates the nature. Can realize fixed wing unmanned aerial vehicle VTOL to possess VTOL, horizontal flight's two-stage propulsion switching, effectively improve flight performance, have great propulsive power, long, the changeable advantages such as speed of cruising of duration, can be used to ground information collection, goods transport, realize that mountain area etc. do not possess the delivery ability of fixed wing take-off and land section.
Description
Technical Field
The utility model relates to a two-stage impels unmanned aerial vehicle, especially relates to a duck formula overall arrangement two-stage impels unmanned aerial vehicle during long voyage.
Background
With the rapid development of the unmanned aerial vehicle in the military and civil fields, the fixed-wing unmanned aerial vehicle is paid much attention in terms of its load and long range, however, the fixed-wing unmanned aerial vehicle with conventional design generally takes off in a wheeled gliding, pneumatic or rocket boosting mode and the like, so that the fixed-wing unmanned aerial vehicle has higher requirements on taking-off and landing conditions, and the fixed-wing unmanned aerial vehicle capable of taking off and landing vertically becomes an important development direction for solving the problems. For a fixed wing unmanned aerial vehicle, the realization of the vertical take-off and landing function is realized mainly by means of vertical propellers or ducted fans and the like, one design method is that the propellers for realizing the vertical take-off and landing function are combined with the propellers for generating the horizontal flight thrust, and further the horizontal flight and the vertical flight are integrated, but the design method can cause that when the horizontal flight is carried out, the propellers for the vertical take-off and landing function become the dead weight of the aircraft, and simultaneously generate additional resistance, so that the flight performance of the unmanned aerial vehicle is seriously reduced, the maneuverability and the operability are realized, and the application direction of the unmanned aerial vehicle is limited. In order to solve the problems, a design mode of the unmanned aerial vehicle capable of achieving vertical take-off and landing and not reducing flat flight performance is provided so as to adapt to the technical requirements and performance requirements of military and civil markets on the unmanned aerial vehicle.
The technical problem of the utility model lies in the following several key problems that current VTOL fixed wing unmanned aerial vehicle exists: (1) the method has the advantages that the vertical take-off and landing functions of the fixed-wing unmanned aerial vehicle are realized, the flight performance of horizontal flight is not reduced, and the flight efficiency is improved; (2) the process of changing from the vertical take-off and landing state to the parallel flight state is a complex pneumatic state, and has higher requirements on a power system, a structural design, lift force generation, a control method and the like, and if a set of propeller system is adopted, the safe and efficient take-off of the unmanned aerial vehicle is difficult to realize; (3) the overall layout design suitable for the vertical take-off and landing fixed wing unmanned aerial vehicle realizes long endurance performance and excellent flight performance, and is also a key problem of the design of the unmanned aerial vehicle.
Disclosure of Invention
The utility model aims to solve the problem that to the shortcoming among the above-mentioned prior art, put forward improvement scheme or alternative, especially a two-stage propulsion unmanned aerial vehicle that possesses low-speed flight performance, long voyage.
In order to solve the above problem, the utility model discloses a scheme as follows: the utility model provides a long endurance duck formula overall arrangement two-stage propulsion unmanned aerial vehicle, its characterized in that, long endurance duck formula overall arrangement two-stage propulsion unmanned aerial vehicle includes organism structural component, two-stage propulsion system, mixes stabilizer part, control rudder face part.
The airframe structure part is used for generating lift force and carrying or loading effective load, the two-stage propulsion system realizes the staged propulsion of the unmanned aerial vehicle, the vertical take-off and landing and the horizontal flight function switching are completed, the mixed stabilizer part provides the flight stability of the unmanned aerial vehicle, and the control surface part is used for the longitudinal and transverse maneuverability of the aircraft.
The machine body structure part consists of a main machine body, a left auxiliary machine body, a right auxiliary machine body, a duck wing, a wing and a V-shaped vertical fin; the duck wing is arranged at the front end of the main body and is positioned at the position of the machine head; the wings are arranged in the middle of the main body; the V-shaped vertical tail is arranged at the tail end of the main body and used for improving the flight stability of the unmanned aerial vehicle; the left auxiliary fuselage and the right auxiliary fuselage are connected to the two ends of the duck wing and the middle part of the wing.
The two-stage propulsion system consists of a first-stage propulsion propeller and a second-stage propulsion propeller; the primary propulsion propeller comprises bilaterally symmetrical double-propeller systems, the bilaterally symmetrical double-propeller systems are fixedly connected to the front edge of the wing and positioned on the outer sides of the left auxiliary fuselage and the right auxiliary fuselage, and the double-propeller systems can tilt; the two-stage propulsion propeller comprises four propeller systems which are respectively arranged at the front end and the rear end of the left auxiliary body and the right auxiliary body and can tilt.
The mixed stabilizer part comprises a front stabilizer and a rear stabilizer; the front stabilizing surface is fixedly connected to the lower sides of the front ends of the left auxiliary machine body and the right auxiliary machine body; the rear stabilizing surface is arranged at the lower side of the rear end of the main body;
the control surface part comprises an aileron and an empennage control surface; the ailerons are arranged at the outer rear edge of the wing; the empennage control surface is arranged at the rear edge of the outer part of the V-shaped vertical fin.
Further, according to the design scheme, the long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle is characterized in that the left auxiliary fuselage and the right auxiliary fuselage are connected to the middle of the wing and are 10% -25% away from the fuselage in length extension; the duck wing is positioned at the front end of the main body and connected with the head of the main body, and the outer end of the duck wing is connected with the front end of the auxiliary double body; the wings are located at the position, 25% -50% of the length of the main fuselage, away from the nose.
Further, according to the design scheme, the long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle is characterized in that the duck wing and the wing both adopt a low-speed wing section or a laminar flow wing section; the span length of the duck wing is 30% -55% of the span length of the duck wing.
Further, according to above-mentioned design the long time of endurance duck formula overall arrangement two-stage propulsion unmanned aerial vehicle, its characterized in that, one-level propulsion screw, second grade propulsion screw can adopt any one in 2 leaves, 3 leaves, 4 leaves paddles respectively.
During unmanned aerial vehicle flight, the one-level impels screw, second grade to impel the screw and is the state of drooping and produce lift, reaches the predetermined height after, and the one-level impels the screw to vert and produces thrust, and after unmanned aerial vehicle reached certain airspeed, the second grade impeld the screw and gradually vert, and thrust is preceding to producing, improves thrust and airspeed. The first-stage propulsion propeller and the second-stage propulsion propeller can respectively adopt 2-blade, 3-blade and 4-blade propellers.
Further, according to the design scheme, the long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle is characterized in that the down-reaction angle of the front stabilizing surface is 60-90 degrees; the front stabilizer and the rear stabilizer both adopt symmetrical wing shapes and are used for simultaneously meeting the support when the ground stays and improving the stability during flying.
Further, according to the design scheme, the long-endurance canard-layout two-stage propulsion unmanned aerial vehicle is characterized in that the ailerons are located at the position, 20% -30% of the extension distance from the main body, of the trailing edge of the outer portion of the wing, and the chord-wise geometric dimension is 20% -30% of the chord length.
The technical effects of the utility model are as follows: (1) by adopting a two-stage propulsion propeller power system, the problem of unstable conversion of the vertical take-off and landing and horizontal flight states of the fixed-wing unmanned aerial vehicle can be effectively solved, and safe and stable switching is realized.
(2) The two-stage propulsion technology combining the first stage and the second stage is adopted to solve the problems of dead weight and flight resistance caused by the vertical take-off and landing function propeller, improve the flight performance and structural strength of the unmanned aerial vehicle, and improve the lift force by 15-20%.
(3) The duck formula overall arrangement and the propulsive integrated design of two-stage are put forward to the novelty, can greatly improve unmanned aerial vehicle's lift characteristic to improve unmanned aerial vehicle structural strength to a certain extent, improve unmanned aerial vehicle load capacity and loading space.
Drawings
Fig. 1 is the utility model discloses an unmanned aerial vehicle stereogram.
Fig. 2 is the utility model discloses an unmanned aerial vehicle top view.
Fig. 3 is the utility model discloses an unmanned aerial vehicle front view.
In the figure, 11 main fuselage, 12 left and right double auxiliary fuselages, 13 canard wing, 14 wing, 15V-shaped vertical tail, 21 primary propulsion propeller, 22 secondary propulsion propeller, 31 front stabilizer, 32 rear stabilizer, 41 aileron and 42 tail rudder surface.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 meaning of the above terms in the present invention can be understood in specific cases by those skilled in the art.
Example 1:
the utility model provides a duck formula overall arrangement two-stage impels unmanned aerial vehicle during long voyage, duck formula overall arrangement two-stage impels unmanned aerial vehicle during long voyage includes organism structural component, two-stage advancing system, mixes stabilizer part, control plane part, organism structural component is used for producing lift, payload carry or load, two-stage advancing system realizes that unmanned aerial vehicle impels in grades, accomplish VTOL, the horizontal flight function switches, it provides unmanned aerial vehicle flight stability to mix stabilizer part, control plane part is used for the aircraft vertically, horizontal maneuverability.
The machine body structure part consists of a main machine body 11, a left auxiliary machine body 12, a right auxiliary machine body 12, a duck wing 13, a wing 14 and a V-shaped vertical fin 15. Main fuselage 11 is used for connecting duck wing 13, wing 14 and V type vertical fin 15, for the detector, GPS, loads such as battery provide main loading space, two supplementary fuselage 12 in a left side and a right side connect duck wing 13's both ends and wing 14 middle part, 10% exhibition length position apart from the fuselage, duck wing 13 is located main fuselage 11 front end, connect main fuselage 11 aircraft nose position, supplementary double fuselage 12 front end is connected to the outer end, wing 14 is located main fuselage 11 apart from aircraft nose 25% fuselage length department, duck wing 13, wing 14 all adopts low-speed wing section or laminar flow wing section, duck wing 13 exhibition length is 30% of wing 14 exhibition length, V type fin 15 is located main fuselage 11 tail ends, be used for improving unmanned aerial vehicle flight stability.
The hybrid propulsion system is composed of a first-stage propulsion propeller 21 and a second-stage propulsion propeller 22, the first-stage propulsion propeller 21 comprises a bilateral symmetry double-propeller system which is fixedly connected to the front edge of the wing 14 and located on the outer sides of the left auxiliary machine body and the right auxiliary machine body 12, the double-propeller system can realize tilting, the second-stage propulsion propeller 22 comprises four propeller systems which are respectively located at the front end and the rear end of the left auxiliary machine body and the rear end of the right auxiliary machine body 12 and can realize tilting. During unmanned aerial vehicle flight, the one-level impels screw 21, second grade to impel screw 22 and is the state of drooping and produce lift, reaches the predetermined height after, and the one-level impels screw 21 to vert and produces thrust, and after unmanned aerial vehicle reached certain airspeed, the second grade impeld screw 22 and progressively verts, and thrust is improved thrust and airspeed to thrust before producing. The first-stage propulsion propeller 21 and the second-stage propulsion propeller 22 both adopt 2-blade propellers.
Mix stabilizer part by preceding stabilizer 31, back stabilizer 32 and constitute, preceding stabilizer 31 links firmly in controlling two auxiliary fuselage 12 front end downside, and preceding stabilizer 31 down-turned angle is 60 degrees, and back stabilizer 32 is located the 11 rear end downside of host computer body, and preceding stabilizer 31, back stabilizer 32 all adopt symmetrical wing type, can satisfy the support when the ground stops simultaneously, improve the stability during flight.
The control surface part consists of an aileron 41 and an empennage control surface 42, the aileron is positioned at the outer rear edge of the wing 14 and is approximately 20 percent of the span length from the fuselage 11, and the chord-wise geometric dimension is 20 percent of the chord length.
Example 2:
the utility model provides a duck formula overall arrangement two-stage impels unmanned aerial vehicle during long voyage, duck formula overall arrangement two-stage impels unmanned aerial vehicle during long voyage includes organism structural component, two-stage advancing system, mixes stabilizer part, control plane part, organism structural component is used for producing lift, payload carry or load, two-stage advancing system realizes that unmanned aerial vehicle impels in grades, accomplish VTOL, the horizontal flight function switches, it provides unmanned aerial vehicle flight stability to mix stabilizer part, control plane part is used for the aircraft vertically, horizontal maneuverability.
The machine body structure part consists of a main machine body 11, a left auxiliary machine body 12, a right auxiliary machine body 12, a duck wing 13, a wing 14 and a V-shaped vertical fin 15. Main fuselage 11 is used for connecting duck wing 13, wing 14 and V type vertical fin 15, for the detector, GPS, loads such as battery provide main loading space, two supplementary fuselage 12 in a left side and a right side connect duck wing 13's both ends and wing 14 middle part, 15% exhibition length position apart from the fuselage, duck wing 13 is located main fuselage 11 front end, connect 11 aircraft nose positions of main fuselage, supplementary double fuselage 12 front ends are connected to the outer end, wing 14 is located 11 distance aircraft nose 35% fuselage length department of main fuselage, duck wing 13, wing 14 all adopts low-speed wing section or laminar flow wing section, duck wing 13 exhibition length is 35% of wing 14 exhibition length, V type fin 15 is located 11 tail ends of main fuselage, be used for improving unmanned aerial vehicle flight stability.
The hybrid propulsion system is composed of a first-stage propulsion propeller 21 and a second-stage propulsion propeller 22, the first-stage propulsion propeller 21 comprises a bilateral symmetry double-propeller system which is fixedly connected to the front edge of the wing 14 and located on the outer sides of the left auxiliary machine body and the right auxiliary machine body 12, the double-propeller system can realize tilting, the second-stage propulsion propeller 22 comprises four propeller systems which are respectively located at the front end and the rear end of the left auxiliary machine body and the rear end of the right auxiliary machine body 12 and can realize tilting. During unmanned aerial vehicle flight, the one-level impels screw 21, second grade to impel screw 22 and is the state of drooping and produce lift, reaches the predetermined height after, and the one-level impels screw 21 to vert and produces thrust, and after unmanned aerial vehicle reached certain airspeed, the second grade impeld screw 22 and progressively verts, and thrust is improved thrust and airspeed to thrust before producing. The first-stage propulsion propeller 21 and the second-stage propulsion propeller 22 both adopt 3-blade propellers.
Mix stabilizer part by preceding stabilizer 31, back stabilizer 32 and constitute, preceding stabilizer 31 links firmly in controlling two auxiliary fuselage 12 front end downside, and preceding stabilizer 31 down-turned angle is 70 degrees, and back stabilizer 32 is located the main fuselage 11 rear end downside, and preceding stabilizer 31, back stabilizer 32 all adopt symmetrical wing type, can satisfy the support when the ground stops simultaneously, improve the stability during flight.
The control surface part consists of an aileron 41 and an empennage control surface 42, the aileron is positioned at the outer rear edge of the wing 14 and is extended from the fuselage 1125 percent, and the chord-wise geometric dimension is 25 percent of the chord length.
Example 3:
the utility model provides a duck formula overall arrangement two-stage impels unmanned aerial vehicle during long voyage, duck formula overall arrangement two-stage impels unmanned aerial vehicle during long voyage includes organism structural component, two-stage advancing system, mixes stabilizer part, control plane part, organism structural component is used for producing lift, payload carry or load, two-stage advancing system realizes that unmanned aerial vehicle impels in grades, accomplish VTOL, the horizontal flight function switches, it provides unmanned aerial vehicle flight stability to mix stabilizer part, control plane part is used for the aircraft vertically, horizontal maneuverability.
The machine body structure part consists of a main machine body 11, a left auxiliary machine body 12, a right auxiliary machine body 12, a duck wing 13, a wing 14 and a V-shaped vertical fin 15. Main fuselage 11 is used for connecting duck wing 13, wing 14 and V type vertical fin 15, for the detector, GPS, loads such as battery provide main loading space, two supplementary fuselage 12 in a left side and a right side connect duck wing 13's both ends and wing 14 middle part, 20% exhibition length position apart from the fuselage, duck wing 13 is located main fuselage 11 front end, connect main fuselage 11 aircraft nose position, supplementary double fuselage 12 front end is connected to the outer end, wing 14 is located main fuselage 11 apart from 40% fuselage length department of aircraft nose, duck wing 13, wing 14 all adopts low-speed wing section or laminar flow wing section, duck wing 13 exhibition length is 45% of wing 14 exhibition length, V type fin 15 is located main fuselage 11 tail ends, be used for improving unmanned aerial vehicle flight stability.
The hybrid propulsion system is composed of a first-stage propulsion propeller 21 and a second-stage propulsion propeller 22, the first-stage propulsion propeller 21 comprises a bilateral symmetry double-propeller system which is fixedly connected to the front edge of the wing 14 and located on the outer sides of the left auxiliary machine body and the right auxiliary machine body 12, the double-propeller system can realize tilting, the second-stage propulsion propeller 22 comprises four propeller systems which are respectively located at the front end and the rear end of the left auxiliary machine body and the rear end of the right auxiliary machine body 12 and can realize tilting. During unmanned aerial vehicle flight, the one-level impels screw 21, second grade to impel screw 22 and is the state of drooping and produce lift, reaches the predetermined height after, and the one-level impels screw 21 to vert and produces thrust, and after unmanned aerial vehicle reached certain airspeed, the second grade impeld screw 22 and progressively verts, and thrust is improved thrust and airspeed to thrust before producing. The first-stage propulsion propeller 21 and the second-stage propulsion propeller 22 both adopt 4-blade propellers.
Mix stabilizer part by preceding stabilizer 31, back stabilizer 32 and constitute, preceding stabilizer 31 links firmly in controlling two supplementary fuselage 12 front end downside, and preceding stabilizer 31 down-turned angle is 80 degrees, and back stabilizer 32 is located the 11 rear end downside of host computer body, and preceding stabilizer 31, back stabilizer 32 all adopt symmetrical wing type, can satisfy the support when the ground stops simultaneously, improve the stability during flight.
The control surface part consists of an aileron 41 and an empennage control surface 42, the aileron is positioned at the outer rear edge of the wing 14 and has the length expanded by about 28 percent from the fuselage 11, and the chord-wise geometric dimension is 28 percent of the chord length.
The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications, additions and substitutions for the specific embodiments described herein may be made by those skilled in the art without departing from the spirit of the invention or exceeding the scope of the invention as defined in the accompanying claims.
Although the terms main fuselage 11, twin right and left auxiliary fuselages 12, canard 13, wing 14, V-tail 15, primary propulsion propeller 21, secondary propulsion propeller 22, front stabilizer 31, rear stabilizer 32, aileron 41, tail rudder 42, etc. are used more herein, the possibility of using other terms is not excluded. These terms are used merely to more conveniently describe and explain the nature of the present invention; they are to be construed in a manner that is inconsistent with the spirit of the invention.
Claims (6)
1. A long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle is characterized by comprising a body structure part, a two-stage propulsion system, a mixed stabilizer part and a control surface part;
the machine body structure part consists of a main machine body (11), a left auxiliary machine body and a right auxiliary machine body (12), a duck wing (13), a wing (14) and a V-shaped vertical fin (15); the duck wing (13) is arranged at the front end of the main body (11) and is positioned at the head position; the wings (14) are arranged in the middle of the main body (11); the V-shaped vertical tail (15) is arranged at the tail end of the main body (11); the left auxiliary fuselage and the right auxiliary fuselage (12) are connected to the two ends of the duck wing (13) and the middle part of the wing (14);
the two-stage propulsion system consists of a first-stage propulsion propeller (21) and a second-stage propulsion propeller (22); the primary propulsion propeller (21) comprises bilaterally symmetrical double-propeller systems, the bilaterally symmetrical double-propeller systems are fixedly connected to the front edges of the wings (14) and positioned on the outer sides of the left auxiliary fuselage and the right auxiliary fuselage (12), and the double-propeller systems can tilt; the two-stage propulsion propeller (22) comprises four propeller systems which are respectively positioned at the front end and the rear end of the left auxiliary machine body and the right auxiliary machine body (12) and can tilt;
the mixed stabilizer part comprises a front stabilizer (31) and a rear stabilizer (32); the front stabilizing surface (31) is fixedly connected to the lower sides of the front ends of the left auxiliary machine body and the right auxiliary machine body (12); the rear stabilizing surface (32) is arranged at the lower side of the rear end of the main body (11);
the control surface part comprises an aileron (41) and a tail control surface (42); the ailerons (41) are arranged at the outer rear edge of the wing (14); the empennage control surface (42) is arranged at the outer rear edge of the V-shaped vertical fin (15).
2. The long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle according to claim 1, wherein the left and right auxiliary fuselages (12) are connected to the middle of the wing (14) and are 10% -25% away from the fuselage in the extended length position; the duck wing (13) is positioned at the front end of the main body (11) and connected with the head position of the main body (11), and the outer end of the duck wing is connected with the front end of the auxiliary double body (12); the wings (14) are positioned at the position, 25% -50% of the length of the main body (11), away from the nose.
3. The long endurance duck-type layout two-stage propulsion drone according to claim 1, wherein the duck wing (13) and the wing (14) both adopt a low speed wing profile or a laminar flow wing profile; the spreading length of the duck wing (13) is 30% -55% of that of the wing (14).
4. The long endurance duck-type layout two-stage propulsion drone according to claim 1, wherein the first stage propulsion propeller (21) and the second stage propulsion propeller (22) may be any one of 2-blade, 3-blade, and 4-blade propellers, respectively.
5. The long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle according to claim 1, wherein a down-ward-off angle of the front stabilizer (31) is 60-90 degrees; the front stabilizer (31) and the rear stabilizer (32) both adopt symmetrical wing profiles and are used for simultaneously meeting the support when the ground stays and improving the stability during flight.
6. The long endurance, canard configuration two-stage propulsive drone of claim 1, wherein the ailerons (41) are located 20% to 30% span from the main fuselage (11) at the outer trailing edge of the wing (14), with chordwise geometry of 20% to 30% chord.
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| CN202120523499.XU CN214824040U (en) | 2021-03-12 | 2021-03-12 | Long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle |
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| CN202120523499.XU CN214824040U (en) | 2021-03-12 | 2021-03-12 | Long-endurance duck-type layout two-stage propulsion unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115402509A (en) * | 2022-11-01 | 2022-11-29 | 上海飞机制造有限公司 | Vertical take-off and landing aircraft |
| WO2023225819A1 (en) * | 2022-05-23 | 2023-11-30 | 深圳市闪至科技有限公司 | Aircraft, aircraft control method and device, and computer-readable storage medium |
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2021
- 2021-03-12 CN CN202120523499.XU patent/CN214824040U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023225819A1 (en) * | 2022-05-23 | 2023-11-30 | 深圳市闪至科技有限公司 | Aircraft, aircraft control method and device, and computer-readable storage medium |
| CN115402509A (en) * | 2022-11-01 | 2022-11-29 | 上海飞机制造有限公司 | Vertical take-off and landing aircraft |
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