CN110562433A - X wing unmanned aerial vehicle - Google Patents
X wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN110562433A CN110562433A CN201910872198.5A CN201910872198A CN110562433A CN 110562433 A CN110562433 A CN 110562433A CN 201910872198 A CN201910872198 A CN 201910872198A CN 110562433 A CN110562433 A CN 110562433A
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- CN
- China
- Prior art keywords
- wing
- connecting arm
- right wing
- left wing
- unmanned aerial
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- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- 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)
- Toys (AREA)
Abstract
the invention provides an X-wing unmanned aerial vehicle. The X-wing drone comprises a connecting arm; the wing assembly is arranged on the connecting arm; the flight controller is arranged at the top of the connecting arm; the steering engine is arranged at the bottom of the connecting arm; the receiver is arranged at the bottom of the connecting arm; and the battery is arranged at the bottom of the connecting arm. The X-wing unmanned aerial vehicle provided by the invention is deformable, has high horizontal flying speed, has vertical take-off and landing capability, and is small in size and convenient to carry.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an X-wing 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 X-wing 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, 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 domestic and foreign research on X-wing aircrafts hardly exists.
Therefore, there is a need to provide a new X-wing drone to solve the above technical problems.
disclosure of Invention
The invention aims to provide an X-wing unmanned aerial vehicle capable of taking off and landing vertically and flying horizontally at high speed.
In order to solve the technical problem, the invention provides an X-wing unmanned aerial vehicle, which comprises: a connecting arm; the wing assembly is arranged on the connecting arm; the flight controller is arranged at the top of the connecting arm; the steering engine is arranged at the bottom of the connecting arm; the receiver is arranged at the bottom of the connecting arm; and the battery is arranged at the bottom of the connecting arm.
preferably, the wing assembly comprises a first left wing, a second left wing, a first right wing and a second right wing, the first left wing, the second left wing, the first right wing and the second right wing are connected with the steering engine through the connecting arm, ailerons are arranged at the bottoms of the first left wing, the second left wing, the first right wing and the second right wing, hinge mechanisms are arranged in the first left wing, the second left wing, the first right wing and the second right wing, and the ailerons are connected with the first left wing, the second left wing, the first right wing and the second right wing through the corresponding hinge mechanisms.
preferably, the aileron and the connecting arm are integrally formed by additive manufacturing, and the aileron and the connecting arm are made of polylactic acid.
preferably, the first left wing, the second left wing, the first right wing and the second right wing have an S-shaped airfoil profile.
Preferably, the included angle between the first left wing and the second left wing and the included angle between the first right wing and the second right wing are variable, and the variable range is 0-90 degrees.
Preferably, the first left wing, the second left wing, the first right wing and the second right wing are all provided with motors, and an output shaft of each motor is provided with a propeller blade.
Preferably, the motor is a 3.7V/1020 hollow cup motor, and the propeller blade is a 75mm blade.
Preferably, the hinge mechanism comprises a plurality of hinges, and the plurality of hinges are provided with the same round rod and the same square rod.
Compared with the related art, the X-wing unmanned aerial vehicle provided by the invention has the following beneficial effects:
the invention provides an X-wing unmanned aerial vehicle, which is characterized in that an included angle among a first left wing, a second left wing, a first right wing and a second right wing is reduced to 0 degree from 90 degrees in a rotating manner in a high-speed flat flight stage by arranging a steering engine, so that the attached air resistance before the first left wing, the second left wing, the first right wing and the second right wing are deformed is reduced; the flight performance is excellent and the attitude is stable through the arrangement of the S-shaped wing section, the ailerons, the flight control, the steering engine and the like; the cross-sectional area was only 7 inches, 17.8cm 12.7cm, and the mass was only 90 g. Small volume, light weight, convenience and portability.
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 exploded view of the overall structure of the present invention;
FIG. 3 is a schematic view of the connection between the wing and the connecting arm according to the present invention;
FIG. 4 is a schematic view of the angle of rotation of the airfoil of the present invention;
FIG. 5 is a schematic view of the present invention in a flight mode;
FIG. 6 is a schematic illustration of the airfoil of the present invention prior to deformation;
FIG. 7 is a schematic representation of a deformed airfoil according to the present invention;
FIG. 8 is a schematic view of the portable fly-away of the present invention;
FIG. 9 is a front view of the present invention;
FIG. 10 is a left side view of the present invention;
Fig. 11 is a top view of the present invention.
reference numbers in the figures: 1. the airplane comprises a connecting arm, 2, a motor, 3, a flight controller, 4, a steering engine, 5, a propeller blade, 6, a receiver, 7, a battery, 8, a first left wing, 9, a second left wing, 10, a first right wing, 11, a second right wing, 12 and an aileron.
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. 1-11, wherein fig. 1 is a schematic structural diagram of the present invention; FIG. 2 is an exploded view of the overall structure of the present invention; FIG. 3 is a schematic view of the connection between the wing and the connecting arm according to the present invention; FIG. 4 is a schematic view of the angle of rotation of the airfoil of the present invention; FIG. 5 is a schematic view of the present invention in a flight mode; FIG. 6 is a schematic illustration of the airfoil of the present invention prior to deformation; FIG. 7 is a schematic representation of a deformed airfoil according to the present invention; FIG. 8 is a schematic view of the portable fly-away of the present invention; FIG. 9 is a front view of the present invention; FIG. 10 is a left side view of the present invention; fig. 11 is a top view of the present invention. X wing unmanned aerial vehicle includes: a connecting arm 1; the wing assembly is arranged on the connecting arm 1; the flight controller 3 is arranged at the top of the connecting arm 1; the steering engine 4 is arranged at the bottom of the connecting arm 1; the receiver 6 is arranged at the bottom of the connecting arm 1; and the battery 7 is arranged at the bottom of the connecting arm 1.
The wing assembly comprises a first left wing 8, a second left wing 9, a first right wing 10 and a second right wing 11, the first left wing 8, the second left wing 9, the first right wing 10 and the second right wing 11 are connected with the steering engine 4 through the connecting arm 1, the steering engine 4 can control the rotation angle of the connecting arm 1, and the rotation angle range of the connecting arm is 0-90 degrees; first left wing 8 the second left wing 9 first right wing 10 with the bottom of second right wing 11 all is equipped with aileron 12, when X wing unmanned aerial vehicle is as a many rotor unmanned aerial vehicle, aileron 12 can regard as the control surface, first left wing 8 the second left wing 9 first right wing 10 with all be equipped with the hinge mechanism in the second right wing 11, four aileron 12 respectively through corresponding hinge mechanism with first left wing 8 the second left wing 9 first right wing 10 with second right wing 11 is connected.
The aileron 12 and the connecting arm 1 are manufactured and integrally formed by additive manufacturing, and the aileron 12 and the connecting arm 1 are made of polylactic acid.
The airfoils of the first left wing 8, the second left wing 9, the first right wing 10 and the second right wing 11 are S-shaped.
The included angle between the first left wing 8 and the second left wing 9 and the included angle between the first right wing 10 and the second right wing 11 are variable, and the variable range is 0-90 degrees.
The first left wing 8, the second left wing 9, the first right wing 10 and the second right wing 11 are all provided with a motor 2, and an output shaft of the motor 2 is provided with a propeller blade 5.
The motor is a 3.7V/1020 hollow cup motor, and the propeller blade 5 is a 75mm blade.
The hinge mechanism comprises a plurality of hinges, and the hinges are provided with the same round rod and the same square rod.
The device can be erected on the ground through the first left wing 8, the second left wing 9, the first right wing 10 and the second right wing 11; the flying mode is vertical take-off, landing and horizontal flying; can have the characteristics of a fixed wing aircraft and a multi-rotor aircraft.
The cross section area of this device is only 7 inches namely 17.8cm 12.7cm, and the quality is only 90g, and is small, the quality is light, and is convenient portable, as shown in fig. 8, can carry out the task as a portable aircraft, and the process of carrying out the task is: the first left wing 8, the second left wing 9, the first right wing 10 and the second right wing 11 are all in contact with the ground, the device is controlled to vertically take off through a ground controller, during taking off, the four motors 2 drive the propeller blades 5 to rotate at high speed, the propeller blades 5 vertically rotate and horizontally fly in the air after taking off, in the process of vertically rotating and horizontally flying, the steering engine 4 enables the first left wing 8, the second left wing 9, the first right wing 10 and the second right wing 11 to rotate by corresponding angles, the air resistance attached after the first left wing 8, the second left wing 9, the first right wing 10 and the second right wing 11 deform is greatly reduced, the propeller blades climb to the air after horizontally flying, keep flying after flying to a certain height, an execution task is started until the destination is reached, the propeller blades continuously fly horizontally after the task is executed, and land after the propeller blades reach a safe area, the horizontal flight is converted into vertical flight, the device descends downwards, the flight posture of the device is adjusted to enable the device to land on the ground stably and vertically, and the S-shaped wing section, the ailerons 12, the flight controller 3, the steering engine 4 and the like are arranged, so that the flight performance is excellent, and the posture is stable.
compared with the related art, the X-wing unmanned aerial vehicle provided by the invention has the following beneficial effects:
The invention provides an X-wing unmanned aerial vehicle, which is characterized in that an included angle among a first left wing 8, a second left wing 9, a first right wing 10 and a second right wing 11 is reduced from 90 degrees to 0 degree in a rotation manner in a high-speed flat flight stage by arranging a steering engine 4, so that the attached air resistance before the first left wing 8, the second left wing 9, the first right wing 10 and the second right wing 11 are deformed is reduced; the S-shaped wing section, the ailerons 12, the flight controller 3, the steering engine 4 and the like are arranged, so that the flight performance is excellent and the attitude is stable; the cross-sectional area was only 7 inches, 17.8cm 12.7cm, and the mass was only 90 g. Small volume, light weight, convenience and portability.
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 (8)
1. An X-wing drone, comprising:
A connecting arm;
The wing assembly is arranged on the connecting arm;
The flight controller is arranged at the top of the connecting arm;
The steering engine is arranged at the bottom of the connecting arm;
The receiver is arranged at the bottom of the connecting arm;
And the battery is arranged at the bottom of the connecting arm.
2. The X-wing unmanned aerial vehicle of claim 1, wherein the wing assembly comprises a first left wing, a second left wing, a first right wing and a second right wing, the first left wing, the second left wing, the first right wing and the second right wing are connected with the steering engine through the connecting arm, ailerons are arranged at the bottoms of the first left wing, the second left wing, the first right wing and the second right wing, hinge mechanisms are arranged in the first left wing, the second left wing, the first right wing and the second right wing, and the four ailerons are connected with the first left wing, the second left wing, the first right wing and the second right wing through the corresponding hinge mechanisms respectively.
3. the X-wing drone of claim 2, wherein the ailerons and the connecting arms are integrally formed by additive manufacturing, and the ailerons and the connecting arms are made of polylactic acid.
4. the X-wing drone of claim 2, wherein the airfoils of the first left wing, the second left wing, the first right wing, and the second right wing are S-shaped.
5. The X-wing drone of claim 2, wherein the included angle between the first left wing and the second left wing and the first right wing and the second right wing is variable, the variable range being 0-90 degrees.
6. the X-wing unmanned aerial vehicle of claim 2, wherein motors are arranged on the first left wing, the second left wing, the first right wing and the second right wing, and propeller blades are arranged on output shafts of the motors.
7. The X-wing drone of claim 6, wherein the motor is a 3.7V/1020 coreless motor, and the propeller blades are 75mm blades.
8. the X-wing drone of claim 2, wherein the hinge mechanism includes a plurality of hinges, with a same circular bar and a same square bar on the plurality of hinges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910872198.5A CN110562433A (en) | 2019-09-16 | 2019-09-16 | X wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910872198.5A CN110562433A (en) | 2019-09-16 | 2019-09-16 | X wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110562433A true CN110562433A (en) | 2019-12-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910872198.5A Pending CN110562433A (en) | 2019-09-16 | 2019-09-16 | X wing unmanned aerial vehicle |
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| CN (1) | CN110562433A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116853490A (en) * | 2023-08-09 | 2023-10-10 | 南京航空航天大学 | Full-moving wing three-position variant tilting rotor aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6601795B1 (en) * | 2002-08-23 | 2003-08-05 | Zhuo Chen | Air vehicle having scissors wings |
| US20150225071A1 (en) * | 2014-02-10 | 2015-08-13 | Northrop Grumman Systems Corporation | Tilt Wing Aerial Vehicle |
| CN106218887A (en) * | 2016-08-22 | 2016-12-14 | 杭州迅蚁网络科技有限公司 | A kind of vertically taking off and landing flyer of distributed-power device layout |
| CN205854491U (en) * | 2016-07-18 | 2017-01-04 | 四川傲势乐翼科技有限公司 | VTOL Fixed Wing AirVehicle |
| CN206511122U (en) * | 2017-02-13 | 2017-09-22 | 深圳市龙云创新航空科技有限公司 | A kind of VTOL Fixed Wing AirVehicle |
-
2019
- 2019-09-16 CN CN201910872198.5A patent/CN110562433A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6601795B1 (en) * | 2002-08-23 | 2003-08-05 | Zhuo Chen | Air vehicle having scissors wings |
| US20150225071A1 (en) * | 2014-02-10 | 2015-08-13 | Northrop Grumman Systems Corporation | Tilt Wing Aerial Vehicle |
| CN205854491U (en) * | 2016-07-18 | 2017-01-04 | 四川傲势乐翼科技有限公司 | VTOL Fixed Wing AirVehicle |
| CN106218887A (en) * | 2016-08-22 | 2016-12-14 | 杭州迅蚁网络科技有限公司 | A kind of vertically taking off and landing flyer of distributed-power device layout |
| CN206511122U (en) * | 2017-02-13 | 2017-09-22 | 深圳市龙云创新航空科技有限公司 | A kind of VTOL Fixed Wing AirVehicle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116853490A (en) * | 2023-08-09 | 2023-10-10 | 南京航空航天大学 | Full-moving wing three-position variant tilting rotor aircraft |
| CN116853490B (en) * | 2023-08-09 | 2024-04-12 | 南京航空航天大学 | Full-moving wing three-position variant tilting rotor aircraft |
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Application publication date: 20191213 |