CN218317307U - Vertical take-off and landing fixed wing unmanned aerial vehicle - Google Patents
Vertical take-off and landing fixed wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN218317307U CN218317307U CN202222733497.0U CN202222733497U CN218317307U CN 218317307 U CN218317307 U CN 218317307U CN 202222733497 U CN202222733497 U CN 202222733497U CN 218317307 U CN218317307 U CN 218317307U
- Authority
- CN
- China
- Prior art keywords
- wing
- fixed
- fuselage
- ribs
- unmanned aerial
- 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.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model belongs to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing fixed wing unmanned aerial vehicle, which comprises a body, wherein the body comprises a body, wings, an undercarriage and a rotor wing structure; the wings comprise a first wing and a second wing which are arranged in parallel up and down, and the fuselage is connected between the first wing and the second wing; the undercarriage is fixedly connected to the tail of the undercarriage; the front ends of the first wing and the second wing are respectively fixed with a rotor structure, the rotor structure comprises a motor and a propeller, and the outer surfaces of the first wing and the second wing are covered with solar panels. The utility model provides a vertical take-off and landing fixed wing overcomes the shortcoming that current fixed wing unmanned aerial vehicle improves the method of long endurance, can change into the fixed wing flight model from gyroplane structure, has reduced the complexity of structure, has reduced self structural weight, and the lift-drag is less; the hybrid power of solar energy and electric energy improves the flight time.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to VTOL fixed wing unmanned vehicles.
Background
The vertical take-off and landing fixed wing unmanned aerial vehicle can take off and land vertically in a rotorcraft mode and can cruise forward in a fixed wing mode. Compared with the traditional rotor plane, the vertical take-off and landing fixed wing unmanned aerial vehicle has the advantages of high forward flight speed, long range and long duration; compared with the conventional fixed wing, the vertical take-off and landing fixed wing unmanned aerial vehicle can take off, land and hover at fixed points, does not depend on an airport runway, and obviously enhances the task capability. These advantages have prompted the vertical take-off and landing fixed wing unmanned aerial vehicle to be a major hotspot for the unmanned aerial vehicle industry. With the increasing application of unmanned aerial vehicles and the increasing requirement for long-endurance, how to improve the long endurance of the vertical take-off and landing fixed wing unmanned aerial vehicle is urgent.
At present, there are two main approaches for improving the long endurance of the vertical take-off and landing fixed wing unmanned aerial vehicle: one method is to use power energy sources such as an oil-electricity hybrid engine to improve the sailing time, and although the method can improve the sailing time, the method also increases the self-loading capacity, makes the structure more complicated and improves the cost. The other method is to reduce the appearance and the weight of the structure as much as possible and improve the lift-drag ratio, but compared with the traditional fixed wing, the lift-drag ratio of the existing vertical take-off and landing fixed wing unmanned aerial vehicle is smaller, and the structure needs to be further modified, so that the energy utilization efficiency is higher.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve above-mentioned technical problem, provide a VTOL fixed wing unmanned vehicles, when extension time of endurance, reduced the complexity of structure, reduced self structure weight.
In order to achieve the technical effects, the utility model adopts the following technical scheme: the utility model provides a vertical take-off and landing fixed wing unmanned aerial vehicle, which comprises a body, wherein the body comprises a body, wings, an undercarriage and a rotor wing structure; the wings comprise a first wing and a second wing which are arranged in parallel up and down, and the fuselage is connected between the first wing and the second wing; the undercarriage is fixedly connected to the tail of the undercarriage; the front ends of the first wing and the second wing are respectively fixed with the rotor wing structure, the rotor wing structure comprises a motor and a propeller, the propeller is fixed on an output shaft of the motor, and the output shaft of the motor is parallel to the direction of the head of the aircraft body; the outer surfaces of the first wing and the second wing are covered with solar panels.
The utility model provides a VTOL fixed wing unmanned aerial vehicle combines together rotor structure and fixed wing aircraft structure, adopts the rotor structure to carry out VTOL taking off and descending with descending stage, switches into fixed wing unmanned aerial vehicle mode flight in the flight stage, has reduced the complexity of structure, has reduced weight, adopts the solar cell panel power supply, has prolonged duration.
As the structural improvement of the utility model, the two sides of the wing opposite to the center of the body are respectively fixed with a rotor wing structure.
As an improvement of the structure of the utility model, the wing comprises a wing rib and a wing skin, the wing rib comprises a plurality of rib plates, a plurality of beams, a front beam and a rear edge, the rib plates are arranged in parallel, the beams sequentially pass through the middle parts of the rib plates, and two ends of the beams are fixedly connected with the rib plates; the front beam connects the front ends of the plurality of ribs, and the rear beam connects the rear ends of the plurality of ribs.
As the utility model discloses structural improvement still includes the side lever, the one end of side lever is connected on the crossbeam, the tip of connecting rod is connected to the other end.
As an improvement of the structure of the utility model, the first wing comprises 8 rib plates, 4 rib plates are respectively arranged at two sides of the body, the front end parts of the two rib plates in the middle are connected with a first fixing frame, and a rotary wing structure is fixed at the end part of the first fixing frame; the second wing comprises 14 rib plates, the two sides of the fuselage are respectively provided with 7 rib plates, the front end parts of the third rib plate and the fourth rib plate counted from the fuselage are connected with a second fixing frame, and the end parts of the second fixing frame are fixedly provided with rotor wing structures.
As the utility model discloses structural improvement, the fuselage includes skeleton and fuselage covering, the skeleton includes that two parallel arrangement's web and two are located the floor on two wings respectively, and two floors are located between two webs, and the top and the bottom of two webs are connected respectively on the rib of two wings, and the back end connection of fuselage skeleton has the undercarriage.
By adopting the technical scheme, the method has the following beneficial effects: the utility model provides a vertical take-off and landing fixed wing overcomes the shortcoming that current fixed wing unmanned aerial vehicle improves the method of long endurance, can change into the fixed wing flight model from gyroplane structure, has reduced the complexity of structure, has reduced self structural weight, and the lift-drag is less; the hybrid power of solar energy and electric energy improves the flight time.
Drawings
Fig. 1 is a schematic structural diagram of a vertical take-off and landing fixed-wing unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram (without a skin) of a vertical take-off and landing fixed-wing unmanned aerial vehicle provided by an embodiment of the invention;
FIG. 3 is an enlarged view of a portion of FIG. 2 at A;
fig. 4 is a schematic partial structural view of a first wing according to an embodiment of the present invention;
fig. 5 is a schematic partial structural view of a second wing according to an embodiment of the present invention.
In the figure:
1. a body; 1.1, a framework; 1.11, a web plate; 2. a first airfoil; 3. A second airfoil; 4. a landing gear; 5. a rotor structure; 5.1, a propeller; 6. a solar panel; 231. a rib; 2310. a rib plate; 2311. a cross beam; 2312. a front beam; 2313. a connecting rod; 2314. a rear beam; 2315. a spacer bar; 2316. a reinforcing bar; 2317. side bars.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the accompanying drawings in the embodiments of the present invention are combined below to clearly and completely describe the technical solutions in the embodiments of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without making creative efforts belong to the protection scope of the present invention.
In the present invention, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. These terms are used primarily to better describe the invention and its embodiments, and are not intended to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in the present invention can be understood by those of ordinary skill in the art as appropriate.
Furthermore, the terms "mounted," "disposed," "provided," "connected," and "coupled" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. The specific meaning of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
"plurality" means two or more unless otherwise specified.
The present invention will be described in further detail below with reference to specific embodiments and with reference to the attached drawings.
Example (b):
the embodiment provides a vertical take-off and landing fixed wing unmanned aerial vehicle, which comprises a body, a landing gear, a lifting gear and a wing structure, wherein the body comprises a body 1, wings, a landing gear 4 and a rotor wing structure 5; the wings comprise a first wing 2 and a second wing 3 which are arranged in parallel up and down, the fuselage is connected between the first wing 2 and the second wing 3, and preferably, the length of the first wing 2 is smaller than that of the second wing 3; the aircraft body 1 comprises a head part and a tail part, and the undercarriage 4 is fixedly connected to the tail part of the aircraft body; the front ends of the first wing 2 and the second wing 3 are respectively fixed with a rotor wing structure, the rotor wing structure 5 comprises a motor and a propeller 5.1, the propeller 5.1 is fixed on an output shaft of the motor, and the output shaft of the motor is parallel to the direction of the head of the airplane body; the outer surfaces of the first wing 2 and the second wing 3 are covered with solar panels 6. The solar panel 6 may be fixed to the rib by screws.
It should be noted that the unmanned aerial vehicle is controlled by the flight controller, and is powered by a battery, and the control mode and principle of the flight controller are the prior art and are not explained here. Solar cell panel is connected with the battery, and solar cell panel can be with solar energy transformation for the electric energy, and in this embodiment, flight controller and battery all can install in the fuselage. When unmanned aerial vehicle is in the stage of taking off or descending, unmanned aerial vehicle adopts the vertical take off and landing mode, and the fuselage changes the gesture, and the head of fuselage is up, and the undercarriage is down, drives whole aircraft behind the rotor structure operation and takes off or descends. When unmanned aerial vehicle was in flight state, the fuselage changed the gesture and resumes to the fixed wing mode, and rotor structure stop work, the head of fuselage is the direction of advance. The fuselage gesture changes, can control through the manual operation remote controller, and remote controller send instruction gives flight controller, and flight controller controls unmanned aerial vehicle and changes the gesture.
In order to improve the flying effect of vertical take-off and landing, two sides of the wing, which are opposite to the center of the fuselage, are respectively fixed with a rotor wing structure. This embodiment adopts double-wing structure, and wing area is great, and when low-speed flight, has more lift than single wing aircraft, and pneumatic efficiency is higher, adopts four rotors to rotate and produces power in order to drive unmanned aerial vehicle VTOL, has realized gyroplane's function, can a tractor serves several purposes.
In this embodiment, optionally, the wing includes a rib 231 and a wing skin, and the wing skin covers the surface of the rib, and may be glued; the rib comprises a rib plate 2310, a cross beam 2311, a front beam 2312 and a rear edge, the rib plate 2310 is arranged in parallel, the cross beam 2311 sequentially penetrates through the middles of the rib plates 2310, and two ends of the cross beam 2311 are fixedly connected with the rib plate 2310; the front beam 2312 connects the front ends of the plurality of ribs 2310, and the rear edge connects the rear ends of the plurality of ribs 2310.
Above-mentioned rib structure is favorable to alleviateing unmanned vehicles's weight, has seted up a plurality of lightening holes on floor 2310, and crossbeam 2311, front-axle beam 2312 and trailing edge connect a plurality of floor 2310 as an organic whole effectively, increase the steadiness of connecting, and the trailing edge is provided with to do benefit to and changes unmanned aerial vehicle gesture.
Specifically, the rear edge includes a plurality of link bars 2313, spacer bars 2315, reinforcing bars 2316 and a rear beam 2314, the spacer bars 2315 are arranged in parallel and at intervals, two ends of the spacer bars 2315 are connected with the link bars 2313 and the rear beam 2314, the link bars 2313 are connected with the tail portions of a plurality of rib plates, the reinforcing bars 2316 are arranged in a plurality of inclined positions, and two ends of each reinforcing bar 2316 are connected with the end portions of two adjacent spacer bars 2315. The space bars and the reinforcing rods act together to form a triangular supporting structure, so that the stability of the structure is further enhanced.
In order to improve the stability of the whole structure of the wing, the wing further comprises a side bar 2317, one end of the side bar 2317 is connected to the cross beam 2311, and the other end of the side bar 2317 is connected to the end of the connecting rod 2313.
Specifically, the first wing comprises 8 rib plates, 4 rib plates are arranged on two sides of the body respectively, the front end parts of the two middle rib plates are connected with a first fixing frame, and a rotor wing structure is fixed at the end part of the first fixing frame; the second wing comprises 14 rib plates, the two sides of the fuselage are respectively provided with 7 rib plates, the front end parts of the third rib plate and the fourth rib plate counted from the fuselage are connected with a second fixing frame, and the end parts of the second fixing frame are fixedly provided with rotor wing structures.
In this embodiment, the fuselage includes skeleton 1.1 and fuselage skin, skeleton 1.1 includes two parallel arrangement's web 1.11 and two floor 2310 that are located two wings respectively, and two floor are located between two webs, and the top and the bottom of two webs are connected respectively on the rib 231 of two wings, and the rear end connection of skeleton has undercarriage 4. The fuselage skeleton is connected as an organic whole with the rib of two wings, and simple structure, when unmanned vehicles descends, the undercarriage has the supporting role.
Fuselage covering covers on the skeleton 1.1, in order to reduce unmanned vehicles's flight resistance, the head of fuselage presents the arrow point form, forms the empty cabin structure that holds the goods in the fuselage, and the afterbody that is located the fuselage of undercarriage one side is equipped with the hatch door. The inside of the fuselage may carry flight controls, batteries or cargo.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A vertical take-off and landing fixed wing unmanned aerial vehicle is characterized by comprising a body, wherein the body comprises a body, wings, an undercarriage and a rotor wing structure; the wings comprise a first wing and a second wing which are arranged in parallel up and down, and the fuselage is connected between the first wing and the second wing; the undercarriage is fixedly connected to the tail of the undercarriage; the front ends of the first wing and the second wing are respectively fixed with the rotor wing structures, each rotor wing structure comprises a motor and a propeller, the propellers are fixed on an output shaft of the motor, and the output shaft of the motor is parallel to the direction of the head of the aircraft body; and the outer surfaces of the first wing and the second wing are covered with solar panels.
2. The VTOL fixed-wing UAV of claim 1, wherein one rotor structure is fixed to each side of the wing opposite to the center of the fuselage.
3. The VTOL fixed-wing unmanned aerial vehicle of claim 1, wherein the wing comprises a rib and a wing skin, the rib comprises a plurality of ribs, a cross beam, a front beam and a rear edge, the plurality of ribs are arranged in parallel, the cross beam sequentially passes through the middle of the plurality of ribs, and two ends of the cross beam are fixedly connected with the ribs; the front beam connects the front ends of the plurality of ribs, and the rear beam connects the rear ends of the plurality of ribs.
4. The VTOL fixed wing UAV of claim 3, wherein the trailing edge comprises a plurality of link rods, spacer rods, a plurality of reinforcement rods and a back beam, the spacer rods are arranged in parallel and at intervals, two ends of the spacer rods are connected with the link rods and the back beam, the reinforcement rods are arranged in a plurality of inclined positions, and two ends of each reinforcement rod are connected with the ends of two adjacent spacer rods.
5. The VTOL fixed-wing UAV of claim 4, further comprising a side bar having one end connected to the cross-beam and the other end connected to an end of a link.
6. The VTOL fixed-wing UAV of claim 3, wherein the first wing comprises 8 ribs, 4 ribs are respectively arranged at two sides of the fuselage, a first fixing frame is connected with the front end parts of the two middle ribs, and a rotor wing structure is fixed at the end part of the first fixing frame; the second wing comprises 14 rib plates, 7 rib plates are arranged on two sides of the airplane body respectively, the front end parts of the third rib plate and the fourth rib plate counted from the airplane body are connected with a second fixing frame, and the end parts of the second fixing frame are fixed with rotor wing structures.
7. The VTOL fixed wing unmanned aerial vehicle of claim 3, wherein the fuselage comprises a skeleton and a fuselage skin, the skeleton comprises two webs arranged in parallel and two ribs respectively arranged on the two wings, the two ribs are arranged between the two webs, the top and the bottom of the two webs are respectively connected to ribs of the two wings, and the landing gear is connected to the rear end of the fuselage skeleton.
8. The VTOL fixed wing UAV according to claim 7, wherein the fuselage skin covers the skeleton, the nose of the fuselage is arrow-shaped, an empty cabin structure for accommodating goods is formed in the fuselage, and a cabin door is arranged at the tail of the fuselage on one side of the landing gear.
9. The VTOL fixed-wing UAV of claim 1, wherein a length of the first wing is less than a length of the second wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222733497.0U CN218317307U (en) | 2022-10-18 | 2022-10-18 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222733497.0U CN218317307U (en) | 2022-10-18 | 2022-10-18 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218317307U true CN218317307U (en) | 2023-01-17 |
Family
ID=84824589
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222733497.0U Active CN218317307U (en) | 2022-10-18 | 2022-10-18 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218317307U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117208259A (en) * | 2023-05-18 | 2023-12-12 | 河北建筑工程学院 | Hybrid unmanned aerial vehicle |
-
2022
- 2022-10-18 CN CN202222733497.0U patent/CN218317307U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117208259A (en) * | 2023-05-18 | 2023-12-12 | 河北建筑工程学院 | Hybrid unmanned aerial vehicle |
| CN117208259B (en) * | 2023-05-18 | 2024-04-16 | 河北建筑工程学院 | Hybrid unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN214451855U (en) | Duck wing VTOL unmanned aerial vehicle | |
| CN110949662B (en) | Novel concept layout airplane with double-wing configuration | |
| CN207917151U (en) | Oily electricity mixing VTOL fixed-wing unmanned plane | |
| CN111268089B (en) | Double-fuselage vertical take-off and landing fixed wing unmanned aerial vehicle structure | |
| CN106628168A (en) | Novel tilt rotor aircraft | |
| CN112937849A (en) | Vertical take-off and landing aircraft with combined layout of tilting type propeller and fixed propeller | |
| CN208377055U (en) | A kind of Fixed Wing AirVehicle | |
| CN218317307U (en) | Vertical take-off and landing fixed wing unmanned aerial vehicle | |
| CN112141329A (en) | Vertical take-off and landing solar unmanned aerial vehicle | |
| CN211281472U (en) | Duct tail sitting posture VTOL unmanned aerial vehicle | |
| CN209176908U (en) | A kind of rotor fixed-wing unmanned plane of composite drive | |
| CN107284658B (en) | Composite vertical/short-distance take-off and landing aircraft | |
| CA3228095A1 (en) | Vertical take-off and landing craft systems and methods | |
| CN215043672U (en) | Aircraft with four ducts in tilting layout | |
| CN218463872U (en) | Vertical take-off and landing aircraft with combined layout of tilting type propeller and fixed propeller | |
| CN214029126U (en) | Coaxial double-propeller combined thrust helicopter | |
| CN112027080B (en) | Hybrid electric propulsion vertical take-off and landing unmanned aerial vehicle using bimodal power cabin | |
| CN108583869B (en) | X-shaped sweepback wing unmanned aerial vehicle | |
| CN112896500A (en) | Aircraft with four ducts in tilting layout | |
| CN217575599U (en) | Light aircraft convenient to VTOL | |
| CN110683030A (en) | Unmanned aerial vehicle capable of taking off and landing vertically | |
| CN220924493U (en) | Aircraft of mixed many rotor designs | |
| CN205345311U (en) | Stationary vane solar powered aircraft | |
| CN217198643U (en) | Aircraft | |
| CN109279007B (en) | Composite driving rotor wing fixed wing unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |