CN219215392U - Unmanned plane - Google Patents

Abstract

The embodiment of the application discloses unmanned aerial vehicle, include: the aircraft comprises an aircraft body, wings, duck wings and a vertical take-off motor arm, wherein the aircraft body is in a spindle shape, and the wings are arranged in the middle of the aircraft body, so that the gravity center of the aircraft is close to the wings, and the flight stability of the aircraft is kept. The duck wing sets up in the aircraft nose below, and the setting of duck wing has replaced the horizontal fin of conventional overall arrangement unmanned aerial vehicle tail to make whole fuselage length reduce, reduced unmanned aerial vehicle and dismantled vanning's packing size, in addition, the duck wing can play pitch control effect in the flight, can provide the lift that is still bigger than the conventional overall arrangement unmanned aerial vehicle that uses the same wing area again, has promoted the ability of carrying on mission nacelle. The lifting force increased by the duck wings enables the gravity center of airplane flight balancing to move forward to the middle of the airplane body, the section of the position is the maximum section of the spindle type airplane body, the section is square and large in space, and the airplane is more suitable for carrying batteries, flight control and task pods. The vertical-lift motor arm plays a role in fixing the vertical-lift power component in the unmanned aerial vehicle lifting process.

Description

Unmanned plane

Technical Field

The embodiment of the application relates to the technical field of aircrafts, in particular to an unmanned aerial vehicle.

Background

The fixed wing unmanned aerial vehicle with the vertical lifting function has the advantages of low lifting requirement and simple control, and has wide application in the field of military scientific research and civil use. The multi-rotor vertical take-off and landing mode using the motor as power is widely applied to the pneumatic design of the vertical take-off and landing fixed-wing unmanned aerial vehicle due to the advantages of simple structure, convenience in maintenance, simplicity and convenience in manufacturing, low cost and the like. Most of the conventional vertical take-off and landing fixed-wing unmanned aerial vehicles are arranged in a conventional manner, the fuselage is long, the purpose is that the horizontal tail wing and the vertical tail wing of the aircraft can be placed at the tail part of the fuselage, the horizontal tail wing and the vertical tail wing can be installed far away from wings as far as possible, and the overlong fuselage is inconvenient for boxing and transportation; because the gravity center of the aircraft needs to be designed near the wing, the conventional layout fuselage is longer, and if the aircraft nose or the aircraft tail is provided with a task load, a power supply, flight control equipment and the like, the gravity center of the aircraft is far away from the near the wing, so that the aircraft is unstable in the flight process. In industry applications, fixed-wing vertical take-off and landing unmanned aerial vehicles typically use a double-tail-rod plus gate type tail structure to supply aircraft thrust, but the double-tail structure adds to the fuselage weight.

Therefore, it is necessary to develop a vertical take-off and landing fixed wing unmanned aerial vehicle which has a short length, a simple structure, a light weight and a more suitable space for carrying task loads.

Disclosure of Invention

The present utility model aims to solve at least one of the technical problems existing in the prior art or related art.

In view of this, the embodiment of the present application proposes a unmanned aerial vehicle, including:

the machine body is in a spindle shape;

a wing disposed on the fuselage;

the wing is an asymmetric biconvex wing with the relative thickness of 10-15%, the root tip ratio is 0.4, the forward and backward sweep angle of the front edge is 15-25 degrees, the forward and backward sweep angle of the rear edge is 15-25 degrees, and the installation angle is 0-5 degrees;

the duck wings are arranged below the machine head of the machine body;

the number of the vertical motor arms is multiple, and the vertical motor arms are arranged at the root of the wing.

In a possible embodiment, the unmanned aerial vehicle further comprises:

the machine belly vertical tail is arranged at one end, close to the machine tail, of the lower part of the machine body;

the machine belly vertical tail is a symmetrical biconvex wing shape with the relative thickness of 10-15%, the root tip ratio is 0.6, the forward and backward glancing angle of the front edge is 15-25 degrees, and the forward and backward glancing angle of the rear edge is 15-25 degrees.

In a possible embodiment, the unmanned aerial vehicle further comprises:

the wing tip vertical tail is arranged at one end far away from the root of the wing, and is perpendicular to the wing;

the wing tip vertical end is a symmetrical biconvex wing shape with the relative thickness of 10-15%, the root tip ratio is 0.5-0.7, the front-edge sweepback angle is 10-20 degrees, and the rear-edge front-back sweepback angle is 10-20 degrees.

In one possible implementation, the duck wings are arranged below the nose of the fuselage in a dihedral angle, the duck wings are asymmetric biconvex wings with a relative thickness of 10% -15%, the root tip ratio is 0.9, the forward and backward sweep angles are 0-5 degrees, the forward and backward sweep angles of the rear edges are 0 degrees, the dihedral angle is 4-8 degrees, and the installation angle is 0-5 degrees.

In a possible embodiment, the unmanned aerial vehicle further comprises:

the vertical rotor wing is connected with the vertical motor arm;

wherein, the vertical rotor wing is a double-blade paddle, and the paddle size is 25-30 inches.

In a possible embodiment, the unmanned aerial vehicle further comprises:

the support foot rest is connected to the lower part of the duck wing.

In a possible embodiment, the unmanned aerial vehicle further comprises:

the propeller is arranged on the tail, the propeller size of the propeller is 16-20 inches, and the number of the propeller blades is 2-3.

Compared with the prior art, the utility model at least comprises the following beneficial effects: the unmanned aerial vehicle that this application embodiment provided includes: the aircraft comprises an aircraft body, wings, duck wings and a vertical take-off motor arm, wherein the aircraft body is in a spindle shape, and the wings are arranged in the middle of the aircraft body, so that the gravity center of the aircraft is close to the wings, and the flight stability of the aircraft is kept. The duck wing sets up in the aircraft nose below, and the setting of duck wing has replaced the horizontal fin of conventional overall arrangement unmanned aerial vehicle tail to make whole fuselage length reduce, reduced unmanned aerial vehicle and dismantled vanning's packing size, in addition, the duck wing can play pitch control effect in the flight, can provide the lift that is still bigger than the conventional overall arrangement unmanned aerial vehicle that uses the same wing area again, has promoted the ability of carrying on mission nacelle. The lifting force increased by the duck wings enables the gravity center of airplane flight balancing to move forward to the middle of the airplane body, the section of the position is the maximum section of the spindle type airplane body, the section is square and large in space, and the airplane is more suitable for carrying batteries, flight control and task pods. The vertical-lift motor arm plays a role in fixing the vertical-lift power component in the unmanned aerial vehicle lifting process.

Drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the application. Also, like reference numerals are used to designate like parts throughout the figures. In the drawings:

FIG. 1 is a top view of an embodiment of a drone of one embodiment provided herein;

FIG. 2 is a side view of an embodiment of a drone of one embodiment provided herein;

FIG. 3 is a rear view of an embodiment of a drone of one embodiment provided herein;

FIG. 4 is a front view of an embodiment of a drone of one embodiment provided herein;

FIG. 5 is a bottom view of an embodiment of a drone of one embodiment provided herein;

the correspondence between the reference numerals and the component names in fig. 1 to 5 is:

1: fuselage, 2: wing, 3: duck wings, 4: vertical motor arm, 5: and (3) hanging up the rotor wing, 6: thrust propeller, 7: the wing slightly hangs down, 8: ventral tail, 9: duck wing control surface, 10: outer aileron, 11: inner aileron, 12: and supporting the foot rest.

Detailed Description

In order to better understand the technical solutions described above, the technical solutions of the embodiments of the present application are described in detail below through the accompanying drawings and the specific embodiments, and it should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical solutions of the embodiments of the present application, and not limit the technical solutions of the present application, and the embodiments of the present application and the technical features in the embodiments of the present application may be combined with each other without conflict.

As shown in fig. 1 to 5, an embodiment of the present application proposes an unmanned aerial vehicle, including: a body 1, wherein the body 1 is in a spindle shape; a wing 2, said wing 2 being arranged on said fuselage 1; the wing 2 is an asymmetric biconvex wing with the relative thickness of 10-15%, the root tip ratio is 0.4, the forward and backward sweep angle of the front edge is 15-25 degrees, the forward and backward sweep angle of the rear edge is 15-25 degrees, and the installation angle is 0-5 degrees; the duck wings 3 are arranged below the nose of the fuselage 1; the number of the vertical motor arms 4 is plural, and the vertical motor arms 4 are provided at the root of the wing 2.

The unmanned aerial vehicle that this application embodiment provided includes: the aircraft comprises an airframe 1, wings 2, a duck wing 3 and a vertical-lift motor arm 4, wherein the airframe 1 is in a spindle shape, and the wings 2 are arranged in the middle of the airframe 1, so that the gravity center of the aircraft is close to the wings 2, and the flight stability of the aircraft is maintained. The duck wing 3 sets up in the aircraft nose below, and the setting of duck wing 3 has replaced the horizontal fin of conventional overall arrangement unmanned aerial vehicle tail to make whole fuselage 1 length reduce, reduced unmanned aerial vehicle dismantles vanning's packing size, in addition, duck wing 3 can play pitch control effect in the flight process and can provide the lift that is still bigger than the conventional overall arrangement unmanned aerial vehicle that uses the same wing 2 area again, promoted the ability of carrying on mission nacelle. The lifting force added by the duck wings 3 enables the gravity center of airplane flight balancing to move forward to the middle of the fuselage 1, the section of the position is the maximum section of the spindle-type fuselage 1, the section is square and large in space, and the aircraft is more suitable for carrying batteries, flight control and mission cabins. The vertical-lift motor arm 4 plays a role in fixing a vertical-lift power component in the unmanned aerial vehicle lifting process.

As shown in fig. 1 to 5, in one possible embodiment, the unmanned aerial vehicle further comprises: the machine belly vertical tail 8 is arranged at one end, close to the machine tail, of the lower part of the machine body 1; the machine belly vertical tail 8 is a symmetrical biconvex airfoil with the relative thickness of 10-15%, the root tip ratio is 0.6, the forward and backward glancing angles of the front edge are 15-25 degrees, and the forward and backward glancing angles of the rear edge are 15-25 degrees.

In the technical scheme, the arrangement of the belly vertical tail 8 enables the unmanned aerial vehicle to have a support at the rear part of the machine body 1 in the stop state or vertical lifting process, and meanwhile plays a role in lifting the height of the machine body 1, so that the ground clearance of the propeller and the belly nacelle is increased.

As shown in fig. 1 to 5, in one possible embodiment, the unmanned aerial vehicle further comprises: a tip-to-tail 7, the tip-to-tail 7 being disposed at an end remote from the root of the wing 2, and the tip-to-tail 7 being disposed perpendicular to the wing 2; the wing tip vertical tail 7 is a symmetrical biconvex wing shape with the relative thickness of 10-15%, the root tip ratio is 0.5-0.7, the front-edge sweepback angle is 10-20 degrees, and the rear-edge front-back sweepback angle is 10-20 degrees.

In this technical scheme, the vertical fin of upper and lower symmetry is installed to wing 2 wing slightly, has so set up and has played the effect of stable course to replaced the vertical fin of conventional overall arrangement unmanned aerial vehicle tail, made short fuselage 1 design realized, reduced unmanned aerial vehicle dismantlement vanning's packing size.

In one possible embodiment, as shown in fig. 4, the duck wings 3 are arranged under the nose of the fuselage 1 at a dihedral angle, the duck wings 3 are asymmetric biconvex wings with a relative thickness of 10% -15%, the root tip ratio is 0.9, the forward and backward sweep angles are 0 ° to 5 °, the forward and backward sweep angles of the rear edge are 0 °, the dihedral angle is 4 ° to 8 °, and the installation angle is 0 ° to 5 °.

In this technical scheme, through setting up the duck wing 3, replaced the horizontal fin of conventional overall arrangement unmanned aerial vehicle tail, combined upper and lower symmetrical wing slightly vertical fin 7, reduced tail length under the prerequisite that does not change every single move and driftage control efficiency for short fuselage 1 design is realized, has reduced unmanned aerial vehicle and has dismantled the packing size of vanning.

As shown in fig. 2, in one possible embodiment, the unmanned aerial vehicle further comprises: a vertical rotor 5, wherein the vertical rotor 5 is connected with the vertical motor arm 4; wherein, the vertical rotor wing 5 is a double-blade paddle, and the paddle size is 25-30 inches.

In this technical scheme, set up and hang down rotor 5 and be used for providing the effect of lifting force for unmanned aerial vehicle at the in-process of taking off and land, the quality of double-bladed oar is lighter, the air resistance in the operation process is less, so set up and be favorable to reducing unmanned aerial vehicle's power energy consumption.

As shown in fig. 3, in a possible embodiment, the unmanned aerial vehicle further includes: a support foot rest 12, the support foot rest 12 is connected to the lower part of the duck wing 3.

In the technical scheme, the support foot rest 12 is arranged to enable the unmanned aerial vehicle to have a support at the front part of the airplane body 1 in the stop state or vertical lifting process, and is fused with the duck wings 3, so that the foot rest function of vertical lifting is realized without increasing additional structural weight and aerodynamic resistance, the height of the airplane body 1 is raised, and the ground clearance of the propeller and the airplane belly pod is increased.

As shown in fig. 1 to 5, in a possible embodiment, the unmanned aerial vehicle further comprises: the propeller 6, the propeller 6 is arranged on the tail, the propeller size of the propeller 6 is 16-20 inches, and the number of the blades is 2-3.

In this solution, the thrust propeller 6 is used to provide a flat flight thrust of the unmanned aerial vehicle.

In some examples, the unmanned aerial vehicle may further include a duck wing control surface 9, an outer aileron 10, and an inner aileron 11, the duck wing control surface 9 being connected to the duck wing 3, the outer aileron 10 and the inner aileron 11 being connected to the wing 2 for adjusting the attitude of the unmanned aerial vehicle.

In the present utility model, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; the term "plurality" means two or more, unless expressly defined otherwise. The terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; "coupled" may be directly coupled or indirectly coupled through intermediaries. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.

In the description of the present utility model, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", "front", "rear", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the devices or units referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present utility model.

In the description of the present specification, the terms "one embodiment," "some embodiments," "particular embodiments," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present utility model. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The above is only a preferred embodiment of the present utility model, and is not intended to limit the present utility model, but various modifications and variations can be made to the present utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.

Claims (7)

1. An unmanned aerial vehicle, comprising:

the machine body is in a spindle shape;

a wing disposed on the fuselage;

the wing is an asymmetric biconvex wing with the relative thickness of 10-15%, the root tip ratio is 0.4, the forward and backward sweep angle of the front edge is 15-25 degrees, the forward and backward sweep angle of the rear edge is 15-25 degrees, and the installation angle is 0-5 degrees;

the duck wings are arranged below the machine head of the machine body;

the number of the vertical motor arms is multiple, and the vertical motor arms are arranged at the root of the wing.

2. The unmanned aerial vehicle of claim 1, further comprising:

the machine belly vertical tail is arranged at one end, close to the machine tail, of the lower part of the machine body;

the machine belly vertical tail is a symmetrical biconvex wing shape with the relative thickness of 10-15%, the root tip ratio is 0.6, the forward and backward glancing angle of the front edge is 15-25 degrees, and the forward and backward glancing angle of the rear edge is 15-25 degrees.

3. The unmanned aerial vehicle of claim 1, further comprising:

the wing tip vertical tail is arranged at one end far away from the root of the wing, and is perpendicular to the wing;

the wing tip vertical end is a symmetrical biconvex wing shape with the relative thickness of 10-15%, the root tip ratio is 0.5-0.7, the front-edge sweepback angle is 10-20 degrees, and the rear-edge front-back sweepback angle is 10-20 degrees.

4. The unmanned aerial vehicle of claim 1, wherein the unmanned aerial vehicle comprises,

the duck wings are arranged below a machine head of the machine body in a downward dihedral angle, the duck wings are asymmetric biconvex wings with the relative thickness of 10% -15%, the root tip ratio is 0.9, the forward and backward glancing angles of the front edge are 0-5 degrees, the forward and backward glancing angles of the rear edge are 0 degrees, the downward dihedral angle is 4-8 degrees, and the installation angle is 0-5 degrees.

5. The unmanned aerial vehicle of claim 1, further comprising:

the vertical rotor wing is connected with the vertical motor arm;

wherein, the vertical rotor wing is a double-blade paddle, and the paddle size is 25-30 inches.

6. The unmanned aerial vehicle of claim 1, further comprising:

the support foot rest is connected to the lower part of the duck wing.

7. The unmanned aerial vehicle of claim 1, further comprising:

the propeller is arranged on the tail, the propeller size of the propeller is 16-20 inches, and the number of the propeller blades is 2-3.

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