CN221214603U - Vertical take-off and landing fixed wing unmanned aerial vehicle - Google Patents

Abstract

The utility model aims to solve the technical problem of providing a vertical take-off and landing fixed wing unmanned aerial vehicle which has a simple structure and a relatively high weight, and is convenient for launching a patrol projectile and completing other tasks. The vertical take-off and landing fixed wing unmanned aerial vehicle comprises a fuselage, wherein a mission load cabin is arranged at the front end of the fuselage, and an energy cabin and a flight control system are arranged in the fuselage; the front end of the fuselage is provided with two first fixed wings, the rear end of the fuselage is provided with two second fixed wings and two third fixed wings, one end of the fuselage is kept away from to two second fixed wings and two third fixed wings is provided with a power system, through the power system design of four sets of vertical arrangement, the vertical take-off of the unmanned aerial vehicle can be realized, the posture of the unmanned aerial vehicle is adjusted through controlling four power systems, the whole machine is enabled to tilt by 90 degrees, the flight is carried out in a fixed wing mode, the efficient pneumatic design is utilized, long-endurance flight can be realized, and very high end attack speed is achieved, and tasks such as the launching of a patrol missile are realized through the set task load cabin.

Description

Vertical take-off and landing fixed wing unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing fixed wing unmanned aerial vehicle.

Background

With the continuous development of unmanned aerial vehicle technology, unmanned aerial vehicle's flight performance and mission ability are receiving attention more and more, especially in the complex environment, unmanned aerial vehicle's vertical take-off and landing technique can improve its adaptability greatly. The method is widely applied to the fields of aerial photography, logistics distribution, geological survey, rescue and the like, and is also used for combat missions such as the deployment of patrol missiles. Conventional fly-by-fly projectiles require complex ground launching systems, and also take into account impact overload during ground launching, and the folding and unfolding mechanism of the wing and the resulting structural strength and rigidity issues.

Disclosure of utility model

The utility model aims to solve the technical problem of providing the vertical take-off and landing fixed wing unmanned aerial vehicle which has a simple structure and a relatively high weight, is convenient for launching a patrol projectile and completing other tasks.

The technical scheme adopted for solving the technical problems is as follows: the vertical take-off and landing fixed wing unmanned aerial vehicle comprises a machine body, wherein a task load cabin is arranged at the front end of the machine body through a detachable structure, and an energy cabin and a flight control system are arranged in the machine body;

Two first fixed wings are symmetrically arranged at the front end of the outer side wall of the machine body in a left-right manner, two second fixed wings are symmetrically arranged at the rear end of the outer side wall of the machine body in a left-right manner, and two third fixed wings are symmetrically arranged at the rear end of the outer side wall of the machine body in an up-down manner;

The two second fixed wings and the two third fixed wings are respectively provided with a power system at one end far away from the machine body;

the energy bin is used for providing the power system and the flight control system with the required kinetic energy.

Further, the power system comprises a propeller and a power control cabin, wherein the propeller is arranged at the front side of the corresponding power control cabin;

The power control cabin comprises a power mechanism and a tilting mechanism, wherein the screw propeller is in driving connection with the power mechanism, and the tilting mechanism is used for adjusting the rotation angle of the corresponding screw propeller.

Further, the surface areas of the first fixed wing, the third fixed wing and the second fixed wing are sequentially increased.

Further, the detachable structure is a screw connection structure.

Further, the mission load cabin is a patrol projectile.

Further, the mission load compartment is an optoelectronic pod.

The utility model has the beneficial effects that:

1. Through four sets of power system designs that arrange perpendicularly, can realize unmanned aerial vehicle's vertical take off, take off perpendicularly and rise to the safe high back, adjust unmanned aerial vehicle's gesture through four power systems of control, make the complete machine tilt 90 degrees, fly with the fixed wing mode, utilize efficient pneumatic design, can realize long-endurance flight to and very high end section attack speed.

2. The mission load cabin that realizes patrolling the missiles through setting up is launched, compares in traditional patrolling the missiles and launches, need not complicated ground transmission system, need not to consider the impact overload when launching on ground to and the folding expansion mechanism of wing and the structural strength rigidity problem that brings from this, and structure weight is lighter, and the system is simpler, and the cost is lower.

3. When the unmanned aerial vehicle flies in the fixed wing mode, pitch and course control can be realized by utilizing the differential motion of four power systems, rolling control can be realized by utilizing the unbalanced anti-torque moment caused by the rotation speed difference of the four power systems, and the control efficiency can be improved by utilizing the rotation speed differential motion and the traditional pneumatic control surface cooperation and joint control.

Drawings

Fig. 1 is a schematic structural view of the vertical take-off and landing fixed wing unmanned aerial vehicle according to the present utility model;

The figure indicates: fuselage 1, mission load compartment 2, first fixed wing 3, second fixed wing 4, third fixed wing 5, driving system 6, screw 601, power control cabin 602.

Detailed Description

The following detailed description of the utility model will be further understood with reference to the drawings, in which embodiments described are merely some, but not all, examples of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

It should be noted that, in the embodiments of the present utility model, all directional indicators such as "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the drawings, which are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the device or element to be referred to must have a specific direction, be configured and operated in a specific direction, and thus should not be construed as limiting the present utility model, but merely serve to explain the relative positional relationships, movement situations, etc. between the components in a specific posture, and if the specific posture is changed, the directional indicators are correspondingly changed.

In the present application, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.

In addition, if there is a description of "first", "second", etc. in the embodiments of the present application, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" as it appears throughout includes three parallel schemes, for example "A and/or B", including the A scheme, or the B scheme, or the scheme where A and B are satisfied simultaneously. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present application.

As shown in fig. 1, the vertical take-off and landing fixed wing unmanned aerial vehicle comprises a body 1, wherein a task load cabin 2 is arranged at the front end of the body 1 through a detachable structure, the task load cabin 2 can be selected according to actual requirements, a patrol projectile can be loaded, and other loads can be replaced, the environment is not limited herein, an energy bin and a flight control system are arranged in the body 1, the energy bin is used for providing power for each power component, the flight control system is used for controlling the flight of the whole unmanned aerial vehicle, and the energy bin and the flight control system are all of the prior art and are not described in detail herein;

Two first fixed wings 3 are symmetrically arranged at the front end of the outer side wall of the machine body 1 in a left-right manner, two second fixed wings 4 are symmetrically arranged at the rear end of the outer side wall of the machine body 1 in a left-right manner, two third fixed wings 5 are symmetrically arranged at the rear end of the outer side wall of the machine body 1 in an up-down manner, and the two second fixed wings 4 and the two third fixed wings 5 form a cross-like structure;

The two second fixed wings 4 and the two third fixed wings 5 are respectively provided with a power system 6 at one end far away from the machine body 1, namely the whole machine is provided with four sets of power systems 6 which are vertically distributed;

the energy bin is used for providing the power system 6 and the flight control system with the required kinetic energy, and is generally a battery assembly.

As shown in fig. 1, in the present embodiment, preferably, the power system 6 includes a propeller 601 and a power control cabin 602, and the propeller 601 is disposed at a front side of the corresponding power control cabin 602;

The power control cabin 602 includes a power mechanism and a tilting mechanism, which are all in the prior art, and are not described in detail herein, the propeller 601 is in driving connection with the power mechanism, the power mechanism is used for driving the corresponding propeller 601 to rotate, the tilting mechanism is used for adjusting the rotation angle of the corresponding propeller 601, a four-rotor mode is adopted for vertical take-off, the deployment is convenient, the operation and the use are convenient, the unmanned aerial vehicle can return to the air autonomously if no attack is performed after the launching of the patrol projectile, and can be reused, after the unmanned aerial vehicle vertically takes off and rises to a safe height, the flying posture of the unmanned aerial vehicle is adjusted through differential control of four rotors, so that the whole unmanned aerial vehicle tilts for 90 degrees, flies in a fixed wing mode, and long-time flying and very high end attack speed can be realized by utilizing an efficient pneumatic design; when the fixed wing mode flies, pitch and course control can be realized by utilizing the differential motion of four rotor wing power, rolling control can be realized by utilizing the unbalanced anti-torque moment caused by the rotation speed difference of the four rotor wing power, and the control efficiency can be improved by utilizing the rotation speed differential motion and the traditional pneumatic control surface to cooperate and jointly control.

As shown in fig. 1, in this embodiment, preferably, the surface areas of the first fixed wing 3, the third fixed wing 5 and the second fixed wing 4 are sequentially increased, and such a pneumatic layout facilitates the vertical take-off and the fixed wing mode flight of the unmanned aerial vehicle.

In this embodiment, as the preference, detachable construction is screw connection structure, also can adopt other dismantlement modes can realize dismantling can, be convenient for change different load cabins through detachable construction, satisfy different task demands.

In this embodiment, as an preference, the mission load cabin 2 is a flying-shell cabin, and the flying-shell is launched by the vertical-take-off and landing fixed-wing unmanned aerial vehicle.

In this embodiment, the task load pod 2 is preferably a photoelectric pod, so as to track, pick up, monitor, etc. the target in the long distance in all weather, and the photoelectric pod is only one of the task load pods 2, and may be replaced by another task load pod 2.

The foregoing description is only of the preferred embodiments of the present application, and is not intended to limit the scope of the application, but rather is intended to cover any equivalents of the structures or equivalent processes disclosed herein or in the alternative, which may be employed directly or indirectly in other related arts.

Claims (6)

1. The utility model provides a fixed wing unmanned aerial vehicle takes off and land perpendicularly, includes fuselage (1), its characterized in that: the front end of the machine body (1) is provided with a task load cabin (2) through a detachable structure, and an energy bin and a flight control system are arranged in the machine body (1);

Two first fixed wings (3) are symmetrically arranged at the front end of the outer side wall of the machine body (1) in a left-right mode, two second fixed wings (4) are symmetrically arranged at the rear end of the outer side wall of the machine body (1) in a left-right mode, and two third fixed wings (5) are symmetrically arranged at the rear end of the outer side wall of the machine body (1) in an up-down mode;

One end, far away from the machine body (1), of each of the two second fixed wings (4) and the two third fixed wings (5) is provided with a power system (6);

The energy bin is used for providing the power system (6) and the flight control system with the required kinetic energy.

2. The vertical take-off and landing fixed wing unmanned aerial vehicle of claim 1, wherein: the power system (6) comprises a propeller (601) and a power control cabin (602), wherein the propeller (601) is arranged at the front side of the corresponding power control cabin (602);

The power control cabin (602) comprises a power mechanism and a tilting mechanism, wherein the propeller (601) is in driving connection with the power mechanism, and the tilting mechanism is used for adjusting the rotation angle of the corresponding propeller (601).

3. The vertical take-off and landing fixed wing unmanned aerial vehicle of claim 1, wherein: the surface areas of the first fixed wing (3), the third fixed wing (5) and the second fixed wing (4) are sequentially increased.

4. The vertical take-off and landing fixed wing unmanned aerial vehicle of claim 1, wherein: the detachable structure is a screw connection structure.

5. The vertical take-off and landing fixed wing unmanned aerial vehicle of claim 1, wherein: the task load cabin (2) is a patrol projectile.

6. The vertical take-off and landing fixed wing unmanned aerial vehicle of claim 1, wherein: the task load cabin (2) is an optoelectronic pod.