CN210634742U

CN210634742U - Unmanned aerial vehicle

Info

Publication number: CN210634742U
Application number: CN201920934351.8U
Authority: CN
Inventors: 陈方豪
Original assignee: SF Technology Co Ltd
Current assignee: Fengyi Technology (Shenzhen) Co.,Ltd.
Priority date: 2019-06-20
Filing date: 2019-06-20
Publication date: 2020-05-29
Anticipated expiration: 2029-06-20

Abstract

The application discloses unmanned aerial vehicle, including the fuselage, the head releasable connection of fuselage have the head radome fairing the afterbody releasable connection of fuselage has the afterbody radome fairing, head radome fairing and afterbody radome fairing are the power function curve along its longitudinal profile's curve section. Because the curve sections of the head fairing and the tail fairing along the longitudinal section of the head fairing and the tail fairing are power function curves, the front flow field and the rear flow field of the airframe are optimized on the basis of smooth transition of the head fairing and the airframe, the pressure difference resistance and the possibility of air flow separation are reduced, the purpose of reducing the flight resistance of the whole aircraft is realized, and the requirement of the whole aircraft on a power system is correspondingly reduced along with the reduction of the flight resistance of the whole aircraft.

Description

Unmanned aerial vehicle

Technical Field

The utility model relates to an aircraft technical field, concretely relates to unmanned aerial vehicle.

Background

Along with the progress of science and technology, unmanned aerial vehicle gets into people's sight gradually, and some auxiliary work can be accomplished to the development of unmanned aerial vehicle technique to help people. In the abominable region of environment, unmanned aerial vehicle can replace people to carry out work such as shoot, put in article, solves a difficult problem for people.

With the continuous development of the logistics industry in recent years, unmanned aerial vehicle cargo transportation is vigorously developed in all countries in the world. The unmanned aerial vehicle fuselage, which is an important component of the unmanned aerial vehicle, is a main structural part for providing installation positions for wings, vertical tails, cargo holds and the like. Because the proportion of the area of the airframe of the logistics unmanned aerial vehicle in the area of the whole machine is relatively high, the requirements on the pneumatic appearance and the pneumatic performance of the airframe are relatively high except for the consideration on the structural strength and rigidity of the airframe, so that the resistance of the airframe is reduced, the lift-drag ratio of the whole machine is improved, the pressure of a power system is reduced, and the energy consumption is reduced.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an unmanned aerial vehicle for reduce whole quick-witted flight resistance, and reduce the requirement of complete machine to driving system.

The utility model provides an unmanned aerial vehicle, the reciprocating impact tunnel drilling machine comprises a machine body, the head releasable connection of fuselage the head fairing the afterbody releasable connection of fuselage has the afterbody fairing, a serial communication port, head fairing and afterbody fairing are power function curve along its longitudinal profile's curve section.

Further, the power function curve is:

wherein n is more than or equal to 0 and less than or equal to 1, R is the radius of an inscribed circle at the connecting part of the fairing and the airframe, and L is the length of the fairing.

Furthermore, the fuselage comprises a square fuselage section located in the middle and oval fuselage sections located at two ends, and the oval fuselage sections are in smooth transition with the corresponding head fairing and the tail fairing respectively.

Further, the curve segment of the transverse cross section of the elliptical fuselage section is an elliptical function curve, and the elliptical function curve is as follows:

wherein x is more than or equal to a and less than or equal to b, y is more than or equal to b and 0 is more than or equal to n.

Furthermore, the fuselage is fixedly connected with a wing, and the fuselage and/or the wing are connected with a battery compartment.

Furthermore, the battery compartment is symmetrically arranged on two sides of the machine body.

Furthermore, the head part of the battery compartment is detachably connected with the head part fairing, and the tail part of the battery compartment is detachably connected with the tail part fairing.

Furthermore, the battery compartment comprises a square battery compartment section positioned in the middle and oval battery compartment sections positioned at two ends, and the curve section of the transverse section of the oval battery compartment section is the oval function curve.

Further, the head fairing is a carbon fiber fairing or a glass fiber fairing.

Further, the tail fairing is a carbon fiber fairing or a glass fiber fairing.

The utility model discloses unmanned aerial vehicle includes head radome fairing, afterbody radome fairing and fuselage, because head radome fairing and afterbody radome fairing are power function curve along its longitudinal profile's curve section, guarantee that it and fuselage are on smooth transition's basis, optimize the fuselage around the flow field, reduce the pressure differential resistance to and the possibility of air current separation, realized reducing the purpose of complete machine flight resistance, along with the reduction of complete machine flight resistance also corresponding reduction the requirement of complete machine to driving system.

Drawings

Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:

fig. 1 is a schematic structural view of an unmanned aerial vehicle provided by the present invention;

fig. 2 is the utility model provides a pair of unmanned aerial vehicle's side view.

Description of reference numerals:

1. a head fairing; 2. a tail fairing; 3. a body; 4. a battery compartment; 5. an airfoil.

Detailed Description

The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

It should be noted that unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly and include, for example, fixed or removable connections or integral connections; 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 meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

As shown in fig. 1 and fig. 2, the utility model provides a pair of unmanned aerial vehicle, including fuselage 3, the head releasable connection of fuselage 3 has head fairing 1, the afterbody releasable connection of fuselage 3 has afterbody fairing 2, and head fairing 1 and afterbody fairing 2 are the power function curve along its longitudinal profile's curve section.

In this context, the fuselage 1 is oriented from the beginning to the end in the longitudinal direction, i.e. in the longitudinal direction of the fuselage, and perpendicular to the longitudinal direction in the transverse direction, i.e. in the direction of the wing span.

According to the scheme, the curve sections of the head fairing 1 and the tail fairing 2 along the longitudinal sections of the head fairing and the tail fairing are power function curves, so that the front flow field and the rear flow field of the airframe 3 are optimized on the basis of smooth transition of the head fairing and the airframe 3, the pressure difference resistance is reduced, the possibility of air flow separation is reduced, the purpose of reducing the flight resistance of the whole aircraft is achieved, and the requirements of the whole aircraft on a power system are correspondingly reduced along with the reduction of the flight resistance of the whole aircraft.

It should be noted that the curved line section herein refers to the outer side edge line of the leading cowl 1 and the trailing cowl 2 in the longitudinal cross section of the leading cowl 1 and the trailing cowl 2.

Further, the power function curve is:

wherein n is more than or equal to 0 and less than or equal to 1, R is the radius of an inscribed circle at the connecting part of the fairing and the machine body, and L is the length of the fairing. The fairing arranged at the head part of the machine body 3 is a head fairing 1, and the fairing arranged at the tail part of the machine body 3 is a tail fairing 2.

By adopting the head fairing 1 and the tail fairing 2 of the power function curve, the front flow field and the rear flow field of the airframe can be optimized on the basis of smooth transition with the airframe 3, and the pressure difference resistance and the possibility of air flow separation are reduced.

Further, the fuselage 3 includes the square fuselage section that is located the middle part and the oval fuselage section that is located both ends, and oval fuselage section is smooth transition with corresponding head radome fairing 1 and afterbody radome fairing 2 respectively, also is that the oval fuselage section of fuselage afterbody and afterbody radome fairing 2 smooth transition, the oval fuselage section of fuselage head and head radome fairing 1 smooth transition. The square fuselage section refers to the fuselage section with a rectangular or square cross section in the fuselage, and the oval fuselage section refers to the fuselage section with an oval cross section in the fuselage.

The middle part of the machine body is a square machine body section, so that the space of the machine cabin can be optimized, namely the space in the machine cabin can be square, and the load capacity in the machine cabin can be improved to the maximum extent. In addition, the two ends of the square fuselage section are connected with the oval fuselage section, so that the stable transition of the cross section of the fuselage is ensured, and the aerodynamic performance of the fuselage is improved.

Further, as a preferable mode, the curve section of the transverse section of the elliptical fuselage section is an elliptical function curve which is:

Further, the fuselage 3 is fixedly connected with wings 5, and the fuselage 3 and/or the wings 5 are connected with battery bins 4.

Further, in order to promote the equilibrium of this unmanned aerial vehicle, then the bilateral symmetry of fuselage 3 is provided with battery compartment 4.

Further, for the improvement of furthest's this unmanned aerial vehicle's power performance, reduce flight resistance, reduce the requirement to driving system, battery compartment 4's head releasable connection has head fairing 1, battery compartment 4's afterbody releasable connection has afterbody fairing 2.

Further, as a preferable mode, the battery compartment 4 includes a square battery compartment section located in the middle and an oval battery compartment section located at both ends, and a curve section of a transverse cross section of the oval battery compartment section is the oval function curve. The square battery bin section is arranged in the middle of the battery box, so that the carrying capacity of the battery can be improved. The square battery compartment section is gradually transited into the oval battery compartment section, so that the smooth transition of the cross-sectional shape of the battery compartment is ensured, and the aerodynamic performance of the machine body is favorably improved.

Further, the head fairing 1 is a carbon fiber fairing or a glass fiber fairing to improve the strength of the head fairing and to reduce the weight thereof.

Further, the tail fairing 2 is a carbon fiber fairing or a glass fiber fairing to improve the strength of the tail fairing and reduce the weight thereof.

The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be understood by those skilled in the art that the scope of the present invention is not limited to the specific combination of the above-mentioned features, but also covers other embodiments formed by any combination of the above-mentioned features or their equivalents without departing from the spirit of the present invention. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.

Claims

1. The utility model provides an unmanned aerial vehicle, includes the fuselage, the head releasable connection of fuselage have the head radome fairing the afterbody releasable connection of fuselage has the afterbody radome fairing, its characterized in that, head radome fairing and afterbody radome fairing are the power function curve along its longitudinal profile's curve section.

2. A drone according to claim 1, wherein the power function curve is:

wherein n is more than or equal to 0 and less than or equal to 1, R is the radius of an inscribed circle at the connecting part of the fairing and the machine body, and L is the length of the fairing.

3. The unmanned aerial vehicle of claim 1, wherein the fuselage comprises a square fuselage section at a middle portion and elliptical fuselage sections at both ends, the elliptical fuselage sections being in smooth transition with the corresponding head fairing and the tail fairing, respectively.

4. The unmanned aerial vehicle of claim 3,

the curve section of the transverse section of the elliptical fuselage section is an elliptical function curve, and the elliptical function curve is as follows:

5. The unmanned aerial vehicle of claim 4, wherein wings are fixedly connected to the fuselage, and a battery compartment is connected to the fuselage and/or the wings.

6. The unmanned aerial vehicle of claim 5, wherein the battery compartment is symmetrically disposed on two sides of the fuselage.

7. The drone of claim 6, wherein the head of the battery compartment is detachably connected with the head fairing and the tail of the battery compartment is detachably connected with the tail fairing.

8. The unmanned aerial vehicle of claim 7, wherein the battery compartment comprises a square battery compartment section at a middle portion and oval battery compartment sections at two ends, a curve section of a transverse cross section of the oval battery compartment sections being the elliptic function curve.

9. An unmanned aerial vehicle as defined in any one of claims 1-8, wherein the head fairing is a carbon fiber fairing or a glass fiber fairing.

10. An unmanned aerial vehicle as defined in any one of claims 1-8, wherein the tail fairing is a carbon fiber fairing or a glass fiber fairing.