RU2530906C1 - Drone - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to VTOL drones. This drone consists of ring-like wing, blower-type propulsor and at least four independent aerodynamic fins. Wing inner surface comprises cylindrical section with diameter D_id and length L_cyl=(0.45÷0.55)D_id, wing chord making b_rw=(1.1÷1.25)D_id, wing profile maximum depth h_max=(0.145÷0.18)D_id, while distance from extreme front point to the beginning of cylindrical section makes L_front=(0.145÷0.165)h_max. Said blower-type propulsor is arranged inside said cylindrical section. Said blower-type propulsor consists of inlet guide vane, impeller and straightener. Said inlet guide vane consists of radial aerodynamic elements connecting said ring-type wing with central body. Said elements feature symmetric profile with constant chord. Impeller vanes and those of straightener feature complex aerodynamic surface.

EFFECT: better aerodynamics, higher efficiency.

7 cl, 12 dwg

Description

The invention relates to the field of transportation, namely to unmanned aerial vehicles of vertical take-off with an annular wing.

The prior art unmanned aerial vehicles (UAVs) of various schemes. In addition to the traditional devices (aircraft, helicopter), there are so-called vertical take-off and landing devices with a fan in the channel (Ducted Fan VTOL UAV) as a carrier system. Typical analogues are iSTAR devices from Allied Aerospace, T-Hawk from Honeywell, IAV from BAE Systems Inc.

The closest in technical essence to the claimed invention is an unmanned aerial vehicle, consisting of an annular wing, a fan-propulsion, a central body and at least four independent aerodynamic rudders (see patent EP 2193994, class B64C 39/02, publ. 06/09/2010).

Common disadvantages of the known devices are low efficiency, insufficient power, poor controllability and low aerodynamic stability of UAVs.

The objective of the invention is to remedy these disadvantages. The technical result consists in improving the aerodynamic characteristics of the UAV and, as a consequence, in increasing the efficiency of its operation. The problem is solved and the technical result is achieved in that the unmanned aircraft, consisting of the annular wing-propulsion fan, central body and at least four independent aerodynamic control surfaces, the inner surface of the annular wing includes a cylindrical portion diameter D _tm and length L _cyl = (0.45 ÷ 0.55) D _vd , chord of the annular wing is b _kk = (1.1 ÷ 1.25) D _vd , the maximum thickness of the profile of the annular wing is h _max = (0.145 ÷ 0.18) D _vd , and the distance from the extreme front point of the annular wings of the start of the cylindrical portion is L _{nose = (0.145 ÷ 0.165) h max} , wherein the inside of the cylindrical portion is fan-propulsion, consisting of inlet guide vanes, the impeller and the flow straightener, the input guide apparatus consists of radial aerodynamic elements, connecting annular wing and the central body and having a symmetric profile with a chord of constant magnitude, the impeller is designed so that its center line curved vane profile of a circular arc, the magnitude of the chord b _pk credited with a linear function of the radius angle of the profiles θ _pk is described by a cubic function of radius, the magnitude of the deflection f _pk is described by a polynomial of the fifth power of the radius, the value profile thickness c _pk is described by a linear function of the radius, and flow straightener device is configured such that the average line profiles its blades are bent along an arc of a circle, the values of the chord b _ca and thickness c _{ca of the} profile are constant, the angle of installation of the profiles θ _{ca is} described by a cubic function of the radius, and the magnitude of the deflection f _{pk is} described by the polynomial to the extent of the radius. The central body is preferably made cylindrical having a diameter D = 0.35D _{qn tm,} and its length is L _qm = (1.75 ÷ 1.95) D _tm. The distance from the beginning of the cylindrical portion of the annular wing to the point of maximum profile thickness is preferably L _hmax = (0.18 ÷ 0.23) h _max . The height from the extreme front point of the annular wing to the cylindrical section is preferably h _nose = (0.65 ÷ 0.8) h _max . The diameter of the annular wing at the outlet is preferably D _o = = (1.05 ÷ 1.19) D _in . The ratio of radial aerodynamic n elements of the input guide apparatus _{of the BHA} to the number of impeller blades preferably _pk n is 7/5.

Figure 1 presents a General view of the proposed UAV;

figure 2 is a cross section of the annular wing and the Central body with characteristic dimensions;

figure 3 - General view of the fan propulsion;

figure 4 is a General view of the radial aerodynamic elements of the input guide apparatus;

figure 5 is the same as in figure 4, side view;

figure 6 is a section aa in figure 5;

Fig.7 is a General view of the impeller blades;

Fig.8 is the same as in Fig.7, a side view;

Fig.9 is a section aa in Fig.8;

figure 10 is a General view of the blade rectifier;

figure 11 is the same as in figure 10, side view;

in Fig.12 is a section aa in Fig.11.

The proposed UAV consists of an annular wing 1, a fan-propulsion device, which includes an input guide apparatus 2, an impeller 3 and a straightening apparatus 4, a central body 5, which contains a payload, and four or more independent aerodynamic rudders 6. These elements have the optimal aerodynamic configuration described below.

The annular wing 1 is a body of revolution with an asymmetric profile containing a cylindrical section in which the fan motor is located. The relative length of this section is

$${\overline{L}}_{c\mathrm{and}l}=\frac{L_{c\mathrm{and}l}}{D_{\mathrm{at}d}}=0.45...0.55$$

where L _cyl is the dimensional length of the cylindrical section, and

D _vd - the outer diameter of the fan-propeller or the diameter of the cylindrical section of the wing 1.

The central body 5 is cylindrical with a diameter D _{VD ct} = 0.35D. Its relative length is

$${\overline{L}}_{ct}=\frac{L_{ct}}{D_{\mathrm{at}d}}=1.75...1.95$$

where L _ct is the dimensional length of the central body.

The geometry of the annular wing 1 is presented in figure 2.

The diameter of the annular wing at the outlet is preferably D _o = = (1.05 ÷ 1.19) D _in .

The dimensionless chord of the annular wing is

$${\overline{b}}_{\mathrm{to}\mathrm{to}}=\frac{b_{\mathrm{to}\mathrm{to}}}{D_{\mathrm{at}d}}=\mathrm{1,1}...1.25$$

where b _kk is the dimensional chord of the annular wing.

The dimensionless maximum annular wing profile thickness is

$${\overline{h}}_{\max }=\frac{h_{\max }}{D_{\mathrm{at}d}}=0.145...0.18$$

where h _max - dimensional maximum thickness of the profile of the annular wing.

The dimensionless distance from the extreme front point of the annular wing to the beginning of the cylindrical section is

$${\overline{L}}_{n\mathrm{about}\mathrm{from}}=\frac{L_{n\mathrm{about}\mathrm{from}}}{h_{\max }}=0.145...0.165$$

where L _nose is the dimensional distance from the extreme front point of the annular wing.

The dimensionless height from the extreme front point of the annular wing to the cylindrical section is

$${\overline{h}}_{n\mathrm{about}\mathrm{from}}=\frac{h_{n\mathrm{about}\mathrm{from}}}{h_{\max }}=0.65...0.8$$

where h _nose is the dimensional height from the extreme front point of the annular wing.

The dimensionless distance from the beginning of the cylindrical section to the point of maximum profile thickness is

$${\overline{L}}_{h\max }=\frac{L_{h\max }}{h_{\max }}=0.18...0.23$$

where L _hmax is the dimensional distance to the point of maximum thickness. The dimensionless diameter of the annular wing at the outlet is

$${\overline{D}}_{\mathrm{at}sx}=\frac{D_{\mathrm{at}sx}}{D_{\mathrm{at}d}}=1.05...1.19$$

where D _o - the dimensional diameter of the annular wing at the exit.

The geometry of the fan-propulsion is shown in Fig.3. The ratio of the number of radial aerodynamic elements of the input guide _vn to the number of impeller vanes n _pk is 7/5.

The input guide apparatus 2 consists of radial aerodynamic elements that act as spacers and connect the annular wing 1 and the central body 5. These elements (see Figs. 4-6) have a symmetrical profile with a chord of constant magnitude, which allows you to align the flow in front of the impeller 3 at different flight modes and leads to an increase in traction of the fan-propulsion.

профилей от радиуса описывается по линейному законуIn the impeller 3 (Fig.7-9), the profiles of the blades have a midline curved in an arc of a circle. Chord value distribution $${\overline{b}}_{R\mathrm{to}}$$

profiles of radius is described linearly

$${\overline{b}}_{R\mathrm{to}}=\frac{b_{R\mathrm{to}}}{R_{R\mathrm{to}}}=-0.162\frac{r}{R_{R\mathrm{to}}}+0.384$$

where r is the current radius of the impeller,

R _pk - the outer radius of the impeller.

The dependence of the angle of installation of the profiles θ _pk on the radius is described by a cubic function

. $${\theta }_{R\mathrm{to}}=-93.17{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^3+275.6{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^2-303.3\frac{r}{R_{R\mathrm{to}}}144.6$$

.

от радиуса описывается полиномом пятой степениDeflection Dependence $${\overline{f}}_{R\mathrm{to}}$$

of radius is described by a polynomial of the fifth degree

. $$\begin{array}{l}{\overline{f}}_{R\mathrm{to}}=\frac{f_{R\mathrm{to}}}{b_{R\mathrm{to}}}=-\mathrm{1,509}{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^5+\mathrm{5,647}{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^{\mathrm{four}}-\mathrm{8,498}{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^3+\\ +\mathrm{6,548}{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^2-\mathrm{2,653}\frac{r}{R_{R\mathrm{to}}}+0.492\end{array}$$

.

от радиуса описывается по линейному законуProfile Thickness Dependence $${\overline{c}}_{R\mathrm{to}}$$

from the radius is described linearly

. $${\overline{c}}_{R\mathrm{to}}=\frac{c_{R\mathrm{to}}}{b_{R\mathrm{to}}}=-\mathrm{0,077}\frac{r}{R_{R\mathrm{to}}}+0.176$$

.

и величина толщины профиля $${\overline{c}}_{са}$$

постоянны и не зависят от текущего радиусаIn the rectifier 4 (FIGS. 10-12) for its blades, the chord value $${\overline{b}}_{\mathrm{from}\mathrm{but}}$$

and profile thickness $${\overline{c}}_{\mathrm{from}\mathrm{but}}$$

constant and independent of the current radius

$${\overline{b}}_{\mathrm{from}\mathrm{but}}=\frac{b_{\mathrm{from}\mathrm{but}}}{R_{R\mathrm{to}}}=0.297$$

$${\overline{c}}_{\mathrm{from}\mathrm{but}}=\frac{c_{\mathrm{from}\mathrm{but}}}{b_{\mathrm{from}\mathrm{but}}}=0.1$$

The dependence of the angle of installation of the profiles θ _CA on the radius is described by a cubic function

. $${\theta }_{\mathrm{from}\mathrm{but}}=-32.52{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^3+92.16{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^2-94.87\frac{r}{R_{R\mathrm{to}}}-49.96$$

.

от радиуса описывается полиномом пятой степениDependence Deflection $${\overline{f}}_{\mathrm{from}\mathrm{but}}$$

of radius is described by a polynomial of the fifth degree

. $$\begin{array}{l}{\overline{f}}_{\mathrm{from}\mathrm{but}}=\frac{f_{\mathrm{from}\mathrm{but}}}{b_{\mathrm{from}\mathrm{but}}}=0.731{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^5-\mathrm{5,592}{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^{\mathrm{four}}+\mathrm{3,493}{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^3-\\ -\mathrm{2,147}{\left(\frac{r}{R_{R\mathrm{to}}}\right)}^2+0.499\frac{r}{R_{R\mathrm{to}}}+\mathrm{0,073}\end{array}$$

.

It was experimentally shown that such geometric parameters of the fan-propulsion provide the necessary traction. In order to transport the required payload weight, the UAV can be scaled accordingly while maintaining the above ratios, and the power consumed by the propulsion fan and the required number of revolutions will change.

Claims (7)

1. An unmanned aerial vehicle, consisting of an annular wing, a fan-propeller, a central body and at least four independent aerodynamic rudders, characterized in that the inner surface of the annular wing includes a cylindrical section with a diameter of D _in and a length of L _cyl = (0.45 ÷ 0.55) D _tm, annular wing chord is b _kk = 1.1 ÷ 1.25D _tm, the maximum thickness of the profile of the annular wing is _{h max = (0.145 ÷ 0.18)} D _tm, and the distance from the foremost point of the ring-wing prior to the cylindrical portion of _nose L = (0.145 ÷ 0.165) h _max , while inside the cylindrical section there is a fan-propeller consisting of an inlet guide vane, an impeller and a straightening apparatus, an inlet guide vane consists of radial aerodynamic elements connecting the annular wing and the central body and having a symmetrical profile with a chord of constant magnitude , the impeller is made in such a way that the middle line of the profiles of its blades is bent along an arc of a circle, the magnitude of the chord b _{rk is} described by a linear function of the radius, the angle of installation and profiles θ _{pk is} described by a cubic function of the radius, the deflection f _{pk is} described by a polynomial of the fifth degree of the radius, the thickness of the profile c _{pk is} described by a linear function of the radius, and the rectifier is designed so that the middle line of the profiles of its blades is curved along an arc of a circle, the values of the chord b _ca and the thickness c _{ca of the} profile are constant, the installation angle of the profiles θ _{ca is} described by a cubic function of the radius, and the deflection f _{pk is} described by a fifth degree polynomial in radius. 2. An aircraft according to claim 1, characterized in that the central body is cylindrical with a diameter D _{VD ct} = 0.35D. 3. The aircraft according to claim 1, characterized in that the length of the central body is L _ct = (1.75 ÷ 1.95) D _in . 4. The aircraft according to claim 1, characterized in that the distance from the beginning of the cylindrical section of the annular wing to the point of maximum profile thickness is L _hmax = (0.18 ÷ 0.23) h _max . 5. The aircraft according to claim 1, characterized in that the height from the extreme front point of the annular wing to the cylindrical section is h _nose = (0.65 ÷ 0.8) h _max . 6. The aircraft according to claim 1, characterized in that the diameter of the annular wing at the outlet is D _o = (1.05 ÷ 1.19) D _in . 7. The aircraft according to claim 1, characterized in that the ratio of the number of radial aerodynamic elements of the input guide _vn to the number of impeller vanes n _pk is 7/5.

Images