VTOL aircraft with a thrust-to-weight ratio smaller than 0.1

Abstract

VTOL aircraft with a thrust-to-weight ratio smaller than 0.1, during vertical take-off/landing, obtains another vertical lift, besides traditional vertical lift generated by low-temp bypass duct directing, under the closing of the propelling nozzle (7) of low-temp duct (6) of a turbofan engine and the opening of the inlet (14) of the low-temp bypass duct (15), the low-temp air (18) from the low-temp duct (6) to flow, in form of low-temp planar jet (20), over the upper surface of the wing along the wingspan, by high-temp bypass duct (15) directing, under the closing of the propelling nozzle (5) of high-temp duct (4) of the turbofan engine and the opening of the inlet (8) of the high-temp bypass duct (9), the high-temp air (18) from the high-temp duct (4) to flow, in form of high-temp planar jet (13), above the low-temp planar jet (20) but not burn up the wing along the wingspan and enables the ailerons (1, 2) to control the balances more efficiently.

Description

CROSS-REFERENCE TO RELATED APPLICATION

This application is claims foreign priority benefit under 35 U.S.C. §119 of Patent Application EP 14075023.3 filed on 17 Apr., 2014, the contents of which are herein incorporated by reference.

BACKGROUND OF THE INVENTION

This invention relates to aircraft, and more particularly, to aircraft with VTOL technology.

Currently, in the traditional VTOL technologies, thrust vectoring technology, such as AV-8, Yak-36 and F-35B, and additional lift engines, such as Yak-38 and Yak-141, in a least efficient way that air doesn't flow over the upper surface of the aircraft but rather over the lower one during vertical take-off/landing, get directly lift from reaction of atmosphere to air jet of jet engine; the use of tilt rotor, such as Boeing's V-22, and rotary wing, such as Boeing's X-50, in a little more efficient way that air both flow over the supper and lower of the aircraft during vertical take-off/landing, get lift from velocity difference of air which both flow the upper and lower surface of aircraft. Because of these limitations, VTOL is impossible for aircraft with thrust-to-weight ratio smaller than 0.1, and more particularly for large aircraft.

BRIEF SUMMARY OF THE INVENTION

An aircraft to achieve vertical take-off/landing in a much more efficient way that air flows over the upper surface of the aircraft rather than the lower one, the aircraft comprising:

• • An aileron, which one pair rotate in opposite way for controlling horizontal balance and another pair in one way for controlling vertical balance during vertical take-off/lading, disposed on both sides of the aircraft axis;
  • A turbofan engine comprising a high-temp duct with an openable/closable propelling nozzle and a low-temp duct with an openable/closable propelling nozzle, both of their propelling nozzles are closed during vertical take-off/landing and opened during forward flight;
  • A low-temp bypass duct comprising an openable/closable inlet connected to the low-temp duct, an outer wall which any cross-sectional area keeps low-temp airflow less than velocity of sound, and a rectangle outlet with a height-to-width ratio smaller than 0.1, this high-temp bypass duct being configured, during vertical take-off/landing, to opens its inlet for causing low-temp airflow in to form a low-temp planar jet on upper surface of the aircraft comprising the ailerons, thereby generating the life and the power controlling vertical and horizontal balances, the low-temp bypass duct being configured, during forward flight, to restore normal state for causing low-temp airflow into atmosphere;
  • A high-temp bypass duct comprising an openable/closable inlet connected to the high-temp duct, an outer wall which any cross-sectional area keeps high-temp airflow less than velocity of sound, and a rectangle outlet with a height-to-width ratio smaller than 0.1, this high-temp bypass duct being configured, during vertical take-off/landing, to opens its inlet for causing high-temp airflow in to form high-temp planar jet above the low-temp one on upper surface of the aircraft for keeping no air to flow over lower surface of the aircraft, the high-temp bypass duct being configured, during forward flight, to restore normal state for causing high-temp airflow into atmosphere;According to the first characteristics of embodiments:
  • The low-temp bypass duct, during vertical take-off/landing, causes the low-temp airflow in to form low-temp planar jet on upper surface of aircraft for generating lift efficiently.
  • The high-temp bypass duct, during vertical take-off/landing, causes the high-temp air anywhere no air flows over lower surface of the aircraft.
  • The aileron, during vertical take-off/landing, one pair rotate in opposite way for controlling the horizontal balance and another pair rotate in one way for controlling the vertical balance.

BRIEF DESCRIPTION OF THE DRAWING

The attached drawings illustrate the invention:

FIG. 1 is a side view of an aircraft with this invention during vertical take-off and landing.

FIG. 2 is a top view of an aircraft with this invention during vertical take-off and landing.

FIG. 3 is a rear view of an aircraft with this invention during vertical take-off and landing.

FIG. 4 is J local view for FIG. 3.

FIG. 5 is A-A Section for FIG. 4

FIG. 6 is B-B Section for FIG. 4.

FIG. 7 is part Section for FIG. 4.

FIG. 8 is K local view for FIG. 3.

FIG. 9 is C-C Section for FIG. 8.

FIG. 10 is a side view of an aircraft with this invention during forward flight.

FIG. 11 is a top view of an aircraft with this invention during forward flight.

FIG. 12 is a rear view of an aircraft with this invention during forward flight.

FIG. 13 is M local view for FIG. 12.

FIG. 14 is D-D Section for FIG. 13.

FIG. 15 is E-E Section for FIG. 13.

FIG. 16 is part Section for FIG. 13.

FIG. 17 is N local view for FIG. 12.

FIG. 18 is F-F Section for FIG. 17.

DETAILED DESCRIPTION OF THE INVENTION

Referring to these drawings, the aircraft comprising: an aileron (1, 2) which one pair (1) rotate in opposite way and another pair (2) rotate in one way; a turbofan engine (3) comprising a low-temp duct (4) with an openable/closable propelling nozzle (5), and a high-temp duct (6) with an openable/closable propelling nozzle (7); a low-temp bypass duct (8) comprising an openable/closable inlet (9) connected to the low-temp duct (4), an outer wall (10) and an inner wall (11) which any cross-sectional area keeps low-temp airflow (12) less than velocity of sound, a rectangle outlet (13) with a height-to-width ratio smaller than 0.1; a high-temp bypass duct (14) comprising an openable/closable inlet (15) connected to the high-temp duct (6), an outer wall (16) Referring to these drawings, the aircraft comprising: an aileron (1, 2) which one pair (1) rotate in opposite way and another pair (2) rotate in one way; a turbofan engine (3) comprising a low-temp duct (4) with an openable/closable propelling nozzle (5), and a high-temp duct (6) with an openable/closable propelling nozzle (7); a low-temp bypass duct (8) comprising an openable/closable inlet (9) connected to the low-temp duct (4), an outer wall (10) and an inner wall (11) which any cross-sectional area keeps low-temp airflow (12) less than velocity of sound, a rectangle outlet (13) with a height-to-width ratio smaller than 0.1; a high-temp bypass duct (14) comprising an openable/closable inlet (15) connected to the high-temp duct (6), an outer wall (16) which any cross-sectional area keeps the high-temp airflow (17) less than velocity of sound, a rectangle outlet (18) with a height-to-width ratio smaller than 0.1. which any cross-sectional area keeps the high-temp airflow (17) less than velocity of sound, a rectangle outlet (18) with a height-to-width ratio smaller than 0.1.

Referring to FIGS. (1-9), the innovative combination being configured, during vertical take-off/lading, to close propelling nozzles (5, 7) of the high-temp duct (4) and low-temp duct (6), and open the inlets (9, 15) of the low-temp bypass duct (8) and high-temp bypass duct (14), cause low-temp air (12) and high-temp air (17) in to flow over corresponding low-temp bypass duct (8) and high-temp bypass duct (14), then the low-temp planar jet (19) spews out of the outlet (13) of low-temp bypass duct (8), over upper surface of the aircraft including the aileron (1, 2), thereby generating lift for vertical take-off/landing and power for controlling the vertical and horizontal balances of the aircraft, and the high-temp planar jet (20) spews out of the outlet (18) of high-temp bypass duct (14), above the low-temp planar jet (19), into atmosphere for keeping no air to flow over lower surface of the aircraft.

Referring to FIGS. (10-18), the innovative combination being configured, during forward flight, to restore normal state in order that low-temp air (12) and high-temp air (17) spew directly into atmosphere from the open propelling nozzles (5, 7) of the high-temp duct (4) and a low-temp duct (6).

All the formulas and calculations for this invention are listed in Annex 1.

All the formulas and calculations used to retrofit an Airbus A-380 based on this invention are listed in Annex 2.

This invention can be used to retrofit and existing aircraft to achieve VTOL or manufacture a VTOL aircraft with a thrust-to-weight ratio smaller than 0.1.

Annex 1

P	Atmospheric pressure	(Unit: Pa)
R	Ideal gas constant	(Unit:]. K −1.
		mol −1)
ρ0	Low-temp jet density at the outlet	(Unit:kg/m3)
ρ1	Atmospheric density	(Unit:kg/m3)
ρ	Jet density on the cross-section	(Unit: kg/m3)
ρm	Jet density of the shaft	(Unit: kg/m3)
T0	Jet temp at the low-temp outlet	(Unit: K)
T1	Atmospheric temp	(Unit: K)
T	Jet temp on the cross-section	(Unit: K)
V0	Jet speed at the outlet of low-temp	(Unit: m/s)
	bypass duc
V{acute over (0)}	Jet speed at the outlet of high-temp	(Unit: m/s)
	bypass duct
V	Jet speed on the cross-section	(Unit: m/s)
Vm	Jet speed of shaft	(Unit: m/s)
h0	Jet height of the outlet	(Unit: m)
hm	Jet height of the cross-section	(Unit: m)
h	Jet height on the cross-section	(Unit: m)
L	Width of the outlet	(Unit: m)
C	Gas specific volume	(Unit: m3/kg)
M	Molar mass	(Unit: kg/mol)
Q	Air inflow of turbofan engine	(Unit: kg/s)
B	Bypass ratio of turbofan engine	(Dimensionless
		unit)
G	Maximum take-off weight	(Unit: T)
X	Distance between any point and outlet
	of low-temp bypass duct in jet direction	(Unit: m)
X1	Distance between wing root and low-
	temp outlet in jet direction	(Unit: m)
X2	Distance between low-temp outlet
	and crossing of jet boundary and trailing	(Unit: m)
	edge of wing in jet direction
X3	Distance between wingtip and
	low-temp outlet in jet direction	(Unit: m)
α	Angle between jet boundary and
	trailing edge of wing	(Unit: °)
β	Angle between chord line of wing
	and long side of outlet	(Unit: °)
γ	Dihedral angle of wing	(Unit: °)
δ	Sweep forward angle of jet	(Unit: °)
ø	Included angle between axis of low-
	temp jet And one of the high-temp jet	(Unit: °)
θ	Sweep back angle of jet	(Unit: °)
F	Total vertical lift	(Unit: T)
F1	Lift between wing root and low-temp outlet	(Unit: T)
F2	Lift between low-temp outlet and crossing
	of jet boundary and trailing edge of wing	(Unit: T)
F3	Lift between wingtip and low-temp outlet	(Unit: T)
F4	Downward pressure generated
	by slant upward deflected jet	(Unit: T)
F5	Thrust generated by jet of low-temp outlet	(Unit: T)
F6	Thrust generated by jet of high-temp outlet	(Unit: T)
b	Constant	(Dimensionless
		unit)
d	Constant	(Dimensionless
		unit)
C	Constant	(Dimensionless
		unit)
n1	S/N of turbofan engine	(Dimensionless
		unit)
n2	S/N of turbofan engine used in vertical
	Take-off/landing	(Dimensionless
		unit)
n3	S/N of outlet of low-temp bypass duct	(Dimensionless
		unit)
TW R	Thrust-to-weight ratio of aircraft	(Dimensionless
		unit)

According to thermodynamic, relative values of the enthalpy of the jet cross-section, in the case of equal pressure and the surrounding gas enthalpy acting as a starting point, is same.

And according to the feature of planar jet, it just spread on the flat which is perpendicular to the outlet section.

$P=\frac{{\rho }_0}{M}{\mathrm{RT}}_0=\frac{{\rho }_1}{M}{\mathrm{RT}}_1=\frac{\rho }{M}\mathrm{RT}$ ${\rho }_0V_0h_0\mathrm{LC}\left(T_0-T_1\right)=\int \rho \mathrm{VL}C\left(T-T_1\right)h$ ${\rho }_0V_0h_0\left(\frac{1}{{\rho }_0}-\frac{1}{{\rho }_1}\right)=\int \rho V\left(\frac{1}{\rho }-\frac{1}{{\rho }_1}\right)h$

And according to the similarity of velocity and density distribution on the various jet sections,

$\begin{array}{cc}\sqrt{\frac{V}{V_m}}=\frac{\rho -{\rho }_1}{{\rho }_m-{\rho }_1}=1-{\left(\frac{h}{h_m}\right)}^{1.5}h_0V_0\left({\rho }_0-{\rho }_1\right)=\int \left(\rho -{\rho }_1\right)Vh\frac{h_0V_0\left({\rho }_0-{\rho }_1\right)}{\left({\rho }_m-{\rho }_1\right)V_mh_m}=\int \frac{\left(\rho -{\rho }_1\right)V}{\left({\rho }_m-{\rho }_1\right)V_mh_m}h={\int }_0^{h_m}{\left[1-{\left(\frac{h}{h_m}\right)}^{1.5}\right]}^3·\frac{1}{h_m}h={\int }_0^1{\left[1-{\left(\frac{h}{h_m}\right)}^{1.5}\right]}^3\left(\frac{h}{h_m}\right)=0.3682\left({\rho }_m-{\rho }_1\right)=\frac{h_0V_0\left({\rho }_0-{\rho }_1\right)}{0.3682·V_mh_m}& \left(1\right)\end{array}$

According to dynamic characteristic of jet, momentum of the various sections, in the case of equal pressure, is same.

$\begin{array}{cc}{\rho }_0{\mathrm{Lh}}_0V_0^2=\int \rho {\mathrm{LV}}^2h{\rho }_0h_0V_0^2=\int \rho V^2h=\int \left(\rho -{\rho }_1\right)V^2h+\int {\rho }_1V^2h\frac{{\rho }_0h_0V_0^2}{\left({\rho }_m-{\rho }_1\right)V_m^2h_m}={\int }_0^1\frac{\left(\rho -{\rho }_1\right)V^2}{\left({\rho }_m-{\rho }_1\right)V_m^2}\left(\frac{h}{h_m}\right)+{\int }_0^1\frac{{\rho }_1V^2}{\left({\rho }_m-{\rho }_1\right)V_m^2}\left(\frac{h}{h_m}\right)={\int }_0^1{\left[1-{\left(\frac{h}{h_m}\right)}^{1.5}\right]}^5\left(\frac{h}{h_m}\right)+\frac{{\rho }_1}{\left({\rho }_m-{\rho }_1\right)}{\int }_0^1{\left[1-{\left(\frac{h}{h_m}\right)}^{1.5}\right]}^4\left(\frac{h}{h_m}\right)=0.2786+\frac{0.3156{\rho }_1}{\left({\rho }_m-{\rho }_1\right)}\frac{0.3682V_0{\rho }_0}{V_m\left({\rho }_0-{\rho }_1\right)}=0.2786+\frac{0.1162h_mV_m{\rho }_1}{h_0V_0\left({\rho }_0-{\rho }_1\right)}& \left(2\right)\end{array}$

Substitute (1) into (2):

$\begin{array}{cc}\frac{0.1162h_m{\rho }_1}{h_0{\rho }_0}·{\left(\frac{V_m}{V_0}\right)}^2+0.2786\frac{\left({\rho }_0-{\rho }_1\right)}{{\rho }_0}·\left(\frac{V_m}{V_0}\right)-0.3682=0\frac{V_m}{V_0}=\frac{\frac{0.2786\left({\rho }_1-{\rho }_0\right)}{{\rho }_0}+\sqrt{{\left[\frac{0.2786\left({\rho }_0-{\rho }_1\right)}{{\rho }_0}\right]}^2+\frac{0.1711h_m{\rho }_1}{h_0{\rho }_0}}}{\frac{0.2324h_m{\rho }_1}{h_0{\rho }_0}}V_m=\frac{1+\sqrt{1+\frac{0.1711h_m{\rho }_0{\rho }_1}{{0.2786}^2{h_0\left({\rho }_0-{\rho }_1\right)}^2}}}{\frac{0.2324h_m{\rho }_1}{0.2786h_0\left({\rho }_0-{\rho }_1\right)}}V_0& \left(3\right)\end{array}$

Substitute (3) into (1)

$\begin{array}{cc}\left({\rho }_m-{\rho }_1\right)=\frac{h_0V_0\left({\rho }_0-{\rho }_1\right)}{0.3682·V_mh_m}{\rho }_m={\rho }_1-\frac{\frac{0.2324}{0.3682\times 0.2786}{\rho }_1}{1+\sqrt{1+\frac{0.1711h_m{\rho }_0{\rho }_1}{{0.2786}^2{h_0\left({\rho }_0-{\rho }_1\right)}^2}}}& \left(4\right)\end{array}$

When X≦X₁ or X≦X₂

$F=P-\left(P-\frac{1}{2}\int {\rho }_mV_m^2Lx\right)=\frac{1}{2}\int {\rho }_mV_m^2Lx$

Substitute (3), (4) into (2)

$=\frac{1}{2}{\int }_0^X\left[{\rho }_1-\frac{\frac{0.2324}{0.3682\times 0.2786}{\rho }_1}{1+\sqrt{1+\frac{0.1711h_m{\rho }_0{\rho }_1}{{0.2786}^2{h_0\left({\rho }_0-{\rho }_1\right)}^2}}}\right]·{\left[\frac{1+\sqrt{1+\frac{0.1711h_m{\rho }_0{\rho }_1}{{0.2786}^2{h_0\left({\rho }_0-{\rho }_1\right)}^2}}}{\frac{0.2324h_m{\rho }_1}{0.2786h_0\left({\rho }_0-{\rho }_1\right)}}\right]}^2·V_0^2Lx=\frac{1}{2}{\int }_0^X\{{{\rho }_1\left[\frac{1+\sqrt{1+\frac{0.1711h_m{\rho }_0{\rho }_1}{{0.2786}^2{h_0\left({\rho }_0-{\rho }_1\right)}^2}}}{\frac{0.2324h_m{\rho }_1}{0.2786h_0\left({\rho }_0-{\rho }_1\right)}}\right]}^2$

$-\frac{0.2324}{0.3682\times 0.2786}{\rho }_1·\left[\frac{1+\sqrt{1+\frac{0.1711h_m{\rho }_1{\rho }_0}{{0.2786}^2{h_0\left({\rho }_1-{\rho }_0\right)}^2}}}{\frac{0.2324h_m{\rho }_1}{0.2786h_0\left({\rho }_1-{\rho }_0\right)}}\right]\}·V_0^2Lx=\frac{1}{2}{\int }_0^x{\rho }_1\left\{\frac{2+\frac{0.1711h_m{\rho }_1{\rho }_0}{{0.2786}^2{h_0\left({\rho }_1-{\rho }_0\right)}^2}+2\sqrt{1+\frac{0.1711h_m{\rho }_1{\rho }_0}{{0.2786}^2{h_0\left({\rho }_1-{\rho }_0\right)}^2}}}{{\left[\frac{0.2324h_m{\rho }_1}{0.2786h_0\left({\rho }_1-{\rho }_0\right)}\right]}^2}-\frac{\left(\frac{0.2324}{0.3682\times 0.2786}+\frac{0.2324}{0.3683\times 0.2786}\sqrt{1+\frac{0.1711h_m{\rho }_1{\rho }_0}{{0.2786}^2{h_0\left({\rho }_1-{\rho }_0\right)}^2}}\right)}{\left({\left[\frac{0.2324h_m{\rho }_1}{0.2786h_0\left({\rho }_1-{\rho }_0\right)}\right]}^2\right)}\right\}·V_0^2x$

$=\frac{1}{2}\stackrel{X}{\underset{0}{\int }}\left\{\frac{0.1711{\rho }_0}{{0.2324}^2\left(\frac{h_m}{h_0}\right)}-\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2{\left(\frac{h_m}{h_0}\right)}^2}-\frac{0.2655\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·\left(\frac{h_m}{h_0}\right)}}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}·\left(\frac{h_m}{h_0}\right)\right]}^2}\right\}·V_0^2Lx$

Because of

$\frac{h_m}{h_0}=2.44\left(\frac{0.12x}{h_0}+0.41\right)$

When X≦X₂ or X≦X₃

$F_1=\frac{1}{2}{\int }_{1.0004}^{2.44\left(\frac{0.12X_1}{h_0}+0.41\right)}\left\{\frac{0.1711{\rho }_0}{{0.2324}^2\left(\frac{h_m}{h_0}\right)}-\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2{\left(\frac{h_m}{h_0}\right)}^2}-\frac{0.2655\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·\left(\frac{h_m}{h_0}\right)}}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}·\left(\frac{h_m}{h_0}\right)\right]}^2}\right\}·\frac{h_0V_0^2L}{2.44\times 0.12}\left(\frac{h_m}{h_0}\right)=\frac{1}{2}{\int }_{1.0004}^{2.44\left(\frac{0.12X}{h_0}+0.41\right)}\left\{\frac{0.1711{\rho }_0}{{0.2324}^2x}-\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2x^2}-\frac{0.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2}·\frac{\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x}}{·x^2}\right\}·\frac{h_0V_0^2L}{2.44\times 0.12}x$ $\int \frac{\sqrt{1+\mathrm{bx}}}{x^2}x=-\left(\frac{\sqrt{1+\mathrm{bx}}}{x}-\frac{b}{2}\ln \frac{\sqrt{1+\mathrm{bx}}-1}{\sqrt{1+\mathrm{bx}}+1}+C\right)$

$F_1=\{\frac{0.1711{\rho }_0}{{0.2324}^2}\ln x+\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2x}+\frac{\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x}}{x}-{\hspace{1em}\frac{0.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2}·\left[\frac{0.1711{\rho }_1{\rho }_0}{2\times {0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}\ln \frac{\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x}-1}{\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x}+1}\right]\}}_{2.44\times 0.41}^{2.44\left(\frac{0.12X_1}{h_0}+0.41\right)}\times \frac{1}{2}\times \frac{h_oV_0^2L}{2.44\times 0.12}$

$\begin{array}{cc}{F}_2={\left\{\frac{0.1711{\rho }_0}{{0.2324}^2}\ln x+\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2x}+\frac{0.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2}·\left[\frac{\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x}}{x}-\frac{0.1711{\rho }_1{\rho }_0}{2\times {0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}\ln \frac{\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x}-1}{\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x+1}}\right]\right\}}_{2.44\times 0.41}^{2.44\left(\frac{0.12X_2}{h_0}+0.41\right)}& \left(6\right)\end{array}$

When X₂≦X≦X₃

$\begin{array}{cc}{F}_3=\frac{1}{2}{\int }_{X_2}^{X_3}\left\{\frac{0.1711{\rho }_0}{{0.2324}^2\left(\frac{h_m}{h_0}\right)}-\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2{\left(\frac{h_m}{h_0}\right)}^2}-\frac{0.2655\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·\left(\frac{h_m}{h_0}\right)}}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}·\left(\frac{h_m}{h_0}\right)\right]}^2}\right\}\times V_0^2\left[L-\left(x-X_2\right)\times \tan \alpha \right]x& \left(7\right)\end{array}$

When force is zero in body axis direction,

$\begin{array}{cc}F_4=F_5+F_6\left(F_4+F_5+F_6\right)\sin \delta =\left(F_5+F_6\right)\sin \theta \delta ={\sin }^{-1}\frac{1}{2}\sin \theta & \left(8\right)\\ F=n_2\left(F_1+F_2+F_3\right)\cos \beta \cos \gamma -n_2\left[F_4\cos \delta +F_6\sin \left(\phi +\gamma \right)-F_6\sin \left(\phi -\gamma \right)\right]& \left(9\right)\end{array}$

VTOL can be achieved once: F>G

Annex 2

n₁=1˜4n₂=1˜2n₃=1˜4M=29 kg/molQ(Air inflow of Trent 900 turbofan engine)=1204 kg/sB(Bypass ratio of Trent 900 turbo fan engine)=8.5:1G(Maximum take−off weight of A380)=560T

T₀=383K

ρ₁=1.293 kg/m²

Assuming:

$\theta =36.5°$ ${\rho }_0=\frac{{\mathrm{MP}}_0}{{\mathrm{RT}}_0}=\frac{101325\times 29\times 0.001}{8.31\times 383}=0.9232\mathrm{kg}\text{/}m^3$ $h_0=0.46m$ $L=6m$ $V_0=\frac{\frac{1}{n_2}\times Q\times \frac{8.5}{8.5+1}}{{\rho }_0\times L\times h_0}=\frac{\frac{1}{2}\times 1204\times \frac{8.5}{8.5+1}}{0.9232\times 6\times 0.46}=211m\text{/}s$ $V_0^{\prime }=V_0=211m\text{/}s$ $F_4=\frac{1}{n_2}{\mathrm{QV}}_0=\frac{1}{2}\times 1204\times 211=127002N=13T$ $F_6=\frac{1}{n_2}Q\times \frac{1}{8.5+1}\times V_0^{\prime }=11370.7368N=1.4T$ $X_1=11m$ $X_2=18m$ $X_3=32m$ $\alpha =14°$ $\beta =5°$ $\gamma =5°$ $\theta =36.5°$ $\phi =2\times 16.3°$

$\begin{array}{c}{F}_1=209832.582[2.9246\ln x+\frac{0.1488}{x}+0.0312·\\ {\left[\frac{\sqrt{1+19.2419x}}{x}-9.621\ln \frac{\sqrt{1+19.2419x}-1}{\sqrt{1+19.2419x}+1}\right]}_{2.44\times 0.41}^{2.44\left(\frac{0.12X_1}{h_0}+0.41\right)}\\ =209832.582\{2.9246\ln \frac{2.44\left(\frac{0.12\times 11}{0.46}+0.41\right)}{2.44\times 0.41}+\\ 0.1488\left[\frac{1}{2.44\left(\frac{0.12\times 11}{0.46}+0.41\right)}-\frac{1}{2.44\times 0.41}\right]+\\ 0.0312·[\frac{\sqrt{1+19.2419\times 2.44\left(\frac{0.12\times 11}{0.46}+0.41\right)}}{2.44\left(\frac{0.12\times 11}{0.46}+0.41\right)}-\\ \frac{\sqrt{1+19.2419\times 2.44\times 0.41}}{2.44\times 0.41}-\\ 9.621\ln \frac{\sqrt{1+19.2419\times 2.44\left(\frac{0.12\times 11}{0.46}+0.41\right)}-1}{\sqrt{1+19.2419\times 2.44\left(\frac{0.12\times 11}{0.46}+0.41\right)}+1}+\\ 9.621\ln \frac{\sqrt{1+19.2419\times 2.44\times 0.41}-1}{\sqrt{1+19.2419\times 2.44\times 0.41}+1}]\}\\ =209832.582\left[6.0811-0.1301-0.0918-0.0873\right]\\ =1211132.68N\\ =124T\end{array}$

$\begin{array}{cc}{F}_2=209832.582\left\{2.9246\ln \frac{2.44\left(\frac{0.12\times 18}{0.46}+0.41\right)}{2.44\times 0.41}+0.1488\left[\frac{1}{2.44\left(\frac{0.12\times 18}{0.46}+0.41\right)}-\frac{1}{2.44\times 0.41}\right]+0.0312·\left[\frac{\sqrt{1+19.2419\times 2.44\left(\frac{0.12\times 18}{0.46}+0.41\right)}}{2.44\left(\frac{0.12\times 18}{0.46}+0.41\right)}-\frac{\sqrt{1+19.2419\times 2.44\times 0.41}}{2.44\times 0.41}\right]-9.621\ln \frac{\sqrt{1+19.2419\times 2.44\left(\frac{0.12\times 18}{0.46}+0.41\right)}-1}{\sqrt{1+19.2419\times 2.44\left(\frac{0.12\times 18}{0.46}+0.41\right)}+1}+9.621\ln \frac{1\sqrt{+19.2419\times 2.44\times 0.41}-1}{\sqrt{1+19.2419\times 2.44\times 0.41}+1}\right]\}=209832.582\left[7.3757-0.1368-0.1015-0.0969\right]=1477326.2936N=151T& \left(6\right)\end{array}$

$F_3=\frac{1}{2}{\int }_{2.44\left(\frac{0.12X_2}{h_0}+0.41\right)}^{2.44\left(\frac{0.12X_3}{h_0}+0.41\right)}\left\{\frac{0.1711{\rho }_0}{{0.2324}^2\left(\frac{h_m}{h_0}\right)}-\frac{1.2655}{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]{\left(\frac{h_m}{h_0}\right)}^2}-\frac{0.2655\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2\left({\rho }_1-{\rho }_0\right)}·\left(\frac{h_m}{h_0}\right)}}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}·\left(\frac{h_m}{h_0}\right)\right]}^2}\right\}\times [L-\hspace{1em}\hspace{1em}\left(\frac{h_0}{2.44\times 0.12}\times \left(\frac{h_m}{h_0}\right)-\frac{0.41h_0}{0.12}-X_2\right)\times \tan \alpha ]\frac{h_0V_0^2}{2.44\times 0.12}\left(\frac{h_m}{h_0}\right)=\frac{1}{2}{\int }_{2.44\left(\frac{0.12X_2}{h_0}+0.41\right)}^{2.44\left(\frac{0.12X_3}{h_0}+0.41\right)}\left\{\frac{0.1711{\rho }_0}{{0.2324}^2x}-\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2x^2}-\frac{0.2655\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·\left(\frac{h_m}{h_0}\right)}}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}·x\right]}^2}\right\}·[L-\hspace{1em}\left(\frac{h_0}{2.44\times 0.12}x-\frac{0.41h_0}{0.12}-X_2\right)\times \tan \alpha ]\frac{h_0V_0^2}{2.44\times 0.12}x=\frac{1}{2}{\int }_{2.44\left(\frac{0.12X_2}{h_0}+0.41\right)}^{2.44\left(\frac{0.12X_3}{h_0}+0.41\right)}〈\frac{0.1711{\rho }_0}{{0.2324}^2x}-\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2x^2}$

$-\frac{0.2655\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x}}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2x^2}\}·\left[1+\left(\frac{0.41h_0}{0.12\times L}+\frac{X_2}{L}\right)·\tan \alpha \right]-\left\{\frac{0.1711{\rho }_0}{{0.2324}^2}-\frac{1.2655}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}\right]}^2x}-\frac{0.2655\sqrt{1+\frac{0.1711{\rho }_1{\rho }_0}{{0.2786}^2{\left({\rho }_1-{\rho }_0\right)}^2}·x}}{{\left[\frac{0.2324{\rho }_1}{0.2786\left({\rho }_1-{\rho }_0\right)}·\right]}^2x}\right\}\frac{h_o\tan \alpha }{2.44\times 0.12\times L}〉\frac{h_0V_0^2L}{2.44\times 0.12}x\int \frac{\sqrt{1+x}}{x}x=2\sqrt{1+x}-\ln \frac{\sqrt{1+x}-1}{\sqrt{1+x}+1}+C$ $F_3=209832.582\{1.8133\times \left[2.9246\ln x+\frac{0.1488}{x}+0.0312·\left(\frac{\sqrt{1+19.2419x}}{x}-9.621\ln \frac{\sqrt{1+19.2419x}-1}{\sqrt{1+19.2419x}+1}\right)\right]-{0.0653\left[2.9246x-0.1488\ln x-0.0312\left(2\sqrt{1+19.2419x}-\ln \left(\frac{\sqrt{1+19.2419x}-1}{\sqrt{1+19.2419x}+1}\right)\right]\right\}}_{12.4578}^{21.3691}$

$\begin{array}{cc}=209832.582\left\{1.8133\times \left[2.9246\ln \frac{21.3691}{12.4578}+0.1488\left(\frac{1}{21.3691}-\frac{1}{12.4578}\right)+0.0312\left(\frac{\sqrt{1+19.2419\times 21.3691}}{21.3691}-\frac{\sqrt{1+19.2419\times 12.4578}}{12.4578}-9.621\ln \frac{\sqrt{1+19.2419\times 21.3691}-1}{\sqrt{1+19.2419\times 21.3691}+1}+9.621\ln \frac{\sqrt{1+19.2419\times 12.4578}-1}{\sqrt{1+19.2419\times 12.4578}+1}\right)\right]-0.0653\left[2.9246\left(21.3691-12.4578\right)-0.1488\ln \frac{21.3691}{12.4578}-0.0312\left(2\sqrt{1+19.2419\times 21.3691}-2\sqrt{1+19.2419\times 12.4578}-\ln \frac{\sqrt{1+19.2419\times 21.3691}-1}{\sqrt{1+19.2419\times 21.3691}+1}+\ln \frac{\sqrt{1+19.2419\times 12.4578}-1}{\sqrt{1+19.2419\times 12.4578}+1}\right)\right]\right\}=209832.582\left\{1.8133\times \left[1.5781-0.005+0.0312\left(-0.2953-0.2934\right)\right]-0.0653\left[26.062-0.0803-0.0312\left(9.5748-0.0305\right)\right]\right\}=239636.5129N=24T& \left(7\right)\\ \begin{array}{c}\delta ={\sin }^{-1}\left(\frac{1}{2}\sin \theta \right)\\ ={\sin }^{-1}\left(\frac{1}{2}\sin 36.5°\right)\\ =17.3°\end{array}& \left(8\right)\end{array}$

According to this sweep forward angle, low-temp planar jet can keep balances during vertical take-off/landing.

$\begin{array}{cc}F=n_2\left(F_1+F_2+F_3\right)\cos \beta \cos \gamma -n_2\left[F_4\cos \delta +F_6\sin \left(\phi +\gamma \right)-F_6\sin \left(\phi -\gamma \right)\right]=2\left(124+151+24\right)\cos 5°\cos 5°-2\left[13\cos 17.3°+1.4\sin \left(2\times 16.3°+5°\right)-1.4\sin \left(2\times 16.3°-5°\right)\right]=568TF-G=568-560=8T>0& \left(9\right)\\ \mathrm{TWR}=\frac{n_3\left(F_5+F_6\right)}{G}=\frac{n_3F_4}{G}=\frac{4\times 13}{560}=0.09<0.1& \left(10\right)\end{array}$

It is clearly demonstrated above that VTOL is achievable on Airbus A380 once remodeled as shown, and more particularly, in case of using just two turbofan engines and thrust-to-weight ratio smaller than 0.1.

Claims

1. An aircraft capable of vertical take-off/landing, comprising: ailerons (1, 2); a turbofan engine (3) including a low-temp duct (6) with an openable and closable propelling nozzle (7) and a high-temp duct (4) with an openable and closable propelling nozzle (5); a low-temp bypass duct (15) including an openable and closable inlet (14) connected to the low-temp duct (6), an outer wall (16), an inner wall (17) and a thin slot outlet (19) set on the upper surface of the wing and in the direction of the wingspan; and a high-temp bypass duct (9) including an openable and closable inlet (8) connected to the high-temp duct (4), an outer wall (10) and a thin slot outlet (12) set above that one (19) of the low-temp bypass duct (15) and in the direction of the wingspan.

2. The aircraft according to claim 1 wherein the low-temp duct (6), during forward flight, spouts out low-temp air (18) directly under the opening of the propelling nozzle (7) of low-temp duct (6) and the closing of the inlet (14) of the low-temp bypass duct (15).

3. The aircraft according to claim 1-2 wherein the high-temp duct (4), during forward flight, spouts out high-temp air (11) directly under the opening of the propelling nozzle (5) of high-temp duct (4) and the closing of the inlet (8) of the high-temp bypass duct (9).

4. The aircraft according to claim 1-3 wherein the low-temp bypass duct (15), during take-off/landing, directing, under the closing of the propelling nozzle (7) of low-temp duct (6) and the opening of the inlet (14) of the low-temp bypass duct (15), the low-temp air (18) from the low-temp duct (6) to flow, in form of low-temp planar jet (20), over the upper surface of the wing in the direction of the wingspan, thereby generating a vertical lift and enabling the ailerons (1, 2) to control horizontal and vertical balances of the aircraft.

5. The aircraft according to claim 1-4 wherein the high-temp bypass duct (9), during take-off/landing, directs, under the closing of the propelling nozzle (5) of high-temp duct (4) and the opening of the inlet (8) of the high-temp bypass duct (9), the high-temp air (18) from the high-temp duct (4) to flow, in form of high-temp planar jet (13), above the low-temp planar jet (20) in the direction of the wingspan, thereby generating another vertical lift and enabling the ailerons (1, 2) to control horizontal and vertical balances of the aircraft more efficiently.

6. The aircraft according to claim 1-5 wherein the thin slot outlet of the high-temp bypass duct, set above that one of the low-temp bypass duct, enables the high-temp planar jet not to burn up the upper surface of the wing during vertical take-off/landing.

7. The aircraft according to claim 1-6 wherein the turbofan engine (3), supplying not only the low-temp air (18) to a low-temp bypass duct (15) but also the high-temp air (11) to the high-temp bypass (9) during vertical take-off/landing, can be changed to an engine's combination with a low-temp air accelerator, or other engine having this feature.