CN104724287B - Saucer-shaped aircraft - Google Patents

Abstract

The invention discloses a saucer-shaped aircraft. The basic structure of the saucer-shaped aircraft comprises an upper aircraft body, a lower aircraft body and a rotation driving mechanism, wherein an aircraft body space is formed between the upper aircraft body and the lower aircraft body; the rotation driving mechanism is used for driving the upper aircraft body to rotate forwards, and under the condition of no stress, the lower aircraft body can rotate reversely because of conservation of angular kinetic energy; the lower aircraft body is provided with a plurality of air flues; one end of each air flue is communicated with the aircraft body space, and the other end of each air flue is communicated with atmosphere; each air flue is internally provided with a turbofan respectively; an annular magnetic suspension guide rail is arranged between the upper aircraft body and the lower aircraft body; the power source is used for providing required power for the rotation driving mechanism, the turbofans and the magnetic suspension guide rail. Compared with the prior art, the saucer-shaped aircraft is simple in operation principle, and is high in lift force; the lift force of the aircraft and the flight driving force are integrated; the appearance of the aircraft body is a symmetrical streamline type; the aircraft body is good in balance property, can perpendicularly take off and land, hover at random and fly at a high speed; because components, such as a propeller, a turbine engine are omitted, the saucer-shaped aircraft is simple in structure, and is good in controllability.

Description

Disc-shaped flying craft

Technical field

The present invention relates to a kind of disc-shaped flying craft.

Background technology

At present, disc-shaped flying craft of the prior art, is mostly real by configuring the form of propeller and turbogenerator The elevating function of existing aircraft, this disc-shaped flying craft is identical with existing plane fleight principle, is all to change wing or propeller Top and bottom flow velocity and flying power is provided.There is the disc-shaped flying craft of this kind of structure, due to portions such as propeller and turbogenerators So that Flight Vehicle Structure is complex, aircraft is heavier, and flight efficiency is low for the presence of part, handling bad.

Content of the invention

It is an object of the invention to proposing a kind of disc-shaped flying craft, it adopts the following technical scheme that

Disc-shaped flying craft, including upper fuselage, lower fuselage and rotary drive mechanism and power source；Upper fuselage and lower fuselage it Between formed organism space；Rotary drive mechanism, for driving upper fuselage and lower fuselage opposite direction rotation；Lower fuselage opens up There are multiple air flues；One end of each air flue is connected with body space, the other end and atmosphere；It is respectively equipped with each air flue Turbofan；Power source, for being rotary drive mechanism and turbofan offer required drive.

Further, it is provided with annular magnetic suspended guide between upper fuselage and lower fuselage, power source is the magnetic suspension of described annular Guide rail provides required drive.

Further, upper fuselage and lower fuselage adopt disc structure.

Further, upper fuselage is identical with the rotation axiss of lower fuselage, and the central axis for disc-shaped flying craft.

Compared with prior art, the present invention has the advantage that

Disc-shaped flying craft in the present invention, thereon fuselage and lower fuselage rotated by central axis opposite direction, and upper fuselage Form organism space and lower fuselage between, when the edge slot between upper fuselage and lower fuselage is sufficiently small, taken out by turbofan Take the gas in body space so that body space internal gas pressure changes, when upper fuselage is rotated with friction speed with lower fuselage When, four face static pressures of two fuselages can change, and the Whole power of each static pressure forms the lift promoting aircraft.Phase , in prior art, operation principle of the present invention is simple, and lift is big for ratio；Aircraft lift is unified with flight driving force, outside fuselage See symmetrically streamlined, fuselage balance is good, can VTOL, arbitrarily hovering and high-speed flight；Due to eliminate propeller and The parts such as turbogenerator are so that the present invention also has the advantages that structure is simple, handling good.

Additionally, as the advantageous embodiment of the present invention, being provided with annular magnetic suspended guide between upper fuselage and lower fuselage, providing Repulsion is to resist the powerful internal force producing because of the change of body internal gas pressure.

Brief description

Fig. 1 is the structural representation of disc-shaped flying craft in the present invention；

Fig. 2 is the force analysis figure of disc-shaped flying craft in the present invention；

Wherein, the upper fuselage of 1-, fuselage under 2-, 3- rotary drive mechanism, 4- annular magnetic suspended guide, 5- power source, 6- machine Body space, 7- air flue, 8- turbofan.

Specific embodiment

Below in conjunction with the accompanying drawings and specific embodiment is described in further detail to the present invention:

In conjunction with shown in Fig. 1, disc-shaped flying craft, including upper fuselage 1, lower fuselage 2, rotary drive mechanism 3 and power source 5.

Upper fuselage 1 and lower fuselage 2 are all using disc structure.

Form organism space 6 between upper fuselage 1 and lower fuselage 2.

Rotary drive mechanism 3, for driving upper fuselage 1 to rotate forward.The rotation axiss of upper fuselage 1 are disc-shaped flying craft Central axis.

In the case of not being subject to external force, because of angular kinetic energy conservation, lower fuselage 2 will reversely rotate, and upper fuselage 1 and lower fuselage 2 Rotation axis coincident.

Forward direction herein with reversely, refer to when positive for clockwise direction when, be reversed counterclockwise；When forward direction is inverse During clockwise, it is reversed clockwise.

Rotary drive mechanism 3 can adopt the power parts such as electromotor.

Due to there is relative rotary motion between upper fuselage 1 and lower fuselage 2 so that certainly existing therebetween edge seam Gap.On the premise of fuselage 1 and lower fuselage 2 relative rotary motion on ensureing, edge slot preferably design sufficiently small.

Additionally, being provided with annular magnetic suspended guide 4 between upper fuselage 1 and lower fuselage 2, repulsion is provided to resist because of gas in body Buckling and the powerful internal force that produces.

Specifically, this annular magnetic suspended guide 4 can be arranged on fuselage 1 and any radial location of lower fuselage 2, is located at side It is optimum at edge.

Multiple air flues 7 are offered on lower fuselage 2.

One end of each air flue 7 is connected with body space 6, the other end and atmosphere.

It is respectively equipped with turbofan 8 in each air flue 7, its role is to, in extraction body space 6, gas is so that body is empty Between 6 internal gas pressures change.

Power source 5, for providing power for rotary drive mechanism 3, annular magnetic suspended guide 4 and turbofan 8.

In conjunction with shown in Fig. 2, in the present invention, the lift derivation of disc-shaped flying craft is specific as follows:

According to Bai Nuli equation, act on body surface pressure and deduct body and air relative motion shape for ambient atmosphere pressure The dynamic pressure becoming, dynamic pressure is bigger, and body pressure is less.

Define a point a of aircraft surface, its coordinate is (x, y, z), the section radius at the plane of a point place are r；

Component on each coordinate axes for the unit mass air is:

f_x=-ω²x,f_y=-ω²y

Then, its equilibrium equation is:

Dp=- ρ (f_xdx+f_yDy)=- ρ (ω²xdx+ω²ydy)

Above-mentioned formula integration is obtained:

$p=-\mathrm{\ρ}\frac{{\mathrm{\ω}}^2}{2}(x^2+y^2)+c---\left(1\right)$

In formula (1), p is pressure, and ρ is ambient air density, and c is constant；

Work as x=0, during y=0, by p=p₀Substitute into above formula, then obtain c=p₀, then formula (1) turn to:

$p=-\mathrm{\ρ}\frac{{\mathrm{\ω}}^2}{2}(x^2+y^2)+p_0---\left(2\right)$

X is known by geometrical relationship²+y²=r², formula (2) can turn to:

$p=-\mathrm{\ρ}\frac{{\mathrm{\ω}}^2}{2}{r}^2+p_0,r\&element;\[0,r\]---\left(3\right)$

In formula (3), r is aircraft radius；

Obtained according to formula (3):

$\left.\begin{array}{c}{p}_1=p_0-\mathrm{\ρ}\frac{{\mathrm{\ω}}_1^2}{2}{r}^2\\ p_2={\mathrm{kp}}_0-{\mathrm{\ρ}}^{\′}\frac{{\mathrm{\ω}}_1^2}{2}{r}^2\\ p_3={\mathrm{kp}}_0-{\mathrm{\ρ}}^{\′}\frac{{\mathrm{\ω}}_2^2}{2}{r}^2\\ p_4=p_0-\mathrm{\ρ}\frac{{\mathrm{\ω}}_2^2}{2}{r}^2\end{array}\right\}---\left(4\right)$

In formula (4), p₁、p₂、p₃、p₄Represent respectively the upper surface of upper fuselage 1, the lower surface of upper fuselage 1, lower fuselage 2 upper Pressure at the lower surface of surface and lower fuselage 2；

ρ '=k ρ (5)

In formula (5), ρ ' represents the atmospheric density in body space 6, and k is decompression coefficient, and k value is stitched with disc-shaped flying craft edge Gap and turbofan 8 power are related；

$\left.\begin{array}{c}{f}_1={\&integral;}_0^{r}2{\mathrm{\πrp}}_{1}dr\\ f_2={\&integral;}_0^{r}2{\mathrm{\πrp}}_{2}dr\\ f_3={\&integral;}_0^{r}2{\mathrm{\πrp}}_{3}dr\\ f_4={\&integral;}_0^{r}2{\mathrm{\πrp}}_{4}dr\end{array}\right\}---\left(6\right)$

In formula (6), f₁、f₂、f₃、f₄Represent respectively the upper surface of upper fuselage 1, the lower surface of upper fuselage 1, lower fuselage 2 upper Static pressure at the lower surface of surface and lower fuselage 2；

F=-f₁+f₂-f₃+f₄(7)

In formula (7), f represents the lift of aircraft, and positive sign represents power upwards, and negative sign represents that power is downward；

F is obtained by formula (3)～formula (7) it may be assumed that

$f=\frac{\mathrm{\π}}{4}(1-k)r^4\mathrm{\ρ}({\mathrm{\ω}}_1^2-{\mathrm{\ω}}_2^2)---\left(8\right)$

From above-mentioned formula (8), the size of lift f and decompression coefficient k, aircraft radius r, ambient air density p, on The angular velocity of rotation ω of fuselage₁, the angular velocity of rotation ω of lower fuselage₂Relevant；

In the case that aircraft radius r and ambient air density p determine, by the rotation of adjustment decompression coefficient k, upper fuselage Tarnsition velocity ω₁, and lower fuselage angular velocity of rotation ω₂Be sized to realize the regulation of lift f size.

Certainly, above only presently preferred embodiments of the present invention, the present invention is not limited to enumerate above-described embodiment.Should say Bright, all equivalent substitutes or obvious change that any those of ordinary skill in the art are made on the basis of the present invention Shape form, each falls within the protection domain of this specification, ought to be protected by the present invention.

Claims (4)

1. disc-shaped flying craft is it is characterised in that include upper fuselage, lower fuselage, rotary drive mechanism and power source；Upper fuselage with Form organism space between lower fuselage；Rotary drive mechanism, for driving upper fuselage and lower fuselage opposite direction rotation；In lower machine Offer multiple air flues with it；One end of each air flue is connected with body space, the other end and atmosphere；In each air flue It is respectively equipped with turbofan；Power source, for being rotary drive mechanism and turbofan offer required drive.

2. disc-shaped flying craft according to claim 1, its feature is, is provided with annular magnetic between upper fuselage and lower fuselage Suspension guide, power source provides required drive for described annular magnetic suspended guide.

3. disc-shaped flying craft according to claim 1 is it is characterised in that upper fuselage and lower fuselage adopt disc structure.

4. disc-shaped flying craft according to claim 1 is it is characterised in that upper fuselage is identical with the rotation axiss of lower fuselage, And the central axis for disc-shaped flying craft.