CN209833977U

CN209833977U - Two-dimensional fluid aircraft

Info

Publication number: CN209833977U
Application number: CN201920477173.0U
Authority: CN
Inventors: 涂常青
Original assignee: Individual
Current assignee: Sichuan Shengde New Environmental Protection Technology Co ltd
Priority date: 2019-04-08
Filing date: 2019-04-08
Publication date: 2019-12-24
Anticipated expiration: 2029-04-08

Abstract

The utility model provides a two-dimensional fluid aircraft, belonging to the aircraft field, which comprises a wing body and a two-dimensional fluid converter; the two-dimensional fluid converter comprises a rectifying cap, a baffle wall and a drainage assembly for introducing airflow, wherein an installation space for installing the rectifying cap is formed on the inner side of the baffle wall, and a rectifying space is formed between the baffle wall and the outer wall of the rectifying cap; the retaining wall conforms to the equal-difference variable-diameter circular arc; the outer side of the radial section of the rectifying cap is circular; a rectification outlet communicated with the rectification space is formed at the side part of the blocking wall; the drainage assembly comprises a fluid outlet, and the fluid outlet faces to the small-diameter end of the fairing cap; the wing body has windward side and leeward side of relative setting, is provided with the archway between windward side and the leeward side, and the rectification export sets up towards the leeward side at the windward side of archway. The two-dimensional fluid aircraft can reduce the production cost, improve the lift force of the aircraft and reduce disturbance.

Description

Two-dimensional fluid aircraft

Technical Field

The utility model relates to an aircraft field particularly, relates to a two-dimensional fluid aircraft.

Background

The conventional fixed wing is designed to obtain a lift force by forming a pressure difference between upper and lower surfaces of the wing. The method for forming the pressure difference comprises the following steps: the power device makes the fixed wing perform relative motion in the air. Taking the fixed wing as a reference system: the air reaches the leading edge of the fixed wing at a relatively high velocity, and the air is split to the upper and lower surfaces of the wing and accelerated rapidly. When high-speed air passes through the top of the upper surface of the wing, the high-speed air still has rising inertia, and the curved surface behind the top extends downwards, so that the air cannot be completely attached to the upper surface of the wing at once, the volume of the air is expanded sharply, and the pressure is reduced (compared with the nearby undisturbed air, the same applies below), namely the pressure of the upper surface of the wing is reduced. Since the lower surface of the wing is a relatively flat surface, the pressure is constant when the volume of the high-speed air passing through the lower surface of the wing is almost constant. When the relative motion of the fixed wing and the air has a certain elevation angle, the air on the lower surface of the wing is compressed to a certain degree, and the pressure is increased, namely the pressure on the lower surface of the wing is increased. The above phenomenon causes the fixed wing to obtain lift.

For conventional fixed wings, relative motion in air is a necessary way to compress and expand air.

But the altitude rises to a certain extent and the air pressure is already small. Compared with the low altitude position, under the condition that the relative speed is not changed, the air expansion amplitude at the upper surface of the wing is reduced, the air pressure at the position is closer to the air pressure at the lower surface of the wing, and the lift force is reduced. To obtain sufficient lift, it is necessary to further increase the speed of the aircraft, so that the air on the lower surface of the wing is further compressed, thereby increasing the air pressure, to compensate for the reduction in lift caused by the reduction in the expansion amplitude of the air on the upper surface of the wing, but the speed of the aircraft cannot be raised infinitely, which explains the limitation of the limit of the lift of the aeronautical aircraft.

Therefore, the existing aircraft taking the fixed wing lift model of the Laite brother utility model as the basic principle has the defects which are difficult to overcome: under the condition of low speed (the static state of the aircraft can be understood as the limit state of low speed), ideal lift force is difficult to obtain, the takeoff and landing of the aircraft are difficult, and the stall can also cause the aircraft to be out of control, thereby endangering the flight safety. The fundamental reason is that it must rely on the high speed movement of the fixed wing itself, which in turn relies on the high speed movement of the aircraft. This indirect method of compressing and expanding air to obtain lift is unreliable.

In addition, the principle of a rotary-wing aircraft is understood to be the deformation of a fixed wing in a circular motion, the same drawbacks as those of a fixed-wing aircraft.

SUMMERY OF THE UTILITY MODEL

The utility model provides a two-dimensional fluid aircraft aims at solving the above-mentioned problem that two-dimensional fluid aircraft exists among the prior art.

The utility model discloses a realize like this:

a two-dimensional fluid aircraft comprises a wing body and a two-dimensional fluid converter;

the two-dimensional fluid converter comprises a rectifying cap, a blocking wall and a drainage assembly for introducing airflow, wherein an installation space for installing the rectifying cap is formed on the inner side of the blocking wall, and a rectifying space is formed between the blocking wall and the outer wall of the rectifying cap;

the baffle wall conforms to the equal-difference variable-diameter arc and is provided with a small-diameter layer and a large-diameter layer;

the outer side of the radial section of the rectifying cap is circular, and the diameter of the outer wall of the rectifying cap is continuously changed along the axial direction to form a small-diameter end and a large-diameter end which are oppositely arranged;

the axis of the baffle wall is superposed with the axis of the rectifying cap;

a rectification outlet communicated with the rectification space is formed at the side part of the blocking wall; the rectifying outlet is formed by a gap between the small-diameter layer and the large-diameter layer of the baffle wall;

the flow directing assembly includes a fluid outlet directed toward a small diameter end of the fairing cap;

the wing body is provided with a windward side and a leeward side which are oppositely arranged, an arch surface is arranged between the windward side and the leeward side, and the rectifying outlet is arranged on the windward side of the arch surface and faces the leeward side.

The utility model discloses an in one embodiment, two-dimensional fluid converter includes the multi-disc water conservancy diversion piece, the water conservancy diversion piece set up in the rectification exit, the one end of water conservancy diversion piece with path layer fixed connection, the other end with path layer fixed connection greatly.

In an embodiment of the present invention, the plane of the flow deflector and the radial direction of the blocking wall form an acute angle.

In an embodiment of the present invention, the flow guiding assembly includes a blower and an air inlet channel;

the entry setting of intake duct is in the windward side, the fan with the export intercommunication of intake duct, the export of fan forms the fluid outlet.

The utility model discloses an in one embodiment, the intake duct is the vortex type pipeline, the vortex type pipeline includes series connection's bleed section and linkage segment, the bleed section is kept away from the one end of linkage segment does fluid inlet, the linkage segment is around establishing the outer loop of fan.

In an embodiment of the present invention, the axial length of the baffle wall is L, the cross-sectional area of the large diameter end of the fairing cap is S, the radial cross-section of the fairing cap has an area S', and the formula is satisfiedL' is the distance from the radial section to the small diameter end of the fairing.

The utility model has the advantages that: the utility model discloses a two-dimensional fluid aircraft that above-mentioned design obtained has following advantage:

1. high performance: the two-dimensional fluid aircraft principle and the structure thereof can control the fluid to generate lift force by using smaller energy, so that the aircraft can obtain enough lift force at low speed, and the performance of the aircraft is greatly improved.

2. High safety: throughout the observation of the laite brother utility model fixed wing aircraft, the severe dependence of the aircraft on the speed of motion is always its fatal defect, once stalled, the aircraft will lose lift immediately, and the aircraft loses control simultaneously, seriously threatens flight safety, and too fast speed will bring severe examination to the power plant and the structural strength of aircraft. The two-dimensional fluid aircraft principle and the structure thereof can ensure that the aircraft can obtain stable lift force at any time. The magnitude of lift can be varied by controlling the velocity of the two-dimensional fluid, without being limited by the speed of motion of the rotor or the aircraft itself. Use the utility model discloses an aircraft can be at any speed down initiative regulation lift to improve take off, flight, the nature controlled under the state such as descending.

3. The practicability is strong: the principle and the structure of the two-dimensional fluid aircraft can enable the aircraft to get rid of the dependence on the speed, a long runway is not needed, and vertical take-off and landing can be realized. Use the utility model discloses an aircraft need rotor motion range of large tracts of land not like rotor craft, does not have high expectations to service environment. The high performance of the aircraft can lead the aircraft to obtain the advantages of large load capacity and low energy consumption. Can very big degree remain the aerodynamic layout of traditional fixed wing aircraft, can also remain traditional flight control system, directly will the utility model discloses use the upgrading transformation at traditional fixed wing aircraft and can remain the advantage of most traditional fixed wing aircraft. Because two-dimensional fluid aircraft principle and structure are extremely simple, can directly apply mechanically in a plurality of application scenes the utility model discloses. Therefore, the principle and the structure of the two-dimensional fluid aircraft have strong practicability and wide application.

4. Good economical efficiency: because the two-dimensional fluid aircraft has a simple structure and no heavy, complex and fine structure, the high-speed moving part is integrated in the aircraft and is close to the power device, the manufacturing cost is reduced, and the reliability is improved. The power device and the impeller can also be directly arranged in the two-dimensional fluid converter, so that the aim of efficiently utilizing the inner space of the aircraft is fulfilled.

The reaction force generated by the two-dimensional fluid counteracts the fluid resistance received during high-speed flight, so that the requirement on the structural strength of the fixed wing is reduced. The reaction force of the two-dimensional fluid can also replace the forward power of the aircraft. Further reducing the overall cost of the aircraft.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

Fig. 1 is a schematic structural diagram of a two-dimensional fluid aircraft provided by an embodiment of the present invention;

fig. 2 is a schematic view of a partial internal structure of a two-dimensional fluid aircraft provided by an embodiment of the present invention;

fig. 3 is a schematic structural diagram of a drainage assembly provided by an embodiment of the present invention;

FIG. 4 is a cross-sectional view taken along line A-A of FIG. 2;

fig. 5 is a sectional view taken along line B-B in fig. 2.

Icon: 001-two-dimensional fluid vehicle; 010-wing body; 030-two-dimensional fluid transducer; 100-a fairing cap; 200-a retaining wall; 300-a drainage assembly; 101-small diameter end; 103-large diameter end; 201-minor diameter layer; 203-large diameter layer; 210-a rectified outlet; 011-windward side; 013-leeward side; 015-arch surface; 230-guide vanes; 310-a fan; 350-vortex type pipe; 351-a gas-introducing section; 353-a connecting end; 311-impeller; 313 — a power plant.

Detailed Description

To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the drawings of the embodiments of the present invention are combined to clearly and completely describe the technical solutions of the embodiments of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention. Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplification of description, and do not indicate or imply that the equipment or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In the present disclosure, unless otherwise expressly stated or limited, the first feature may comprise both the first and second features directly contacting each other, and also may comprise the first and second features not being directly contacting each other but being in contact with each other by means of further features between them. Also, the first feature being above, on or above the second feature includes the first feature being directly above and obliquely above the second feature, or merely means that the first feature is at a higher level than the second feature. A first feature that underlies, and underlies a second feature includes a first feature that is directly under and obliquely under a second feature, or simply means that the first feature is at a lesser level than the second feature.

Examples

The present embodiment provides a two-dimensional fluid aircraft 001, please refer to fig. 1 and fig. 2, such a two-dimensional fluid aircraft 001 includes a wing body 010 and a two-dimensional fluid converter 030; the two-dimensional fluid converter 030 includes a rectification cap 100, a blocking wall 200, and a flow guide assembly 300 for introducing a flow of gas, an inner side of the blocking wall 200 forming an installation space for installing the rectification cap 100, and a rectification space formed between the blocking wall 200 and an outer wall of the rectification cap 100;

the baffle wall 200 conforms to an equal-difference variable-diameter circular arc and is provided with a small-diameter layer 201 and a large-diameter layer 203; the outer side of the radial section of the fairing cap 100 is circular, and the diameter of the outer wall of the fairing cap 100 is continuously changed along the axial direction to form a small-diameter end 101 and a large-diameter end 103 which are oppositely arranged;

the axis of the baffle wall 200 is superposed with the axis of the fairing cap 100; a rectification outlet 210 communicated with the rectification space is formed at the side of the blocking wall 200; the rectification outlet 210 is formed by a gap between the small-diameter layer 201 and the large-diameter layer 203 of the barrier wall 200;

the flow directing assembly 300 includes a fluid outlet directed toward the small diameter end 101 of the fairing 100; the wing body 010 has a windward side 011 and a leeward side 013 which are oppositely arranged, an arch 015 is arranged between the windward side 011 and the leeward side 013, and the fairing exits 210 are arranged towards the leeward side 013 at the windward side 011 of the arch 015.

Referring to fig. 4 and 5, in the present embodiment, an installation space for installing the fairing cap 100 is formed in the windward side 011 of the wing body 010 in a hollow manner, an inner wall of the installation space is the baffle wall 200, and an axial direction of the installation space is arranged along a length direction of the wing body 010. After the airflow is guided to the small-diameter end 101 of the fairing cap 100 by the flow guide assembly 300, the turbulent airflow is rectified into a two-dimensional airflow by the two-dimensional fluid converter 030 and is sprayed to the arch surface 015, the medium above the turbulent airflow is also driven to move backwards due to the driving action of the two-dimensional fluid, the surrounding medium cannot immediately supplement the vacant position caused by the leaving of the medium due to inertia, the volume of the medium at the vacant position is expanded, and the pressure is reduced. While the other side opposite to the cambered surface 015 is a flat surface, there is no volume expansion or little expansion of the fluid, so the pressure is relatively greater, so that the entire wing body 010 has a lift force from the flat surface to the cambered surface 015.

In this embodiment, the two-dimensional fluid converter 030 includes a plurality of flow deflectors 230, the flow deflectors 230 are disposed at the rectification outlet 210, one end of each flow deflector 230 is fixedly connected to the small-diameter layer 201, and the other end of each flow deflector 230 is fixedly connected to the large-diameter layer 203. The plane of the guide vane 230 forms an acute angle with the radial direction of the blocking wall 200. The arrangement of the guide vane 230 can guide the moving direction of the two-dimensional fluid, and on the other hand, the device can be reinforced. The side of the baffle 230 adjacent to the fairing space is directly impacted by the fluid and should be angled as closely as possible to follow the helical extent of the majority of the fluid.

Referring to fig. 3, the flow guiding assembly 300 includes a fan 310 and an air inlet; the inlet of the air inlet channel is arranged on the windward side 011, the fan 310 is communicated with the outlet of the air inlet channel, and the outlet of the fan 310 forms a fluid outlet. The inlet of the air inlet channel is arranged on the windward side 011, so that air can be assisted to enter the fan 310, and the working strength of the fan 310 is reduced.

The fan 310 comprises an impeller 311 and a power device 313, and the output end of the power device 313 is connected with the impeller 311. The impeller 311 is rotated by the power unit 313.

In this embodiment, the air inlet channel is a scroll-type pipeline 350, the scroll-type pipeline 350 includes a bleed air section 351 and a connection section that are connected in series, one end of the bleed air section 351 that is far away from the connection section is a fluid inlet, and the connection section is around the outer ring of the fan 310. By arranging the scroll-type pipeline 350, the fluid can smoothly enter the fan 310 and is blown into the small-diameter end 101 of the fairing 100 through the fan 310, and the collision of the airflow and the inner wall of the pipeline is reduced.

Specifically, the axial length of the baffle wall 200 is L, the cross-sectional area of the large diameter end 103 of the fairing 100 is S, and the radial cross-section of the fairing 100 has an area S', which satisfies the formulaL' is a distance from the radial cross section to the small-diameter end 101 of the fairing 100.

The fairing cap 100 with the variable diameter continuously can ensure that the two-dimensional fluid discharged from each position of the fairing outlet 210 has approximately the same amount, and ensure that the two-dimensional fluid flow velocity at each position of the arch 015 of the wing body 010 is approximately the same, so that the lifting force applied to the wing body 010 is uniform.

The principle basis of the two-dimensional fluid aircraft 001 provided by the embodiment is as follows:

1. any object that performs relative mechanical motion in a fluid causes a volume of the fluid on the surface of the object to compress or expand, and the pressure and temperature of the object change, and the object is subjected to corresponding reaction forces.

Taking gas as an example: the pressure of the gas on the surface of the object means: the object is subjected to forces resulting from the gas molecules hitting with a certain probability per surface area, which is related to the density, molecular mass, hitting speed and angle of the gas. From a microscopic perspective: the force resulting from multiple molecules striking the surface of the object with lower momentum at the same time and a single molecule striking the surface of the object with higher momentum is the same for the same total momentum. The law of the method conforms to Newton's second law: and f is ma.

f is the force to which the object is subjected by the impact of gas molecules; m is the total mass of molecules involved in the impact; a is the crash acceleration.

2. Under the condition of constant mass and heat energy: the pressure is increased when the gas volume is reduced, whereas the pressure is reduced when the gas volume is increased.

Gas pressure formula: PV ═ nRT.

P is the gas pressure; v is the gas volume; n is the mass of the gas; r is a constant of 8.31441 ± 0.00026J (mol.k); t is the gas temperature.

3. The mechanical force is conducted at the speed of sound. The fluid that is compressed or expanded will conduct the pressure changes to the surroundings, and the longer the time, the more the changes will affect the total amount of fluid, and the more its amplitude of the pressure changes will be leveled out. The mathematical law of the method conforms to the law of conservation of energy, and the expanding speed of the conduction range is the speed of sound.

4. The conduction range of mechanical force is a sphere with radius expanding at sonic speed, and the specific speed and conduction limit range of the sphere are limited by the characteristics of viscosity, temperature, density, specific heat capacity and the like of fluid.

Taking uniform air at normal temperature and pressure as an example, the mechanical force transmission range is as follows: from the sphere volume formula: v ═ 4/3 (pi (R) ^ 3; and, radius of mechanical force conduction range: r is ut;

the formula can be obtained: and V is (4/3) pi (ut) ^ 3.

In the formula: v is the air volume in the mechanical force conduction range; π is the circumference ratio; r is the mechanical force transmission range radius; u is the speed of sound of air, and at normal temperature (15 ℃), u is 331.3+ (0.606x15) ═ 340.4 m/s; t is time in units of s.

It can be seen from this that: in the open area, the conduction of mechanical forces is expanded by the 3 rd power of the product of the speed of sound and time.

It should be distinguished that in the case where the fluid is formed by driving a medium in the form of heat radiation, magnetic force, light, etc., u should be substituted for the speed of light, not the speed of sound. The utility model discloses only concentrate the principle of having discussed the adoption mechanical force and having formed lift, nevertheless not be restricted to the mechanical force, the utility model discloses a realization methods such as heat radiation, magnetic force, light can be used mechanically equally to the principle.

5. At a larger time and space scale, when an object performs relative motion in a medium at a low speed, the fluid pressure change of the surface of the object is small, the change is conducted to a larger range, and the compression and expansion amplitudes of the medium are not easy to observe. Therefore, the change in fluid volume has little effect and can be considered as an ideal fluid, so the mechanical characteristics can still be explained by using Bernoulli's theorem. On a smaller time, spatial scale then not, any object moving in a medium has its mechanical force transmitted from its surface to the surrounding fluid from the near to the far in turn, such as: when the object starts to move relatively in the medium, the fluid affected by the mechanical force is limited in a very small range, and the phenomena of medium compression and expansion exist. The resulting fluid, the phenomenon of pressure increase and decrease, is present.

6. When the relative motion of the object and the medium reaches a certain speed, the medium is compressed and expanded to become non-negligible. Such as: when the moving speed of the object in the air is close to Mach number 0.3, the degree of air compression and expansion on the surface of the object is already obvious, and the Bernoulli theorem cannot explain the mechanical characteristics of the object.

7. The inertia of the fluid itself is one of the reasons for the compression and expansion of the fluid during its movement.

8. The essence of the aircraft (fixed wing aircraft, rotorcraft, glider, submersible or devices of similar principle, etc., the same below) to obtain lift is the pressure difference generated when the medium (earth atmosphere, alien atmosphere, water or other fluids, the same below) is compressed and expanded, and the vector opposite to the gravity is the lift. The specific method comprises the following steps: the aircraft lift device and air perform high-speed relative motion, the inertia of the airflow enables the aircraft lift device to be greatly compressed and expanded, so that the air pressure is changed, the air pressure borne by the lift device is changed, and the vector of the total stress of the aircraft lift device in the direction opposite to the gravity is the lift force. The aircraft is subjected to the resistance which is the vector of the pressure change generated during air compression and expansion in the horizontal direction, the frictional resistance, the heat consumption and the like.

9. The nature of moving the air is not different from that of moving the fixed wing itself, and the air is compressed and expanded by the relative movement of the fixed wing and the air, and a pressure difference is formed between the upper and lower surfaces of the wing, and a lift force is generated if the vector of the pressure difference is opposite to the direction of gravity.

10. The pressure of the fluid in direct contact with the aircraft on the aircraft surface directly determines the total force exerted by the aircraft, the vector of which in the opposite direction to gravity is the lift force. Further: the lift can be controlled by controlling the fluid directly contacting the upper and lower surfaces of the airfoil, without being limited by the total amount of fluid. Namely: the two-dimensional fluid vehicle 001 can produce the same aerodynamic effects as a conventional fixed-wing vehicle.

Based on above 10 theoretical foundations, the utility model provides a two-dimensional fluid aircraft 001 has following characteristic: the medium is accelerated by the drainage assembly 300 to form a fluid, the fluid is rectified into a two-dimensional fluid by the two-dimensional fluid converter 030, the two-dimensional fluid is ejected out of the arched surface 015 of the wing body 010 along the tangential direction, and the two-dimensional fluid is greatly expanded by utilizing the curved surface of the arched surface 015 and the inertia of the fluid, so that the fluid pressure is greatly reduced, and the lift force is further obtained.

When the wing body 010 is normally arranged, that is, the cambered surface 015 is arranged above and the plane is arranged below, the impeller 311 rotates at a high speed, a medium is sucked from the volute pipeline, fluid passing through the impeller 311 forms spiral axial composite fluid, and then the spiral axial composite fluid is injected into the two-dimensional fluid converter 030; the two-dimensional fluid converter 030 rectifies the fluid into an approximate two-dimensional shape and then tangentially ejects the fluid along the top point on the upper surface of the fixed wing, namely the two-dimensional fluid; the inertia of the two-dimensional fluid causes a portion of the fluid to continue moving rearward while another portion of the fluid slides rearward and downward along the arcuate surfaces 015. In the process, the volume of the fluid is expanded sharply, and the pressure is reduced rapidly, so that the pressure on the upper surface of the fixed wing is reduced. Due to the driving action of the two-dimensional fluid, the medium above the two-dimensional fluid is also driven to move backwards, and the surrounding medium cannot immediately supplement the vacant space caused by the leaving of the medium due to inertia, the volume of the medium at the vacant space expands, and the pressure of the medium is reduced. The upper surface of the stationary vane thus forms a negative pressure region. Due to the limitation of the speed of sound, the conduction range of the negative pressure in unit time is limited, and when the movement speed of the two-dimensional fluid is further increased, the pressure of the negative pressure area is further reduced. The fluid flow velocity at the lower surface of the fixed wing is low, the volume of the fixed wing is hardly expanded, and the pressure is not reduced. The vector of the pressure on the upper surface and the lower surface of the fixed wing in the direction opposite to the gravity is the lift force.

Therefore, the two-dimensional fluid aircraft 001 can stably obtain the lift force at any time, can realize flight control by controlling the speed of the two-dimensional fluid, and can also close the function.

The two-dimensional fluid vehicle 001 provided by the present application has the following advantages:

1. high performance: the two-dimensional fluid aircraft 001 principle and the structure thereof can control the fluid to generate lift force by using smaller energy, so that the aircraft can obtain enough lift force at low speed, and the performance of the aircraft is greatly improved.

2. High safety: throughout the observation of the laite brother utility model fixed wing aircraft, the severe dependence of the aircraft on the speed of motion is always its fatal defect, once stalled, the aircraft will lose lift immediately, and the aircraft loses control simultaneously, seriously threatens flight safety, and too fast speed will bring severe examination to the power plant and the structural strength of aircraft. The principle of the two-dimensional fluid aircraft 001 and the structure thereof can ensure that the aircraft can obtain stable lift force at any time. The magnitude of lift can be varied by controlling the velocity of the two-dimensional fluid, without being limited by the speed of motion of the rotor or the aircraft itself. Use the utility model discloses an aircraft can be at any speed down initiative regulation lift to improve take off, flight, the nature controlled under the state such as descending.

3. The practicability is strong: the two-dimensional fluid aircraft 001 principle and the structure thereof can enable the aircraft to get rid of the dependence on the speed, do not need a longer runway, and can also realize vertical take-off and landing. Use the utility model discloses an aircraft need rotor motion range of large tracts of land not like rotor craft, does not have high expectations to service environment. The high performance of the aircraft can lead the aircraft to obtain the advantages of large load capacity and low energy consumption. Can very big degree remain the aerodynamic layout of traditional fixed wing aircraft, can also remain traditional flight control system, directly will the utility model discloses use the upgrading transformation at traditional fixed wing aircraft and can remain the advantage of most traditional fixed wing aircraft. Because two-dimensional fluid aircraft 001 principle and its structure are extremely simple, can directly apply mechanically in a plurality of application scenes the utility model discloses. Therefore, the principle of the two-dimensional fluid aircraft 001 and the structure thereof have strong practicability and wide application.

4. Good economical efficiency: because the two-dimensional fluid aircraft 001 is simple in structure and free of heavy, complex and delicate structures, high-speed moving parts are integrated inside the aircraft and close to the power plant 313, manufacturing cost is reduced, and reliability is improved. The power unit 313 and the impeller 311 may be directly disposed inside the two-dimensional fluid converter 030, thereby achieving the purpose of efficiently utilizing the space inside the aircraft.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A two-dimensional fluid aircraft is characterized by comprising a wing body and a two-dimensional fluid converter;

the axis of the baffle wall is superposed with the axis of the rectifying cap;

2. The two-dimensional fluid vehicle of claim 1, wherein the two-dimensional fluid converter comprises a plurality of flow deflectors, the flow deflectors are arranged at the flow rectification outlet, one end of each flow deflector is fixedly connected with the small-diameter layer, and the other end of each flow deflector is fixedly connected with the large-diameter layer.

3. The two-dimensional fluid vehicle of claim 2, wherein the plane of the deflector forms an acute angle with the radial direction of the baffle wall.

4. The two-dimensional fluidic aerial vehicle of claim 1, wherein the flow directing assembly comprises a fan and an air intake;

5. The two-dimensional fluid aircraft of claim 4, wherein the air inlet channel is a scroll-type pipeline, the scroll-type pipeline comprises a bleed section and a connecting section which are connected in series, one end of the bleed section, which is far away from the connecting section, is the fluid inlet, and the connecting section is wound on an outer ring of the fan.

6. The two-dimensional fluidic aircraft of claim 1, wherein said dam wall has an axial length L, said large diameter end of said fairing has a cross-sectional area S, and said fairing has a radial cross-section having an area S' that satisfies the formulaL' is the distance from the radial section to the small diameter end of the fairing.