CN117508567A

CN117508567A - Novel duct (hub) driving aircraft

Info

Publication number: CN117508567A
Application number: CN202110608093.6A
Authority: CN
Inventors: 请求不公布姓名
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-06-01
Filing date: 2021-06-01
Publication date: 2024-02-06

Abstract

The novel ducted (hub) driven aircraft combines only a hub support and a blade, a variable blade (1) and a ducted structure (2) are connected and fixed and unfixed, and the wheel drive or the blade drive is switched by switching a speed change structure (3) or driving of other transmission or speed change devices, wherein the variable blade (1) rotates or a shell (9) rotates; in some application schemes, a flexible wing (4) which can be flexibly folded and telescopic is adapted to be used, a rotating system (5) changes angles and directions of a driving system with a variable blade (1) and other components, a landing gear system for taking off and landing of a landing gear system, and intelligent control and manned control are used for various control modes of an aircraft.

Description

Novel duct (hub) driving aircraft

Technical Field

The present invention relates to the field of aircraft.

Background

At present, with the rapid development of society, people choose more and more to go out, but in places with sparse population and mountains and water, the construction cost of highway and railway airports is too high, and the unmanned aerial vehicle which can fly and is suitable for vehicles running on highways and transport things is very important.

The aircraft is driven by adopting a helicopter-like spiral structure, so that the advantages of the aircraft are obvious compared with those of a fixed wing aircraft, but the disadvantages are more serious. The unsafe of the multiaxial rotor structure easily causes crash events, and in recent years, the accident of a helicopter is continuous, and the air flow, spin and mechanical runaway are problems faced by the aircraft with similar principles, so that the helicopter has serious accident once having no fixed wing. At present, the domestic helicopters have fewer maintenance amounts, so that the number of accidents is increased, and once the aircraft adopts a large number of multiaxial flight technologies, more dangerous accidents occur. The fixed wing can have a high probability of forced landing even in the complete absence of power, so the fixed wing is the first choice for flying an automobile from the safety point of view.

In the prior art, the tire driving system and the rotor system cannot be shared, and through the solutions of rotating the rotor, increasing the rotor and the like, the system is greatly reduced in bulkiness and safety, increased in dead weight, insufficient in thrust-weight ratio under the prior art condition, low in practicality and the like, and closed loop cannot be realized by the technologies of low practicality and the like under the automobile state.

Disclosure of Invention

The invention mainly aims to provide a novel duct (hub) type driving aircraft, which can be applied to schemes such as balance cars, wheelbarrows, unmanned aerial vehicles, aerobuses, motorcycles, multi-wheelers and the like, and solves the problems that a wheel type system cannot be well combined with an aerostructure, the duct driver is single in use, low in efficiency, low in compatibility of two forms and the like in the prior art by means of technical combination of one or more of the above technologies such as paddle-hub support mutual conversion, gearbox conversion, paddle folding, paddle expansion and contraction, duct interlayer design, duct lip and/or tail, driver rotation, coaxial technology and the like.

In order to achieve the above object, the present invention provides a novel ducted (hub) driven aircraft, comprising:

the variable blade consists of a single blade or a plurality of groups of blades and a rotating shaft and/or a hub, and the rotating shaft and/or the hub is connected with at least one or a plurality of the motor, the hub motor, the wheel motor, the transmission and the transmission shaft in a combined way; the single or multiple groups of blades, folding blades and telescopic blades are combined and then connected with the shell, the duct structure, other parts of the invention and other devices of the aircraft through automatic or semi-automatic and manual connection of at least one or multiple combinations of snap-in fixing, rotary fixing, mortise-tenon fixing, drawing-in type, line stepping motor, rotary motor and magnetic device, and the connection fixing or decomposition work with the shell is adjusted. The function is that in the wheel type form, the variable blade is used as a supporting system of the wheel hub; in blade mode, the aircraft is provided with driving force.

Duct structure: taking the shell as a duct main body structure, wherein one end and/or the head and tail ends of the shell are/is provided with a curve and/or lip-like structure; and/or a sandwich structure is arranged at the inner side of the shell and is formed by combining one or more than one of a single or a plurality of groups of curve combined structures with tesla valves, tesla-like valves and single or a plurality of groups of curve combined structures; the duct head and tail end or one end of the duct is provided with a curve, linear and/or lip type expansion structure and a combined structure which are automatically and/or manually opened by at least one or more of buckling, folding and rotating, and the duct head and tail end or one end of the duct is used for accelerating the airflow at the head and tail of the shell through the curve structure, the sandwich structure is used for turbulent flow generated by high-pressure airflow and low-pressure airflow, and the turbulent flow is discharged out of the system through the quick type of the curve structure.

Speed change structure: the speed change structure is connected with the motor, the engine or other power devices of the transmission shaft through one or more of a speed reducer, a star gear set, clutch switching, a connecting device, a supporting structure and gear switching to form a mode of outputting various rotating speeds and torque, and the bypass structure and the variable blades are switched and connected. The high-torque low-rotation-speed scheme is formed by connecting a speed reducer, a star gear and a connecting device to a shell or a duct in a wheel mode, and is output to the blades through a speed change structure in a flying mode.

Variable wing: the wing, the duck wing, the flap and/or the tail wing are/is formed by one or more of the single or multiple groups of the front and rear aircraft accommodating parts, the front side of the aircraft, the rear side of the aircraft, the front cover of the aircraft, the rear cover of the aircraft and the top of the aircraft through one or more of the combination of overturning, folding, stretching and rotating.

A rotation system: through one or more combination of a swing arm, a pull rod, a suspension, a steering gear and a supporting arm, one or more combination of a variable blade, a culvert structure, a variable speed structure, a transmission shaft and a driver are/is combined through rotation, extension, pushing and/or pulling of electric, electromagnetic, hydraulic and/or mechanical driving, and through adjustment and change of the direction and/or angle of a single or multiple groups of combination structures, the flight mode of the aircraft is flexibly adjusted through intelligent control and/or manned control, so that multiple schemes such as coaxial take-off and landing are realized.

Lifting system: the aircraft bottom has landing gear and tires for take-off and landing by turning, telescoping, pushing and/or pulling.

And (3) intelligent control: the intelligent control system is characterized by comprising one or more of satellite positioning, airspeed sensing, air inlet flow sensors, current sensors, six-axis sensors, ten-axis sensors, gyroscopes, magnetic compasses, inclination sensors, current sensors, inertia measuring units, acceleration sensors, audio acquisition, audio playing, video acquisition, video playing, ultrasonic sensors, millimeter wave sensors and laser sensors, and is connected with one or more of SOC chips, manned control, AI automatic driving systems, electronic equipment terminals and remote terminals through one or a combination of Bluetooth, wireless network, wireless transmission, wired transmission schemes and the like and controls a novel duct (hub) to drive other components of the aircraft and/or other devices of the aircraft. The function is to collect data through sensors, operate the SOC and give instructions by artificial intelligence, the driver or other electronic devices.

And (3) manned control: and (3) manned control: the manned control of the aircraft is formed by combining one or more of seat with rotatable direction, rotation center control, virtual reality display, lateral direction integrated flight control and non-pilot control with intelligent control. The manual control device has the function of manually controlling the aircraft when the aircraft is manned.

By applying the technical scheme of the invention, the novel duct (hub) driving aircraft comprises: in the wheel mode, the variable blade (1) is fixed on the duct structure (2) or the shell (9), and the shell (9) rotates to drive the tire on the variable blade to rotate through the transmission device or the speed change structure (3); in the flight mode, the variable blade (1) is separated from the duct structure (2) or the shell (9), and the transmission device or the speed change structure (3) directly drives the variable blade (1) to rotate; in some application schemes, a foldable and telescopic variable wing (4) is adapted, a rotating system (5) changes angles and directions of a driving system with a variable blade (1) and other components, a landing gear system for taking off and landing of a landing gear system, and intelligent control and manned control are used for various control modes of an aircraft.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:

fig. 1 shows a schematic view of a part of the structure of a novel ducted (hub) driven aircraft according to the invention;

FIG. 2 shows a partially expanded structural schematic diagram of a novel ducted (hub) driven aircraft according to the present invention;

fig. 3 shows a schematic view of a part of an application example of a novel ducted (hub) driven aircraft according to the invention.

Wherein the above figures include the following reference numerals:

1. a variable blade; 11. the paddle is fixed; 12. blade expansion; 2. a bypass structure; 21. expanding a duct; 3. a speed change structure; 4. a variable wing; 41. a variable flap; 42. a variable tail; 5. a rotating system; 9. a housing.

Detailed Description

It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.

The invention provides a novel duct (hub) driving aircraft, please refer to fig. 1 to 3, comprising:

FIG. 1 is a partial structure of the present invention in one embodiment, a comparison of a wheeled mode and an aircraft mode, wherein a variable blade (1) is fixed on a ducted structure (2) or a shell (9) through a blade fixing (11) in the wheeled mode, and the shell (9) is driven to rotate through a speed reducing mechanism of a speed changing structure (3) to drive a tire on the shell to rotate;

in the flight mode, the blade fixing (11) of the variable blade (1) is unlocked and separated from the duct structure (2) or the shell (9), the variable speed structure (3) is connected through switching, and the variable blade (1) is directly driven to rotate through the transmission device;

FIG. 2 shows a partially expanded structure of the present invention in one embodiment, the ducted expansion (21) is mounted outside the ducted structure (2) or the housing (9), and then the blade expansion (12) increases the diameter of the blade by folding or telescoping;

fig. 3 shows a part of the flying structure of the present invention, which is an embodiment of the present invention, wherein the variable wing (4) of the aircraft is conveniently stored without increasing unnecessary burden in the wheel mode, and can be a part of the upper transno-tail scheme, the part of the outer shell of the aircraft (the flying car) is called as a variable flap (41) by rotating, and can be a part of the flap, the variable tail (42) is stored in the aircraft by folding and telescopic way, and the stable-use tail is opened when the aircraft is switched to the flying mode,

the rotation system (5) can adjust the angle or direction of the driving system to obtain more lifting force or become a coaxial scheme.

In some applications, not shown but landing gear systems are used for landing gear systems for take-off and landing, intelligent control and manned control are used for various modes of maneuvering of the aircraft.

From the above description, it can be seen that the above embodiments of the present invention achieve the following technical effects:

the novel duct (hub) driving aircraft provided by the invention comprises: the variable blades (1) are connected and fixed with the duct structure (2) and are released, and the wheel drive or the paddle drive is switched by switching the speed change structure (3) or driving of other transmission or speed change devices, wherein the variable blades (1) rotate or the shell (9) rotates; in some application schemes, a flexible wing (4) which can be flexibly folded and telescopic is adapted to be used, a rotating system (5) changes angles and directions of a driving system with a variable blade (1) and other components, a landing gear system for taking off and landing of a landing gear system, and intelligent control and manned control are used for various control modes of an aircraft.

It should be noted that the terms "first," "second," and the like in the description and claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that embodiments of the present application described herein may be capable of being practiced otherwise than as specifically illustrated and described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.

Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. Novel duct (wheel hub) drive aircraft, its characterized in that includes: the variable blades (1) are connected and fixed with the duct structure (2) and are released, and the wheel drive or the paddle drive is switched by switching the speed change structure (3) or driving of other transmission or speed change devices, wherein the variable blades (1) rotate or the shell (9) rotates; the landing gear system is used for taking off and landing, and the intelligent control and manned control are used for various control modes of the aircraft.

2. The novel ducted (hub) driven aircraft of claim 1, wherein the variable blades are composed of single or multiple groups of blades and a rotating shaft and/or a hub, wherein the rotating shaft and/or the hub is connected with at least one or a combination of more of a motor, a hub motor, a transmission and a transmission shaft; the blade is automatically or semi-automatically or manually connected by at least one or a combination of the above components of the occluding fixing, the rotating fixing, the mortise and tenon fixing, the drawing and inserting type, the linear stepping motor, the rotating motor and the magnetic device, and the connecting fixing or the decomposing work with the shell and/or the duct structure is adjusted.

3. The novel ducted (hub) driven aircraft of claim 2, wherein the variable blades are connected in combination with at least one or more of the housing, ducted structure, other parts of the invention, and other devices of the aircraft by at least one or more of single or multiple sets of blades, folded blades, and telescoping blades.

4. The novel ducted (hub) driven aircraft of claim 1, wherein the ducted structure takes a shell as a ducted main body structure, and one end and/or the head and tail ends of the shell are/is provided with a curve and/or lip-like structure; and/or a sandwich structure is arranged at the inner side of the shell and is formed by combining one or more than one of a single or a plurality of groups of curve combined structures with tesla valves, tesla-like valves and single or a plurality of groups of curve combined structures; the culvert head and tail ends or one end of the culvert are provided with curved, linear and/or lip-shaped expansion structures and combined structures which are automatically and/or manually opened by at least one or more of buckling, folding and rotating.

5. The novel ducted (hub) driven aircraft of claim 1, wherein the variable speed structure is connected with a motor, an engine or other power devices which are provided with transmission shafts, the variable speed structure is combined into a mode of outputting various rotational speeds and torque through one or more of a speed reducer, a star gear set, clutch switching, a connecting device, a supporting structure and gear switching, and the ducted structure and the variable blades are switched.

6. The novel ducted (hub) driven aircraft according to claim 1, wherein the variable wing is formed by one or more of a front and rear aircraft accommodating interior, an aircraft front side, an aircraft rear side, an aircraft front cover, an aircraft rear cover and an aircraft top by one or more of turning, folding, telescoping and rotating, and the wing, the duck wing, the flap and/or the tail wing are formed by unfolding one or more of the above combinations, the effect is that the folded wing can provide huge lifting energy, the thrust ratio requirement of the driver is reduced, the duck wing and the flap are realized by the rotation of an aircraft shell on a front beam and a rear beam, and the like, better aerodynamic shape and operation space are provided for the aircraft, the tail wing functions can be partially or completely replaced by a reverse scheme on the wing and a duck wing scheme, and the stability of the aircraft is increased.

7. The novel ducted (hub) driven aircraft according to claim 1, wherein the rotating system is configured to flexibly adjust the flight mode of the aircraft by means of one or more of swing arms, tie rods, suspensions, diverters, support arms, and by means of one or more of rotation, telescoping, pushing and/or pulling driven by electric, electromagnetic, hydraulic and/or mechanical, to combine one or more of variable blades, ducted structures, variable speed structures, transmission shafts, drivers, and by means of adjusting, changing the direction and/or angle of the above combined structures of one or more groups, and by means of intelligent control and/or manned control, to implement multiple schemes such as coaxial, vertical take-off and landing.

8. The novel ducted (hub) driven aircraft of claim 1, wherein the landing system has landing gear and tires for take-off and landing at the bottom of the aircraft by rotating, telescoping, pushing and/or pulling.

9. The novel ducted (hub) driven aircraft of claim 1, wherein the intelligent control is provided with one or more of satellite positioning, airspeed sensing, air intake flow sensor, current sensor, six-axis sensor, ten-axis sensor, gyroscope, magnetic compass, tilt sensor, current sensor, inertial measurement unit, acceleration sensor, audio acquisition, audio playback, video acquisition, video playback, ultrasonic sensor, millimeter wave sensor, laser sensor, and the like, and is connected to one or more of SOC chip, manned control, AI autopilot system, electronic equipment terminal, remote terminal, and the like, and controls the novel ducted (hub) driven aircraft other components, and/or aircraft other devices, by one or more of bluetooth, wireless network, wireless transmission, wired transmission scheme, and the like.

10. The novel ducted (hub) driven aircraft of claim 1, wherein the manned control: the manned control of the aircraft is formed by combining one or more of seat with rotatable direction, rotation center control, virtual reality display, lateral direction integrated flight control and non-pilot control with intelligent control.