CN219115711U

CN219115711U - Single aircraft capable of taking off and landing vertically for long endurance

Info

Publication number: CN219115711U
Application number: CN202223332800.2U
Authority: CN
Inventors: 胡振宇
Original assignee: Lingke Aerospace Technology Jiangyin Co ltd
Current assignee: Lingke Aerospace Technology Jiangyin Co ltd
Priority date: 2022-12-13
Filing date: 2022-12-13
Publication date: 2023-06-02
Anticipated expiration: 2032-12-13

Abstract

The utility model belongs to the technical field of aircrafts, in particular to a vertically taking-off and landing long-endurance single-person aircraft, which aims at the problems that the existing vertically taking-off and landing single-person aircraft cannot realize long-distance flat flight, but can fly horizontally, and the like, and the single-person aircraft has the advantages of low speed, short range, incapability of taking off and landing vertically and the like.

Description

Single aircraft capable of taking off and landing vertically for long endurance

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a vertical take-off and landing long-endurance single-person aircraft.

Background

Free flying like a bird is a dream of humans for thousands of years.

The existing vertical take-off and landing aircrafts comprise an overhead coaxial double-rotor scheme, an overhead single-rotor scheme, a jet backpack, rocket braces and the like, and the common advantages of the schemes are vertical take-off and landing, but the common main disadvantages are that no fixed wing exists, long-distance flat flight cannot be realized, the endurance and the range are very short, the speed is low, the flight cost is high, the operation is complex, and the safety is poor.

The existing light single-person aircrafts capable of flying horizontally, such as a power paraglider, a power delta wing aircraft and the like, can realize horizontal flying, but have low speed, short range and no vertical take-off and landing.

In order to solve the problems, the utility model provides a single aircraft with vertical take-off and landing and long endurance.

Disclosure of Invention

The utility model provides a single-person aircraft capable of taking off and landing vertically for long endurance, which solves the defects that the single-person aircraft capable of taking off and landing vertically in the prior art cannot realize long-distance flat flight, but can fly horizontally, and the like, and has the advantages of low speed, short range, incapability of taking off and landing vertically.

The utility model provides the following technical scheme:

a vertical take-off and landing long endurance single person aircraft comprising:

the two fixed wing main bodies are rotatably connected with a rotating shaft on one side, away from each other, of each fixed wing main body, one end of the rotating shaft is fixedly connected with a rotating disc, one side of the rotating disc is fixedly provided with an attitude control engine, one side of each fixed wing main body is fixedly provided with two fixed engines, the outer walls of the two fixed engines are provided with the same protective cover, the protective cover is fixedly connected with the fixed wing main bodies, the two fixed wing main bodies are fixedly connected with the same mounting box, and the inside of the mounting box is provided with a flight comprehensive control console computer;

a support assembly for providing support to the pilot's leg.

In one possible design, the support assembly comprises a fixed sliding seat fixedly arranged on one side of the two fixed wing main bodies and an electric push rod fixedly embedded in the installation box, the two fixed sliding seats are internally and slidably connected with the same support frame, a connecting rod is fixedly connected in the support frame, and one end of a piston rod of the electric push rod is fixedly connected with the top of the connecting rod.

In one possible design, the two fixed wing bodies are provided with a conformal power supply system inside, and the conformal power supply system is fixedly connected with one end of the rotating shaft through a motor.

In one possible design, one side of the mounting box is provided with an escape umbrella bag.

In one possible design, two sides that the attitude control engine kept away from each other are all provided with the second LED lamp, the side of fixed wing main part all is provided with several first LED lamp.

In one possible design, the mounting box is provided with cross-fastened safety belts, which are fixedly connected by means of a buckle.

In one possible design, the flight integrated console computer is electrically connected to both of the two conformal power supply systems, and both of the conformal power supply systems are electrically connected to the plurality of attitude control engines and the stationary engine.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the utility model as claimed.

According to the utility model, the single aircraft can realize vertical lifting, and a system scheme with a thrust-weight ratio larger than that of the fixed engines is realized through a plurality of engine attitude control engines, so that vertical lifting and vertical landing in a take-off and landing stage are realized under the condition of not depending on external force and auxiliary facilities;

according to the utility model, the single aircraft can acquire lift force through arranging the fixed wings, physical force is saved through arranging the supporting frames, long-distance sailing of the aircraft can be realized, when the aircraft is converted into a horizontal flight attitude, the lifting force is generated by the main body of the fixed wings through the lifting of the flight speed of the aircraft so as to offset gravity loss, and at the stage, the oil consumption control can be realized through reducing the thrust or closing a plurality of engine attitude control engines or the fixed engines, so that the design goal of long-term sailing is realized; in the flight process, the length of the supporting frame can be adjusted through the electric push rod, so that a pilot can obtain support for legs, and the physical consumption in the flight process is reduced;

according to the utility model, the single aircraft can perform gesture switching between vertical lifting and horizontal flight, and after vertical take-off, the gesture engine can be horizontally turned by vertical steering through swinging deflection of the gesture engine to generate transverse speed, so that the tilting of the aircraft and a pilot is realized, and finally, the gesture switching from vertical hovering to horizontal flight is achieved; when a pilot needs to switch from horizontal flight to vertical hovering or vertical landing, the swing deflection of the attitude control engine can be used for enabling the attitude control engine to be turned from horizontal to vertical, so that the transverse speed is reduced until the horizontal speed is zero, and at the moment, the hovering or landing under the vertical state is realized through closed-loop program control of a flight comprehensive control console computer;

according to the utility model, the single aircraft can realize vertical lifting and horizontal flight, can change in two postures, is also provided with the fixed wing and the support frame, can realize long-distance navigation, is also provided with a plurality of LED lamps, and can play a role in marking and reminding for the aircraft at night.

Drawings

Fig. 1 is a schematic three-dimensional structure of a single-person aircraft for vertical take-off and landing long endurance according to an embodiment of the present utility model;

fig. 2 is a schematic rear view of a three-dimensional structure of a single-person aircraft with vertical take-off and landing long endurance according to an embodiment of the present utility model;

fig. 3 is an enlarged schematic view of a attitude control engine of a single aircraft with a vertical take-off and landing long endurance according to an embodiment of the present utility model.

Reference numerals:

1. a fixed wing body; 2. a gesture control engine; 3. fixing the engine; 4. a protective cover; 5. a conformal power supply system; 6. an escape umbrella bag; 7. a flight integrated console computer; 8. a flight safety belt; 9. a mounting box; 10. fixing the sliding seat; 11. a support frame; 12. a connecting rod; 13. an electric push rod; 14. a rotating shaft; 15. a turntable; 16. a first LED lamp; 17. and a second LED lamp.

Detailed Description

Embodiments of the present utility model will be described below with reference to the accompanying drawings in the embodiments of the present utility model.

In describing embodiments of the present utility model, it should be noted that, unless explicitly stated and limited otherwise, the terms "coupled" and "mounted" should be interpreted broadly, and for example, "coupled" may or may not be detachably coupled; may be directly connected or indirectly connected through an intermediate medium. In addition, "communication" may be direct communication or may be indirect communication through an intermediary. Wherein, "fixed" means that the relative positional relationship is not changed after being connected to each other. References to orientation terms, such as "inner", "outer", "top", "bottom", etc., in the embodiments of the present utility model are merely to refer to the orientation of the drawings and, therefore, the use of orientation terms is intended to better and more clearly illustrate and understand the embodiments of the present utility model, rather than to indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be construed as limiting the embodiments of the present utility model.

In embodiments of the present utility model, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature.

In the embodiment of the present utility model, "and/or" is merely an association relationship describing an association object, and indicates that three relationships may exist, for example, a and/or B may indicate: a exists alone, A and B exist together, and B exists alone. In addition, the character "/" herein generally indicates that the front and rear associated objects are an "or" relationship.

Reference in the specification to "one embodiment" or "some embodiments" or the like means that a particular feature, structure, or characteristic described in connection with the embodiment is included in one or more embodiments of the utility model. Thus, appearances of the phrases "in one embodiment," "in some embodiments," "in other embodiments," and the like in the specification are not necessarily all referring to the same embodiment, but mean "one or more but not all embodiments" unless expressly specified otherwise. The terms "comprising," "including," "having," and variations thereof mean "including but not limited to," unless expressly specified otherwise.

Example 1

Referring to fig. 1-3, a vertical take-off and landing long endurance single person aircraft comprising:

the utility model provides a three-dimensional aircraft engine attitude control engine, including, but not limited to, two fixed wing main bodies 1, one side that two fixed wing main bodies 1 keep away from each other is all rotated and is connected with pivot 14, the one end fixedly connected with carousel 15 of pivot 14, one side fixed mounting of carousel 15 has attitude control engine 2, one side of two fixed wing main bodies 1 is all fixed mounting has two fixed engines 3, the outer wall of two fixed engines 3 is provided with same safety cover 4, safety cover 4 and fixed wing main body 1 fixed connection, the same mounting box 9 of fixedly connected with between two fixed wing main bodies 1, the inside of mounting box 9 is provided with flight comprehensive control platform computer 7, alternatively, this single aircraft engine attitude control engine 2, fixed engine 3 can be the aeroengine of different types, including: turbojet engines, turbofan engines, electric ducted fan engines, and the like;

and the support assembly is used for providing support for the legs of the pilot.

The technical scheme can realize a single aircraft capable of sailing for a long distance and lifting vertically.

Referring to fig. 2, in the present embodiment, the supporting component includes a fixed slide 10 fixedly mounted on one side of two fixed wing bodies 1 and an electric push rod 13 fixedly embedded in the installation box 9, the two fixed slide 10 are slidably connected with the same supporting frame 11, a connecting rod 12 is fixedly connected in the supporting frame 11, and one end of a piston rod of the electric push rod 13 is fixedly connected with the top of the connecting rod 12.

The technical scheme can enable the legs of the pilot to have supporting points in the flight process, and physical strength is saved.

Example 2

the two fixed wing main bodies 1 are rotatably connected with a rotating shaft 14 at one side, which is far away from each other, of the two fixed wing main bodies 1, one end of the rotating shaft 14 is fixedly connected with a rotary table 15, one side of the rotary table 15 is fixedly provided with an attitude control engine 2, one side of the two fixed wing main bodies 1 is fixedly provided with two fixed engines 3, the outer walls of the two fixed engines 3 are provided with the same protective cover 4, the protective cover 4 is fixedly connected with the fixed wing main bodies 1, the two fixed wing main bodies 1 are fixedly connected with the same installation box 9, and the inside of the installation box 9 is provided with a flying comprehensive control console computer 7;

Referring to fig. 1, in the present embodiment, the two fixed wing bodies 1 are provided with a conformal power supply system 5 inside, and optionally, the conformal power supply system 5 may be changed according to different power types, including but not limited to: conformal oil tank, conformal group battery etc. conformal power supply system 5 passes through motor and the one end fixed connection of pivot 14.

The technical scheme can provide power for the aircraft and can realize the change of the direction of the attitude control engine 2.

Referring to fig. 1, in the present embodiment, one side of the installation case 9 is provided with an escape parachute kit 6, and alternatively, the escape parachute kit 6 may be a parachute, a paraglider, an inflatable parachute, or any one of parachute kit capable of achieving a speed reduction and a smooth landing by manufacturing air resistance.

The technical scheme can enable the pilot to have escape means when the aircraft fails.

Referring to fig. 1, in the present embodiment, two attitude control engines 2 are provided with second LED lamps 17 on the sides far away from each other, and a plurality of first LED lamps 16 are provided on the sides of the fixed wing main body 1.

The technical scheme can realize the light marking of the outline of the aircraft, and plays a role in prompting vigilance.

Referring to fig. 1, in this embodiment, a cross-fixed safety belt 8 is provided on a mounting box 9, and the safety belt 8 is fixedly connected by a buckle.

The technical scheme can fix the pilot and the aircraft together, and ensure the safety of the pilot.

Referring to fig. 1 and 2, in the present embodiment, the flight integrated console computer 7 is electrically connected to two conformal power supply systems 5, and the two conformal power supply systems 5 are electrically connected to a plurality of gesture control engines 2 and fixed engines 3.

The technical scheme can enable the flight comprehensive control console computer 7 to realize flight control of the aircraft.

However, as is well known to those skilled in the art, the working principles and wiring methods of the flight integrated console computer and the engine are common, and all of them are conventional means or common general knowledge, and will not be described in detail herein, and those skilled in the art can perform any optional matching according to their needs or convenience.

The working principle and the using flow of the technical scheme are as follows: the single aircraft is connected with the pilot and relatively fixed through a flight safety belt 8 (before use, the escape parachute bag 6 is fixed on the pilot);

a take-off and landing stage: the thrust-weight ratio of the aircraft is larger than 1 through the plurality of engines including the attitude control engine 2 and the fixed engine 3, so that the vertical lift-off and vertical landing in the take-off and landing stage are realized under the condition of not depending on external force and auxiliary facilities;

and (3) flight stage: after vertical take-off, the attitude control engine 2 can be deflected by swinging of the attitude control engine 2 to generate transverse speed from vertical steering to horizontal, so that tilting of an aircraft and a pilot is realized, and finally, attitude conversion from vertical hovering to horizontal flight is achieved; in the flight process, the rolling control of the aircraft and the pilot can be realized through the differential swing of the attitude control engine 2, the horizontal/vertical attitude switching is realized through the homodromous swing of the attitude control engine 2, and the pitching and yaw control in the horizontal flight process is realized through the body inclination of the pilot;

posture switching: when a pilot needs to switch from horizontal flight to vertical hovering or vertical landing, the swing deflection of the attitude control engine 2 can be used for enabling the attitude control engine 2 to be turned from horizontal to vertical, so that the transverse speed is reduced until the horizontal speed is zero, and at the moment, the hovering or landing under the vertical state is realized through the closed-loop program control of the flight comprehensive control console computer 7;

in the flight process, the length of the supporting frame 11 can be adjusted through the electric push rod 13, so that a pilot can obtain support for legs, and the physical consumption in the flight process is reduced;

through installing a plurality of LED lamps at the side of aircraft, can indicate the place and the profile of aircraft, even also can be convenient for ground observation at night.

The present utility model is not limited to the above embodiments, and any person skilled in the art can easily think about the changes or substitutions within the technical scope of the present utility model, and the changes or substitutions are intended to be covered by the scope of the present utility model; embodiments of the utility model and features of the embodiments may be combined with each other without conflict. Therefore, the protection scope of the utility model is subject to the protection scope of the claims.

Claims

1. A vertical take-off and landing long endurance single person aircraft, comprising:

the novel aircraft comprises two fixed wing main bodies (1), wherein one sides, away from each other, of the fixed wing main bodies (1) are respectively and rotatably connected with a rotating shaft (14), one end of each rotating shaft (14) is fixedly connected with a rotating disc (15), one side of each rotating disc (15) is fixedly provided with an attitude control engine (2), one side of each fixed wing main body (1) is respectively and fixedly provided with two fixed engines (3), the outer walls of the two fixed engines (3) are respectively provided with the same protective cover (4), the protective covers (4) are fixedly connected with the fixed wing main bodies (1), the two fixed wing main bodies (1) are fixedly connected with the same installation box (9), and the inside of each installation box (9) is provided with a flying comprehensive control console computer (7);

a support assembly for providing support to the pilot's leg.

2. The single aircraft for vertical take-off and landing as claimed in claim 1, wherein the supporting assembly comprises a fixed sliding seat (10) fixedly installed on one side of the two fixed wing main bodies (1) and an electric push rod (13) fixedly embedded in the installation box (9), the two fixed sliding seat (10) are slidably connected with the same supporting frame (11), a connecting rod (12) is fixedly connected in the supporting frame (11), and one end of a piston rod of the electric push rod (13) is fixedly connected with the top of the connecting rod (12).

3. A single-person aircraft for vertical take-off and landing long voyage according to claim 1, wherein the inside of both fixed wing bodies (1) is provided with a conformal power supply system (5), and the conformal power supply system (5) is fixedly connected with one end of a rotating shaft (14) through a motor.

4. A vertically taking off and landing long endurance single person aircraft as claimed in claim 1, wherein one side of the installation box (9) is provided with an escape parachute bag (6).

5. The single aircraft for vertical take-off and landing long endurance according to claim 1, wherein the two attitude control engines (2) are provided with second LED lamps (17) on the sides far away from each other, and the side surfaces of the fixed wing main body (1) are provided with a plurality of first LED lamps (16).

6. A vertically taking off and landing long endurance single person aircraft as claimed in claim 1, wherein the mounting box (9) is provided with cross-fixed flight belts (8), the flight belts (8) being fixedly connected by a buckle.

7. The single-person aircraft for vertical take-off and landing long voyage according to claim 1, wherein the flight comprehensive control console computer (7) is electrically connected with two conformal power supply systems (5), and the two conformal power supply systems (5) are electrically connected with a plurality of attitude control engines (2) and fixed engines (3).