CN113942647A

CN113942647A - Sea (water) air two-purpose dish-shaped aircraft

Info

Publication number: CN113942647A
Application number: CN202010709341.1A
Authority: CN
Inventors: 不公告发明人
Original assignee: Tai Yanhong
Current assignee: Tai Yanhong
Priority date: 2020-07-17
Filing date: 2020-07-17
Publication date: 2022-01-18

Abstract

The invention relates to a sea (water) air dual-purpose disc-shaped (oblate disc-shaped) aircraft, belonging to the field of aerospace. With the prior known engine, the engine and the tail nozzle can extend and turn according to the required angle, the middle part is a disc cabin, and the periphery is a disc shell. Has the functions and the operation characteristics of a fixed wing and a gyroplane. The middle part is thicker than the periphery in appearance. The pressure difference is formed between the upper part and the lower part of the machine body as power. The disc shell and the disc cabin have a sealing function, and the opening and the sealing are realized under the support of the telescopic system. And a bidirectional magnetic suspension balance system is selected and matched to ensure the overall balance. The aircraft can vertically take off or land on the ground and the water surface and rotate left and right in situ. The bottom is provided with a retractable air bag which can suspend and dive in water. The helicopter can be replaced under severe meteorological conditions, and no harm is caused by the helicopter. The cockpit is arranged in the dish cabin, and the top of the cockpit is provided with a parachute, and the cockpit has a manual mode and an automatic mode. No airports and runways are required. The appearance structure of the device can be used as a space detector, a space capsule, a speed reduction capsule and a landing capsule.

Description

Sea (water) air two-purpose dish-shaped aircraft

Technical Field

The invention belongs to the field of aerospace, and relates to a novel dish-shaped aircraft which is characterized by being widely applied to space, air, water surface and underwater, strong in wind resistance, strong in regional adaptability and wide in application range.

Background

The disk-shaped aircraft has great potential market and application value in civil aviation and military aviation.

The existing dish-shaped aircraft is good in design and product, but not in accordance with public standards, far away from ideal, poor in practical effect, narrow in application range, only limited to air use, only used under visual flight rules, incapable of being used under severe meteorological conditions and low in safety.

The invention relates to a novel dish-shaped aircraft, which has a unique aerodynamic shape, meets the requirements of air, sky and sea, meets the expectation of the public and is much better than the existing aircraft under extreme weather conditions.

Integration, set fixed wing and helicopter function and operation mode, current aircraft uses more in a flexible way relatively, and the range of application is wider, compares other aircraft and can adapt to abominable meteorological condition more, and complicated geographical environment, factor of safety is higher.

Disclosure of Invention

The invention aims to provide a sea (water) air dual-purpose dish-shaped aircraft which can overcome severe meteorological conditions and natural conditions better than the existing aircraft. A disk-shaped aircraft is provided with an annular device which is divided into an inner core body and an outer shell. The inner core body and the outer shell have two working states of opening and closing. The aircraft is provided with an oblate disk body or a spherical segment-shaped engine body or an arched engine body, and has a convex middle part or a convex top part according to the requirements of functions and environment. The aircraft can move vertically or horizontally and turn left and right in situ.

The parachute device or system is mainly provided with a top parachute device or system, the using mode is commonly two modes, namely a manual mode and an automatic mode, and the two modes can be switched, changed and set freely and quickly.

The shell can be a bidirectional magnetic suspension balancing device and a system, and plays a role in balancing the machine body.

The aircraft of the invention is provided with a sealing device and a system, has a floating function and a corresponding device or system, and also has equipment, devices and systems which are required to be equipped and assembled by other aircrafts, fixed wings and helicopters, and other tools, devices, equipment and systems required by aviation flight, space application, space use and interstellar exploration, and is provided with software required by the equipment and the devices.

Compared with the prior art, the invention has the advantages that:

1. the aircraft can vertically take off or land on the ground, and can hover in the air and rotate left and right in situ in the air.

2. The aircraft has a sealing function, can vertically take off or land on the water surface by matching with the retractable air bags. Can float on the water surface, suspend in the water, submerge in the water and rotate left and right in situ in the water.

4. The aircraft can be used as a space capsule, a speed reduction capsule, a landing capsule and a space detector.

5. The aircraft can replace a helicopter, can be invisible, can be used as an amphibious tourism and sightseeing aircraft, and has no harm brought by the helicopter.

6. The aircraft can be used as a flying car and a seawater-air multipurpose aircraft.

7. The aircraft of the present invention does not require airports and runways.

8. The inner sides of the outer shell and the inner core body of the aircraft are concave surfaces, the outer sides of the outer shell and the inner core body are not provided with vertical surfaces, and radar reflection is small.

Drawings

FIG. 1 is a sectional view of the principal side structure of the present invention.

FIG. 2 is a side sectional view of the shell and core combination in an open position.

FIG. 3 is a side sectional view of the closed configuration of the junction of the outer shell and the inner core of the present invention.

The main parts in the figures are numbered as follows:

1-core

2-funnel-shaped outer shell

3-engine

4-cockpit

5-speed reducing umbrella cabin

6-fluid inlet/outlet-generating lift force, and the joint of the inner core and the shell switch

7-fluid out/in-fluid ejection thrust

8-fluid

9. Retractable air bag

10. Bidirectional magnetic suspension device

Detailed Description

The invention will be further illustrated with reference to the following example in connection with fig. 2, without the inventive content being restricted to the scope described.

Referring to fig. 2, to achieve the above objects, the main structure of the present invention mainly comprises,

1-core

2-funnel-shaped outer shell

3-engine

4-cockpit

5-speed reducing umbrella cabin

7-fluid out/in-fluid ejection thrust

8-fluid

9. Retractable air bag

10. Bidirectional magnetic suspension device

The outer shell is a funnel-shaped outer shell and is designed outside the inner core body, a channel is arranged between the outer shell and the inner core body in an open state, the inner core body is a disc-shaped or oblate disc body or a segment-shaped body or an arched body, the upper edge of the outer shell can be lapped on the upper surface of the inner core, the outer shell is lapped on the inner core part and is bent towards the inner core, and the bending angle of the outer shell is consistent with that of the upper surface of the inner core.

When interior nuclear body and shell closure state, the kernel upper surface is hugged closely to the shell upper edge, reaches airtight standard, has the cavity at this moment between interior nuclear body and shell, and the air storage has certain buoyancy in the cavity, can float at the surface of water.

Under the control of the telescopic system, the opening and closing of the joint between the shell and the upper part of the inner core can be realized.

Firstly, under the state that the joint of the shell and the inner core body is open, fluid enters the power equipment from the top through the channel cavity, and flows out from the bottom, the fluid passes through the upper surface of the inner core before entering the channel cavity to generate lift force, and is accelerated by the power system to generate thrust force, and the airflow is sprayed out, so that the single airflow does work, and the vertical take-off and landing of the fluid in the air and on the land are realized.

The angle of the power nozzle is changed, the engine extends out, and the original site left and right steering, front and back left and right movement are realized.

The combination of the shell and the inner core body is in a closed state, partial air is arranged in the cavity channel, and the invention can float on the water surface, suspend in the water and submerge under the water by adding the retractable air bag. The power output angle and direction of the terminal are changed, and the left-right steering, the front-back left-right movement and the on-site left-right steering are realized.

The bidirectional magnetic suspension device is internally provided with two magnetic suspension tracks, and the two magnetic suspension bodies rotate in opposite directions and can keep the balance of the machine body in the air and in water.

Finally, the description is as follows:

parts not specifically described in the above description are prior art or are realizable by prior art. All equivalent changes and modifications made according to the content of the claims of the present invention should be regarded as the technical scope of the present invention.

The embodiments of the invention shown in the drawings and described in accordance with the drawings are exemplary only, and the invention is not limited to these embodiments.

It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the structures and/or processing steps closely related to the scheme according to the present invention are shown in the drawings, and other details not closely related to the present invention are omitted.

The foregoing is directed to embodiments of the present application and it is noted that numerous modifications and adaptations may be made by those skilled in the art without departing from the principles of the present application and are intended to be within the scope of the present application.

The technical solutions of the present invention are clearly described with reference to the accompanying drawings, and it is obvious that the described embodiments are some embodiments of the present invention, and all other embodiments obtained by those skilled in the art without any inventive work belong to the protection scope of the present invention.

The present invention is illustrated in relation to the position and function of various systems, devices or components with respect to each other for ease of description and simplicity of description, and is not necessarily intended to have a particular orientation, be it configured and operable in a particular orientation and should not be construed as limiting the present invention.

The above description is only for the patent of the present invention, and there are unlimited specific structures and designs objectively, and not therefore the scope of the present invention is limited, and all equivalent structures or equivalent flow transformations made by using the description and drawings of the present invention, or the equivalent working principle, or directly or indirectly applied to other related technical fields are included in the scope of the present invention.

Claims

1. A disk-shaped aircraft comprises an inner core, a funnel-shaped outer shell, a power system, an electronic system, a safety system, a telescopic system and a balance system.

2. A dish-shaped aircraft according to claim 1 wherein said aircraft has a funnel-shaped outer skin.

3. The disc-shaped aircraft according to claim 1, wherein said aircraft core is provided with no outer shell at the upper part and a funnel-shaped outer shell at the lower part.

4. The disc-shaped aircraft according to claim 1, wherein the aircraft body, the aircraft core and the aircraft funnel-shaped outer shell are thicker in the middle than in the periphery.

5. A dish-shaped aircraft according to claim 1, wherein said inner core and said outer shell are operable in two modes, open and closed.

6. The disc-shaped aircraft of claim 1 wherein said open and closed positions are limited to the junction of the inner core and outer skin of the disc-shaped aircraft.

7. The disc-shaped aircraft according to claim 1, wherein the funnel-shaped outer shell of the aircraft has a portion capable of overlapping the upper half edge of the inner core, and is in a parallel state with the upper half of the inner core in a radian consistent with the upper half of the inner core.

8. A dish-shaped aircraft as claimed in claim 1 wherein there is space between said aircraft core and said outer skin.

9. The disc-shaped aircraft according to claim 1, wherein the inner core and the outer shell have a channel therebetween in an open state, the channel being in communication with each other in an up-down direction, the channel being curved.

10. A dish-shaped aircraft according to claim 1 wherein said aircraft has a space, chamber between the core and the outer skin in the closed position.

11. The dish-shaped aircraft of claim 1, wherein said inner core and said outer shell are open for ingress and egress of fluid from the upper periphery during normal flight.

12. The disc-shaped aircraft according to claim 1, wherein said inner core and said outer skin are open such that at stall the aircraft fluid enters under the funnel-shaped outer skin, passes over the rim and exits the upper surface of the inner core.

13. The dish shaped aircraft of claim 1 wherein said fluid generates lift in both forward and reverse directions across the upper surface of the inner core.

14. A dish-shaped aircraft according to claim 1 wherein said fluid produces thrust when exiting the aircraft from below.

15. A saucer shaped aircraft as claimed in claim 1, wherein a machine parachute is provided on top of the core.

16. The disc-shaped aircraft as claimed in claim 1, wherein the lower portion of the funnel-shaped outer shell is provided with a retractable air bag.

17. A dish-shaped aircraft as claimed in claim 1, configured and equipped with the devices, apparatuses and systems available in existing aircraft.

18. A dish aircraft according to claim 1, wherein said fluid comprises fresh water, sea water, air.

19. A saucer shaped aircraft as claimed in claim 1, provided with bidirectional magnetic levitation balancing means, devices.

20. A dish aircraft as claimed in claim 1, wherein said dish aircraft is adapted for use with a coaxial contra-rotating engine.