Sea (water) and air dual-purpose disc-shaped aircraft

Abstract

The present invention is a circular disc-shaped (flat disc-shaped) dual-purpose sea (water) and air aircraft belonging to the field of aerospace. It uses an existing known engine, and the engine and tail nozzle can be extended and turned at the required angle. The middle part is a disc cabin, and the outer part is a disc shell. It has the functions and operating characteristics of both fixed-wing and rotary-wing aircraft. In appearance, the middle part is thicker than the surrounding area. A pressure difference is formed between the upper and lower parts of the fuselage as power. There is a sealing function between the disc shell and the disc cabin, and opening and sealing are achieved with the support of a telescopic system. An optional two-way magnetic suspension balance system is provided to ensure overall balance. The aircraft can take off or land vertically on the ground or water surface, and rotate left and right on the spot. There is a retractable airbag at the bottom, which can float and dive in water. It can replace helicopters in severe weather conditions without any incidental damage from helicopters. The cockpit is set in the disc cabin, and a parachute is set on the top, with manual and automatic modes. No airport or runway is required. Its appearance and structural characteristics can be used as a space probe, space capsule, deceleration cabin, and landing cabin.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace and relates to a novel disc-shaped aircraft, which is characterized by being widely applicable to space, air, water surface and underwater, having strong wind resistance, strong regional adaptability and a wide range of applications. Background Art

[0002] Disc-shaped aircraft have huge potential market and application value in both civil aviation and military aviation.

[0003] The existing disc-shaped aircraft designs and products have good ideas, but they do not meet the public standards and are far from ideal. They have poor practical effects and a narrow range of applications. They are limited to air use and can only be used under visual flight rules. They cannot be used in severe weather conditions and have low safety.

[0004] A new type of disc-shaped aircraft has been invented. Its unique aerodynamic shape meets the needs of air, space and sea, meets public expectations, and is much better than existing aircraft in extreme weather conditions.

[0005] It integrates and combines the functions and operation methods of fixed-wing and helicopters. Compared with existing aircraft, it is more flexible to use and has a wider range of applications. Compared with other aircraft, it can better adapt to adverse weather conditions and complex geographical environments and has a higher safety factor. Summary of the Invention

[0006] The present invention aims to provide a dual-purpose saucer-shaped aircraft for sea (water) and air that can better overcome adverse weather conditions and natural conditions than existing aircraft. A circular saucer-shaped aircraft has an annular device and is divided into an inner core and an outer shell. The inner core and the outer shell have two working states: open and closed. It has an oblate disc body, a spherical body, or an arched body. Depending on the function and environmental requirements, the appearance may be convex in the middle or convex at the top. The aircraft of the present invention is equipped with one or more engines, and multiple engines can be added as needed. The engines and engine nozzles can be turned and extended at the required angles to control the flight attitude. The aircraft of the present invention can move vertically or horizontally, and turn left and right on the spot.

[0007] There are mainly top parachute devices or systems, and there are two common ways of use, manual mode and automatic mode, and the two modes can be switched, changed and set quickly and at will.

[0008] The outer shell can be equipped with a bidirectional magnetic suspension balance device and system to balance the body.

[0009] The aircraft of the present invention has sealed devices and systems, floating functions and corresponding devices or systems, as well as equipment, devices and systems that other aircraft, fixed-wing aircraft and helicopters should have and be equipped with, and other tools, devices, equipment, instruments and systems required for aviation flight, space applications, space use and interstellar exploration, and are equipped with the required software.

[0010] Compared with the prior art, the present invention has the following advantages:

[0011] 1. The aircraft of the present invention can take off or land vertically on the ground, hover in the air, and rotate left and right in place in the air.

[0012] 2. The aircraft of the present invention has a sealed function and is equipped with a retractable airbag, which allows it to take off or land vertically on the water surface. It can float on the water surface, suspend in the water, dive in the water, and rotate left and right in place in the water.

[0013] 4. The aircraft of the present invention can be used as a space capsule, a deceleration cabin, a landing cabin, and a space probe.

[0014] 5. The aircraft of the present invention can replace or substitute for helicopters, is invisible, and can be used as an amphibious tourism aircraft without the collateral damage of helicopters.

[0015] 6. The aircraft of the present invention can be used as a flying car and a multi-purpose aircraft for sea, air and sea.

[0016] 7. The aircraft of the present invention does not require an airport or a runway.

[0017] 8. The inner sides of the outer shell and the inner core of the aircraft of the present invention are concave, and the outer sides have no vertical surfaces, so the radar reflection is small. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a sectional view of the main side structure of the present invention.

[0019] Figure 2 This is a side structural cross-sectional view of the junction between the outer shell and the inner core of the present invention in an open state.

[0020] Figure 3 It is a side structural cross-sectional view of the closed state of the junction between the outer shell and the inner core of the present invention.

[0021] The main parts in the figure are marked as follows:

[0022] 1- Kernel

[0023] 2-Funnel-shaped shell

[0024] 3-Engine

[0025] 4-Cockpit

[0026] 5-Deceleration parachute cabin

[0027] 6- Fluid inlet / outlet - generates lift, where the core and shell switch meet

[0028] 7-Fluid inlet / outlet-fluid ejection thrust

[0029] 8-Fluid

[0030] 9. Retractable airbag

[0031] 10. Bidirectional magnetic levitation device DETAILED DESCRIPTION

[0032] The following embodiments will be combined with the attached Figure 2 The present invention is further described, but the content of the present invention is not limited to the scope of the description.

[0033] See also Figure 2 As shown, in order to achieve the above purpose, the main structure of the present invention mainly includes:

[0034] 1- Kernel

[0035] 2-Funnel-shaped shell

[0036] 3-Engine

[0037] 4-Cockpit

[0038] 5-Deceleration parachute cabin

[0039] 6- Fluid inlet / outlet - generates lift, where the core and shell switch meet

[0040] 7-Fluid inlet / outlet-fluid ejection thrust

[0041] 8-Fluid

[0042] 9. Retractable airbag

[0043] 10. Bidirectional magnetic levitation device

[0044] The outer shell is a funnel-shaped shell, which is designed outside the inner core. When in the open state, there is a channel between the outer shell and the inner core. The inner core is a disc-shaped or oblate disk or a spherical body or an arched body. The upper edge of the outer shell can be placed on the upper surface of the inner core, and the part of the outer shell placed on the inner core is bent toward the inner core, and its bending angle tends to be consistent with the upper surface of the inner core.

[0045] When the inner core and the outer shell are in a closed state, the upper edge of the outer shell is in close contact with the upper surface of the inner core, meeting the airtight standard. At this time, there is a chamber between the inner core and the outer shell. The chamber stores air and has a certain buoyancy, allowing it to float on the water.

[0046] Under the control of the telescopic system, the junction between the outer shell and the upper part of the inner core can be opened and closed.

[0047] First, when the joint between the outer shell and the inner core is in an open state, the fluid enters the power equipment from the top through the channel chamber and exits from the bottom. Before entering the channel chamber, the fluid passes through the upper surface of the inner core, generating lift. After being accelerated by the power system, thrust is generated, and the air flow is ejected. The work of a single air flow is completed, realizing its vertical take-off and landing in the air and on land.

[0048] By changing the angle of the power nozzle and extending the engine, the vehicle can turn left and right on the spot and move forward, backward, left and right.

[0049] The outer shell and the inner core are in a closed state, with some air in the chamber. Combined with the retractable airbag, the invention can float on the water surface, suspend in the water, and dive underwater. By changing the terminal power output angle and direction, it can achieve in-situ left and right steering, forward and backward, and left and right movement.

[0050] The bidirectional magnetic levitation device has two magnetic levitation tracks inside, with bidirectional magnetic suspension bodies on the tracks. The magnetic suspension bodies rotate in relative directions and can maintain the balance of the body in the air and in water.

[0051] Finally, the following points should be noted:

[0052] All parts not specifically described in the above description are prior art or can be achieved by prior art. All equivalent changes and modifications made according to the content of the patent application of the present invention should be regarded as the technical scope of the present invention.

[0053] The embodiments of the invention shown in the drawings and described with reference to the drawings are merely exemplary and the invention is not limited to these embodiments.

[0054] It should also be noted that, in order to avoid obscuring the present invention due to unnecessary details, only structures and / or processing steps closely related to the present invention are shown in the accompanying drawings, while other details that are not closely related to the present invention are omitted.

[0055] The above is only a specific implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

[0056] The technical solution of the present invention is clearly described in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention. All other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0057] The positional relationships and functions of the various systems, devices or components shown in the present invention are only for the convenience of describing the present invention and simplifying the description. They do not necessarily have to have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as limiting the present invention.

[0058] The above is only a description of the patent of this invention. Objectively, there are infinite specific structures and designs, but this does not limit the patent scope of this invention. Any equivalent structure or equivalent process transformation, or equivalent working principle made by using the description and illustrations of this invention, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of this invention.

Claims

1. A disc-shaped aircraft comprising a core and a funnel-shaped outer shell, a power system, an electronic system, a safety system, a telescopic system, and a balancing system; The aircraft has a funnel-shaped shell, the upper part of the aircraft core has no shell, and the lower part has the funnel-shaped shell; The inner core and the funnel-shaped outer shell have two working states, open and closed, and the opening and closing of the junction between the outer shell and the upper part of the inner core are realized under the control of the telescopic system; The funnel-shaped outer shell of the aircraft can partially rest on the edge of the upper half of the inner core and has the same curvature as the upper half of the inner core and is in a parallel state; There is a space between the core and the outer shell of the aircraft; There is a channel between the core and the shell of the aircraft when in an open state, communicating with each other from top to bottom, and the channel is arc-shaped; When the aircraft is in a closed state, there is a chamber between the inner core and the outer shell; When the core and the shell are in an open state, the fluid enters from the upper periphery and exits from the bottom during normal flight; There is a retractable airbag at the bottom of the funnel-shaped shell; When the funnel-shaped shell is combined with the core in a closed state, there is some air in the chamber channel, and the retractable airbag enables the aircraft to float on the water surface, suspend in the water, and dive underwater.

2. A disc-shaped aircraft as claimed in claim 1, characterized in that The aircraft as a whole, the aircraft core, and the aircraft funnel-shaped shell are all thicker in the middle than in the surrounding areas.

3. A disc-shaped aircraft as claimed in claim 1, characterized in that The open and closed states are only limited to the junction of the inner core and the outer shell of the circular disc-shaped aircraft.

4. A disc-shaped aircraft as claimed in claim 1, characterized in that When the core and the shell are in an open state, when the aircraft stalls, fluid enters from the bottom of the funnel-shaped shell, passes through the edge, and exits from the upper surface of the core.

5. A disc-shaped aircraft as claimed in claim 4, characterized in that The fluid generates lift when flowing through the upper surface of the inner core in both forward and reverse directions.

6. A saucer-shaped aircraft as claimed in claim 1, characterized in that The fluid generates thrust as it exits the vehicle from below.

7. A saucer-shaped aircraft as claimed in claim 1, wherein a mechanical parachute is provided on top of the inner core.

8. A disc-shaped aircraft as claimed in claim 1, characterized in that The fluid includes fresh water, sea water, and air.

9. A disc-shaped aircraft as claimed in claim 1, equipped with a bidirectional magnetic suspension balancing device.

10. The disc-shaped aircraft as claimed in claim 1, which adopts a coaxial counter-propeller engine.

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