aerostat

Abstract

The present application provides a kind of aircraft with hot air and helium of buoyancy gas, its structure is particularly light, it combines and improves the performance of three kinds of aircrafts of airplane, airship and hot air balloon, configures relevant components, and can realize the mutual transformation between the structure and performance of three kinds of products of airplane, airship and hot air balloon in vertical take-off, cruising flight, suspension according to needs, and the key structure is multiple cylindrical airbag buoyancy bodies for assembly, which has multiple layers of strong diaphragm and inflation or exhaust chamber, increasing the diameter of the number of layers and length, so as to increase the structural strength of passenger and cargo carrying capacity; it not only reduces the structural weight of the aircraft, but also reduces the height of the aircraft body by deflation, reduces the flight resistance; carry on the sea voyage and the sea skimming flight.

Description

Technical Field

[0001] This invention relates to aircraft in the aviation field, and in particular to a particularly light-weight aircraft, airship, and hot air balloon. This invention can also be used in navigation, and therefore also relates to seagoing vessels, making it a tri-amphibious transportation tool. Background Technology

[0002] Conventional hot air balloons have a long history, poor aviation performance, and limited uses. Airships are large, use expensive helium as a lifting gas, and suffer from continuous leakage losses. Existing aircraft, on the other hand, need to improve their performance to meet various application needs, including reducing fuselage weight, saving energy and emissions, saving time, and being used as air taxis and intercity buses in cities. Summary of the Invention

[0003] To help overcome the aforementioned technical deficiencies, the purpose of this invention is to provide a novel type of aircraft transportation that effectively utilizes the buoyancy of a large amount of gas, including hot air, helium, and buoyancy from negative pressure air, as well as the propulsion power of aircraft engines and electric propellers, thereby enabling it to switch between hot air balloons, airships, and airplanes as needed. With the equipment configuration as required, this invention can also be modified to float on the sea or fly above the sea, forming a tri-amphibious transportation vehicle. Summary of the Invention

[0004] The technical solution for achieving the objective of this invention is as follows: The basic structure of the aircraft of the present invention is composed of multiple cylindrical airbag buoys and related components, which serve as unit bodies for constructing a lightweight aircraft structure. Each cylindrical body is arranged along a horizontal axis and is separated along the axis by at least several layers of strong, airtight diaphragms, forming several buoyancy chambers filled with buoyancy gas, preferably hot air or helium. At the center of each chamber is a completely hollow, penetrating all of the several buoyancy chambers separated by the diaphragms, thus forming a small-diameter, closed, inflatable space or hollow chamber located entirely inside the cylindrical airbag. Below the lower edge of this hollow chamber is a pressurized chamber sealed by a single horizontal diaphragm penetrating each layer within the cylindrical body. The rigid aircraft fuselage, wing, and wing box beam skeleton are all connected to this pressurized chamber to generate structural support. This hollow chamber space serves as both a secondary gasbag for conventional airships, equipped with air pumps, valves, and air inlets and outlets for inflation or deflation, and a semi-rigid load-bearing structure formed by a cylindrical gasbag containing multiple layers of gas bags outside its circumference. This structure can extract as much air as possible from the secondary gasbag in the hollow chamber, creating negative pressure and generating lift. At the same time, this load-bearing structure, under the slinging effect of numerous cable groups of the buoyancy helium gasbag located inside and above the cylindrical gasbag, also partially replaces the conventional rigid frame of the aircraft structure, forming a load-bearing structure to support the central wing box beam of the two wings on both sides of the aircraft fuselage and the passenger and cargo cabin. The numerous cylindrical airbags are provided with their respective shapes at specific locations within the streamlined aerodynamic shape of the aircraft they form, including a slightly longitudinally pointed shape on the lower surface of the bottom for use on ships at sea; the passenger cabin and its access passage are airtightly installed in a reference space about 2 meters above the lower edge of the hollow chamber, which is attached and suspended, and extends through the interior or exterior of each adjacent cylindrical airbag buoyancy body. The upper, lower, left, right, front, and rear cylindrical airbags are interconnected and enclosed to form a cavity-type airbag internal space. When the skin or double-layered airbag on the upper surface of this space opens to the left and right, it is used to release or retract the helium gasbag containing the buoyancy body located above the aircraft and its wings by means of a cable. A solar photovoltaic panel is installed on the upper surface of the cylindrical airbag buoyancy body of this aircraft, which uses its electricity to assist the flamethrower in heating the hot air inside the cylindrical airbag. When the aircraft enters cruise flight, the hot air inside the numerous cylindrical airbag buoyancy bodies can be released in an appropriate amount, thereby reducing the thickness of the aircraft fuselage to about 2 meters and reducing flight drag. Attached Figure Description

[0005] Appendix Figure 1It is a three-dimensional schematic diagram of a cylindrical airbag buoyancy body with a certain diameter and length as a component unit; Appendix Figure 2 This is a partial three-dimensional structural diagram of an aircraft constructed using six cylindrical airbag buoys, as described in the embodiment. The specific embodiments of the present invention will now be described with reference to the accompanying drawings: Appendix Figure 1 In this diagram, "1" refers to a cylindrical airbag buoy with a specific diameter and length; "2" is a smaller-diameter cylindrical airbag buoy or hollow chamber located axially at the center of "1," also with a specific diameter and length. It can be filled with hot air via a pump, valves, and inlet / outlet ducts, and, when equipped with a suitable helium membrane, can be filled with or vented with lighter helium; "3" refers to the vertical surfaces at both ends of "1"; "4" is the outer wall membrane of "1"; "5" is the outer wall membrane of the small-diameter hollow chamber; "6" is a large-diameter airbag buoy containing the smaller-diameter airbag buoy of "2"; and "7" is used to support the smaller airbag buoy of "2". The rigid support clamp base and center reference point of the cylindrical airbag shape are arranged in a space extending upwards to 2 meters, downwards, horizontally to the left, right, front, and rear, containing various facilities such as passenger cabins, aisles, igniters, fuselage, and wing frames; "8" is the left or right support column for supporting the rigid clamp clamp "7". The lower end of the support column is fixed to the rigid frame beam of the lightweight structure aircraft of this invention with an upper buoyancy body. The support column, together with the multi-layered pressurized chamber, is used to support the central wing box beam "9" of the wing; "10" is several layers of vertically arranged partition membranes inside "1" along the axial direction. It is fixedly connected from the skin "4" to the skin of the small-diameter hollow chamber "5". Appendix Figure 2 The "11" in this invention refers to the cockpit of the lightweight aircraft, which is transformed from a buoyancy body. Located above the center of the nose, it is a transparent thin-shell bulkhead structure and is also located in the adjacent... Figure 1Within a 2-meter height above the "7" baseline, on the left and right sides slightly behind the cockpit, there are flamethrowers for heating air. Above the flamethrower nozzles is a casing that just covers the nozzles. The top side of this casing has a horizontal, rigid, thin-walled hot air intake tube that extends at least several centimeters into the large-diameter cylindrical structure of "6". Passenger cabin "12" and its aisle, like cockpit "11", are attached to or suspended by cables to the inside or outside of the cylindrical airbag of "1". At this point, the positions of cockpit "11" and passenger cabin "12" are... 1” The shape of the cylindrical airbag skin has been set to conform to the requirements of the streamlined shape of the aircraft, thus changing the standard cylindrical shape; “13” is the location of the aircraft wing; under the wing is a wing-mounted aircraft engine, which can be a turbofan, turboprop or electric propeller, located on both sides of the fuselage; this type of aircraft can be equipped with or without wings depending on the model, type and specification of the aircraft, and can become an airship without wings; it can also be equipped with sail-type control surfaces that push outward from both sides of the fuselage instead of conventional rudders; "14" refers to an upper layer of gas-filled gasbags, formed by horizontally connecting the upper surface skins of all the individual "1" cylindrical buoyant bodies. This upper layer can be single or double-layered and filled with gas. Below, at the bottom, is a lower layer of gasbags of the same type. These two types of gasbags, together with the surrounding "1" cylindrical buoyant bodies, form a cavity "15." The space within this cavity can be used for both internal aircraft storage and as a cavity-type auxiliary gasbag. During vertical takeoff and landing, it extracts air to generate lift or draws in external air to generate descent. During cruise flight... It can provide storage space to house lighter helium gasbags that are released or retracted from the top of the aircraft using multiple sets of traction cables; "16" refers to an aircraft landing gear that uses an air pump to pressurize the air in the various auxiliary gasbags inside the aircraft, including the pressurized auxiliary gasbags, and extends it under the fuselage as an inflatable gasbag package. For aircraft that need to take off and land on the ground, several rows of small rollers are provided on the bottom plane of the inflatable gasbag package with auxiliary reinforcement rigid struts; "17" refers to the option to install solar panels on the upper surface of the gasbag, which generate electricity to charge the battery and heat the gas in the gasbag.

[0006] Effect: The aircraft of this invention utilizes multiple cylindrical airbags that alter fuselage height and reduce drag by changing the type and quantity of inflated gas. It extensively uses buoyancy gas and its lift force, enabling vertical ascent. Simultaneously, it leverages the structural support of this flexible, multi-layered structure in its inflated state, working in conjunction with the aircraft's rigid frame to provide support and usable space while reducing weight. Furthermore, as a vertical takeoff and landing (VTOL) aircraft, its effective passenger and cargo load capacity is planned and implemented based on its available net lift. As a ground-based takeoff and landing (BLT) lightweight aircraft, its optimal configuration requires a sufficiently powerful aero-engine and wings. By equipping the sides or upper surface of the fuselage with sufficiently powerful aero-engines, including electric propellers, ground-based takeoff and landing can be achieved. In particular, by redirecting the engine exhaust airflow downwards, the aircraft can achieve vertical takeoff and landing, as well as hovering and levitation. The lightweight aircraft of this invention is especially suitable for use with elevators or buoyant platforms to lift the aircraft to runways hundreds of meters above the ground for takeoff. Example

[0007] As per the attached examples Figure 2 As shown, without helium gas bags and wings, the average size of the six cylindrical buoys used is 8 meters in diameter, with the smaller inner cylinders having a diameter of 4 meters and an average length of 3 meters. The total weight of the buoy is over 30 kilograms. The aircraft is approximately 9 meters wide and 24 meters long. With the inflatable landing gear erected on the ground, the height is slightly over 8 meters. The buoyancy gas inside each of the six cylinders is interconnected by air ducts. The cavity-like gas bag formed by these six cylinders has a volume of approximately 300 cubic meters. Its net lift is sufficient to support a small airship with two seats, similar to a hot air balloon, equipped with power and directional control. When the electricity generated by the solar photovoltaic panels on its upper surface is used to maintain the heat of the air inside the gas bag, the hovering time of this buoy can be continuously extended. Increasing its diameter, length, and other parameters can create an aircraft that can carry more passengers and travel at higher speeds.

Claims

1. An aircraft formed by the transformation of a hot air balloon or airship composed of multiple cylindrical buoyant bodies, characterized in that... Its basic structure is composed of multiple cylindrical airbag-shaped buoyant bodies and related components, which together form the unit body for constructing a lightweight aircraft structure. Each cylinder is arranged along a horizontal axis and is separated by at least several layers of strong, airtight diaphragms, forming several buoyant chambers filled with buoyant gas, preferably hot air or helium. At the center of each chamber is a completely hollow, penetrating all of the buoyant chambers separated by the diaphragms, thus forming a small-diameter, closed, inflatable space or hollow chamber located entirely within the cylindrical airbag. Below the lower edge of this hollow chamber is a pressurized chamber sealed by a single horizontal diaphragm penetrating each layer within the cylindrical body. The airframe, wings, and wing box beams of the aircraft are all integrated with this pressurized chamber to generate structural support. This hollow chamber space serves as both a secondary gasbag for conventional airships, equipped with air pumps, valves, and air inlets and outlets for inflation or deflation, and a semi-rigid load-bearing structure formed by a cylindrical gasbag containing multiple layers of gas bags outside its circumference. This structure can extract as much air as possible from the secondary gasbag in the hollow chamber, creating negative pressure and generating lift. At the same time, this load-bearing structure, under the sling action of numerous cable groups of the helium gasbags located inside and above the cylindrical gasbags, also partially replaces the conventional rigid frame of the aircraft structure, forming the load-bearing structure for supporting the central wing box beams of the wings on both sides of the aircraft fuselage and the passenger and cargo cabins. The numerous cylindrical airbags are provided with their respective shapes at specific locations within the streamlined aerodynamic shape of the aircraft they form, including a slightly longitudinally pointed shape on the lower surface of the bottom for use on ships at sea; the passenger cabin and its access passage are airtightly installed in a reference space about 2 meters above the lower edge of the hollow chamber, which is attached and suspended, and extends through the interior or exterior of each adjacent cylindrical airbag buoyancy body. The upper, lower, left, right, front, and rear cylindrical airbags are interconnected and enclosed to form a cavity-type airbag internal space. When the skin or double-layered airbag on the upper surface of this space opens to the left and right, it is used to release or retract the helium gasbag containing the buoyancy body located above the aircraft and its wings by means of a cable. A solar photovoltaic panel is installed on the upper surface of the cylindrical airbag buoyancy body of this aircraft, and its electricity assists the flamethrower in heating the hot air inside the cylindrical airbag. When the aircraft enters cruise flight, the hot air inside the numerous cylindrical airbag buoyancy bodies can be released in an appropriate amount, thereby reducing the thickness of the aircraft fuselage to about 2 meters and reducing flight drag.

2. A particularly lightweight fuselage structure for an aircraft that can be transformed from a hot air balloon or airship composed of multiple cylindrical buoyant bodies, characterized in that... It is composed of multiple cylindrical airbag buoys and related components that form the unit body from the airbag buoy to the lightweight aircraft structure. Each cylinder is arranged along a horizontal axis and is separated by at least several layers of strong, airtight diaphragms to form several buoy chambers filled with buoyancy gas, such as preferably hot air or helium. At the center of each chamber is a completely hollow buoy chamber that runs through all of the several buoy chambers separated by the diaphragms, thus forming a small-diameter, closed, inflatable space or hollow chamber located inside the cylindrical airbag. Below the lower edge of this hollow chamber is a pressurized chamber sealed by a single horizontal diaphragm that runs through each layer of the cylindrical body. The rigid aircraft fuselage, wings, wing box, and spars are all connected to this pressurized chamber to generate structural support.

3. A pressurized aircraft landing gear for an aircraft that is transformed from a hot air balloon or airship composed of multiple cylindrical buoys, characterized in that... It is a high-pressure airbag or hot air balloon or aircraft landing gear made by pressurizing air from the auxiliary airbag inside the aircraft and filling it into the airbag that extends downward to touch the ground. Its lower surface can be equipped with multiple rows of small rollers, which can further form a landing gear that can take off and land on the ground runway.

4. An aircraft that is transformed from a hot air balloon or airship composed of multiple cylindrical buoys has its passenger cabin and aisles attached to or suspended by cables inside or outside the cylindrical airbag, just like the cockpit. In this case, the shape of the cylindrical airbag skin at the location of the cockpit and passenger cabin is set to conform to the requirements of the aircraft's streamlined shape, thus changing the standard cylindrical shape.

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