The present invention relates to an aircraft having an airframe in which a main fuselage and auxiliary fuselages are connected by a main wing, a front wing, and a horizontal stabilizer.
The prototype of the aircraft of the present invention is described in U.S. Pat. No. 6,969,026 (Patent Document 1). This aircraft has the feature of being able to fly stably even at low speeds.
Patent Document 1: U.S. Pat. No. 6,969,026
Patent Document 2: U.S. Pat. No. 9,933,521
Patent Document 3: WO1097/43180
An example of the use of the aircraft of the present invention is an aerial refueling aircraft. Traditionally, aerial refueling has been used to save fuel consumed during takeoff or to save round-trip fuel required when returning to the base for refueling. U.S. Pat. No. 9,933,521 (Patent Document 2) introduces an aircraft that can simultaneously refuel multiple aircraft in the air.
For aerial refueling, a flexible refueling pipe or rod-shaped boom is used (WO1097/43180 (Patent Document 3). Advanced maneuvering technology is required to connect the boom while following an aircraft flying ahead in the air.
In this way, when a plurality of aircraft fly close to each other, safe and stable flight performance is required. For stable flight of aircraft flying immediately behind, aerial refueling aircraft are required to have a structure that does not disturb the air flow. An object of the present invention is to solve these problems.
The following configurations are means for solving the above-mentioned problems, respectively.
An aircraft having a main fuselage 12, and a pair of left and right auxiliary fuselage 14, 16, that the fuselages are connected by the front wing 30, the main wing 26, and the horizontal stabilizer 32 wherein;
the chords of the front wing 30, the main wing 26, and the horizontal stabilizer 32 are all almost constant over the entire length;
a narrow portion 28 in which the chord of the main wing 26 is narrower than the other parts is provided at the connection portion between the main fuselage 12 and the main wing 26; and
the narrow portion 28 of the main wing 26 is connected to the side surface of the main fuselage 12 or penetrates the main fuselage 12.
The aircraft according to the configuration 1, the main wing 26, the pair of left and right auxiliary fuselage 14, 16 are connected by interposing a flat columnar support 48 facing in the same direction as the vertical stabilizer 34.
The aircraft according to the configuration 2, cross section of the auxiliary fuselage 14 and 16 is a perfect circular.
The aircraft according to the configuration 3, the aircraft have booms 56 and 58 made of rigid pipes for aerial refueling along the outer wall surface of the auxiliary fuselage.
The aircraft according to the configuration 1, the aircraft have a main fuselage and two pairs of left and right auxiliary fuselage 18, 20.
(1) Comparing the chords of the front wing 30, the main wing 26, and the horizontal stabilizer 32, the chord of the main wing 26 is the widest. As the narrow portion 28 is provided at the connecting portion between the main wing 26 and the main fuselage 12, the turbulence of the airflow in this portion is reduced. Since the main fuselage 12 and the pair of left and right auxiliary fuselage are connected by three wings, there is no risk of a decrease in strength.
(2) When the main wing 26 and the pair of left and right auxiliary fuselage 14 and 16 relate to the flat columnar support 48 interposed therebetween, the turbulence of the airflow in this portion is reduced.
(3) When the cross sections of the auxiliary fuselages 14 and 16 are made perfectly circular, pressurized hydrogen fuel and the like can be loaded.
(4) Since a large amount of fuel can be loaded on the auxiliary fuselage 14 and 16, the booms 56 and 58 made of rigid pipes can be used to supply fuel to other aircraft.
(5) Since there is little turbulence in the airflow and stable flight is possible, fuel can be safely supplied to other aircraft.
Hereinafter, embodiments of the present invention will be described in detail for each example.
As shown in
As shown in
The main engines 22 and 24 are fixed to the outer surfaces of the auxiliary fuselage 14 and the auxiliary fuselage 16, respectively. The main engine 22 is supplied with fuel from the auxiliary fuselage 14. The main engine 24 is supplied with fuel from the auxiliary fuselage 16.
The rigidity of the airframe is enhanced by the structure that combines the three wings 26, 30, and 32. Since the three wings of the front wing 30, the main wing 26, and the horizontal stabilizer 32 share the support of the airframe. The burden on the main wing 26 for supporting the weight of the airframe is small.
Conventionally, in a general aircraft, almost the entire weight of the airframe is supported only by the main wing. Therefore, the connecting part between the fuselage and the main wing has a thick wing thickness and a wider chord structure than the other parts so as to maintain sufficient strength.
On the other hand, in the airplane of the present invention, the chords of the front wing 30, the main wing 26, and the horizontal stabilizer 32 are all substantially constant over the entire length. Further, since the load shared by the main wing 26 is small, the wing thickness can be reduced and, as an exception, the chord can be made narrower than the other parts at the connecting portion between the main fuselage 12 and the main wing 26.
In the example of
Since the connection between the auxiliary fuselage 14 and 16 and the front wing 30 and the horizontal stabilizer 32 has a small shared load and these chords are narrow, any structure of
With the above structure, mutual interference of airflow during flight at the connected portion of the main fuselage and the main wing is reduced, air resistance is reduced, and stable flight is possible. Moreover, the weight of the aircraft can be reduced.
As shown in
As shown in
If the booms 56 and 58 are aligned with the cylindrical outer wall surface of these auxiliary fuselage bodies, a long boom for refueling can be supported. If the booms 56 and 58 made of rigid pipes are used, the connection is easier and the refueling can be performed with higher safety than the flexible hose.
Moreover, since the wing structure described above has less turbulence in the airflow, stable flight is possible even when a plurality of airplanes fly close to each other.
The main fuselage 12 and the pair of auxiliary fuselages 14, 16 are used for an aerial refueling device using booms 54, 56, 58 made of rigid pipes. As shown in
If it is a large aircraft as shown by the alternate long and short dash line of
In this airplane, the main wing 26, the front wing 30, and the horizontal stabilizer 32 have a linear shape and are mounted in parallel with each other. Therefore, as shown in
It is possible to make an aircraft having a main fuselage and two pairs of left and right auxiliary fuselage. In this way, when flying alone, the cruising range can be greatly extended. In addition, when using for an aerial refueling aircraft, it is possible to refuel for five small aircrafts and for three large aircrafts at the same time.
As shown in
As shown in
When conventional aircraft increase in speed, long runways are required for takeoff and landing. In addition, since the approach angle to the airport at the time of landing is as low as several degrees, noise damage to the neighborhood of the airport is serious. The aircraft of the present invention has high performance if it is an STOL aircraft, and solves this problem.
For example, if hydrogen-fueled engines 22 and 24 are provided, a mechanism for mixing silver iodide in the exhaust gas can be provided to stimulate clouds and make it rain. By stimulating typhoon clouds and cumulonimbus clouds on the sea to make it rain on the sea, it is possible to reduce the amount of rainfall on land.
Number | Date | Country | Kind |
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2022-13798 | Jan 2022 | JP | national |