JPH011694A - catamaran airship - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention] [Field of use in the field of work] The present invention relates to improvements in airships.

[Conventional technology]

Conventional airships most commonly have a so-called cigar-shaped single-hull cabin with a cabin beneath the air chamber, and there are no exceptions to the type of airships that are in practical use.

Ideas that have been seen include a single-body air chamber with main wings and a tail, and a donut-shaped air chamber.

[Problem that the invention seeks to solve]

The conventional airships mentioned above had the following problems.

(1) With a single cigar-shaped air chamber, there is nothing to resist rolling, the roll stability after levitation is poor, and it is easily affected by slight weather changes.

(2) Similarly, it is difficult to say that pitch stability, especially yaw stability, is excellent.

(3) Because it is a single hull, it is unstable when moored on the ground or when moving on the ground, and in reality, large airships are moored with numerous cables pulled from both sides of the hull to prevent them from overturning. .

(4) The tensile strength of the outer skin against the pressure of the filling gas is proportional to the diameter of the air chamber at a constant pressure, so the size of the air chamber is limited by the strength of the outer skin. Therefore, in a single shell, the volume There is a limit to the amount of buoyancy that can be achieved, and the payload becomes limited.

(5) In the case of a single-hull air chamber attached to the main wing and tail.

Compared to a model with only a single shell, the stability of roll, pitch, and torsion is slightly improved, but it cannot be said that it has increased by a sufficient amount, and the limit of the size of the air chamber is the same as with a model with only a single shell.

(6) A donut-shaped air chamber has high flight resistance and poor maneuverability. Furthermore, the installation conditions for the propellant are not sufficient.

[Means for solving problems]

The present invention aims to provide an airship configured as follows as a means for solving the above problems.

That is, it is a twin-hulled airship characterized by having air chambers provided on the left and right sides, and a gas having a lower specific gravity than the air filled in the air chambers.

[For production]

Since the present invention is configured as described above, it has the following effects.

(1) Since it is a twin-hulled type, the air chambers, which have a large apparent area and weight relative to buoyancy and air resistance, are located at the left and right ends, which are the maximum width of the airship, so for example,
Rolling caused by internal factors such as rapid movement of crew members or dropping of objects is most efficiently resisted by the buoyancy moment (around the center of gravity), air resistance moment, and weight inertia moment, making it more stable than a single-hull structure. Extremely sensitive.

(2) Stability is high because the moment of inertia of one weight of buoyancy moment efficiently resists rolling due to weather changes, such as wind and other disturbances.

(3) For the same reason, it is highly stable against yawing. The wide horizontal stabilizer provides good stability against pitching.

(4) If a living area such as a cabin is placed in the center of the airship, that is, between the twin hulls, even if the airship rolls or yawings a little, the left and right air chambers, that is, the twin hulls, will move up and down or left and right in a seesaw manner. It is convenient because there is no need to move the residential area located in the middle.

(5) Since it is a twin-hulled type, it has sufficient width on the left and right sides, so the width between the wheels can be made sufficiently large, the stability against rolling over on the ground is increased, and mooring, movement, etc. are facilitated.

(6) Since it is a twin-hull type, it is possible to use two bodies whose diameter is the strength limit of the air chamber outer skin.

Therefore, an airship having approximately twice the buoyancy, ie, twice the payload, as a single-hull type is obtained.

〔Example〕

85 according to FIG. 1 and FIG. 2 regarding one embodiment of the present invention.
! I will clarify.

In both figures, IL is a teardrop-shaped outer body installed at the left end of the main wing 4L, which will be described later, and the interior is supported by an appropriate lightweight skeleton.
The outer shell is airtightly covered with a plastic fiber cloth that has been treated with a weather- and oil-resistant rubber coating to form an air chamber. A pulp (not shown) is provided in one corner, and helium gas is filled to an appropriate pressure. IR is outer body IL
This is an outer shell provided at the right end of the main wing 4B, which will be described later, so as to form a pair of twin fuselage t-, and is configured symmetrically with the outer fuselage IL. 2
is a central fuselage supported by the outer fuselage IL and the main wings 4L, 4R, and the horizontal stabilizer 5L and 5B, which will be described later, along the longitudinal direction of the outer fuselage IL and the outer fuselage IL. Outer body IL
It has the following configuration according to the same IB, and the inside is filled with Sihelium gas. 3 is the passenger cabin provided at the bottom of the center fuselage 2, 4L is the main wing, and the main wing 4B, which will be described later.
It is configured to support the outer fuselage IL, the outer fuselage 1B, and the center fuselage 2 as a beam during flight and ground, and its surface is thin so that its cross section forms a so-called airfoil shape. It is made of aluminum cladding and is constructed to generate lift during flight. 4 liters is the main g4L
This is a pair of left and right main wings, and as mentioned above, they are basically an integral structure with the main wing 4L, but the shape is symmetrical with the main wing 4L,
The outer skin is an aluminum clad plate. Main g4I above
, the meeting area of the outer skin between the 4R and the outer fuselage IL, IR and the center fuselage 2 is appropriately air-ringed symmetrically with the main wing 4L so as not to impair aerodynamic performance. 0 Ride comfort, maneuverability, etc. In order to keep the aerodynamic center close to the center of gravity and maintain good longitudinal stability.

Since the main wings 4L and 4R need to be placed slightly behind the center of gravity, their longitudinal position relative to the outer fuselage IL, IR, and center fuselage 2 is required to be near the center of gravity of the entire airship.
Most of the support strength connecting the outer fuselage IL, IB-, and center fuselage 2t is borne by the main wing 4L and the IR, and horizontal stabilizers 5L and 5B, which will be described later, are designed to provide supplementary support. 5L is the horizontal stabilizer on the left side that fully connects the legs of the outer fuselage IL, IB, and center fuselage 2 to obtain vertical stability, 5F- is the horizontal stabilizer on the right side, and 6L is the ninth horizontal stabilizer that provides directional stability. Vertical tail fin installed perpendicularly to tail fin 5L,
Similarly, 6L is a vertical stabilizer installed perpendicularly to the horizontal stabilizer 5B in symmetry with the duty tail g6L, and 7L is a left-hand flap that is provided at the rear of the main wing 4L in a front-rear view and can be extended and retracted to generate lift. Used for increase. 7R is the right flap installed on the main wing 4 symmetrically with flap 7L, 8L is in flight,
Elevator 8B is installed in the rear area of horizontal stabilizer 5L to control ascending and descending, 8B is an elevator installed on Mizubi j15R symmetrically with elevator 8L, and 9L is for directional control during flight. A rudder installed at the rear of the vertical stabilizer 6L, 9
Similarly, B is a rudder installed on the vertical stabilizer 6i11 symmetrically with the rudder 9L, and the IOL is designed so that the propulsion axis points upward during takeoff, and after takeoff and flight, the propulsion axis is rotated horizontally for propulsion. A propeller installed on the left side of the center fuselage 2,
101 (also a propeller installed on the right side symmetrically with the propeller IOL, 11La Propeller 10L engine is housed in a cigar-shaped nacelle, and near its center is supported by a torque arm protruding from the central body 2, and by the rotation of the torque arm 360 degrees along with the propeller IOL in the direction of the double arrows in the figure.
'It can be rotated freely. 11R is the engine 1, which is also installed on the right side symmetrically with engine IIL.
2L is a main landing gear wheel provided below the main landing gear wheel 4L for ground running, and 12B- is also a main landing gear wheel symmetrically with the main landing gear wheel 12L.
This is the main landing gear wheel provided below R.

Next, the effect will be explained.

First, the takeoff weight, which is important for an aircraft, is set to be slightly larger than the overall buoyancy when the outer fuselage IL, IR, and center fuselage 2 are adjusted to the optimal pressure, and people or cargo must be loaded to reach this value. do. Then, the aircraft took off with engines IIL and 11B flying upwards. After ascending to a predetermined altitude, the propeller IOL and the propeller IOL will begin to fly horizontally. When reaching the destination, turn the propeller IOL and 10B upward again, and move the propeller 10L.
In order to land, the aircraft's rotational speed is extremely low, and the lift is slightly adjusted to improve buoyancy and overall weight.

If you want to land quickly from a high altitude, turn the propellers 10L and 10B downwards and quickly descend to a specified height, then turn the propellers, IOL and 10B upwards and fly to the ground.
You may land on the ground.

Alternatively, if the above landing is unstable due to wind, etc., flaps 7L and 7R are extended to increase the lift of main wings 4L and 4F, and propellers 10L and 10B are directed diagonally forward and upward. Then, set the horizontal component of thrust and the vertical component as appropriate.
You may land as if you were an airplane. However, in that case, the main gear wheels 12L and 12B are required to have appropriate strength in advance. Of course, other structures are also required to be designed with corresponding robustness.

The lift force during flight is generated by the main wings 4L and 4L when the airship reaches cruising speed, and is designed to balance out the excess of the payload relative to the buoyancy. Alternatively, if the load is too large, the propeller IOL and propeller 10B may be oriented slightly upwards to compensate for the output force, or the flaps 7L and 7R may be extended slightly to increase lift. Alternatively, the required amount of helium gas may be injected into the outer hull IL and IB from a high-pressure helium cylinder installed onboard the ship in order to increase the volume within the allowable limits. Although there is no particular mention of the ailerons and trim tabs, they may of course be provided.
Two sets each of L and 9B are provided, but the number can be increased or decreased as desired.

However, airships generally have low speeds, so the rudder is not as effective.
If the number is small, a large area is required. central torso 2
You can freely increase or decrease the number of cabins, and if you abolish them, cabin 3
may be attached directly to the main wings 4L, aR, or
Thrust power is not limited to propellers; of course, jet engines and other sources may be used.Also, one land-going vessel can be used for sightseeing, transporting people, transporting cargo, or any other purpose, and is exclusively used for transporting cargo. If you select , cabin 3 is not required.

In the above embodiment, helium gas was used as the gas to fill the outer shells IL1 and IR and the center shell 2 in consideration of fire protection, but the gas is not limited to helium gas. or,
The structure of the outer shell IL, IR, and center shell 2 is also divided into several chambers with an airtight membrane, and if a pulp that can be artificially controlled to open and close is attached between each air chamber, it will be possible to prevent any emergency from occurring. Even if an accident creates a hole in the air chamber of one compartment, the gas leak will remain only in that compartment, preventing any serious damage.

〔Effect of the invention〕

Since the present invention is configured as described above, it has the following effects.

(1) High stability against rolling and yawing provides good ride comfort and superior maneuverability.

(2) Since the cabin can be placed between the twin hulls, the displacement of the cabin relative to the space is extremely small, providing a comfortable ride.

(3) Since there is sufficient width between the wheels, there is no concern about overturning, and the mooring performance and ground mobility are excellent. This improves the so-called ease of use, giving great potential for new developments in air transport between remote islands where long runways cannot be built, for example.

(4) Since airships with high speed and stability can be obtained by using main wings, etc., the field of transporting goods by air will expand and encourage the rise of industry.

[Brief explanation of drawings]

FIG. 1 is a perspective view of one embodiment of the present invention, and FIG. 2 is a front view of FIG. 1. IL, IR--Outer body, 2--Central body, 3
...cabin, 4L, 4R...main wing, 5
L. 5R1...Horizontal stabilizer, 6L, 6R...Vertical stabilizer. 7L, 7B...Flap, 8L, 8B...
Elevator, 9L, 9B... Rudder, IOL, 1
0B...propeller, txL, txR...engine, 12L, 12B...main gear wheel. Figure 1

Claims (1)

[Claims] A twin-hulled airship characterized by having air chambers provided on the left and right sides and a gas body with a specific gravity smaller than the air filled in the air chambers.