JPH034640Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to an aircraft towed by a helicopter or the like.

[Prior art]

Traditionally, airships were built using buoyant gas held in gas bags contained within an elongated container to minimize air resistance. However, this type of elongated shape is somewhat disadvantageous, especially in the case of large dimensions, for the following reasons.

First, achieving good aerodynamic shape in large airships requires a rigid structure that contains multiple gas bags and defines the outer shape of the airship. And such structures are extremely expensive.

small airships, so-called blimps
are made without any rigid structures, but these cannot create an ideal streamlined shape.

Also, a major drawback of traditional airships is that the airship acts as a weather vane and tends to rock with changes in wind direction, making it difficult to moor large airships in situations other than calm. This means that it is difficult to load cargo.

Airships have traditionally used buoyant gas bags at substantially atmospheric pressure. These bags expand and contract depending on the ambient pressure and temperature, so that the volume of the bags depends on weather conditions and the height of the airship, giving wide variations in effective lift. This means that airship operations have traditionally been very weather dependent; for example, an airship must wait until the air temperature is sufficiently warm before it can take off.

Balloons containing buoyant gas at a pressure substantially higher than atmospheric pressure, so-called "overpressure" balloons ("super-
pressure"balloons) were previously used as free-flying balloons for atmospheric monitoring. The use of this type of manned balloon as part of a project named ATMOSAT was announced by the APCA.
Journal Vol. 27 No. 6 June 1977 (APCA
Journal, vol. 27, No. 6 of June 1977). The balloon used was 10 meters in diameter and had an inner layer of Kevlarcloth,
bilaminated mylar
layer and aluminized
It is constructed with a sanderch construction including an outer sheet of Mylar. Kevlar is DuPont's trade name for polyester fiber, and Mylar is the trade name for polyester that is made into thin sheets and has high tensile strength.

The overpressure balloons ever made are free-flying balloons with gondolas suspended below the balloon by a series of cables attached to tabs spaced around the bottom of the balloon. Ta. The balloon fabric is strong enough to hold these suspension means without a load-bearing net placed on the top of the balloon. These ATMOSAT
The performance of the balloon has shown great stability, and the internal pressurization has been shown to be sufficient to overcome any atmospheric disturbances that would otherwise cause the balloon to change altitude and disturb the measurements. It has been reported.

As used herein, the term "overpressure balloon" refers to an essentially constant dimension and a balloon that, once properly inflated, does not change due to changes in external pressure and temperature of the kind that occur with normal atmospheric changes and changes in altitude. means a balloon of inelastic material having a shape. A superpressurized balloon is a balloon so large that it is launched at a pressure slightly above atmospheric pressure and can fly at least a few thousand feet (hundreds to thousands of meters) without releasing buoyant gas (helium). From atmospheric pressure
Usually designed to safely accommodate internal pressures as high as 35 mbar. However, depending on the dimensions, an overpressure balloon can accommodate a pressure of 100 mbar above the surrounding pressure, and this pressure
Certain materials can be used to increase the pressure to 300 mbar or more. The fabric used for these overpressure balloons depends on the internal pressure and diameter to be used, e.g.
175 lb/in and 700 lb/in (approx.
31.2 Kg/cm and approximately 124.8 Kg/cm).

[Issues with conventional technology]

Although various aircraft equipped with balloons as described above are known, none of these are suitable for carrying heavy loads.

It is therefore an object of the invention to provide an aircraft suitable for carrying heavy loads.

A further object of the present invention is to provide an aircraft that can be towed by, for example, a helicopter and has a structure suitable for being moored on the ground.

[Means to solve the problem]

According to the present invention, the object as described above has a horizontal axis and a buoyant gas containing a buoyant gas having substantially constant dimensions and shape when inflated and capable of rotating about the horizontal axis. a spherical balloon coupled to the horizontal axis for rotation; a load-bearing yoke coupled to the horizontal axis for rotation about the horizontal axis independently of the spherical balloon; Independently of the balloon and the load-bearing yoke,
a towing yoke rotatably connected to the horizontal axis, the towing yoke being rotatable about the horizontal axis between a towing position and a mooring position; In the towing position, the towing yoke extends upwardly from the connection with the horizontal shaft, and in the mooring position, the towing yoke extends downward from the connection with the horizontal shaft, The problem is solved by providing an aircraft characterized in that it makes it possible to attach a towing yoke to a mooring member for mooring the aircraft to the ground.

Preferably, the traction yoke is curved to match the curve of the spherical balloon, and the gap between the contour of the spherical balloon and the adjacent surface of the traction yoke is 1/3 of the radius of the spherical balloon. They are arranged as shown below.

Furthermore, the spherical balloon preferably includes an air compressor surrounding the auxiliary bladder and supplying outside air to the auxiliary bladder at a higher pressure than the balloon gas to control the buoyancy of the aircraft.

[Reference example]

Next, reference examples that can be referred to when implementing the present invention will be described with reference to FIGS. 1 to 3.

The airship shown in Figures 1 to 3 is always approximately
It has a buoyancy force provided by a non-rigid spherical balloon or envelope 10 filled with helium at a pressure maintained above 1035 mbar. The envelope material is Kevlar 29 woven as standard biasweave.
(Kevlar−29) Sanderch structure formed from fibers with single heavy biases
is woven every 3 inches, and has a bonded layer of double-laminated mylar on the inside and a bonded sheet of hot-dip aluminized mylar on the outside. On each side of the balloon, this material is rigidly bonded to the edges of a circular dish-shaped steel plate 14. These plates 14
also provides an anchorage for a cable 12 that extends circumferentially around the balloon in between. plate 14
has a central opening that is welded around a hollow central shaft 16 (see FIG. 3). Although the balloon material is fairly smooth in texture, small bulges are formed by the cable 12 that provide a ribbed outer surface. Plate 14 has helium filling port 17
(normally closed) and a helium pressure regulator 18 in the form of a motor-driven valve that automatically vents helium to the atmosphere if the internal pressure of the balloon rises to 40 mbar or more above atmospheric pressure. There is.

Horizontal shaft 16 supports a central auxiliary bladder 20, shown schematically in FIG. The auxiliary bladder 20 has two ends 22 tapered downwardly and sealed to the horizontal axis, and is held in the inflated state by a circular hoop 24 held spaced from the horizontal axis 16. An inflatable enclosure having a retained center portion. The center of the horizontal axis within the balloon has a cavity with a port that connects to the inside of the auxiliary bladder and whose end is also in sealing communication with a non-rotating supply tube 28 shown in FIG. A twin-shaft blower air compressor (not shown) is provided for supplying air through tube 28 to the auxiliary bladder to inflate the auxiliary bladder against the pressure of helium in the supply to alter the buoyancy of the balloon. ing. When fully inflated, the auxiliary bladder assumes a generally spherical shape as indicated at 20' in FIG.

Balloons do not contain any substantial internal structure, as in rigid airships, although there may be cables connecting the horizontal axis to points on the envelope and maintaining the correct spherical shape of the balloon. Although there may be one or more dividing devices extending radially of the horizontal axis to divide the inner subspace into separate compartments, the use of multiple separate gas bags as used in Canadian Patent No. 153,756 is Avoided. The distribution of lift gas throughout the balloon is substantially uniform.

The end 16a of the horizontal shaft can rotate in a bearing 30 provided at the upper end of the arm 32 of the load-bearing yoke, generally indicated at 34. These arms each include an electric motor 35 driving a gear train terminating in a gear wheel 37 mounted at the end of the horizontal shaft 16, which motors drive the horizontal shaft in the direction shown in FIG. and arranged to rotate the balloon. The drive train may be provided with a slip clutch or similar element to prevent undue rotational stress on the balloon. As can be understood from the arrows at the bottom of FIG. 1, the direction of movement of the airship is such that the entire surface of the balloon is constantly rising. The rotation is controlled to a few rpm, but the speed is variable. The rotating and ribbed surface of the balloon prevents laminar air flow,
This provides turbulent flow that is accelerated (low pressure) on the upper side and retarded (high pressure) on the lower surface, thus providing lift. This rotation is thought to also reduce drag on the balloon as it moves through the air. The rotational speed is chosen to give optimum values of lift and drag reduction.

The upper end of the arm 32 also supports a variable pitch propulsion system, i.e., a gas turbine engine 40 mounted in a pod that can pivot about a horizontal axis coincident with that of the horizontal axis 16, the engine pointing vertically upward. It is possible to turn vertically downward and slightly backwards over 200 degrees.

Variable pitch propulsion systems have engines that drive the aircraft in forward or reverse motion, raise or lower the aircraft, and tilt the aircraft about a cyntral fore and aft axis or around a vertical axis. It also allows thrust reversal so that the aircraft can be rotated.

The center of the load-bearing yoke 34 is connected to the cargo area 3
Gondola 3 including load engagement means in the form of 6a
It is 6. The arm 32 conforms to the shape of the balloon and is curved to position the gondola 36 very close to the bottom of the balloon, the distance separating the bottom of the balloon from the top of the gondola being preferably less than 1/10 of the radius of the balloon. In any case, it should be smaller than 1/3 of the balloon radius. This improves the maneuverability of the aircraft compared to standard balloon construction, where the gondola is supported by a relatively long cable from the balloon, and reasonably allows the balloon to be held only by a mooring cable connected to the gondola. Ensure that it can be held firmly. At the forward upper end of the gondola there is provided a cabin 36b for a screw member for controlling the aircraft. The cabin is pressurized to allow operation at high altitudes where drag on the aircraft is reduced. The base of the gondola has a skid 38 provided for landing on the ground and may be provided with floats for use against water areas.

The arm 32 is longitudinally elongated and streamlined, and is provided with a rudder 41.
The main body of a gondola is generally in the form of an aerofoil having a relatively high width-to-height ratio (at least 6 to 1) along most of its length. The aft section of the gondola has ailerons 42 . The rudder 41 and ailerons 42 provide useful control in case of engine failure and can also be used to control the rocking motion of the gondola.

Engine 40 provides forward force to the yoke and causes it to swing back as the aircraft accelerates.
bach) can be mounted slightly below the indicated position to compensate for the tendency to

The airship described above was designed to have a 160 foot diameter balloon, giving a gross weight of 29 tons and a payload for freoght of 20 tons. The speed of movement is approximately 80 miles/hour (approximately 128.7 km/hour).

〔Example〕

An aircraft according to a preferred embodiment of the present invention will now be described with reference to FIGS. 4-10c.

First, Figures 4-7 illustrate an aircraft according to an embodiment of the invention intended for use as a lifting device, particularly for use with helicopters.

The aircraft according to this embodiment has an end plate 11
4 and a ribbed overpressure spherical balloon 110 having a horizontal axis 116 and a central auxiliary bladder 120, these members having smaller balloon dimensions.
That is, it is similar to the corresponding member in the reference example above, except that it is approximately 72 feet (approximately 22 meters) in diameter.

Aircraft load-bearing yoke 13 according to this embodiment
2 has a sturdy load-engaging hitch 134 in the center, bordered on each side by a pot 136 containing an air compressor for the auxiliary air bladder and a helium source for the balloon, and legs on which the aircraft can be mounted. It is a simple semicircular member with The upper end of the load-bearing yoke 132 is pivotally connected to the protruding end portion of the horizontal shaft 116. A traction yoke 140 is pivotally connected to the end of the horizontal shaft and is similar to the load-bearing yoke 132 but of lighter construction and provides a center for the cable 142, preferably in the form of a winch 141. It also has attachment means. Load support yoke 132 and traction yoke 140
are mutually pivotable such that they can form either relatively small angles of less than 90° or large angles of close to 180°. The load-bearing yoke 132 may also support means for rotating the balloon 110 similar to the means described with respect to the reference example above.

The cable 142 has a hitch connection designed to receive the lower end of a tow bar 160 shown in FIG. 4, the upper end of which is connected to a helicopter as shown. Tow bar 1
60 preferably includes a helicopter and a towing yoke 14
It is a flexible elastic member in the form of a long curved tube providing a semi-rigid connection between zero but with sufficient elasticity to accommodate shock loads. The wireless control system can be operated from the helicopter to control the functions of the auxiliary bladder, compressor and balloon rotation motor (if used), and to monitor the pressure of helium within the balloon. In the example, there is no crew on the aircraft itself.

The method of using this aircraft is shown in Figures 4 to 7.
It is clear from the explanation of the figure. FIG. 5 shows a state in which the aircraft is statically moored to be secured and held on the ground by two heavy mooring weights W attached to the load support yoke 132 and the traction yoke 140, respectively.

Load engagement hitch 134 of load support yoke 132
The first mooring weight is released and a load is attached to it. The tow yoke 140 is released from the second mooring weight and connected to the helicopter's tow bar by a cable 142 extending from a winch 141, as shown in Figure 7a. Cable 142 is then pulled by a winch and the auxiliary bladder is vented to atmosphere until the aircraft has sufficient lift to lift the load, and the aircraft and load L are shown in FIGS. 4 and 7b. It is towed as if it were.

Figures 7d to 7g show the subsequent maneuvers.
The vertical position of Figure 7d allows free rotation to be reversed. The rotation is illustrated in Figure 7e. Figure 7f shows the reverse tow position allowing braking and precise maneuvering. Figure 7g shows another inversion process. The helicopter moves from its original horizontal course and pulls the aircraft in the opposite direction. The aircraft turns, but since the load is attached by the pivot attachment, it does not turn.

Upon landing, the towing yoke 140 is again released from the helicopter and before the load is released.
Used for mooring aircraft to the ground.

The aircraft can be easily made transportable by deflating the balloon and dismantling the arms.

FIG. 8 shows a modification of the apparatus of FIGS. 4 and 7 in which the central portion of the horizontal axis 216 is shown omitted.

The apparatus of FIG. 8 includes an overpressure balloon 210 attached to end plates 214 on either side of a central axis passing through the center of the balloon. These end plates are located on the outer ends of the arms of load-bearing yoke 232 and on the arms of traction yoke 240, located in alignment with the horizontal axis so that the balloon can rotate about said horizontal axis. has an outwardly extending spigot held in place by a bearing on the outer end of the spigot. The load-bearing yoke connects the load-engaging hitches 234 between the pods 236.
and the traction yoke 240 has a central hitch member 241, all of which are similar to the corresponding members of the previous embodiments. However, in this case, instead of a central auxiliary air sac,
Two auxiliary bladders 220 are provided, each connected to one of the end plates 214 and each supplied with air via an arm of the load-bearing yoke 232. Means may also be provided for inflating one auxiliary bladder more than the other when it is necessary to balance the aircraft, ensuring that the pressures between the auxiliary bladders are properly balanced. It is also possible to provide means for this purpose.

FIG. 9 shows another embodiment of the aircraft of FIGS. 4-8, which has a balloon 310 secured to an end plate 314 and a tow yoke 340 to which a winch 341 is attached. and connection means for rotatably connecting to. This connection means
It may be a part of the central axis shown in FIGS. 4 to 7,
Alternatively, the spigot shown in FIG. 8 may be used.
In this embodiment, the load supporting yoke 332 is
(Similar to those in Figures 4 to 7 or 8)
It takes the form of two separate arms extending from the pivot connection with the traction yoke 340 to the load engagement means 334. The load engagement means 334 is, for example,
It can be a hook or sling as shown suitable for holding elongated objects such as pipes (for oil or gas piping) or large timbers.

Figures 10a-10c schematically illustrate various forms of load-bearing yokes that can be used in place of the semicircular yokes of Figures 4-8.

〔effect〕

According to the present invention, it is possible to provide an aircraft suitable for transporting heavy loads.

Further, according to the present invention, it is possible to provide an aircraft that can be towed by a helicopter or the like and has a structure suitable for being moored on the ground.

[Brief explanation of the drawing]

FIG. 1 is a side view of a maneuverable airship according to a reference example. Figure 2 is a front view of the airship shown in Figure 1. Third
The figure is an enlarged partial cross-sectional view taken along line 3--3 of FIG. FIG. 4 is a side view of an aircraft according to an embodiment of the present invention. Figure 5 is a diagram showing the aircraft of Figure 4 when moored on the ground; Figure 6 is a front elevational view of the aircraft shown in Figure 4. Figures 7a to 7g show the fourth
1 is a schematic diagram illustrating the operation of the aircraft shown in the figure; FIG. 8 is a front view of a carrier aircraft according to another embodiment. FIG. 9 is a front view of an aircraft according to yet another embodiment. 1st
Figures 0a to 10c are schematic illustrations of support means according to other embodiments. 110... Overpressure spherical balloon, 114... End plate, 116... Horizontal axis, 120... Auxiliary air sac,
132... Load support yoke, 134... Load engagement hitch, 136... Pot, 140... Traction yoke, 141... Winch, 142... Cable,
160...Tow bar, 210...Overpressure balloon, 21
4...End plate, 216...Horizontal shaft, 220
...Auxiliary air bladder, 232...Load supporting yoke, 23
4...Potsudo, 240...Traction yoke, 241...
...Central hit member, 310... Balloon, 314...
End plate, 332...Load supporting yoke, 33
4... Load engagement means, 340... Traction yoke, 3
41...Winch, L...Load, W...Mooring weight.

Claims (1)

[Claims for Utility Model Registration] 1. A buoyant gas containing a buoyant gas having a substantially constant size and shape when inflated and capable of rotating about the horizontal axis; a spherical balloon connected to the horizontal axis; a load-bearing yoke connected to the horizontal axis for rotation about the horizontal axis independently of the spherical balloon; a towing yoke coupled to the horizontal axis for rotation about the horizontal axis independently of the load-bearing yoke, the towing yoke being able to move between the towing position and the mooring position; rotatable about the horizontal axis; in the towing position, the towing yoke extends upwardly from the connection with the horizontal axis; in the mooring position, the towing yoke extends from the connection with the horizontal axis; An aircraft, characterized in that the towing yoke extends downwardly from the base of the aircraft to enable attachment of the towing yoke to a mooring member for mooring the aircraft to the ground. 2. The traction yoke 140 is curved to match the curve of the spherical balloon, and the outer shape of the spherical balloon 110 and the traction yoke 140 are curved to match the curve of the spherical balloon.
The gap between the adjacent surfaces of the spherical balloon 110
The aircraft according to claim 1, wherein the aircraft is arranged such that the radius is 1/3 or less of the radius of the aircraft. 3. The spherical balloon 110 surrounds the auxiliary air sac 220, and the auxiliary air sac 22 is at a higher pressure than the gas in the balloon.
2. The aircraft according to claim 1 or 2, which is equipped with an air compressor for controlling the buoyancy of the aircraft by supplying outside air to the aircraft.