FR3062370A1 - AIRCRAFT - Google Patents

Abstract

Aircraft not using thermal energy, capable of traveling considerable distances, (approximately 5,000 km at a speed of approximately 100 km / h with 2 pilots) having propeller electric motors, (30) -, for traction, and motors (31) for vertical movement, operating by the energy provided by the photovoltaic panels, placed on the wings (7) and (11) and above the casing (2) - and thanks to the energy provided by the accumulators placed inside the fuselage (1) and having helium reservoirs (3) contained in the casing (2) to provide lift. The invention consists in that this aircraft has no landing gear, nor mooring mat for its shelter in a shed. The landing is carried out by using the mooring rings (21) placed in the mooring plates (18) placed under the fuselage (1), and into which the locks (22) placed on the landing platform ( 27). It rotates about the axis (36) placed on the transport platform (29) by a crown system, toothed (32) and the motor (33) carried on the transport platform (29) .- in order to present the fuselage in front of the hangar door without dangerous maneuvers -, the platform (29) is towed to the inside of the hangar

Description

Holder (s):

BENATAR MARCOS.

BENATAR MARCOS.

Agent (s): nyme.

CABINET BOETTCHER Société ano © AERONEF.

©) Aircraft not using thermal energy, able to travel significant distances, (around 5,000Km at a speed of around 100Km / h with 2 pilots) having electric propeller motors, (30) -, for traction, and motors (31) - for vertical movement, operating thanks to the energy supplied by the photovoltaic panels, placed on the wings (7) and (11) and above the envelope (2) - and thanks to the energy supplied by the accumulators placed inside the fuselage (1) and having helium tanks (3) contained in the envelope (2) to ensure the lift.

The invention consists in that this aircraft does not have a landing gear or a mooring mast for sheltering in a hangar. Landing is carried out using the mooring rings (21) placed in the mooring plates (18) placed under the fuselage (1), and into which the latches (22) placed on the landing platform ( 27). The latter pivots around the axis (36) placed on the transport platform (29) by a system of crown, toothed (32) and of the motor (33) carried on the transport platform (29). in order to present the fuselage in front of the hangar door without dangerous maneuvers -, The platform (29) is towed to the inside of the hangar

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BENATAR

Marcos

Page 1

PRESENTATION

The present invention relates to:

An aircraft that will not use thermal energy

Aircraft having photovoltaic panels and helium reservoirs capable of traveling long distances, for example 5,000 km, with at least 2 pilots, and a speed of approximately 100 km / h, capable of landing on a truck trailer, capable of use without significant modifications, different energies as they are applied industrially

The device will be powered by photovoltaic electric energy

Today solar-powered aircraft have either a short range or a total lack of comfort for the pilot in the search for the greatest possible lightness of the aircraft.

The solar plane, Solar Impulse, becomes a benchmark in solar energy The high quality of the experience - Solar Impulse - was to demonstrate in July 2015 that transoceanic flight - Japan - Hawaii - 7,100 km— was possible, at using only solar energy supplied by the photovoltaic panels placed on the ... wings and stored in the aircraft's accumulators.

However, this flight, which lasted 120 hours, demonstrated the limit of human resistance. The pilot, confined to a tiny cabin arrived exhausted.

Indeed the solar energy is stored and transmitted to the engines by accumulators, which today are still heavy .. As the design of Solar Impulse requires maximum lightness, the accumulators of this device were reduced, and did not allow the era of providing enough power to transport two pilots

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The device I offer is different

Description:

It is an airplane which will be able to fly without thermal energy, but with solar energy, supplied by photovoltaic panels - by having enough accumulators to supplement the solar energy in order to have in complete safety a flight over a long distance , but having helium tanks to ensure all or part of the lift

The energy necessary to obtain the flight of an airplane is intended for lift - balancing the weight of the aircraft and for thrust - ensuring the movement of the airplane in the air, balancing the drag. lift - on takeoff - requires the maximum energy from an airplane's engines, however moving through the air for level flight requires only around 30% to 40% of the engine power.

In the device presented, the lift will be given in large part by helium tanks capable of balancing the weight, or part of the weight of the device. Thus the energy obtained by solar panels and the energy supplied by Li-Po accumulators (or others) will be used mainly for the movement of the device, in the air, in level flight.

The aircraft is an airplane with wings covered with photovoltaic panels The search to conserve all the energy for the movement of the aircraft, flight, of course requires the lightness of the aircraft.

This leads to the elimination of the on-board landing gear, which is a heavy device because it is robust to ensure a safe landing.

The landing of the aircraft and its movement on land will be ensured by truck trailers adapted to the aircraft - allowing shelter in a normal airport hangar. - This system can be used by an airship. he device in the vertical plane is produced by two vertical electric motors. : they are necessary to guide the aircraft exactly in the vertical direction at takeoff and landing., and for the different phases of a long distance flight., (level flight, ascent, level etc ...)

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The apparatus representing the invention consists of

Plate 1 - Figure 1 a carbon fiber fuselage (1) carrying on each side the helium tanks (3) contained in a carbon fiber envelope (2), which has the shape of a large airplane wing carrier

Each of the helium tanks has air balloons for controlling the gas pressure. The action of the balloons is controlled by the pilot.

The envelope (2) carries the intrados flaps (4) necessary for the flight.

At the front of the fuselage (1) - and at the top is the cockpit (5) because the underside of the aircraft must be free, for the landing maneuver.

Above the fuselage (1) are the supports (6) of the main wing (7)

The wing (7) carries photovoltaic panels (8).

Above the fuselage (1) are the masts (9) and (10) carrying the shrouds which support the wing. (7)

At the rear of the fuselage is the secondary wing (11) which carries photovoltaic panels.

At the rear of the fuselage (1) are placed the masts (12) and (13) carrying the shrouds supporting the rear wing (11)

These guys are useful because the wings ailes (front and rear) support the motors

Photovoltaic panels are placed above the envelope (2) which contains the helium tanks (3) on either side of the fuselage (1)

At the rear of the fuselage (1) are placed the aircraft fin (17) and the ailerons (18) - necessary for piloting the aircraft.

Plate 2 — Figure 2

The main wing (7) carries the photovoltaic panels (8) On the fuselage (1) are the masts (9) and (10) carrying the shrouds supporting the wing. On the wing (7) are fixed the 4 electric motors (30 -) - (30-1-2-3-4) 3062370

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Plate 2 Figure 2

Inside the fuselage (1) are placed the electric accumulators (16)

The envelope (2) of the helium tanks (3) is covered with photo voltaic panels (15)

The secondary-rear wing - (11) carries the 2 vertical motors (31) (31-1, 31-2) and the photovoltaic panels (14)

The guy lines (12) and (13) are attached to the fuselage.

Plate 3 ..... Figure 3

Under the fuselage (1) are 2 mooring plates (18) and (19) - each having for example, 6 mooring rings (20) and (21) -The mooring plates can rotate -90 ° for landing.

Plate 3 ------- Figure 4

The mooring plates are vertical in order to present the mooring rings (21), - in front of the mooring locks (22) of the landing trailer

Plate 4 ------ Figure (5)

For landing the aircraft uses the 2 vertical motors (31) to position the aircraft exactly. The device is guided by photocells and by the pilot Board 4 — Figure (6)

Each ring (21) corresponds to a lock (22) fixed on the platform (27)

Inside a mooring ring (21) penetrates the mooring latch (22) composed of a steel rod fixed to the rack (23)

The rack (23) is controlled by the pinion (24) driven by an electric motor (25) The mooring platform (27) is placed on the traction platform (29) by ball bearings (35)

The platform (27) rotates about an axis (36) fixed on the transport platform (29)

The mooring platform (27) has a ring gear (28)

Plate 5 ----- Figure (7)

The mooring platform (27) has its ring gear (28) which is actuated by the pinion (32) driven by an attached electric motor (33). on the traction platform (29). which is used to move the device ashore

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Plate (5) -—Figure (7)

The wings of planes using photovoltaic panels are generally very long in order to put the maximum of panels. The wingspan may be too large to enter a regular airliner hangar. In this case it is necessary to enter the device through the fuselage usually shorter

The pinion (32) placed on the transport platform (29) acts on the ring gear (28) of the platform (27), in order to place the fuselage in the exact position necessary on the traction platform (29), to enter in the hangar (35), whatever the orientation of the aircraft on landing on the platform (27) Board (6) ----- Figure (8)

The aircraft can enter the hangar without tractor operations.

Trailer handling for this type of very large aircraft can be reduced. With this system, this aircraft does not require a landing strip in very good condition, nor specially equipped. You just need to have enough road for the tractor. Without any other. infrastructure it is possible to maintain the device on the ground, passing ropes (slings) through the rings (20) - (21)-restrained by concrete blocks or tree trunks.

Plate (6) ----- Figure (9)

On each of the main and secondary wings (7) and (11) carrying the solar panels (8) a system of jacks (36) makes it possible to place the solar panels around the axis (37) at an angle perpendicular to the sun. This system is automatic or controlled by the pilot.

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Technical realization of the proposed aircraft

The aircraft will not use thermal energy, but the energy given by its photovoltaic panels and in addition, the energy supplied by lithium-polymer batteries. Of course there are (and there will be soon) more powerful batteries, but these Li-Po batteries are used by millions of copies and offer the necessary security.

In the exemplary embodiment, the aircraft presented will have to travel approximately 5,000 km at a speed of 60 kT (100 km / hour) - with 2 pilots taking turns in the cabin (5) for a comfortable flight., (50 hours flight ). The cabin will be pressurized.

Technical data used:

Photovoltaic energy requires large areas. In order to carry the maximum number of cells, this aircraft will have two large surface wings. : a main wing, (7) of length 70 meters and width 6 meters which will carry the 4 traction motors (30) and a rear wing (l 1) of 60 meters by 6 meters which carries the 2 vertical motors (31) helium tanks, (3) - placed inside the pressurized envelope (2) on either side of the fuselage (1) -, are necessary in this device in order to have a lift capable of balancing all or part of the weight of the device in order to reserve the maximum power of the motors for level travel.

The solar energy received (calculated as the average of the energy received in 24 hours) is 250 watt: m ² . But you have to take into account the yields of the various components of the energy chain

Indeed, the final yield of photovoltaic energy reaching the accumulators is 0.22, - The efficiency of the accumulators is 0.96—

Electric motors have an output of 0.80, and that of propellers with large blades powered by motors, is 0.70 .......

Ultimately the final yield - usable - in the traction of this aircraft, is 0.12 That is to say that for 1 square meter of photovoltaic panel, the usable energy is 250 watt / m ² x 0, 12 = 30 watts / m ² ....

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A) To keep all the energy available for level flight, that is to say to obtain the lift balancing the weight of the aircraft, helium tanks are used (3). lighter than air, which, in application of the Archimedes principle - in the air - makes it possible to support an aircraft, such as for example, a balloon or an airship. A volume of 1 m3, of Helium allows to balance a mass of 1 Kg: To balance a mass of 1000 Kg it is necessary

1000 m 3 of helium.

B) To use photovoltaic energy and provide additional energy, as a first approach, batteries (16) Lithium-polymer - (- Li-po—) are used, produced in millions of copies worldwide, and having good reliability. These Li-po accumulators, provide 30 watt / hour for 1 Kg of accumulator - for l.OOOKg of accumulator, there is therefore available 30 KWh

The device

The airplane studied must perform a flight of 5000 km to 50 km / hour, with electric motors and at least two pilots taking turns for a "comfortable" flight

An airplane requires two energies to fly:

The energy to get lift - balancing the weight of the device

The energy to obtain the traction - balancing the drag of the device, In all cases it is the lift which requires the most energy Thus for 100 KW supplied by the motors, the traction will only use 40% power between 30 and 40 KW.

For example - Solar Impulse - has 4 motors of 10 KW each, (40 KW) but only uses 7 KW - in level flight, (approx. 20% of the power - motors -) - because this device was designed in the extreme search for lightness - An airplane with a 100KW motor would use only 20 KW in level In the project presented the calculation will be made on 50 KW in order to avoid any dangerous situation ----- (for 4 motors each 40 KW) -

The energy that will be used by 1 device during the journey from 5000 km to 100 km / hour in level only, could be 50 KW per hour, for 50 hours.

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The energy required would be 50 hours x 50 KW = 2500 KWh.

The construction of the device presented makes it possible to use a volume on each side of the fuselage (1) made of carbon fiber, an envelope (2) 32 m long by 20 m wide and 8 m high, i.e. a volume of 32 x 20 mx 8 m = 5160 m 3 on each side of the fuselage.

It is possible to accommodate helium tanks on either side of the fuselage

The helium tanks, can be of cylindrical shape each, for example

6m wide x 6m high x 30m long, or 1,080 m3 each.

It is therefore possible to accommodate 4 tanks on each side

These 8 helium tanks are stored in the wing-shaped envelope (2) and in carbon fiber (the envelope is pressurized), that is to say 32 m long x 20 m wide on each side of the fuselage. / 1)

This envelope is covered with photo voltaic panels (15), in order to obtain the most surface for solar energy.

Photovoltaic panels

The photovoltaic cells will be placed on the surface of the front wing, either a panel 65 m long by 5 m wide = 325 m ² from the rear wing, or a panel 40 m long by 5 m wide = 200 m ² of the envelope of the helium tanks, i.e. 2 panels of 25 m = 700 m ² x ² = 1400 m ² 1400 m ²

This gives a surface of: 1925 m ² of panels that can provide usable power: (30 watt per: m ² ,) of 1925 m ² x30w = 57.75 Kwh

By applying a safety coefficient of 30% the total useful solar energy is 40 kW per hour

For 50 hours the energy supplied by the solar panels is

40kwx 50h = 2000 KWh - out of a total necessary of 2500 kWh for level flight

The system weights:

The total energy requirement being 2500 KWh, it will be necessary to use in addition 1 energy supplied by accumulators either 500 KWh at the rate of 300 wh per kg or a accumulator weight of: (approx.) 1660 Kg

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Page 9

Today it is possible to have solar panels on light panels in - monocrystalline - weighing 1 Kg per m ² .

For 2025 m ² of panels the weight would be 2025 Kg

The weight of the fuselage which appears as a tube 60 m long by 8 meters side x 8 m high), or 2048 m ² in carbon fiber, at 1 Kg per m ² , or: 2408 Kg

The weight of the envelopes of helium tanks, i.e. two parallelepipeds of 32 meters long, 28 m wide and 7 m high, of total surface

2632 m ² , carbon fiber at 1 Kg / m ²

The weight of the 6 motors of 40 KW each

The weight of the wings carrying the solar panels, i.e. front wing of 70m x 6m = 420 m ² rear wing 60 mx 6m - 360 m ²

780 m ² of carbon fiber at lkg / m ² or 780 kg = the weight of the pilots and accessories

The weight of the aircraft presented would be 10,525 Kg

2.632 Kg

300 kg

780 kg

1000 Kg

However, the lift of the 8 helium tanks of each 1.080 m3 (8.000 Kg) will make it possible to obtain an aircraft whose mass in vertical movement would be

10.525Kg -8000 Kg = 2.525 Kg

The plane must have sufficient energy for the displacement, of 2525 Kg

For take-off: the power of 2 vertical motors of 40 KW each is sufficient

For level flight the power of 50 KW is also sufficient.

(on a total power of the 4 motors of 40 KW each = 160 KW) For a long distance flight made of ascending journeys then journeys in stages, it is possible to operate the 2 vertical motors of 40 KW each.

(which will of course be used during takeoff and landing, to present the aircraft in front of the landing platform)

Takeoff can be done with the power of 80 KW from the 2 vertical motors sufficient for a lifting mass of 2525 Kg

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Landing On the proposed aircraft, there is no landing gear

The landing will be carried out on a platform driven by a tractor on the ground.

For landing, the vertical motors (31-) are in action.

Under the fuselage, there are two mooring plates (19) (20) which will be opened at 90 °. These mooring plates are located under the fuselage (on either side of the aircraft's center of gravity). They can be 15 meters long, each having 6 rings (20) and (21) of 1 meter diameter mooring

Each mooring ring corresponds to a mooring lock. The mooring lock is a steel rod 2 meters long (22) fixed on the rack (23) actuated by the pinion (24) driven by the electric motor. (26). placed on the platform (27) Cells allow precise adjustment. In addition there are twelve mooring rings, and it suffices to place a single lock to hold the plane on the platform

Transport in the garage shed - Plate (6) Figure (8)

In planes with wings with photovoltaic panels have very large wings which do not allow entry into a usual hangar

On the other hand the fuselage is shorter and the plane will penetrate by the fuselage

The plane being placed on the platform (27) it is necessary to give it the position allowing to present the fuselage perpendicular to the entry of the hangar (35)

The platform (27) rotates around an axis placed on the traction platform (29) It has a ring gear (28) driven by the pinion (32) of the electric motor (33) fixed on the transport platform (29) .

The platform (27) can be 25 meters long by 8 meters wide. The traction platform (29) can be manufactured like a truck trailer, driven by a conventional airport tractor.

If there is no truck or platform available, the plane can be moored simply by passing through the rings a rope (sling) fixed to the ground by breeze blocks or even a tree trunk

The photovoltaic panels can be tilted to be perpendicular to the sun, according to the pilot's order.

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It should be noted that the wingspan for Airbus A350 is 60 meters and for a Boeing 747, 64 meters which indicates that the wing width of the proposed aircraft is too large for hangars prevalent in the world (The international regulations limit the width of hangars to 80 meters.) The plane being placed on the mooring platform (27) it must be given the position allowing the fuselage to be presented perpendicular to the entrance to the hangar (35) which will allow hangaring at all international airports.

The platform (27) rotates around an axis (36) placed on the traction platform (29) It has a ring gear (28) driven by the pinion (32) of the electric motor (33) fixed on the transport platform (29).

The platform (27) can be 25 meters long by 8 meters wide. The traction platform (29) can be manufactured like a truck trailer, driven by a conventional airport tractor.

If there is no truck or platform available, the aircraft can be moored simply by passing through the rings (21) a rope (sling) fixed to the ground by concrete blocks or even by tree trunks .

Plate 6 - Figure 9

The photovoltaic panels (8) can be tilted. They ^A pivot around the axis (38) to be perpendicular to the sun, according to the pilot's command, or automatically thanks to the jack (37)

The envelope (2) containing the helium tanks will be pressurized, to avoid helium leaks

It should be noted that in the aircraft presented the envelope (2) of the helium tanks has a volume of 5160 m3 on each side of the fuselage, that is to say a total volume of 10.320 m 3 which would be sufficient to ensure the lift of the 'device. (10125 Kg)

This option can be considered, but the option of 8 tanks offers more security by avoiding the theft in dead leaf

Pilots with cockpit (5) pressurized this device will allow a long distance flight (5,000 km) without difficulty for the crew.

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Note on possible adaptations on this device

The design of this device provides an interesting volume in the fuselage for present and future accumulators

For example, aluminum accumulators (already at the start of production) will have. 2000 wh per kg ..! The available volume in the fuselage (1) of the aircraft is today for 1,600 kg in Li-po batteries providing 500Kwh.

With the same weight in aluminum accumulators it would be possible to have 3,200 kWh? ! Thus, while retaining the need for 500 KWh, the weight of aluminum accumulators would only be 250 kg. On the other hand, if a weight of 1,600 kg is kept in the weight estimate for accumulators, aluminum accumulators will allow flight, with a longer range

Note on nuclear micro-plants usable in the near future

One gram of uranium provides 69 times more energy than 1000 grams of kerosene. The aircraft presented has been calculated for a power of 4 horizontal engines of 40 KW each and 2 vertical engines of 40 KW each, that is to say 240 KW.

Today an aircraft using a power of 240 KW will use (at most) liters of kerosene per 100 Km For 5000Km, the engines will use 1500 liters of kerosene (or 1275 KG.) This corresponds to slightly less than the energy supplied per gram uranium, (replaced today by thorium, less irradiating) By adding the energy supplied by the solar panels of the device - without any other modification of the device, - we have 42 KW (solar) +240 KW nuclear Or 282 Kw while the device only needs 160 KW ... (total of engines) and would only use 50 KW in level.

Mini nuclear power plants exist. The device could use a micro power plant An American firm is already producing mini power plants intended for small towns of 20,000 inhabitants, with a diameter of 2 meters by 4 meters in height.

the fuselage (1) of the aircraft has a sufficient dimension ... So without major modifications and in the fairly near future, the proposed aircraft could be equipped with a micro-central

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A micro-power plant of 20 grams of thorium / or another Sssible material (non-irradiating) installed in the fuselage of the aircraft with the necessary protections, would weigh a maximum of 1 ton.

By retaining the dimensions of the device proposed above, and by combining the advantages of a micro nuclear power plant as well as (your accumulators of the future, the aircraft will have a greater range of action or even a greater possibility in weights transported

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Claims (6)

1) Aircraft allowing a flight up to 5,000 km or more, with 1, or 2 pilots or more, without thermal energy, characterized in that the movement of the device is ensured by electric motors, using the electric energy supplied by accumulators (16) contained in the fuselage (1), powered by the photovoltaic panels placed on the surface of the wings (8) and on the surface of the envelope (2), containing the helium tanks (3) which contribute to the lift of the device. 2) Aircraft according to claim - (1) - characterized in that there is no landing gear, and that the landing is done by opening the mooring plates (18) at 90 ° and ( 19) arranged under the fuselage (1) and which each carry the mooring rings (20) - (21). 3) aircraft according to claim - (2) - characterized in that the landing can be done on the mooring platform (27) which carries a system of locks each composed of a steel rod (22) carried by a rack (23) driven by the pinion (24) of the motor (25) and which enters the corresponding mooring ring (21) 4) aircraft according to claims - (1) and (2) -, characterized in that in the absence of ground infrastructure, using the equipment in mooring rings (20) and (21) on the mooring plates (18) and (19), it will be possible to hold the device on the ground by slings, passed through the rings (20) and (21) and fixed to the ground by breeze blocks or trunks of trees. 5) aircraft according to claim - (3) -, characterized in that the mooring platform (27) has a ring gear (28) driven by the pinion (32) of the motor (33) allowing it to rotate around the axis (36) fixed on the transport platform (29) which is driven by an airport tractor to take the exact place in the hangar without difficult maneuvers. 6) Aircraft according to claims - (1) and - (2) -, characterized in that, by its design, it will be able to use the new technologies in accumulators and in nuclear micro-plants without major modifications 1/6 PLATE 1 2/6 PLATE 2 PLATE 3 4/6 PLATE 4 5/6 PLATE 5 6/6