阅读说明：本技术 飞行器 (Aircraft with a flight control device ) 是由 T·沃贝克 于 2019-07-03 设计创作，主要内容包括：本发明提供一种飞行器(10),该飞行器具有以下特征：该飞行器(10)包括电部件(12,13)和具有冷却盘管(14)的螺旋桨涵道；并且该飞行器(10)被布置成用于将热量从所述电部件(11,12)导出至该冷却盘管。(The invention provides an aircraft (10) having the following features: the aircraft (10) comprises electrical components (12, 13) and a propeller duct with a cooling coil (14); and the aircraft (10) is arranged to conduct heat away from the electrical components (11, 12) to the cooling coil.)

1. An aircraft (10) is described,

it is characterized by the following features:

the aircraft (10) comprises electrical components (12, 13) and a propeller duct with cooling coils (14), and

-the aircraft (10) is arranged for conducting heat away from the electrical components (11, 12) to the cooling coil.

2. The aircraft (10) of claim 1,

it is characterized by the following features:

the aircraft (10) comprising a fuselage (11) and wings (15),

-said electrical components (12, 13) are arranged in the fuselage (11), and

-the propeller duct (14) is arranged in the wing (15).

3. The aircraft (10) according to claim 1 or 2,

it is characterized by the following features:

-the electrical component (12, 13) comprises an inverter (12) and a battery (13).

4. The aircraft (10) according to one of claims 1 to 3,

it is characterized by the following features:

-the aircraft (10) has a fully electric drive.

5. The aircraft (10) according to one of claims 1 to 4,

it is characterized by the following features:

the aircraft (10) comprises a folded or foldable wing (15).

6. The aircraft (10) according to one of claims 1 to 5,

it is characterized by the following features:

-the aircraft (10) comprises a battery system capable of being rapidly charged.

7. The aircraft (10) according to one of claims 1 to 6,

it is characterized by the following features:

-the aircraft (10) comprises a horizontally fixed ducted propeller for takeoff and landing.

8. The aircraft (10) according to claim 7,

it is characterized by the following features:

the aircraft (10) has a plurality of sheets, and

-the horizontal ducted propeller can be selectively covered by means of the sheet.

9. The aircraft (10) according to one of claims 1 to 8,

it is characterized by the following features:

-the aircraft (10) comprises a vertically fixed ducted propeller for generating propulsion.

10. The aircraft (10) according to one of claims 1 to 9,

it is characterized by the following features:

-the aircraft (10) is selectively fully autonomously controllable.

Technical Field

The invention relates to an aircraft, in particular to a fully electric aircraft capable of taking off and landing Vertically (VTOL).

Background

VTOL refers in aerospace technology to, translinguistically, any type of aircraft, drone or rocket capable of being raised and re-landed substantially vertically and without the need for a takeoff and landing runway. This generic term is used broadly hereinafter to include not only fixed-wing aircraft with wings, but also rotary-wing aircraft (e.g., helicopters, autogyres, proprotors) and hybrid aircraft (e.g., compound helicopters or combined gyroplanes) as well as vertically-raisable aircraft. Furthermore, aircraft capable of taking off and landing (STOL) within an especially short distance, taking off but landing vertically (STOVL) within a short distance, or taking off but landing horizontally (VTHL) vertically are also included.

US 20160273448 a1 discloses a ducted propeller turbine propulsion device. The propulsion device comprises an oil circuit with an air-oil cooler. In order to increase the capacity of the cooler, the cooler is equipped with means for injecting water. The thermal capacity of the water enhances cooling, while the extraction of water increases the thrust of the turbine propulsion device.

CN 206939095U seems to disclose a similar arrangement.

Disclosure of Invention

The invention provides an aircraft according to the preferred embodiment, in particular an all-electric aircraft which can be vertically lifted and landed in the above-mentioned manner.

One advantage of this solution is the wide possibility of achieving efficient cooling without aerodynamic losses.

Further advantageous embodiments of the invention are given in the alternative. Thus, for example, the aircraft can be designed with wings that are bent or even selectively bendable. The corresponding variant increases the effective wing area in horizontal flight without extending the footprint of the aircraft.

Furthermore, the aircraft can have a rapidly rechargeable battery system which provides the drive energy for vertical take-off and landing as well as for horizontal flight and makes it possible to charge the aircraft briefly.

In this case, for driving the aircraft, instead of the free rotor, a plurality of ducted propellers (reduced fans) of different sizes can be used, which are known, for example, from hovercraft or fancraft (sumpfborenet) outside the aeronautical arts. In such an embodiment, the cylindrical casing surrounding the propeller can significantly reduce the propulsion losses due to the turbulence at the blade tips. Suitable ducted propellers can be oriented horizontally or vertically, be pivotally embodied between these two positions, or be covered by flaps (lovers) in horizontal flight for aerodynamic reasons. Furthermore, it is conceivable to generate a pure level of propulsion by means of fixed ducted propellers.

Finally, in addition to the preferably fully autonomous operation of the aircraft, it is also conceivable to allow manual control by a human pilot in the case of sufficient qualification, which gives the device according to the invention the greatest possible flexibility in handling.

Drawings

One embodiment of the invention is illustrated in the accompanying drawings and will be described in greater detail below.

Fig. 1 shows a partial cross section of an aircraft according to the invention.

Detailed Description

The sole figure shows the structural features of an aircraft 10 capable of vertical takeoff and landing, designed with ducted propellers 14 integrated with wings 15. There is a highest power demand and thus a maximum cooling demand during vertical flight; in this flight phase, however, the lowest cooling efficiency can be achieved by convection on the outer skin of the aircraft 10, because of the small relative velocity between the ambient air and the aircraft 10. Thus, according to the invention, high wind speeds are utilized in the region of the ducted propellers 14 activated at take-off and landing by placing a cooling structure in the ducted structure. Here, the surface can be implemented largely flat-and therefore aerodynamically optimal-or with cooling fins to maximize the cooling efficiency by laminating the cooling structure into the composite fiber. A heat transfer liquid flows through the cooling structure, which absorbs the heat of the liquid-cooled components, such as the HV battery 13, the converter 12 and possibly the electric motor, and dissipates said heat again via a bypass cooler.

In horizontal flight, liquid is not guided via the propeller duct 14, but rather over a large area via the fuselage 11 or the wings 15 of the aircraft 10. The heat transfer area can thereby be maximized and the waste heat generated in horizontal flight is released to the environment. The cooling structures used for this purpose may likewise be laminated or connected to the inner skin of the fuselage 11 or wing 15 in thermal contact with a filler material or other interface material. Switching to ducted cooling again during the transition to vertical landing flight.

This makes it possible to achieve satisfactory cooling without a significant increase in air resistance.