阅读说明：本技术 飞行器 (Aircraft with a flight control device ) 是由 M·福里 于 2019-07-04 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：所述飞行器(10)包括巡航螺旋桨(11)、升降螺旋桨(12)、能量电池(13)、以及功率电池(14)；所述能量电池(13)与所述巡航螺旋桨(11)电连接；所述功率电池(14)与所述升降螺旋桨(12)电连接。(The invention provides an aircraft (10) having the following features: the aircraft (10) comprises a cruise propeller (11), a lifting propeller (12), an energy battery (13) and a power battery (14); the energy battery (13) is electrically connected with the cruise propeller (11); the power battery (14) is electrically connected with the lifting propeller (12).)

1. An aircraft (10) is described,

it is characterized by the following features:

-the aircraft (10) comprises a cruise propeller (11), a lift propeller (12), an energy battery (13), and a power battery (14),

-the energy battery (13) is electrically connected to the cruise propeller (11), and

-the power battery (14) is electrically connected with the lifting propeller (12).

2. The aircraft (10) of claim 1,

it is characterized by the following features:

-the aircraft (10) additionally comprises a battery backup (15), and

-the backup battery (15) is also electrically connected to the lifting propeller (12).

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

it is characterized by the following features:

-the aircraft (10) additionally comprises a direct voltage converter (16), and

-the direct voltage converter (16) electrically connects the energy battery (13) at least with the power battery (14).

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 bent or bendable wing.

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 (13, 14, 15) 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 fan propeller for take-off and landing.

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

it is characterized by the following features:

-the aircraft (10) has a plurality of panels, and

the horizontal ducted fan propeller can be selectively covered by means of the blades.

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 fan 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 completely 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 rotorcraft (e.g., helicopters, autogyres, proprotors) and hybrid aircraft (e.g., compound helicopters or combined gyroplanes) as well as convertible aircraft. Furthermore, aircraft capable of taking off and landing (STOL) within an especially short distance, taking off within a short distance but landing vertically (STOVL), or taking off vertically but landing horizontally (VTHL) are also included.

CN 106981914 a discloses a two-battery based energy control method and system supported by a vehicle. The vehicle is switched among a normal mode, a recovery mode, a standby battery charging mode or an isolation mode according to the vehicle state, wherein in the normal mode, the vehicle load is supplied with current by the first battery; in a recovery mode, simultaneously charging the vehicle load, the first battery and the second battery by the current generator; charging, by the power generator, the second battery in a backup battery charging mode; and in the isolated mode, delivering power for the vehicle load by the first battery and for starting the engine by the second battery. Corresponding to different power requirements under various operating conditions, the battery should therefore be charged and discharged efficiently throughout the operating cycle.

EP 2592686B 1 describes a control system for controlling the operation of batteries connected to an electrical power network, having a plurality of batteries arranged on the electrical power network and a control device which determines the individual charge and discharge rates of the individual batteries by means of demand prediction on the basis of the battery charge and the energy supply.

DE 4118594C 1 proposes, for electric vehicles, a combination of a high-power battery, which has a relatively high specific energy content, such as a nickel/cadmium battery, or a sodium/sulfur battery, or a zinc/bromine battery, as a large energy accumulator, with a smaller battery of the same voltage, which has a smaller specific energy content, but a relatively high power with respect to its weight and a significantly smaller cost performance, such as a lead gel battery or a high lead-acid battery.

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.

A particular advantage of the present solution is that the battery system of the aircraft according to the invention has a small installation space and weight.

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 fan propellers (ducted fans) of different sizes can be used, which are known, for example, from hovercraft or fancraft (sumpfboroten) outside the field of aeronautics. In such an embodiment, the cylindrical housing surrounding the propeller can significantly reduce the propulsion losses due to turbulence at the blade tips. Suitable ducted fan propellers can be oriented horizontally or vertically, be embodied pivotably 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 a fixed ducted fan propeller.

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.

The figures show a highly simplified block diagram of an aircraft.

Detailed Description

The single figure schematically shows the structural features of a preferred embodiment of the aircraft 10 according to the invention, the hybrid battery system 13, 14, 15 of which is divided in a visible manner into a plurality of sub-batteries which are adapted to different flight phases. The energy battery 13, which is designed to the maximum possible energy density, is used to drive the cruise propeller, while the power battery 14, which is optimized with regard to the short-term power output and is supported by parallel-connected battery backups 15 when required, supplies the lifting propeller 12, in particular for taking off and landing.

A dc voltage converter 16, which is dimensioned appropriately, connects the energy cell 13 described in the present embodiment to the power cell 14 and the battery backup 15, so that the latter can be recharged by the energy cell 13 during cruising flight. At the same time, it should be understood that the electrical connection provided with the reference numeral 17 can also be omitted in an alternative embodiment if it appears that during flight it is not necessary to recharge the backup battery 15.