• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention provides an aircraft (10) with the following features: the aircraft (10) has a short-range radio measuring device (11); and the short-range radio measuring device (11) is set up to recognize a trajectory (12) which is predetermined by a ground station (14) on the basis of a position detection (13) of the aircraft (10).
    公开号:CH715281A2
    申请号:CH00996/19
    申请日:2019-08-07
    公开日:2020-02-28
    发明作者:Fauri Mikel
    申请人:Porsche Ag；
    IPC主号:
    专利说明:

    Description: The present invention relates to an aircraft, in particular a fully electric, vertical take-off and landing (VTOL) aircraft.
    As a VTOL in the aerospace industry any language of aircraft, drone or rocket is referred to, which has the ability to take off and put back on essentially vertically and without a runway. This collective term is used in a broad sense below, which includes not only fixed-wing aircraft with wings, but also rotary-wing aircraft such as helicopters, gyroplanes, flight screwdrivers and hybrids such as compound helicopters or combination screwdrivers and convertible aircraft. Also included are aircraft with the ability to take off and land on particularly short distances (short take-off and landing, STOL), take off on short distances but land vertically {short take-off and vertical landing, STOVL) or take off vertically, but land horizontally (vertical take-off and horizontal landing, VTHL).
    US 5 716 032 A describes an automatic landing system for guiding an unmanned aircraft along a predetermined path to a predetermined point on the ground. The system includes an image processing device in a motion compensation processor that calculates aircraft parameters. These calculations are based on the movement of elements in the video of an imaging sensor on board the aircraft. The motion compensation processor also measures the distance between two beacons that are a known distance apart on either side of the apparent point of impact. A recovery control processor on the ground calculates commands for the autopilot, which corrects the flight path of the aircraft. The video image can either be transmitted to the ground station via a data connection or the image processing can be carried out on board the aircraft.
    A precision aircraft landing approach system according to DE 60106 446 T2 determines the location of the aircraft in real time by measuring an elapsed time between a query and transponder response signal at a plurality of predetermined locations. The system achieves accurate aircraft positioning by measuring the transponder response difference phase to calculate an approach angle.
    The inventive approach is based on the knowledge that vertical landings on small and densely converted landing sites should take place on a precisely specified trajectory in order to prevent collisions with or interference from other users, vehicles, pedestrians, etc.
    The proposed approach also takes into account the fact that high-precision on-board systems for spatial location and understanding of the location are usually difficult and expensive.
    Finally, the invention is based on the insight that the correct approach to certain landing sites - for example helicopter landing sites - should be well known, and it is therefore not necessary for every approaching aircraft to acquire this knowledge automatically. Instead, they only need to be told in a suitable way how to follow the intended trajectory.
    Against this background, the invention provides an aircraft, in particular a fully electric aircraft capable of vertical takeoff and landing in the above sense, according to independent claim 1.
    An advantage of this radar-based detection system is that it makes it easier to use predefined characters and symbols even under the most unfavorable viewing conditions.
    [0010] Further advantageous embodiments of the invention are specified in the dependent claims. For example, the aircraft can be equipped with bent or, optionally, foldable wings. A corresponding variant increases the wing area effective in horizontal flight, but without extending the standing area of the aircraft.
    Furthermore, the aircraft may have a quickly chargeable battery system which provides the drive energy for vertical take-off and landing as well as horizontal flight and enables the aircraft to be charged at short notice while stationary.
    To propel the aircraft, instead of free-running rotors, several ducted fans (ducted fans) of different sizes can also be used, as are known apart from aeronautical engineering, for example from hovercraft or sump boats. In such an embodiment, the cylindrical housing surrounding the propeller can considerably reduce the thrust losses due to turbulence at the blade tips. Suitable jacketed propellers may be aligned horizontally or vertically, designed to be pivotable between the two positions or, for aerodynamic reasons, covered in horizontal flight by slats ilouvers). In addition, a pure horizontal thrust generation by means of fixed jacket propellers is conceivable.
    Finally - in addition to preferably fully autonomous operation of the aircraft - with sufficient qualification, the granting of a manual control to the human pilot is also considered, which gives the device according to the invention the greatest possible flexibility in handling.
    An embodiment of the invention is shown in the drawing and is described in more detail below.
    The figure shows the proposed solution.
    CH 715 281 A2 [0016] The single figure illustrates the structural features of a preferred embodiment of the aircraft (10) according to the invention. The system in the aircraft (10) comprises a short-range radio measuring device (11) directed towards the ground and simple recognition software which interprets predefined symbols and characters, which in turn are read from a ferroelectric liquid display (15) based on the reflection of the radio waves.
    The ground station (14) in turn comprises a system for position detection (13), the combination of sensors of which enables an accurate reading of the position of the aircraft (10) relative to the ground station (14), the liquid display (15) serving as a guide on the ground as well as a suitable control.
    The system of the ground station (14) for position detection (13) recognizes with high accuracy the relative position of the aircraft (10) in relation to the ground station (14). Such a positioning system can be a combination of different sensors (camera, radar, lidar, etc.), which may be arranged differently in order to improve the accuracy of the position detection (13). This sensor assembly does not have to be light or energy-saving and can therefore be manufactured inexpensively.
    The control of the ground station (14) stores a predefined trajectory (12) for the approach. By comparing this flight path (12) and the current position of the aircraft (10), the control calculates the required movements of the aircraft (10) together with their speeds in order to follow the flight path (12). The respective direction of movement and their speed are shown on the liquid display (15) by corresponding direction arrows or numbers. The short-range radio measuring device (11) reads said characters and numbers and transmits them to the flight controller, which reacts accordingly.
    权利要求:
    Claims (10)
    [1]
    Claims
    1. Aircraft (10), characterized by the following features:
    - The aircraft (10) has a short-range radio measuring device (11) and
    - The short-range radio measuring device (11) is set up to recognize a trajectory (12), which is predetermined by a ground station (14) on the basis of a position detection (13) of the aircraft (10).
    [2]
    2. Aircraft (10) according to claim 1, characterized by the following features:
    - The aircraft (10) further comprises recognition software for laying out certain symbols and the trajectory (12) is predetermined by the symbols.
    [3]
    3. Aircraft (10) according to claim 2, characterized by the following features:
    The post-range radio measuring device is set up to read the symbols from a ferroelectric liquid display (15) and
    - The trajectory (12) is specified by means of the liquid display (15).
    [4]
    4. Aircraft (10) according to one of claims 1 to 3, characterized by the following feature:
    - The aircraft (10) has a fully electric drive.
    [5]
    5. Aircraft (10) according to one of claims 1 to 4, characterized by the following feature:
    - The aircraft (10) comprises kinked or kinkable wings.
    [6]
    6. Aircraft (10) according to one of claims 1 to 5, characterized by the following feature:
    The aircraft (10) comprises a quick-charge battery system.
    [7]
    7. Aircraft (10) according to one of claims 1 to 6, characterized by the following feature:
    - The aircraft (10) comprises horizontally fixed jacketed propellers for take-off and landing.
    [8]
    8. Aircraft (10) according to claim 7, characterized by the following features:
    - The aircraft (10) has fins and
    - The horizontal jacket propellers can be covered with the slats.
    [9]
    9. Aircraft (10) according to one of claims 1 to 8, characterized by the following feature:
    - The aircraft (10) comprises vertically fixed jacket propellers for generating propulsion.
    [10]
    10. Aircraft (10) according to one of claims 1 to 9, characterized by the following feature:
    - The aircraft (10) can optionally be controlled fully autonomously.
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    同族专利:
    公开号 | 公开日
    FR3085083A1|2020-02-21|
    CN110844098A|2020-02-28|
    US20200122829A1|2020-04-23|
    DE102018120198A1|2020-02-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    AT515456B1|2014-02-18|2018-04-15|Iat 21 Innovative Aeronautics Tech Gmbh|aircraft|
    US9856018B2|2016-01-11|2018-01-02|The Boeing Company|Ducted fan doors for aircraft|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018120198.2A|DE102018120198A1|2018-08-20|2018-08-20|aircraft|
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