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DE102005003028A1 - Rotor arrangement for model or micro helicopter has main rotor with further drive rotors connected rigidly or vertically adjustable for fixing immovable anywhere along relevant motor on drive sleeve - Google Patents

Rotor arrangement for model or micro helicopter has main rotor with further drive rotors connected rigidly or vertically adjustable for fixing immovable anywhere along relevant motor on drive sleeve Download PDF

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Publication number
DE102005003028A1
DE102005003028A1 DE102005003028A DE102005003028A DE102005003028A1 DE 102005003028 A1 DE102005003028 A1 DE 102005003028A1 DE 102005003028 A DE102005003028 A DE 102005003028A DE 102005003028 A DE102005003028 A DE 102005003028A DE 102005003028 A1 DE102005003028 A1 DE 102005003028A1
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DE
Germany
Prior art keywords
rotor
rotors
control units
main rotor
rotor arrangement
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
DE102005003028A
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German (de)
Inventor
Ruediger Ufermann
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Individual
Original Assignee
Individual
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Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to DE102005003028A priority Critical patent/DE102005003028A1/en
Publication of DE102005003028A1 publication Critical patent/DE102005003028A1/en
Withdrawn legal-status Critical Current

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Classifications

    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H27/00—Toy aircraft; Other flying toys
    • A63H27/12—Helicopters ; Flying tops
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/80—UAVs characterised by their small size, e.g. micro air vehicles [MAV]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/60—UAVs characterised by the material
    • B64U20/65—Composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

The rotor arrangement has a main rotor (6) and control units (A,B,C) or further drive rotors which have rotor-integral drive sleeves (7,11). The main rotor or other drive rotors can be connected rigidly or vertically adjustable so that they can be fixed immovable anywhere along the relevant motor (8) on the drive sleeve. The rotors of the control unit are offset outwards axially concentric so that they are no longer affected aerodynamically by the air throughput of the main rotor whereby all the rotors can also lie in one plane or in a plane above the main rotor.

Description

Die Erfindung betrifft eine Rotoranordnung für einen Modellhubschrauber oder Mikrohubschrauber nach dem Oberbegriff des Hauptanspruchs (1).The The invention relates to a rotor assembly for a model helicopter or micro helicopter according to the preamble of the main claim (1).

Im Stand der Technik werden Ausführungsformen verschiedenartiger Rotoranordnungen beschrieben.in the The state of the art becomes embodiments various rotor assemblies described.

Aufgabe der Erfindung ist es eine Rotoranordnung vorzustellen, deren Eigenschaften ein stabileres aerodynamisches Verhalten erwarten lassen.task The invention is to present a rotor assembly whose properties to expect a more stable aerodynamic behavior.

Diese Aufgabe wird durch eine Rotoranordnung nach den Merkmalen des Anspruchs 1 gelöst.These The object is achieved by a rotor assembly according to the features of the claim 1 solved.

In folgendem wird die Erfindung anhand eines bevorzugten Ausführungsbeispiels in Verbindung mit zwei Zeichnungen beschrieben. Dabei zeigt:In The following is the invention with reference to a preferred embodiment described in conjunction with two drawings. Showing:

1. eine vereinfachte Draufsicht auf die Rotoranordnung im Einsatz mit Mikrohubschrauber (1). 1 , a simplified plan view of the rotor assembly in use with micro helicopter ( 1 ).

2 eine vereinfachte Vorderansicht des Mikrohubschraubers (1) nach 1. 2 a simplified front view of the micro helicopter ( 1 ) to 1 ,

Erfindungsgemäß weist der Hauptrotor (6) des Mikrohubschraubers (1) bzw. Modellhubschraubers die Antriebshülsen (7, 11) auf, die an ihren oberen Enden mit der Achse des Motoren (8, 3...n) form- oder kraftschlüssig verbunden sind, so dass der Hauptrotor (6) bzw. die Steuerrotoren (2...n) je nach Bedarf mehr oder weniger weit in Längsrichtung über den Motor geschoben werden können. wobei durch diese Masseverlagerung eine verbesserte spezifische aerodynamische Eigenstabilität mit erhöhter Flugbeherrschbarkeit erreicht werden soll. Alle Rotoren werden in Bezug auf ihre Lage in Längsrichtung zu den jeweiligen Motoren so platziert, dass das günstigste Gesamtmoment bezogen auf die Gesamtkonstruktion erreicht wird. In einer ersten Ausführungsform bestehen die Rotoren aus einem kohlefaserverstärktem Kunststoff mit integralen Antriebshülsen.According to the invention, the main rotor ( 6 ) of the micro helicopter ( 1 ) or model helicopter the drive sleeves ( 7 . 11 ) at their upper ends with the axis of the engines ( 8th . 3 ... n) are positively or non-positively connected, so that the main rotor ( 6 ) or the control rotors ( 2 ... n) can be pushed more or less longitudinally over the engine as needed. whereby an improved specific aerodynamic inherent stability with increased controllability over the air is to be achieved by this mass displacement. All rotors are placed with respect to their position in the longitudinal direction of the respective motors so that the most favorable total torque is achieved based on the overall construction. In a first embodiment, the rotors consist of a carbon fiber reinforced plastic with integral drive sleeves.

Die Steuereinheiten (A, B, C) mit den Steuerrotoren (2...n) und den Motoren (3...n) sind identisch aufgebaut und unterhalb oder oberhalb des Rumpfes (5) aus kohlefaserverstärktem Kunststoff mit den luftdurchlässigen Öffnungen (10) in präformierten Montagevorrichtungen platziert. Der Rumpf (5) kann auch kreisförmig ausgebildet sein und mit einem ovalförmigen Schutzgitter (30) versehen werden, wobei die Landevorrichtung (20, 21, 22) dann entfallen kann. Falls gefordert können die Steuereinheiten (A, B, C) so weit nach außen bzw. – auch in einer Ebene – verlagert werden, dass eine gegenseitige aerodynamische Beeinflussung praktisch nicht mehr gegeben ist. Die Motoren der Steuereinheit (A, B, C) und der Motor (8) werden über eine zentrale Steuerlogik geschaltet und ferngesteuert, wobei die Elektronik und die Energieversorgung in präformierten Teilen des Rumpfes (5) verlierungssicher eingebracht werden können. Der Mikrohubschrauber (1) kann mit optischen Systemen zur Umgebungsbeobachtung ausgestattet werden und auch als VTOL bzw. UAV eingesetzt werden.The control units (A, B, C) with the control rotors ( 2 ... n) and the engines ( 3 ... n) are identically constructed and below or above the fuselage ( 5 ) made of carbon fiber reinforced plastic with the air-permeable openings ( 10 ) are placed in preformed fixtures. The hull ( 5 ) may also be circular and with an oval-shaped protective grid ( 30 ), the landing device ( 20 . 21 . 22 ) can then be omitted. If required, the control units (A, B, C) can be displaced so far outward or - even in one plane - that a mutual aerodynamic influence practically no longer exists. The engines of the control unit (A, B, C) and the engine ( 8th ) are switched via a central control logic and remotely controlled, whereby the electronics and the power supply in preformed parts of the fuselage ( 5 ) can be introduced safely. The micro helicopter ( 1 ) can be equipped with optical systems for environmental observation and can also be used as a VTOL or UAV.

11
Mikrohubschraubermicro helicopter
22
Steuerrotorcontrol rotor
33
Motorengine
44
Drehrichtungdirection of rotation
55
Rumpfhull
66
Hauptrotormain rotor
77
Antriebshülse drive sleeve
88th
Motorengine
9 9
Drehrichtungdirection of rotation
1010
luftdurchlässige Öffnungenair-permeable openings
11 11
Antriebshülsedrive sleeve
20, 21, 2220 21, 22
Landevorrichtunglanding device
3030
ovalförmiges Schutzgitteroval shaped protective grid
AA
Steuereinheitcontrol unit
B, C B C
Steuereinheitcontrol unit

Claims (9)

Rotoranordnung, dadurch gekennzeichnet, dass der Hauptrotor (6) und die Steuereinheiten (A, B, C) bzw. weitere Antriebsrotoren oder Steuereinheiten, die rotorintegralen bzw. die kraft- oder formschlüssig damit verbundenen Antriebshülsen (7, 11...n) aufweisen, wobei der Hauptrotor (6) bzw. weitere Antriebsrotoren oder auch Steuerrotoren (2...n) starr oder höhenverstellbar damit verbunden sein können und so in Längsrichtung des Hauptrotors (6) bedarfsspezifisch kontinuierlich verschoben werden, um an jedem Ort längsseitig des jeweiligen Motors wieder an der Antriebshülse (7) unverlierbar fixiert werden zu können.Rotor arrangement, characterized in that the main rotor ( 6 ) and the control units (A, B, C) or further drive rotors or control units, the rotor-integral or the force or form-fitting associated drive sleeves ( 7 . 11 ... n), the main rotor ( 6 ) or further drive rotors or control rotors ( 2 ... n) can be rigidly or height-adjustable connected to it and so in the longitudinal direction of the main rotor ( 6 ) are continuously shifted according to demand, at each location along the side of the respective motor back to the drive sleeve ( 7 ) can be fixed captive. Rotoranordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Rotoren der Steuereinheiten (A, B, C) unterhalb oder oberhalb des Rumpfes (5) angeordnet sind.Rotor assembly according to claim 1, characterized in that the rotors of the control units (A, B, C) below or above the hull ( 5 ) are arranged. Rotoranordnung nach Anspruch 1 und 2, dadurch gekennzeichnet, dass die Rotoren der Steuereinheit (A, B, C) soweit axialkonzentrisch nach außen versetzt sind, dass sie vom Luftdurchsatz des Hauptrotors (6) praktisch nicht mehr aerodynamisch beeinflusst werden, wobei alle Rotoren auch in einer Ebene liegen können bzw. auch in einer Ebene über dem Hauptrotor (6)Rotor arrangement according to claim 1 and 2, characterized in that the rotors of the control unit (A, B, C) are as far axially concentrically outwardly offset that they from the air flow of the main rotors ( 6 ) are practically no longer aerodynamically influenced, wherein all rotors can also lie in one plane or also in a plane above the main rotor ( 6 ) Rotoranordnung nach Anspruch 1 und 3, dadurch gekennzeichnet, dass der Rumpf (5) kreisförmig luftdurchlässig ausgebildet ist.Rotor arrangement according to Claims 1 and 3, characterized in that the hull ( 5 ) is circular permeable to air. Rotoranordnung nach Anspruch 1 und 4, dadurch gekennzeichnet, dass die Motoren der Steuereinheiten (A, B, C) plan mit der Oberfläche des Rumpfes (5) abschließen oder auch darüber hinausgehend angeordnet sein können.Rotor arrangement according to Claims 1 and 4, characterized in that the motors of the control units (A, B, C) are flush with the surface of the fuselage (A, B, C). 5 ) or can be arranged beyond. Rotoranordnung nach Anspruch 1 und 5, dadurch gekennzeichnet, dass der Rumpf (5) und das ovalförmige Schutzgitter (30) aus eigenstabilem luftdurchlässigem maschenförmigen kohlefaserverstärktem Kunststoff bestehen.Rotor arrangement according to Claims 1 and 5, characterized in that the hull ( 5 ) and the oval-shaped protective grid ( 30 ) consist of inherently stable air-permeable mesh-shaped carbon fiber reinforced plastic. Rotoranordnung nach Anspruch 1 und 6, dadurch gekennzeichnet, dass die Rotoren der Steuereinheiten (A, B, C) keine integralen Antriebshülsen aufweisen.Rotor arrangement according to Claims 1 and 6, characterized that the rotors of the control units (A, B, C) are not integral Drive sleeves have. Rotoranordnung nach Anspruch 1 und 7, dadurch gekennzeichnet, dass der Motor (8) und die Motoren der Steuereinheiten (A, B, C) durch eine zentrale Steuerlogik gesteuert werden und auch ferngesteuert sein können, wobei präformierte Teile des Rumpfes (5) zur Aufnahme der Elektronik und der Energieversorgung eingesetzt werden können.Rotor assembly according to claim 1 and 7, characterized in that the engine ( 8th ) and the motors of the control units (A, B, C) are controlled by a central control logic and can also be remotely controlled, whereby preformed parts of the fuselage ( 5 ) can be used to accommodate the electronics and the power supply. Rotoranordnung nach Anspruch 1 und 8, dadurch gekennzeichnet, dass insgesamt vier Steuereinheiten (A, B, C, D) im Winkel von jeweils 90° beabstandet eingesetzt werden.Rotor arrangement according to Claims 1 and 8, characterized that a total of four control units (A, B, C, D) at an angle of each 90 ° apart be used.
DE102005003028A 2005-01-22 2005-01-22 Rotor arrangement for model or micro helicopter has main rotor with further drive rotors connected rigidly or vertically adjustable for fixing immovable anywhere along relevant motor on drive sleeve Withdrawn DE102005003028A1 (en)

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DE102005003028A DE102005003028A1 (en) 2005-01-22 2005-01-22 Rotor arrangement for model or micro helicopter has main rotor with further drive rotors connected rigidly or vertically adjustable for fixing immovable anywhere along relevant motor on drive sleeve

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DE102005003028A DE102005003028A1 (en) 2005-01-22 2005-01-22 Rotor arrangement for model or micro helicopter has main rotor with further drive rotors connected rigidly or vertically adjustable for fixing immovable anywhere along relevant motor on drive sleeve

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Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2937306A1 (en) * 2008-10-20 2010-04-23 Breizhtech Amphibious gyropendular drone for use in e.g. defense application, has safety device arranged in periphery of propulsion device for assuring floatability of drone, and upper propulsion device for maintaining drone in air during levitation
FR2959208A1 (en) * 2010-04-22 2011-10-28 Eurl Jmdtheque GYROPENDULAR ENGINE WITH COMPENSATORY PROPULSION AND COLLIMATION OF MULTIMODAL MULTI-MEDIUM FLUID FLOWING GRADIENT WITH VERTICAL LANDING AND LANDING
CN102390528A (en) * 2011-10-21 2012-03-28 南京理工大学 Air flight and omnibearing adsorption micro-robot
WO2013060693A2 (en) 2011-10-27 2013-05-02 Desaulniers Jean-Marc Joseph Active geometric exoskeleton with pseudo-rhombohedral annular fairing for gyropendular craft
ITPI20130081A1 (en) * 2013-09-10 2015-03-11 Sandro Moretti PERFECT STRUCTURE OF DRONE
WO2015061857A1 (en) * 2013-11-01 2015-05-07 The University Of Queensland A rotorcraft
WO2015109322A1 (en) * 2014-01-20 2015-07-23 Robodub Inc. Multicopters with variable flight characteristics
CN105034729A (en) * 2015-07-21 2015-11-11 中国科学院自动化研究所 Deformable multi-mode ground and air flying robot
FR3032687A1 (en) * 2015-02-16 2016-08-19 Hutchinson AERODYNE VTOL WITH A SOUFFLANTE (S) AXIALE (S) CARRIER (S)
WO2018139661A1 (en) * 2017-01-30 2018-08-02 日本電産株式会社 Unmanned aircraft
US10315759B2 (en) * 2015-04-04 2019-06-11 California Institute Of Technology Multi-rotor vehicle with yaw control and autorotation
CN110127053A (en) * 2019-05-08 2019-08-16 重庆大学 Portable Foldable Flight-Adsorption Inspection Drone
WO2020002147A1 (en) * 2018-06-29 2020-01-02 Robert Bosch Gmbh Flying device
US20220194573A1 (en) * 2020-12-22 2022-06-23 California Institute Of Technology Thrusters for Multi-Copter Yaw Control and Forward Flight
US11975824B2 (en) 2020-12-11 2024-05-07 California Institute Of Technology Systems for flight control on a multi-rotor aircraft
US12269581B2 (en) 2021-03-17 2025-04-08 TooFon, Inc. Systems and methods for efficient cruise and hover in VTOL

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2937306A1 (en) * 2008-10-20 2010-04-23 Breizhtech Amphibious gyropendular drone for use in e.g. defense application, has safety device arranged in periphery of propulsion device for assuring floatability of drone, and upper propulsion device for maintaining drone in air during levitation
FR2959208A1 (en) * 2010-04-22 2011-10-28 Eurl Jmdtheque GYROPENDULAR ENGINE WITH COMPENSATORY PROPULSION AND COLLIMATION OF MULTIMODAL MULTI-MEDIUM FLUID FLOWING GRADIENT WITH VERTICAL LANDING AND LANDING
WO2011131733A3 (en) * 2010-04-22 2011-12-29 Desaulniers Jean-Marc Joseph Vertical take-off and landing multimodal, multienvironment, gyropendular craft with compensatory propulsion and fluidic gradient collimation
CN102390528A (en) * 2011-10-21 2012-03-28 南京理工大学 Air flight and omnibearing adsorption micro-robot
CN102390528B (en) * 2011-10-21 2014-01-08 南京理工大学 Air flight and omnibearing adsorption micro-robot
WO2013060693A2 (en) 2011-10-27 2013-05-02 Desaulniers Jean-Marc Joseph Active geometric exoskeleton with pseudo-rhombohedral annular fairing for gyropendular craft
ITPI20130081A1 (en) * 2013-09-10 2015-03-11 Sandro Moretti PERFECT STRUCTURE OF DRONE
WO2015036907A1 (en) * 2013-09-10 2015-03-19 Università Degli Studi Di Firenze An improved drone structure
US10081432B2 (en) 2013-09-10 2018-09-25 Universita Degli Studi Di Firenze Drone structure
WO2015061857A1 (en) * 2013-11-01 2015-05-07 The University Of Queensland A rotorcraft
AU2014344813B2 (en) * 2013-11-01 2018-09-13 The University Of Queensland A rotorcraft
US10124888B2 (en) 2013-11-01 2018-11-13 The University Of Queensland Rotorcraft
US10407162B2 (en) 2014-01-20 2019-09-10 Robodub Inc. Multicopters with variable flight characteristics
CN106061838A (en) * 2014-01-20 2016-10-26 罗博杜伯公司 Multirotor helicopter with variable flight characteristics
WO2015109322A1 (en) * 2014-01-20 2015-07-23 Robodub Inc. Multicopters with variable flight characteristics
FR3032687A1 (en) * 2015-02-16 2016-08-19 Hutchinson AERODYNE VTOL WITH A SOUFFLANTE (S) AXIALE (S) CARRIER (S)
WO2016132040A1 (en) * 2015-02-16 2016-08-25 Hutchinson Vtol aerodyne with supporting axial blower(s)
US9902493B2 (en) 2015-02-16 2018-02-27 Hutchinson VTOL aerodyne with supporting axial blower(s)
US10315759B2 (en) * 2015-04-04 2019-06-11 California Institute Of Technology Multi-rotor vehicle with yaw control and autorotation
CN105034729B (en) * 2015-07-21 2017-05-24 中国科学院自动化研究所 Deformable multi-mode ground and air flying robot
CN105034729A (en) * 2015-07-21 2015-11-11 中国科学院自动化研究所 Deformable multi-mode ground and air flying robot
WO2018139661A1 (en) * 2017-01-30 2018-08-02 日本電産株式会社 Unmanned aircraft
CN110167839A (en) * 2017-01-30 2019-08-23 日本电产株式会社 Unmanned flight's body
JPWO2018139661A1 (en) * 2017-01-30 2019-11-14 日本電産株式会社 Unmanned aerial vehicle
WO2020002147A1 (en) * 2018-06-29 2020-01-02 Robert Bosch Gmbh Flying device
CN110127053A (en) * 2019-05-08 2019-08-16 重庆大学 Portable Foldable Flight-Adsorption Inspection Drone
CN110127053B (en) * 2019-05-08 2021-03-26 重庆大学 Portable foldable flying-adsorption inspection drone
US11975824B2 (en) 2020-12-11 2024-05-07 California Institute Of Technology Systems for flight control on a multi-rotor aircraft
US20220194573A1 (en) * 2020-12-22 2022-06-23 California Institute Of Technology Thrusters for Multi-Copter Yaw Control and Forward Flight
US12269581B2 (en) 2021-03-17 2025-04-08 TooFon, Inc. Systems and methods for efficient cruise and hover in VTOL

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