EP2125506A2 - Dirigeable - Google Patents

Dirigeable

Info

Publication number
EP2125506A2
EP2125506A2 EP08716573A EP08716573A EP2125506A2 EP 2125506 A2 EP2125506 A2 EP 2125506A2 EP 08716573 A EP08716573 A EP 08716573A EP 08716573 A EP08716573 A EP 08716573A EP 2125506 A2 EP2125506 A2 EP 2125506A2
Authority
EP
European Patent Office
Prior art keywords
drives
airship
balloon
airship according
arms
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Withdrawn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
EP08716573A
Other languages
German (de)
English (en)
Inventor
Thomas Krause
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Technische Universitaet Chemnitz
Original Assignee
Technische Universitaet Chemnitz
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Technische Universitaet Chemnitz filed Critical Technische Universitaet Chemnitz
Publication of EP2125506A2 publication Critical patent/EP2125506A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/06—Rigid airships; Semi-rigid airships
    • B64B1/24—Arrangement of propulsion plant
    • B64B1/30—Arrangement of propellers
    • B64B1/32—Arrangement of propellers surrounding hull

Definitions

  • the present invention relates to an airship with a balloon and a drive system with multiple drives for moving the airship, wherein the invention can be applied both to impact airships, which are also known as autonomous airships or blimps, as well as zeppelins.
  • a Blimp does not have a solid inner frame, but consists of a freely deformable shell, the balloon.
  • the flight characteristics are however comparable and if such airships are to fly autonomously, then due to the constant disturbances by wind a robust regulation of the position and the movement is necessary.
  • the standard drive of an airship usually consists of two propeller drives at the level of the nacelle mounted under the balloon.
  • This form of drive involves some disadvantages in the autonomous control or use of an autopilot.
  • the propulsive power applied by the propeller drives does not act in the same place as the externally acting forces on the airship.
  • the consequences are effects on the positional movement of the airship during load changes.
  • This has a rocking and / or tilting of the airship to the result, which must be corrected.
  • it is known, in addition to the rear of the balloon Provide the tail to minimize the rocking.
  • the problem of looking up is not completely eliminable with the known techniques.
  • the object is achieved by an airship with a balloon and a drive system with multiple drives for moving the airship, wherein at least three drives are provided, which are arranged spatially distributed on the balloon that resulting from the drives and variable in its point force and torque vector can be generated.
  • the at least three drives span a surface which intersects the balloon, wherein a point of application of the force and moment vector resulting from the drives acts on this surface and is displaceable in this surface.
  • the area spanned by the drives can be arranged orthogonal to a longitudinal axis of the balloon (and then coincides with a cross-sectional area of the balloon).
  • the surface spanned by the drives may also be non-orthogonal to the longitudinal axis of the balloon (and then forms a plane of intersection of the balloon).
  • the drives can be controlled separately from each other, as this can vary the individual force vectors and thus can shift the resulting vector.
  • At least one of the drives is arranged to be longitudinally displaceable relative to the longitudinal axis of the balloon.
  • the drives can be mounted on separately rotatable arms.
  • the at least three drives are arranged circumferentially above and below a median line of the balloon.
  • two drives are arranged circumferentially above and two drives circumferentially below the median line of the balloon.
  • the boom, on which arranged above the median line Drives are mounted to be aligned substantially parallel to the arms to which the arranged below the median line drives are attached.
  • four drives are provided, of which two drives are arranged diametrically opposite.
  • the arms of the diametrically opposed drives can be aligned substantially in a line.
  • four drives are provided, wherein three of the drives span a surface which intersects the balloon and wherein the fourth drive is disposed outside this surface and forms with the surface a space in which the point of application of the force resulting from the drives - And moment vector is changeable in position.
  • the drives for moving the airship are arranged below the balloon
  • the drives of the airship of the present invention can be arranged distributed around the circumference of the balloon, that resulting from the individual force and moment vectors of the drives force and Moment vector is located in the middle of the plane spanned by the drives surface of the balloon and thus acts at the same point as the resulting wind forces from the outside.
  • this point is adjustable and adaptable to the external wind forces. This can prevent a rocking of the airship.
  • the present propulsion system of the airship has the significant advantage over previous drive systems that the force vectors can be displaced in the area spanned by the drives or the space spanned by the drives, and thus can also be spatially aligned. As a result, the cause of a rotational or tilting movement is prevented.
  • Another major advantage of the new drive concept is that it can react to any disturbance variable independently with the actuators (drives), which considerably simplifies the development of a control, regardless of whether a linear, cascaded controller or a non-linear regulator is used.
  • fuzzy controllers or other non-linear controllers can also be used.
  • the drives can be controlled separately from each other.
  • the flexible mounting of the drives in conjunction with the independent controllability of the drives enables the resulting force and moment vector to be freely positioned and rotated on the surface that the motors of the drives span. This allows a very high maneuverability of the airship with up to 6 degrees of freedom.
  • an airship can be constructed which can be maneuvered in 5 degrees of freedom. This allows this airship in two straight-line movements, that is forward, backward, up and down, and in three directions of rotation.
  • the boom to which the upper drives are attached are aligned approximately parallel to the arms to which the lower drives are attached.
  • the drives can be rigidly or rotatably mounted and controlled symmetrically or independently, so that an optimal control of the movement and positioning of the airship can be ensured. This arrangement is structurally favorable to implement.
  • the four drives can be positioned around the balloon on the top left, top right, bottom right and bottom left, making it possible to supply the airship with up to 6 degrees of freedom maneuver. In this way, in addition to the linear directions of movement, three directions of rotation with the aid of this embodiment are adjustable. If the arms of the diametrically opposed drives are aligned approximately in a line, then the airship can be controlled particularly easily and safely by the symmetrical arrangement of arms and drives.
  • Figure 1 is a schematic side view of an embodiment of an airship
  • Figure 2 is a schematic front view of the embodiment of the airship of Figure 1, in which the drives are provided above and below the median line of the balloon;
  • Figure 3 is a schematic front view of another embodiment of a
  • the drives are distributed diametrically opposite to the balloon around.
  • FIG. 1 shows schematically a side view of a possible embodiment variant of the present airship 1.
  • the airship 1 has a helium-filled pressure balloon 2.
  • the balloon 2 shown in the example is about 4 meters long and has a diameter of about 2 meters. In other embodiments, not shown, the balloon 2 may also have other dimensions.
  • a nacelle 3 is attached at the bottom of the balloon 2.
  • the nacelle 3 can be used, for example, that in the gondola 3 electronics and batteries are stored.
  • the drives 4 are propellers. In principle, however, comes as drive 4 for the present airship 1, any drive into consideration, which is able to apply a thrust to move the airship 1.
  • propulsion jet drives can also be used as drives 4.
  • two propellers 4 Above a median line of the balloon 2, two propellers 4 are also rotatably mounted on separate axes 5 in the example shown in FIG. Thus, the orientations of the propeller 4 can be changed separately from each other.
  • each axis or each boom 5, to which the drives 4 are mounted independently rotatable, which is indicated schematically by the arrows A and B in Figure 1.
  • the drives 4 of the airship 1 are arranged on the circumference of the balloon 2, that a resulting from the drives 4 and variable in its position force and moment vector F can be generated.
  • the drives 4 act in such a way that the force and moment vector F is located approximately in the center of a surface spanned by the drives (which in the present embodiment corresponds approximately to the middle of the cross-sectional area of the balloon 2) and thus at the same point as the resulting wind forces from the outside.
  • a rocking or tilting of the airship 1 can be largely prevented.
  • Figure 2 shows schematically a front view of the airship 1 of Figure 1.
  • the boom 5 above and below the median line of the balloon 2 are arranged approximately parallel to each other. This makes it possible to achieve a particularly good, symmetrical control of the airship 1.
  • the boom 5 are not arranged parallel to each other.
  • the arms 5 are rotatable separately from each other according to the directions of rotation demonstrated by the arrows A, B, C, D.
  • the drives 4 are designed in the form of propellers, which are arranged above and below the median line of the balloon 2 approximately symmetrically to one another.
  • the thrust forces acting on the airship 1, above and below the median line of the balloon 2 can be particularly well coordinated.
  • the drives 4, which are arranged above and below the median line of the balloon 2 are not provided symmetrically to each other.
  • up to 5 degrees of freedom can be set with regard to the maneuverability of the airship 1.
  • the airship 1 is movable forward and backward, up and down and in three directions of rotation or inclination.
  • FIG. 3 schematically shows a front view of a further embodiment of the present airship T
  • the airship 1 ' like the airship 1, has a helium-filled pressure balloon 2, to which a nacelle, which is not shown in FIG.
  • each two drives 4 are diametrically opposite.
  • the drives 4 in the embodiment shown in Figure 3 of the present airship 1 'top left, top right, bottom right and bottom left around the balloon 2 are arranged distributed.
  • the drives 4 are rotatably mounted on arms 5, wherein the arms 5 of the diametrically opposed drives 4 are aligned approximately in a line and also according to the arrows A, B, C 1 D are rotatable.
  • the independent control is immediately necessary if the resulting vector should leave the middle of the spanned surface or in addition torques must be generated.
  • the resulting force and moment vector F can be freely positioned on the surface that the drives 4 span and rotated in position.
  • the drives 4 can be rigidly attached. If the drives are rigidly mounted, however, only forward movements and torques are possible. In practice, however, at least one additional component is usually needed for the height. Therefore, the drives are usually mounted rotatably and symmetrically or independently controlled.
  • the present airship 1, 1 ' has over conventional airships the advantage that its location is completely changeable in space.
  • the airship 1, 1 ' is adaptable to air currents.
  • both in upwind and downwind always a very low air resistance of the airship 1, 1 'are set, which you can turn in the wind.
  • the present airship 1, 1 characterized by the fact that with him very tight tropics can be realized.
  • an essential advantage of the present airship 1, 1 ' lies in the fact that the point of application and the size and direction of the resulting force and moment vector F of the drives 4 of the airship 1, 1' can be set directly with the actuators or drives 4. Accordingly, a simple control is possible in which can be acted directly on the respective disturbing size.
  • the present arrangement of the drives 4 to the balloon 2 around a particularly good navigation and maneuverability of the airship 1, 1 ' can be achieved by the present arrangement of the drives 4 to the balloon 2 around a particularly good navigation and maneuverability of the airship 1, 1 '. If, for example, a strong thrust force is generated by the drives 4 arranged above the balloon 2 or laterally on the balloon 2, while a lower thrust force is generated by the drives 4 arranged below on the balloon, an inclination can occur in the airship 1, 1 ' down to be realized. Conversely, a low thrust at the top and a higher thrust at the bottom make it possible to tilt the airship 1, 1 'upwards.
  • the airship 1, 1 ' can be turned upwards in place. If, for example, only the left drives 4 of the airship 1, 1 'are operated, a movement can take place to the right, conversely the airship 1, 1' can be moved to the left by the activation of the right drives 4.
  • the present airship 1, 1 ' is also able to rotate about its own longitudinal axis.
  • the propeller 4 shown on the right in Figure 3 are turned down and the propeller 4 shown on the left turned up.
  • three drives 4 may be provided in the present airship.
  • one of the drives 4 can be arranged centrally above the balloon 2, wherein the drives 4 arranged below can be provided, for example, as shown in FIGS. 2 or 3.
  • two drives 4 are provided, as shown in Figures 2 and 3, while at the bottom of the nacelle 3, only one drive 4 is provided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne un dirigeable comprenant un ballon et plusieurs mécanismes de propulsion conçus pour déplacer le dirigeable. Cette invention peut être mise en oeuvre aussi bien avec des dirigeables souples qu'avec des dirigeables rigides. L'objectif de cette invention est de mettre au point un tel dirigeable de manière à empêcher une oscillation ou un basculement du dirigeable dans une large mesure. Cet objectif est atteint grâce aux mécanismes de propulsion qui sont au moins trois et qui sont placés autour du ballon de manière à pouvoir produire un vecteur force et couple dont la position peut varier.
EP08716573A 2007-03-15 2008-03-17 Dirigeable Withdrawn EP2125506A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200710013147 DE102007013147A1 (de) 2007-03-15 2007-03-15 Luftschiff
PCT/EP2008/002103 WO2008110385A2 (fr) 2007-03-15 2008-03-17 Dirigeable

Publications (1)

Publication Number Publication Date
EP2125506A2 true EP2125506A2 (fr) 2009-12-02

Family

ID=39673401

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08716573A Withdrawn EP2125506A2 (fr) 2007-03-15 2008-03-17 Dirigeable

Country Status (3)

Country Link
EP (1) EP2125506A2 (fr)
DE (1) DE102007013147A1 (fr)
WO (1) WO2008110385A2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3192735A1 (fr) 2016-01-12 2017-07-19 Mancraft AS Système de moteur hybride
WO2018122830A1 (fr) 2016-12-31 2018-07-05 Ratti Jayant Véhicule aérien sans pilote à endurance élevée

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009023665A1 (de) 2009-06-03 2010-12-09 Aee Aircraft Electronic Engineering Gmbh Verfahren zum Steuern eines Fluggeräts und ein Fluggerät für ein derartiges Verfahren
FR2959208B1 (fr) 2010-04-22 2012-05-25 Eurl Jmdtheque Engin gyropendulaire a propulsion compensatoire et collimation de gradient fluidique multi-milieux multimodal a decollage et atterrissage vertical
FR2981911B1 (fr) 2011-10-27 2014-04-25 Jean Marc Joseph Desaulniers Exosquelette geometrique actif a carenage annulaire pseudo-rhomboedrique pour engin gyropendulaire
GR20120100226A (el) 2012-04-24 2013-11-18 Laskarri Limited, Σκαφος ουδετερης ανωσης
CN103507948A (zh) * 2013-10-16 2014-01-15 黄克玉 无主机翼飞机
CN104443343B (zh) * 2014-11-13 2016-07-06 上海交通大学 矢量推进悬浮式飞行装置
FR3122165A1 (fr) 2021-04-21 2022-10-28 Safran Nacelles Ensemble propulsif, en particulier d’aéronef, pour la protection à l’encontre d’un effort de balourd et procédé de protection

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993004916A1 (fr) * 1991-09-09 1993-03-18 Av-Intel Inc. Ballon dirigeable

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4995572A (en) * 1989-06-05 1991-02-26 Piasecki Aircraft Corporation High altitude multi-stage data acquisition system and method of launching stratospheric altitude air-buoyant vehicles
US5449129A (en) * 1994-02-18 1995-09-12 Lockheed Corporation Propulsion system for a lighter-than-air vehicle
US6196498B1 (en) * 1999-12-21 2001-03-06 Lockheed Martin Corporation Semi-buoyant vehicle with aerodynamic lift capability
DE20107956U1 (de) * 2001-05-11 2002-03-07 Ott Johannes Luftschiff mit aerostatischem Auftriebskörper
ITMI20021815A1 (it) * 2002-08-09 2004-02-10 Nautilus S R L Aeromobile a sostentazione statica ad alta manovrabilita'
US7236885B2 (en) * 2005-07-08 2007-06-26 Bell Geospace, Inc. Method and system for geophysical data acquisition on an airship

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993004916A1 (fr) * 1991-09-09 1993-03-18 Av-Intel Inc. Ballon dirigeable

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3192735A1 (fr) 2016-01-12 2017-07-19 Mancraft AS Système de moteur hybride
WO2018122830A1 (fr) 2016-12-31 2018-07-05 Ratti Jayant Véhicule aérien sans pilote à endurance élevée

Also Published As

Publication number Publication date
DE102007013147A1 (de) 2008-09-18
WO2008110385A3 (fr) 2008-10-30
WO2008110385A2 (fr) 2008-09-18

Similar Documents

Publication Publication Date Title
EP2125506A2 (fr) Dirigeable
DE602004002376T2 (de) Rotor und flugzeug, die im schwebeflug passiv stabil sind
DE102007020609B4 (de) Flugobjekt mit Tandemrotoren
EP1943143B1 (fr) Avion
DE2922059C2 (de) Verbundflugzeug
DE60101477T2 (de) Ringflügelflugzeug
EP1742837B1 (fr) Bateau a propulsion par energie eolienne par un element a vol libre, du type cerf-volant, soumis a l'action du vent
DE69534767T2 (de) Hauptrotor system für hubschrauber
DE102005046155B4 (de) Hubschrauber mit koaxialen Hauptrotoren
EP1868884B1 (fr) Systeme de propulsion d'un aerostat
EP3464059B1 (fr) Aéronef
DE1431187A1 (de) Vorrichtung zum kuenstlichen Erzeugen von Steuergefuehlen,insbesondere bei Luftfahrzeugen
DE2640433C2 (de) Schubvektor-Luftschiff
DE102019123725B4 (de) Auftriebs- und Flugsteuerungseinheit für ein Fluggerät und Fluggerät
DE2651577C2 (de) Verfahren und Vorrichtung zur Steuerung eines Fluggerätes mit gegenläufigen starren Rotoren
DE102019130804B4 (de) Drohne, Verfahren zum Betreiben einer Drohne und Elektronische Steuer- und Regeleinrichtung zur Steuerung und Regelung des Betriebs einer Drohne
DE2226701A1 (de) Steuersystem für Vtol- oder V/Stol-Flugzeuge
DE102010037916A1 (de) Motorisierter Spielzeug-Flugkörper
CH672465A5 (en) Helicopter with concentric contra-rotatory rotors - has adjustable slats for guidance of air entering apertures in upper surface of sectors of housing
DE102019128097B4 (de) Steuervorrichtung für eine Drohne
DE857470C (de) Flugzeug mit einem Tragwerk mit veraenderlicher Kruemmung
DE567584C (de) Hubschrauber
DE2606424A1 (de) Pendel - rotorsteuerung
DE2934418A1 (de) Flugobjekt
DE1431185A1 (de) Steuervorrichtung fuer Luftfahrzeug-Triebwerkanlagen

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20090915

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

17Q First examination report despatched

Effective date: 20091211

17Q First examination report despatched

Effective date: 20101216

DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20121002