WO2009046554A1 - Dirigeable à air chaud - Google Patents

Dirigeable à air chaud Download PDF

Info

Publication number
WO2009046554A1
WO2009046554A1 PCT/CH2008/000412 CH2008000412W WO2009046554A1 WO 2009046554 A1 WO2009046554 A1 WO 2009046554A1 CH 2008000412 W CH2008000412 W CH 2008000412W WO 2009046554 A1 WO2009046554 A1 WO 2009046554A1
Authority
WO
WIPO (PCT)
Prior art keywords
hot
shaft
airship
hot airship
turbines
Prior art date
Application number
PCT/CH2008/000412
Other languages
German (de)
English (en)
Inventor
Andreas Reinhard
Original Assignee
Iii-Solutions Gmbh
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 Iii-Solutions Gmbh filed Critical Iii-Solutions Gmbh
Publication of WO2009046554A1 publication Critical patent/WO2009046554A1/fr

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
    • B64B1/08—Framework construction
    • 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
    • B64B1/10—Tail unit construction
    • 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
    • B64B1/22—Arrangement of cabins or gondolas
    • 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

Definitions

  • the present invention relates to a hot airship according to the preamble of claim 1.
  • Hot airships with motor drive are known for example from DE 102 01 133 (Dl).
  • D2 hot air balloon with additional buoyancy caused by lifting radiator from DE 203 15 020 Ul
  • the well-known from Dl drive for additional generation of propulsion and thermal lift is intended for a heavy aircraft itself, which has a continuous keel and is designed for lifting and transporting heavy loads, in which the additional load by the claimed power generator not too much May like weight.
  • the proposed solution of D2 is basically intended for a pressurized, substantially spherical, hot air balloon and is only very suitable for an airship.
  • the object of the present invention is to provide a motor drive for an airship, which drive simultaneously provides the thermal buoyancy for this airship, the airship is constructed as Tensairity- structure according to EP 1 606 161.
  • a drive unit consisting of a cluster of several small turbines acts on a common drive element, which mechanically drives a arranged in the rear of the airship main propeller and parallel to an electric generator.
  • This supplies a battery and one in the tail and in the bow of the airship arranged cross-flow Popeller.
  • These are arranged in rudder surfaces, which are around the bow and stern.
  • node elements rotatable about the longitudinal axis of the airship and are pivotable transversely thereto.
  • the hot exhaust gases of the several small turbines deliver, either directly or via heat exchangers, the hot air for the buoyancy of the airship.
  • FIG. 1 shows a side view of the hot airship according to the invention
  • FIG. 2a is a side view of the drive unit
  • Fig. 2b is a front view of a detail
  • Fig. 3 is a side view, partially open, of the rear area of the airship.
  • Fig. 1 is a side view of the inventive hot airship.
  • An insulating sheath 1 is spanned between see an upper train push rod 2 and a lower train push rod 3.
  • the two train push rods 2, 3 open at the front in a front node element 4 and the rear in a rear node element 5.
  • the two node elements , 5 each carry a rudder surface 6, 7, which are pivotable about an axis transverse to the longitudinal axis of the airship.
  • the front rudder surface 6 and the rear rudder surface 7 are each placed on a front and a rear cone 8, 9. Also attached to the cones 8, 9 are each a transverse jet propeller 10.
  • the two cones 8, 9 are each arranged rotatable about the longitudinal axis of the airship by at least ⁇ 90 °, so that the rudder surface 6, 7 both as lateral rudder, as can also be used as dynamic buoyancy rudders or, maW make the airship controllable in both the horizontal and the vertical plane.
  • the two transverse propellers 10 allow the maneuvering of the airship at a standstill and at low speeds.
  • the payload platform is attached, the payload, for example, from the pilot and five passengers can exist. Also in the payload area a kerosene tank 11 is provided for the operation of the turbines. In the payload area, a towed wheel 12 is also attached.
  • the control of the rudder surfaces 6, 7 takes place wirelessly, for example via WLAN from a pilot-operated laptop, in which the entire avionics is integrated. As an alternative to wireless control, this can also be constructed according to the fly-by-wire principle.
  • the drive unit is shown.
  • Several turbines 20, for example, the three, are arranged as a cluster around a gear 21. With their mechanical power, these turbines 20 generate the propulsion, with their thermal power the buoyancy of the airship.
  • an emergency burner is provided, which in case of failure of all turbines 20, fed by kerosene from the tank 11, generates the necessary hot air for buoyancy.
  • the Querstrahlpropeller 10 are powered by the battery 26, also other electrical loads.
  • the shaft of the generator 25 is connected directly to the shaft 23, which drives a jacket propeller 27 (in FIG. 3) fastened to the rear cone 9.
  • a first universal joint 28 is flanged, to which a main shaft 29 .anschliesst, which is connected to the universal joint 28 by an axially displaceable Ausmaschine Division 30.
  • the main shaft 29 is formed for example as a hollow shaft, which may be made of fiberglass or CFK.
  • the entire drive unit on the frame 24 can be arranged both inside the hot airship, as well as in the outside - hanging on the lower tension - pressure element 3. In this case, the main shaft 29 is guided through an opening in the shell 1. If the arrangement is provided in the interior, fresh air ducts 33 are provided, which direct fresh air from outside the shell 1 to the turbines 20.
  • the hot exhaust gases are conducted in ducts 34, either directly into the interior of the hot airship or via a heat exchanger which, as is known, can operate both in circulating air and in fresh air mode.
  • ducts 34 either directly into the interior of the hot airship or via a heat exchanger which, as is known, can operate both in circulating air and in fresh air mode.
  • Fig. 3 the other end of the main shaft 29 is shown, with a second universal joint 31 which is flanged against the interior of the hot airship to the designated by the numeral 32 shaft of the ducted propeller 28.
  • the drive unit can also be mounted in the rear cone 9, whereby the torque transmission via the main shaft 29 without universal joints 29, 31 manages, or the shaft of the ducted propeller 28 can be connected directly to the shaft 23.
  • the hot airship according to the invention has a closed casing 1 which is under a pressure in the lower region of the casing 1 in the range from 0.01 hPa to 2 hPa.
  • the sheath 1 in the region of the lower tension-push rod 3, where the pressure is measured is, one or more controllable openings through which excess hot air can be discharged.

Landscapes

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

Abstract

Plusieurs turbines (20) sont placées autour d'une roue dentée (21). La poussée en avant du dirigeable est générée avec la puissance mécanique fournie par les turbines, tandis que la poussée verticale est générée avec leur puissance thermique. Une roue dentée (22), engrenant avec la roue dentée (21), est placée sur les arbres de sortie des turbines (20). Les turbines (20) ainsi qu'un arbre (23) portant la première roue dentée (21) sont montés sur un bâti (24), sur lequel sont également montés un générateur (25) et une batterie (26) alimentée par ledit générateur. L'arbre du générateur (25) est directement relié à l'arbre (23), qui entraîne une hélice carénée fixée au cône arrière. En variante, un réducteur ou un multiplicateur de vitesse peut être placé entre l'arbre du générateur et l'arbre (23). Un premier joint universel (28) est fixé à l'arbre (23) par bride, joint auquel un arbre principal (29) peut être relié par l'intermédiaire d'une pièce de compensation (30) à déplacement axial. L'arbre principal (29) est réalisé par exemple sous la forme d'un arbre creux. L'air frais est amené dans des canaux (33), tandis que les gaz d'échappement chauds sont amenés dans des canaux (34).
PCT/CH2008/000412 2007-10-10 2008-10-06 Dirigeable à air chaud WO2009046554A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH15812007 2007-10-10
CH1581/07 2007-10-10

Publications (1)

Publication Number Publication Date
WO2009046554A1 true WO2009046554A1 (fr) 2009-04-16

Family

ID=39561993

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH2008/000412 WO2009046554A1 (fr) 2007-10-10 2008-10-06 Dirigeable à air chaud

Country Status (1)

Country Link
WO (1) WO2009046554A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104832234A (zh) * 2015-03-25 2015-08-12 中国空间技术研究院 一种基于稀相催化燃烧和有机朗肯循环的新概念动力系统

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1026458A (en) * 1964-03-23 1966-04-20 Bristol Siddeley Engines Ltd Aircraft power plant
DE2518946A1 (de) * 1975-04-29 1976-11-11 Klaus D Decker Luftschiff mit kombinierter anlage fuer antrieb und lageregelung
DE7706367U1 (de) * 1977-03-02 1977-09-01 Schulz, Walter, 7000 Stuttgart Heissluftschiff
GB1548884A (en) * 1976-06-29 1979-07-18 Walden O A R Lighterthan-air-craft of the rigid dirigible type with controllable buoyncy
DE3327944A1 (de) * 1983-08-03 1985-02-21 Walter 7000 Stuttgart Schulz Prallheissluftschiff mit turbopropantrieb
US20060192048A1 (en) * 2003-03-21 2006-08-31 Mauro Pedretti Lifting body for an airship

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1026458A (en) * 1964-03-23 1966-04-20 Bristol Siddeley Engines Ltd Aircraft power plant
DE2518946A1 (de) * 1975-04-29 1976-11-11 Klaus D Decker Luftschiff mit kombinierter anlage fuer antrieb und lageregelung
GB1548884A (en) * 1976-06-29 1979-07-18 Walden O A R Lighterthan-air-craft of the rigid dirigible type with controllable buoyncy
DE7706367U1 (de) * 1977-03-02 1977-09-01 Schulz, Walter, 7000 Stuttgart Heissluftschiff
DE3327944A1 (de) * 1983-08-03 1985-02-21 Walter 7000 Stuttgart Schulz Prallheissluftschiff mit turbopropantrieb
US20060192048A1 (en) * 2003-03-21 2006-08-31 Mauro Pedretti Lifting body for an airship

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104832234A (zh) * 2015-03-25 2015-08-12 中国空间技术研究院 一种基于稀相催化燃烧和有机朗肯循环的新概念动力系统

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