DE460671C - Recoil drive for aircraft - Google Patents

Recoil drive for aircraft

Info

Publication number
DE460671C
DE460671C DEJ27737D DEJ0027737D DE460671C DE 460671 C DE460671 C DE 460671C DE J27737 D DEJ27737 D DE J27737D DE J0027737 D DEJ0027737 D DE J0027737D DE 460671 C DE460671 C DE 460671C
Authority
DE
Germany
Prior art keywords
aircraft
air
compressor
canal
suction
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.)
Expired
Application number
DEJ27737D
Other languages
German (de)
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.)
KURT GERSON DIPL ING
Original Assignee
KURT GERSON DIPL ING
Publication date
Priority to DEJ27737D priority Critical patent/DE460671C/en
Application granted granted Critical
Publication of DE460671C publication Critical patent/DE460671C/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/12—Injection-induction jet engines

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Devices For Checking Fares Or Tickets At Control Points (AREA)

Description

Rückstoßantrieb für Luftfahrzeuge Es ist bereits vorgeschlagen worden, Luftfahrzeuge mit einem ihren Körper durchdringenden Kanal zu versehen und in diesem Luftförderanlagen vorzusehen, durch welche die Luft von vorn angesaugt und nach hinten ausgestoßen wird. Es ist auch bekannt, den Kanal so auszubilden, daß er sich hinter der Eintrittsöffnung zunächst verengt und dann wieder erweitert. Auch ist bereits vorgeschlagen, bei Rückstoßantrieben die angesaugt e Luft vor dem Ausstoßen mittels eines Kompressors zu verdichten.Aircraft recoil propulsion It has already been proposed To provide aircraft with a channel penetrating their body and in this Provide air conveying systems through which the air is sucked in from the front and after is ejected at the rear. It is also known to form the channel so that it is behind the inlet opening initially narrowed and then expanded again. Also is Already proposed in the case of recoil drives, the sucked in air before ejection to compress by means of a compressor.

Die vorliegende Erfindung will den an sich bekannten Rückstoßantrieb weiter ausbauen, und zwar dadurch, daß die Luftförderanlage aus Motor, Kompressor und Druckluftbehälter besteht, wobei die zum Kompressor führende Saugleitung wie die vom Vorratsbehälter abzweigende Druckleitung gemeinsam an der möglichst weit nach vorn verlegten engsten Stelle des Kanals einmünden. Außerdem ist eine Umsteuervorrichtung zurUmkehrung von Ansaug- und Ausstoßrichtung vorgesehen.The present invention aims at the recoil drive known per se expand further, namely by the fact that the air supply system from the engine, compressor and compressed air tank, the suction line leading to the compressor such as the pressure line branching off from the storage tank jointly on the as far as possible towards the narrowest point of the canal. There is also a reversing device intended to reverse the suction and discharge directions.

In der Zeichnung ist die Erfindung beispielsweise dargestellt, und zwar zeigt: Abb. r einen Längsschnitt durch das Luftfahrzeug, Abb. 2 und 3 Querschnitte nach den Linien 2-2 bzw. 3-3 der Abb. i.In the drawing, the invention is shown, for example, and although: Fig. r shows a longitudinal section through the aircraft, Fig. 2 and 3 cross sections according to lines 2-2 and 3-3 of Fig. i.

Der Körper m des Luftfahrzeuges ist von einem Kanal o durchzogen. Der Kanal hat unweit von vorn eine Verengung. In dieser Verengung enden zwei Rohre, welche zu der unterhalb des Luftkanals liegenden. Luftförderanlage führen. Der Motor a treibt den Kompressor b, und die Luft wird durch das Rohr d angesaugt und in den Vorratsbehälter c geleitet. Von hier aus wird die Luft durch das Rohr e zur engsten Stelle des Kanals zurückgeleitet und ausgestoßen.The body m of the aircraft is traversed by a channel o. The canal has a narrowing not far from the front. Two pipes end in this narrowing, which to the one below the air duct. Lead air conveyor system. The motor a drives the compressor b, and the air is sucked in through the pipe d and into the Reservoir c directed. From here the air becomes the narrowest through the pipe e And ejected.

Mit i und j sind Passagierkabinen, mit h die Führerkabine, mit l der Maschinenraum, mit g und h Wassertanks, mit ia die Tragfläche, mit p das Seitensteuer, mit p,. das Höhensteuer, mit r die Um.steuervorrichtung bezeichnet.With i and j are passenger cabins, with h the driver's cabin, with l the engine room, with g and h water tanks, with ia the wing, with p the rudder, with p ,. the height control, with r denotes the Um.steuervorrichtung.

Durch Umsteuerung der Ansauge- und Ausstoßrichtung der Luft kann eine große Bremswirkung erzeugt werden, was zum Landen von großer Wichtigkeit `ist.By reversing the suction and discharge direction of the air, a great braking effect can be generated, which is of great importance for landing.

Claims (2)

PATENTANSPRÜCHE: i. Rückstoßantrieb für Luftfahrzeuge u. dgl., bei dem die Luft mittels gebläseartiger Vorrichtungen durch einen den Körper des Luftfahrzeuges durchziehenden Kanal von vorn angesaugt und nach hinten ausgestoßen wird, dadurch gekennzeichnet, da,ß die Luftförderanlage aus Motor, Kompressor und Druckluftvorratsbehälter besteht, wobei die zum Kompressor führende Saugleitung. wie die vom Vorratsbehälter abzweigende Druckleitung gemeinsam an der möglichst weit nach vorn verlegten engsten Stelle des Kanals einmünden. PATENT CLAIMS: i. Recoil drive for aircraft and the like which the air by means of fan-like devices through the body of the aircraft through canal is sucked in from the front and ejected to the rear, thereby marked because, ß the air delivery system consisting of the motor, compressor and compressed air reservoir exists, whereby the suction line leading to the compressor. like the one from the storage container branching pressure line together at the narrowest one, which is laid as far forward as possible Merge at the point of the canal. 2. Antrieb nach Anspruch i, gekennzeichnet durch eine Umsteuervorrichtung zur Umkehrung der Ansauge- und Ausstoßrichtung.2. Drive according to claim i, characterized by a Reversing device for reversing the suction and discharge directions.
DEJ27737D Recoil drive for aircraft Expired DE460671C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEJ27737D DE460671C (en) Recoil drive for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEJ27737D DE460671C (en) Recoil drive for aircraft

Publications (1)

Publication Number Publication Date
DE460671C true DE460671C (en) 1928-08-24

Family

ID=7203065

Family Applications (1)

Application Number Title Priority Date Filing Date
DEJ27737D Expired DE460671C (en) Recoil drive for aircraft

Country Status (1)

Country Link
DE (1) DE460671C (en)

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