DE677449C

DE677449C - Hydraulic pressure system on aircraft

Info

Publication number: DE677449C
Application number: DEH152967D
Authority: DE
Inventors: Paul Zimmermann
Original assignee: Henschel Flugzeugwerke AG
Current assignee: Henschel Flugzeugwerke AG
Priority date: 1937-09-15
Filing date: 1937-09-15
Publication date: 1939-06-26

Description

Bei den hydraulischen Druckanlagen in Flugzeugen, die dem Antrieb der verschiedenen verstellbaren Bauteile dienen, besteht der Ubelstand, daß in den Kurvenfluglagen des Flugzeuges die Druckflüssigkeit aus dem in der Pumpenanlage vorgesehenen Ausgleichbehälter in das an diesem angeordnete Belüftungsrohr eintritt und dadurch Flüssigkeitsmengen nach außen gelangen. DabeiIn the case of hydraulic pressure systems in aircraft, which are used to drive the various serve adjustable components, there is the Ubelstand that in the curve flight attitudes of the aircraft takes the hydraulic fluid from the expansion tank provided in the pump system enters the ventilation pipe arranged on this and thereby amounts of liquid get to the outside. Included

»ο kann der Flüssigkeitsvorrat sich allmählich so weit verringern, daß die Betriebsfähigkeit der Druckanlage beeinträchtigt wird. Man hat zwar bereits .in dem Belüftungsrohr ein Kugelrückschlagventil vorgesehen, welches das Belüftungsrohr in der Rückenlage des Flugzeuges absperrt; jedoch hat die Erfahrung gezeigt, daß schon beim Fliegen von Kurven Flüssigkeit in das Belüftungsrohr gelangt, das in diesem Fall vom Kugelventil»Ο the fluid supply can gradually increase reduce it to such an extent that the operability of the printing system is impaired. Man has already provided a ball check valve in the ventilation pipe, which shut off the ventilation pipe in the supine position of the aircraft; however, experience has shown that liquid gets into the ventilation pipe even when flying turns, in this case from the ball valve

ao noch nicht abgesperrt wird. Da im Verlauf eines Fluges das Einstellen des Flugzeuges.in eine schräge Fluglage oft erforderlich wird, ist auch bei jeweils verhältnismäßig geringen Austrittsmengen bei längeren Flügen mit einem erheblichen Flüssigkeitsverlust zu rechnen.ao is not yet locked. Since in the course of a flight the adjustment of the aircraft an inclined attitude is often required, is also relatively low in each case Leakage increases on longer flights with a considerable loss of fluid calculate.

Durch die Erfindung wird dieser Übelstand behoben. Gemäß der Erfindung ist das auf der Wandung des Ausgleichbehälters aufgesetzte Belüftungsrohr nur durch eine quer zur Flugrichtung verlaufende Umführungsleitung mit dem Behälterinnern verbunden, derart, daß sich die Vorkammer des Belüftungsrohres und die Einmündungsstelle der Umführungsleitung in dem Behälter einander gegenüberliegen. This drawback is remedied by the invention. According to the invention this is on the wall of the expansion tank attached ventilation pipe only through a transverse to The bypass line running in the direction of flight is connected to the interior of the container in such a way that that the antechamber of the ventilation pipe and the junction of the bypass line face each other in the container.

Die Erfindung bezweckt, in der einen Kurvenfluglage eine Steigleitung für oie Flüssigkeit nach dem Belüftungsrohr zu schaffen, deren Entmündungsstelle am Behälter in derThe aim of the invention is to create a riser for oie liquid after the ventilation pipe in a turning position, the opening point of which on the container in the

Claims

opposite turn is above the highest liquid level. With this device, the liquid can only pass the conduit pipe when the aircraft is in the supine position reach. In this situation, however, the well-known ball check valve occurs in the Ventilation pipe in action. Through the invention any loss of fluid in the hydraulic pressure system of the Flugto prevented.

An exemplary embodiment of the subject matter of the invention is shown in the drawing.

Show it

Fig. Ι a side view of the expansion tank, partly in the cut, and the

Fig. 2 to 4 the expansion tank in different positions of the aircraft.

The expansion tank 1 of preferably rectangular box shape has on one At the end of the ventilation pipe 2, which is provided with a ball check valve 3. In the Chamber 4 of the ventilation pipe, in front of the ball valve 3, opens the bypass line 5, which opens into the container 1 at the opposite end thereof. This bypass line 5 can be formed by a tube, as the accompanying drawing shows, or by a partitioned chamber in the interior of the container be. The installation of the container 1 in the aircraft takes place in such a way that the bypass line 5 is perpendicular to the direction of flight. Then the liquid behaves in the container in the different flight positions, as shown in Figures 2 to 4. the "Accordingly, no liquid can get into the ventilation pipe 2 in any position of the aircraft, but flows out of the bypass line 5 always return to container 1. The container shape and arrangement can of course be any.

Patentansi'UUCu:

Hydraulic pressure system in aircraft with expansion tank, which is in the Arranged pump system and with one that can be shut off automatically by a valve Ventilation pipe is provided, characterized in that the ventilation pipe placed on the wall of the expansion tank (1) (2) connected to the interior of the container only by a bypass line (5) running transversely to the direction of flight is such that the antechamber (4) of the ventilation pipe (2) and the junction of the bypass line (5) in the container (1) each other opposite.

1 sheet of drawings