Abstract: The invention relates to a fluid valve arrangement having a bistable fluid valve for at least one fluid line with a valve body which can be moved into two positions for two switching states, a pressure pulse generator being provided for valve switchover in the feed line for switching over a feed line and a return line between two flow lines, and the fluid valve comprising a reversing unit which has two chambers which are separated from one another by a bistable surface element, the two chambers being connected to the two flow lines and the bistable surface element being operatively coupled to the valve body in order to actuate it. As a result, a bistable fluid valve is provided which can be reversed by way of pressure pulses or pressure flanks and otherwise has no energy requirement.

Abstract: A bistable fluid valve is characterized by two valve chambers which are arranged adjacent to one another and are closed off with respect to one another by a partition and each have an inlet opening and an outlet opening situated opposite one another, by an S-shaped elastic strip element which extends through both valve chambers, is articulatedly mounted in the region of the partition and can assume two positions in which it sealingly closes off either one or the other outlet opening, and also by an actuation element which is fastened to the strip element and by means of which the strip element can be switched between the two positions. The fluid valve according to the invention comprises only a single movable component of very low mass, which can thus operate in a fast-reacting manner.

Abstract: A landing gear vibration absorber (1) of a helicopter (2) with a landing gear (3) comprising a pair of skids (4, 5) and at least one cross tube (6, 7) for mounting the skids (4, 5) to a helicopter's fuselage (8). At least one spring-mass system (10, 20, 24) is mounted to the landing gear (3). Said at least one spring-mass system (10, 20, 24) is tuned to the helicopter's main excitation frequency and said at least one spring-mass system (10, 20, 24) being located at or near at least one antinode of the landing gear (3). The invention is related as well to a method of operating a landing gear vibration absorber (1) of a helicopter (2).

Abstract: The invention relates to a fluid valve arrangement having a bistable fluid valve for at least one fluid line with a valve body which can be moved into two positions for two switching states, a pressure pulse generator being provided for valve switchover in the feed line for switching over a feed line and a return line between two flow lines, and the fluid valve comprising a reversing unit which has two chambers which are separated from one another by a bistable surface element, the two chambers being connected to the two flow lines and the bistable surface element being operatively coupled to the valve body in order to actuate it. As a result, a bistable fluid valve is provided which can be reversed by way of pressure pulses or pressure flanks and otherwise has no energy requirement.