Abstract: System and method for specifying a graphical query in a graphical program. User input configuring a plurality of nodes and connections between the nodes that specifies a query may be received. The input may be received to a graphical user interface (GUI) and may specify at least a data source and an output for the query. The nodes may include a portion of a graphical data flow program and may indicate data flow among the nodes. In response to the input, the GUI may display one or more options for specifying further characteristics of the query. Further user input specifying where nodes may specify one or more conditions for the query. Executable code implementing the specified query may be generated in accordance with the user input. Generating executable code may include generating a query in a query language and may also include generating machine code to invoke the language-specific query.

Abstract: A solid fuel propulsion system for a ran jet rocket having a combustion chamber (B) surrounded by a tubular casing (2) and a gas generator (G) disposed upstream from the combustion chamber (B) and surrounded by a tubular casing (1) for generation of a combustible gas from a solid fuel, disposed between the gas generator (G) and the combustion chamber (B) is a gas-stream regulator unit (R) for regulation of the flow of the combustible gas from the gas generator (G) to the combustion chamber (B). The propulsion system has a middle section (4) in which the gas stream regulator unit (R) is housed. The middle section is connected in a load-bearing manner with the combustion chamber casing (2) and the gas generator casing (1) and is provided with a first pressure head (8) sealing the gas generator (G), and a second pressure head (9) sealing the combustion chamber (B). Disposed between the pressure heads (8, 9) is a base unit which houses the gas stream regulator unit (R) and braces the pressure heads (8, 9).

Abstract: The air intake for air-breathing engines for supersonic flight velocities, especially ram jet engines and ram rocket engines of missiles, with an essentially rectangular intake contour, has a closing flap covering the said intake contour and an actuating mechanism. The closing flap has a one-piece design and is adapted to the intake contour such that it completely covers the air intake in its closed position, so that all peripheral scarved front edges are covered and thereby protected against erosion as well as against the penetration of foreign bodies.

Abstract: An improved combination of a cover for closing the air inlet openings into he combustion chamber of a jet rocket engine and strike device for destroying the cover is disclosed. In accordance with the improved arrangement, the cover is composed of a material which is internally prestressed and a device is provided for retaining the strike device in a prestrike position relative to the cover which is operative to release the strike device upon the reaching of a predetermined magnitude of the pressure acting on the strike device.

Abstract: In securing a missile to an aircraft, a socket-like recess is formed in the missile housing, a coupling head is releasably secured within the recess by a device including releasable locking members. In addition, an explosive charge is located in the device or the coupling head for displacing the coupling head out of the socket-like recess in the housing when the locking members have been disengaged from the coupling head.