Abstract: A logic unit operable under the Byzantine algorithm for the architectural configuration of a composite assembly which tolerates an amount of F errors in simultaneous manner as to time and a plurality of inputs for in-reading of data into registers of a set of registers, and a plurality of outputs for out-reading of data from the registers, whereby each output is connectable with an input of a further logic unit, whereby the registers are coupled with the inputs and outputs in such a manner that each register is capable of being read-in and being capable of being read-out independently of the position of the logic unit within the assembly, by means of a position invariant, relative identification, as well as a computer unit with such a logic unit, as well as the fault-tolerant assembly of such logic/computer units, and a method of operating a fault tolerant assembly.
Abstract: A circuit arrangement for the fault tolerant execution of digital computer programs includes a plurality of arithmetic logic units embodied as processor pool elements connected together so that they can each execute the program in parallel. The processor elements are connected to each other through respective data, clock and reset cross-strapping interconnect lines, and are each connected to one or more serial field buses. Each processor element includes at least one microprocessor controller for controlling the functions of the processor element in such a manner that any selected number of the processor elements can be automatically actuated at any time to simultaneously execute the program in parallel and thereby achieve a prescribed degree of redundancy in the circuit arrangement.
Abstract: A band-pass filter for a waveguide, which additionally serves as a blocking filter for the concerted suppression of interference frequencies. In addition to a centrally arranged aperture (3), a waveguide aperture has two identically designed apertures (4), which are laid out for natural resonance for an interference frequency f (ind S1) to be blocked by the waveguide filter, and are arranged symmetrical to the central aperture opening (3). In waveguide devices, the invention is used to meet the statutory frequency specifications and simultaneously suppress interference frequencies.
Abstract: An apparatus for launching and dispensing multiple satellites into orbit includes a central structure and a plurality of satellites releasably bundled around the central structure to form a cohesive, single payload mounted on an upper stage of a launcher rocket. The central structure includes a central tube and an adapter shell that fits onto the upper stage of the rocket. Each satellite has the shape of a partial cylinder segment of which an outer wall is a cylindrical segment shell. The satellites are bundled and secured together around the central structure by tension bands, whereby the cylindrical segment shells form a load-bearing complete outer cylindrical shell that surrounds the central tube. This structure provides sufficient stiffness and strength to withstand the loads that arise during launch, while having a reduced mass. The satellites themselves, rather than the central structure, bear the loads during launch. This allows the central structure to be of relatively lightweight construction.
December 9, 1999
Date of Patent:
August 21, 2001
DaimlerChrysler Aerospace AG
Ernst Hornung, Huba Ory, Andreas Rittweger, Markus Quadt, Peter Borgwardt, Joerg Bolz
Abstract: A temperature regulating arrangement (7) at least partially surrounds a fuel or oxidizer storage tank (1). The tank (1) is divided by a polymer membrane (3) into a first partial chamber (2) receiving the fuel (2′) therein, and a second partial chamber (4) receiving a gaseous pressure medium (4′) therein. The temperature regulating arrangement (7) includes thermal insulation, at least one heater, at least one heat sensor, and a temperature control and regulating unit. By heating the second partial chamber containing the gaseous pressure medium, any fuel vapor permeating through the membrane (3) from the first partial chamber (2) into the second partial chamber (4) is prevented from condensing within the second partial chamber (4). The permeation process is also limited. It is simply necessary to maintain the second partial chamber (4) at a temperature a few degrees Celsius higher than the temperature of the liquid fuel.
Abstract: An electrostatic ion propulsion engine for satellites and spacecraft is equipped with an electron source for neutralizing the propellant gas ion beam or jet emitted by the engine. The electron source includes an anode housing, a hollow cathode tube with gas flowing therethrough, a cathode element at the outlet end of the cathode tube within the interior space of the anode housing, and a pin- or rod-shaped auxiliary electrode arranged along the lengthwise axis in the hollow cathode tube. An ignition pulse is applied to the auxiliary electrode relative to the cathode tube, which causes a pulse discharge in the cathode tube, and in turn ignites the gas discharge between the anode and the cathode which generates the electron current.
Abstract: A lightweight pallet especially for holding payloads in a spacecraft has a sandwich construction with a core grid of longitudinal carrier beams and cross-connectors mounted between a top flat sheet metal plate and a bottom flat sheet metal plate and a bottom sheet metal plate. A cross-beam is secured to the front end and to the rear end of the pallet. The cross-beams carry journal pins for mounting the pallets to respective yokes in the cargo bay of a spacecraft. The cover plates are provided with cut-outs forming square or rectangular holes with rounded corners. Hole patterns or threaded holes are provided for the connection of junction plates and payloads to the pallet. The junction plates are secured where the longitudinal beams and the cross-connectors meet. At least one of the two laterally outer longitudinal beams has a recess for the recessed mounting of payload supply unit such as a power supply. The recess is then closed again by a plate capable of taking up shear stress.
Abstract: A device for fastening an injection element 4 with its foot 5 in a hole of a base plate 1 of an injection head 2 of a rocket engine, the foot 5 is tapered in steps up to its end. A first shoulder 7 of the foot abuts against the base plate 1; a thread (6) screwed into the base plate 1 is present after the first shoulder 7; the thread 6 is followed by a second shoulder 8 and then by a first, smooth cylindrical piece 9. This is followed by a third shoulder 11, on which a solder ring 12 made of a gold alloy is seated. A second, smooth cylindrical piece 13, which has a solder gap 13a between it and the corresponding hole in the base plate 1, follows after the third shoulder 11 up to the end. A process for fastening the injection element 4 provides for the solder ring 12 being first placed on the third shoulder 11, after which the injection element 4 is screwed into the base plate by means of a hexagon 22, and the injection head 2 is subsequently heated to about 1,035.degree. C.
January 30, 1998
Date of Patent:
September 5, 2000
DaimlerChrysler Aerospace AG
Hans-Joachim Klotz, Bernhard Stahn, Rudiger Ewald
Abstract: A FMCW radar tank level gauge (14) that measures a level (13) in a tank (10) by obtaining a set of phase shift data points of mixed transmitted waves and received waves. The set of spectral data phase shift values has a received target marker indicating the level. An adaptive set of masking threshold phase shift values corresponding to at least a portion of the spectral data phase shift values are calculated. The adaptive set of masking threshold values are compared with the corresponding spectral data values to identify at least one spectral data value associated with the level. The level of the tank is calculated from at least one spectral data value and the level of the tank is reported.
June 26, 1998
Date of Patent:
August 22, 2000
Rosemount Inc., DaimlerChrysler Aerospace AG
Stefan Cramer, Rolf Gluth, Thomas Schake, Brian E. Richter
Abstract: A phased-array antenna, particularly for the radar frequency range, comprising at least a predetermined number of transmit/receive radiator elements arranged linearly and/or matrix-shaped, a power distribution as well as a phase shifter network and a transmit/receive change-over arrangement. The transmit/receive change-over arrangement includes a serial feed comprising a waveguide with coupling in/coupling out locations disposed along its length and to which the phase shifter network, and possibly a further power distribution network, is coupled and also the transmitting/receiving arrangements are coupled. With this arrangement, an otherwise needed transmit/receive switch, for example, a circulator, is not necessary.
Abstract: An inert gas for fighting a fire occurring in an enclosed space is produced by the reaction of ammonia with atmospheric air to produce nitrogen mixed with water vapor which is introduced into the fire in the enclosed space. This fire fighting gas mixture is produced in a small gas turbine having a combustion chamber into which ammonia, preferably liquid ammonia, is sprayed. Additionally, water may be sprayed into the combustion chamber to cool the combustion gas to a desired temperature and supplied to the turbine which feeds its exhaust gas to a mixing chamber where a further temperature control may be performed by spraying water into the mixing chamber. The gas output of the mixing chamber is used for the fire fighting.