Bayerische Motoren Werke Aktiengesellschaft

Daimler Chrysler Ag

Eads Deutschland Gmbh

B Ayerische M Otoren W Erke a Ktiengesellschaft

Juergen Becker

Bernd Kupetz

Michael Hoetger

Raymond Freymann

Wolfgang Strobl

Walter Huebner

Andreas Obieglo

Norbert Kraus

Christian Goebel

Goeran Gensicke

Rainer Class

Hans-Guenther Ziegler

Peter Doemeland

A method is provided for producing a hot-formed component, in particular a sheet-metal component made of steel, aluminum, magnesium or a combination of the materials. The method includes the acts of: heating a semifinished product, in particular a sheet-metal blank or a pre-shaped sheet-metal component, inserting the semifinished product into a molding tool, and quenching the semifinished product in the molding tool, wherein a change is made to the microstructure of the material at least in one portion. Before the insertion of the semifinished product into the molding tool, an insulating device is applied in at least one predetermined region of the semifinished product. The insulating device is connected in a form-fitting, integral and/or force-fitting manner to the semifinished product.

Method for producing hot-formed components

A sheet metal component that is made of a press-hardened steel sheet material and is to be used as a vehicle body component for a motor vehicle, is provided. The sheet metal component has at least one overhardened component region which is provided to act as a predetermined breaking point in the event of being subject to a crash load. A component assembly and a motor vehicle body, which have at least one such press-hardened sheet metal component, are also provided.

Press-hardened sheet metal component with at least one predetermined breaking point, and component assembly and motor vehicle body with such a sheet metal component

A molding tool is provided for producing hot-formed components, in particular formed sheet metal parts. The molding tool includes a tool lower part and a tool upper part which are movable in relation to each other, and which include corresponding operative faces for shaping a hot-formed component. The operative face of at least one of the tool parts is configured so as to be coolable and that tool part includes cooling lines therein. At least one of the tool parts includes a clearance which in a closed state of the molding tool, conjointly with the hot-formed component, forms an air chamber. The air chamber functions as a thermal insulator between the hot-formed component and the tool part.

Molding tool for producing hot-formed components

A device for a press for shaping a sheet metal part with a section which can be shaped out separately as an undercut in the device. The device includes a press-side ram, a swage and a die which can be driven separately, serves to shape out the undercut, and interacts with an undercut contour which is arranged substantially in a filler slide which is mounted such that it can be moved rotationally in the swage. The filler slide can be transferred from a shaping-out position into a position which exposes the undercut in the sheet metal part, and vice versa. At least one temperature-control device is provided in the filler slide, by way of which temperature-control device the filler slide can be temperature-controlled at least in sections.

Rotary slide with cooling and temperature-controlled zones

A heat exchanger arrangement is provided for an internal-combustion engine having a heat engine, which converts hot steam of a working medium by way of an expansion device to kinetic energy. The working medium, that can be delivered by a pump, can be heated in a first heat exchanger by a coolant and in a second heat exchanger by an exhaust gas of the internal-combustion engine. In the delivery direction, the working medium first flows through the first heat exchanger and, subsequently, through the second heat exchanger. The exhaust gas can flow through the first heat exchanger.

Internal combustion engine and heat engine with multiple heat exchangers

In a method for assembling a plurality of component individual parts in stages to form a complex composite component, in order to achieve as high an accuracy as possible of the finished component, the individual parts are positioned relative to one another and fixed during the staged assembly process, such that there may be no need for any reclamping of the intermediate component between the individual assembly stages. For this purpose, a clamping frame is used, which is first equipped with some clamping elements, into which is introduced a first set of component individual elements which are assembled together with one another to form an intermediate component. In the second step, the clamping frame is equipped with further clamping elements, into which the component individual elements corresponding to them are introduced, and, in a further assembly step, these further component individual elements are assembled together with the intermediate component to form the finished component. For receiving and fixing the further clamping elements on the clamping frame, docking stations are provided, which may ensure a reproducible positioning and orientation of the clamping elements on the clamping frame.

Method and clamping frame for joining a number of piece parts to form a complex assembled part

Process for designing flight controllers, in which first for the rigid airplane and then for the elastic airplane the damping and the phase delay for each excitation frequency is determined, and the flight controller is adapted in such a manner that the structural responses to each excitation frequency for both the rigid airplane and the elastic airplane in the open control circuit outside two design fields, applicable to the elastic airplane, are laid around the instability points in the data field comprising damping and phase delay, whereby for the design of the elastic airplane between the phase delays of &minus;270 degrees and &minus;495 degrees, a damping exceeding &minus;6 dB is allowed.

Process for designing flight controllers

Flight control system for the longitudinal control of an automatically controlled airplane having adjusting surfaces provided for the longitudinal control which, viewed from the longitudinal axis of the airplane, are on the outside and on the inside. For the stabilization and control of the airplane in its longitudinal axis, the inner adjusting surfaces are controlled to experience an amplification which is substantially larger than that of the outer adjusting surfaces.

Flight control device for improving the longitudinal stability of an automatically controlled airplane and method of operating same

Method for compensating structural vibrations of an aircraft caused by wind blasts and buffeting in an aircraft in flight includes the steps of: detecting the structural vibrations by measurement technology using roll rates determined in an inertial sensing system, supplying the determined disturbing values to a flight control system, producing phase- and amplitude-correct control flap movements by generating appropriate control signals in respective control drives to counteract the phases and amplitudes of the excited vibrations.

Growing community of inventors

Munich, Germany

Juergen Becker