Abstract: A situation display system has a movable section for attachment to a helmet nd a stationary section, including a stationary map providing a real map background for showing situation display elements on the map. The movable section is connected through a flexible cable to a device for the remote control of the situation display elements which are computer generated. By accurate measurements of the location of the helmet and its distance to the map, signals are provided which are processed independently of any movements of an operator wearing the helmet so that the elements are correctly displayed and seen on the map. Thus, a tactical situation display is obtained for a military command system.

Abstract: A remote control for a rolling flying body enables that body to also perf pitching movements about its pitch axis and yawing movements about its yaw axis. For this purpose the flying body is equipped with a plurality of control nozzles distributed about the circumference of the flying body. These control nozzles or rather the fluid flow through the control nozzles is so controlled by control valves that two nozzles forming a pair are simultaneously activated for causing the desired pitching and yawing movements. The duration of the control impulse signals is determined exclusively by the rolling frequency of the flying body or missile.

Abstract: A high temperature heat shield system for re-entry vehicles and high speed ircraft is assembled from separate insulating panels made of metal foil layers diffusion soldered together and with a ceramic fiber material filled into interspaces between the metal foil layers. In this arrangement structural metal foil layers carry mechanical loads while separate reflecting foil layers and the ceramic fiber material are non-load bearing.

Abstract: In a method and system for storing gas, especially an inert gas for elect impulse space drives which use inert gas as a reaction mass, the inert gas is filled into a storage tank in the gaseous and/or liquid state and is then cooled to solidify it into the solid state in which it is then stored. While in the earth's atmosphere, temperature regulation is achieved by means of thermal insulation of the tank and a convective heat exchange between a cryogenic coolant and the inert gas in the tank. While in the vacuum of space, temperature regulation is achieved by means of radiant heat exchange between the tank and deep space. For extracting the gas from the tank, the frozen gas is locally sublimated from the solid to the gaseous state by a controlled localized heat application, whereby the required gas pressure is developed for withdrawing gas from the tank which holds the gas in the solid state, except at a heated outlet area.

Abstract: A system for producing pressure or shear-waves in a solid medium uses a wave generator with at least one primary induction coil and at least one short-circuited secondary coil. The short-circuited secondary coil is rigidly connected to the solid medium for directly transmitting to the solid medium the repulsion force generated between the primary and secondary coils by a short-circuit current caused to flow in the secondary coil when electrical power is applied to the primary coil. Thus, the system is a transformer in which the short-circuited secondary coil is directly used as the tool for the wave application.

Abstract: Printed circuit boards may be held in place in a releasable manner in the amping gap of a clamping device having a mounting member and clamping member arranged in parallel to each other to form the clamping gap. The clamping member is pivoted or journalled to the mounting member and an adjustable biasing spring tends to close the clamping gap. The device is simple, universally usable, and has a wide clamping range as well as a high clamping force and good heat removing abilities. An axial movement of an adjustment member permits opening or closing the clamping device.

Abstract: Expansion gaps formed between bellows type side walls of evacuated heat ilating wall components of gas and pressure-tight containers are sealed by elastically deformable corrugated expansion sheet metal strips welded to the surfaces of neighboring wall components, and by specially shaped junction covers secured in a gas-tight manner to the wall components and to the strips. The covers have a central cavity and ondulating depressions merging into corrugations of the sheet metal strips. The expansion gaps are also evacuated and filled with a suitable insulating material. Mechanically loadable support elements may be located in the expansion gaps.

Abstract: A suction device for taking-up, transporting, and depositing work pieces, ch as flat blanks of limp sheet material or panels, is equipped with a plurality of suction tubes. Each suction tube is individually connectable to a source of reduced pressure, whereby a pattern of effective suction tubes may be conformed to any particular configuration of a blank. The tubes are arranged in a housing, for example, in rows and columns. At least a portion of the housing is formed as a reduced pressure chamber. Each tube is individually connectable to the reduced pressure chamber to make the respective tube effective. Disconnection makes the tube ineffective. The connection of disconnection simultaneously moves the respective tube into a work position or into a rest position.

Abstract: A rotary mirror for an optical system has a mirror section with first and cond edges and a bearing connecting to each edge. A reinforcing rib and a slot extend alongside at least the first and second edges, and preferably at a right angle to a rotational axis of the two bearings. Each rib may extend on one or the other side of the respective slot or the slot may extend within the respective reinforcing rib. In all embodiments the slot rib combination decouples the mirror section from any misalignment of the bearings to prevent introducing distortions into the mirror section.

Abstract: In order to be able to determine in a simple manner the angular deviations etween the optical axes (OT, OS) of a telescope lens (2) and of a star tracker lens (8) which arise during the course of operation of a space telescope due to external influences, the entry (7a) of an orderly arranged light conductor bundle (7) is arranged in the focal plane (f.sub.t) of the space telescope lens (2) and the exit (7b) of the light conductor bundle (7) is lead into the focal plane (f.sub.k) of a collimator (9) arranged in the object-side opening of the star tracker lens (8). The angular deviation is determined by comparing the coordinates (y.sub.o, z.sub.o, y'.sub.o, z'.sub.o) of the images (S, S') of a reference star arising in the space telescope and in the star tracker. The collimator (9) may be mounted at the edge of the star tracker opening and a prism system (10, 11) may be provided for reflecting or imaging its beam path into the beam path of the star tracker.

Abstract: The panel sections of a solar collector, for example of a spacecraft, are ld or mounted in a folded down condition at least during launching and until they are unfolded. For this purpose a hold down device that must be released for the unfolding, is used. The device includes a piece of flexible rope or cable, one end of which is connected to the spacecraft body, while the other end is connected to the outermost panel section to hold all panel sections in the folded condition against forces tending to unfold the panel sections, until the rope or cable is severed by a severing mechanism. The effective cable length is adjustable and an elastic member is so arranged that it can dampen shocks and compensate for different temperature responsive expansions of the rope or cable and of the collector structure.

Abstract: In order to avoid a negative coupling between blade lead-lag movements and lade angle adjustment movements in a helicopter rotor, the angle (.beta.) between a control rod (5) for the blade angle adjustment and an effective damping plane (M) of the rotor is increased as compared to the respective angle in conventional rotors. This increase of the angle (.beta.) is accomplished by arranging a damping device (9) having the effective plane (M) for suppressing blade lead-lag movements in such a way on a blade angle control sleeve (4), that the effective plane (M) of the damping device (9) encloses an angle (.alpha.) with the lead-lag plane of the rotor.

Abstract: On board functions are performed in an aircraft with the aid of a central control computer connected to a plurality of input and output devices including data terminals for passengers and flight attendants, through a data bus system and through decoder/encoder units linking the data terminals to the data bus system for providing an operation with digital signals. Thus, digital signals are transmitted back and forth between the central control computer and the data terminals in such a way that computations initiated on a data terminal are performed by the central control computer and so that the computation results and any other information are displayed on a display field forming part of the data terminals, one of which is provided at each passenger seat. Modified terminals are provided at various other locations within the aircraft cabin for use by a flight attendant.

Abstract: A fly-by-wire control system for the elevator assemblies of an aircraft is quipped with a mechanical auxiliary control (8) and with a synchronizing coupling (10). The electrical control links connecting the controlling computers to the elevator drives are each equipped with an override mechanism (4,2). A mechanical cable link (9) of the auxiliary mechanical control (8) connects a pilot operated mechanical control member such as a pitch control wheel having a detent to the respective override mechanism. This combination makes sure that the pilot initiated control signals have performance priority over any other signals at all times. The synchronizing coupling (10) is arranged between the mechanical control links leading to the respective elevator flap drives to assure a symmetric flap deflection on both sides at high speed flight under failure conditions. Centering springs (12) assure a centered position of the flap if the respective flap side signal transmission linkage (4.

Abstract: An elevator control system especially for an aircraft such as an airplane, s equipped with an electrically controllable elevator flap drive system for the elevator flap on each side of the aircraft. Additionally, the system is equipped with a mechanically controlled auxiliary drive system which is responsive to a hand wheel operated by the pilot. A single hand wheel has mechanical connecting links to the elevator flaps on both sides of the aircraft. Monitoring features enable the pilot to test the auxiliary mechanical drive system without actually switching on that system. The auxiliary mechanically operated system is functional even if all other power systems failed, since a ram air turbine is provided for generating the hydraulic pressure for driving the auxiliary system.

Abstract: A computer aided riveting robot has a machine frame for movably mounting a work piece positioning support and riveting tool positioning carriers. A rectangular three-dimensional coordinate system is defined in the machine frame, whereby an x-y-plane (61) constitutes a reference plane. The machine frame extends upwardly from a machine base in the y-direction of the rectangular coordinate system. The work piece positioning support extends upwardly in the y-direction and supports a work piece so that its largest surface area extends approximately in an x-y-plane of the rectangular coordinate system. The work piece positioning support in turn is supported by guide rails for moving the work piece back and forth in the x-direction. Two riveting tool carriers are supported in the machine frame and hold two riveting tools for movement in the z-direction. The tool carriers extend in the y-direction and are so arranged that the work piece extends between the two tool carriers.

Abstract: A vertical rudder control and drive system for an aircraft, such as an aiane, is equipped with electrically controllable vertical rudder drive systems on each side of the aircraft. Additionally, the control system is equipped with a mechanically controllable auxiliary drive system for the operation of the vertical rudder in response to foot pedals operated by the pilot when there should be a failure in the electrically controlled drive systems. A mechanical control signal transmitting link is provided between the foot pedals and the hydro-mechanical drive for the vertical rudder. Monitoring features enable the pilot to test the mechanical drive system without actually using that system in flight. Preflight tests may be performed.

Abstract: An aircraft, such as a helicopter, is trimmed into a desired position by ducing a trimming control signal during the maneuver for the desired positive and adjusting control forces in response to the trimming control signal. The trimming control signal (.delta..sub.T) is produced by comparing a rated or reference signal (R) representing the desired displacement from the force free position of the stick, with a measured signal (.theta.) representing the rotational speed of an aircraft about a given axis. In addition to the trimming operation a stabilization of the position of the aircraft is performed at the moment when the pilot does not touch the control stick. The measured signals thus include information regarding the deviation of the aircraft from the desired position. Thus, a trimming motor automatically maintains the aircraft into the desired attitude.

Abstract: Auxiliary winglets or control surfaces for aircraft wings are tiltable ab an axis extending in the flight direction and about an axis extending substantially perpendicularly to the flight direction. The auxiliary wing tips have a configuration which assure a wing surface continuity, especially when the tips are in their normal wing extending position, but also in any other position of the winglets. Additionally, at least the leading auxiliary winglets are located upstream of the elastic wing axis, as viewed in the flight direction and they have a forward sweep or negative sweepback. The combination of these features permits a simultaneous reduction of induced drag and of stress caused by wind gusts, and for increasing the effectiveness of the wing's ailerons. Thus, these auxiliary winglets have three advantages simultaneously.

Abstract: A structural component having a curved wall, such as an aircraft fuselage pipe, has a grid structure formed of box frames produced by winding tapes of fiber reinforced synthetic material, so-called prepregs, onto mold bodies. These mold bodies are then assembled on a mandrel for covering with a planking and curing whereby the tapes are bonded together to form stringers intersecting with ribs in a grid structure and whereby the planking is bonded to the grid structure. The ribs are reinforced by fiber reinforced belt segments of synthetic material inserted into gaps between adjacent short ends of the mold bodies, whereby these belt segments are bonded to the ribs during curing. The belt segments ave a width corresponding to a multiple of the width of the stringers and hence protrude radially inwardly. Preferably, an edge reinforcing strip of fiber reinforced material is arranged alongside the radially inner edge of the belt segments.