Abstract: A method for controlling a aircraft with a plurality of drive units, in particular a plurality of electrical drive units, and a controller for flight control. At least one lateral control signal is entered into the controller for flight control in order to initiate a lateral movement of the aircraft. The significant point is that a speed (V) of the aircraft is ascertained through a speed estimation (6) and, depending on the estimated airspeed (V), a commanded roll angle (?C) and a commanded pitch angle (?c), a rate of turn ({dot over (?)}) is calculated. The lateral movement is automatically initiated with the calculated rate of turn ({dot over (?)}) through input of the lateral control signal.

Abstract: In an embodiment, a method is provided. The method comprises selecting at least one set of line of sight (LOS) vectors oriented in one or more directions outward from a vehicle; determining at least one air data solution based on the at least one set of LOS vectors; adjusting at least one value of an air vector equation based on a predetermined quantity; upon adjusting the at least one value, then determining at least one modified air data solution, wherein the at least one modified air data solution is determined based on the at least one set of LOS vectors and the at least one value; and comparing a difference between the at least one air data solution and the at least one modified air data solution to a threshold value, wherein the threshold value is indicative of error with respect to the at least one set of LOS vectors.

Abstract: In accordance with an embodiment, a method of operating an aircraft includes operating the aircraft in a first mode including determining an attitude based on a pilot stick signal, where a translational speed or an attitude of the aircraft is proportional to an amplitude of the pilot stick signal in the first mode; transitioning from the first mode to a second mode when a velocity of the aircraft exceeds a first velocity threshold; and operating the aircraft in the second mode where the output of the rate controller is proportional to the amplitude of the pilot stick signal.

Abstract: A sheet feeder includes a separation roller, a retard roller, and a return latch. The separation roller rotates in a forward direction to separate a sheet and transport the separated sheet in a sheet transport direction. The retard roller forms, together with the separation roller, a nip point and rotates in a reverse direction to return a sheet in a direction opposite to the sheet transport direction. The return latch moves from a retracted position to a protruding position to return a sheet remaining after separation by the separation roller to a position upstream of the nip point in the sheet transport direction. The return latch, when at the retracted position, is retracted from a sheet transport path and, when at the protruding position, protrudes to the sheet transport path.

Abstract: The technology disclosed herein can include a motor unit having a motor with a motor gear to rotate a drive shaft and a drive gear. A manual input shaft can also be configured to transmit rotation to the drive shaft. The motor can have a central axis that forms an angle of less than 90 degrees with a plane substantially defined by an outer surface of a gear box coupled to the motor. A mounting bracket is configured to allow mechanical communication between the motor unit and an internal ring gear. The internal ring gear can be mounted to a vehicle and a turret can be pivotably disposed within the internal ring gear. A motor unit is mounted on the turret and a drive gear is rotatably mounted on the motor unit and in direct engagement with the internal ring gear.

Abstract: An assembly for changing the posture of a weapon coupled to a sensor system comprises a weapon mount configured to support a weapon. The assembly further comprises a movement mechanism coupled between the weapon mount and the sensor system. The movement mechanism is movable between a first configuration in which a boresight or barrel of the weapon is aligned with a first axis of a line of sight of the sensor system and a second configuration in which the barrel of the weapon is disposed along a second axis rotated with respect to the first axis such that the weapon is no longer pointed in the same direction as the sensor.

Abstract: The present invention relates to the field of unmanned air vehicles, more commonly designated drone. More specifically, the invention applies to an armed drone system (10), notably equipped with a firing device and a steerable optronics ball (B) comprising means of illuminating targets (C). The invention proposes that the firing device be oriented towards the rear, so as to reduce the problems of masking of the optronics ball (B) by elements located in its line of sight, such as a front wheel (FW) for example. Moreover, because of operational use involving a phase (10S) for firing weapons and illuminating the target (C) from the back, the armed drone (10) moving away from the target, the vulnerability of the drone (10) is lessened.

Abstract: A method of displaying target engageability information to a pilot of an aircraft in flight including calculating according to instantaneous aircraft position and motion relative to at least one target to be engaged and to characteristics of a weapon, earliest and latest weapon release points between which the weapon is presently capable of engaging a target of interest and generating display symbols indicating a weapon launch acceptable region and the instantaneous position of the aircraft relative thereto. A system for displaying the information and a target engageability display symbology are also described.

Abstract: A seating system for a weapon operator of a military vehicle such as a tank has adjustable chest and back supports which can be locked to secure the weapon operator in position with respect to weapon controls in spite of highly dynamic changes in the position of the vehicle.

Abstract: An apparatus and fire protection system for detecting and extinguishing a spark, flame, or fire on a heat sensitive explosive object, which identifies, locates and relays vital information related to the particular endangered explosive object. The invention can be used to protect any heat sensitive object from thermal damage, explosive or not. Thermal energy activates a power supply, which powers the system, including a plurality of status sensor circuits that determine the status of the source of thermal energy. Each source of thermal energy is individually encoded to relay traits specific to the particular hazardous item, such as cook-off rate, type of energetic material and detonation temperature. Ultimately, all the information from the plurality of circuits and the EEPROM is relayed to personnel via the main system status display board. This permits personnel to become aware of a potential threat and monitor efforts to subdue the threat.

Abstract: External armament apparatus, including a machine gun, an associated ammunition box for supplying belted ammunition to the gun, a flare dispenser, a missile launcher or other external stores apparatus, and a forward looking infrared sensor (FLIR), is exteriorly supported on a landing gear sponson tow plate of a helicopter, adjacent a cabin area gunner's window. The external mounting of the gun and other armament apparatus frees up cabin space, permits the gunner's window to be closed with the gun in a ready position, and permits a 0.50 caliber machine gun to be used an alternative to either a 7.62 mm mini-gun or a single barrel 7.62 mm machine gun adjacent the gunner's window.

Abstract: A method for providing a pilot with information associated with at least one region of a field of view visible to the pilot from within a cockpit without requiring a visual display. The method includes the steps of determining an eye gaze direction relative to a given frame of reference for at least one eye of the pilot, determining a reference direction relative to the given frame of reference, comparing the eye gaze direction with the reference direction, and if the eve gaze direction and the reference direction are equal to within a given degree of accuracy, generating audio output audible to the pilot and indicative of information associated with the reference direction.

Abstract: Sight head with integrated laser designator for use in an aircraft such as a rotorcraft. The laser designator (32) is integrated into a zone of a main external assembly of the pod (14) of the sight head (12), enclosed externally in an existing fairing (34). It comprises a laser transmitter (36), a power supply (38) and a radio receiver (40). The laser transmitter (36) is fitted to the site head structure using adjusting screws (46) which allows the alignment to be modified.

Abstract: The present invention relates to a suspension device (4) for connecting an item of on-board equipment (2) to the structure (3) of a vehicle, particularly a rotary-wing aircraft, said suspension device (4) comprising first and second parts (5, 6) shaped in the form of plates and capable of being fixed to said structure (3) and to said item of equipment (2), and suspension means (7) which are arranged between said first and second parts (5, 6). According to the invention, the suspension device (4) additionally comprises a locking system (20) capable of bringing the suspension device (4) into one of two positions: a locked position in which the locking system (20) immobilizes the first and second parts (5, 6) one with respect to the other, and an unlocked position in which the locking system (20) releases said parts (5, 6) so that they can move relative to one another, and means (21) for controlling the locking system (20).

Abstract: This invention discloses a system for tracking one or more objects (22) within a region of interest, including at least one electromagnetic field generator (20), fixed with respect to an external frame of reference, at least one passive transponder (30), fixed to an object (22) being tracked, wherein an electromagnetic field generated by the electromagnetic field generator (20) causes the transponder (30) to generate electromagnetic signals and at least one electromagnetic sensor (24), fixed with respect to the external frame of reference, which receives electromagnetic signals generated by the transponder (30) and determines the three-dimensional position and three-axis rotational orientation of the object (20) using these signals. A method of tracking translation and rotation of one or more objects within a region of interest is also disclosed.