Abstract:
L'invention a pour objet une munition (10) ou un composant de munition comprenant un chargement pyrotechnique (23) associé à une structure (12), telle une enveloppe. Cette munition est caractérisée en ce qu'une partie au moins de la structure (12) est réalisée en un matériau énergétique comprenant au moins un composant énergétique mélangé à au moins un premier matériau de renfort structural.
Abstract:
A flying platform (10), propelled by at least one ducted fan (11) causing a vertically downwardly directed airstream in and through a cylindrical duct (12). A vane system in the duct (12) has two mutually perpendicular pairs (31-34) of diametrically opposite first vanes, each extending in from the duct rim toward the center of the duct. Each pair of first vanes provides a pair of generally vertical walls parallel to a diametral line across the duct, and they define duct passages between the pairs of vanes and define quadrants between adjacent pairs. Each first vane has an upper, fixed, rigid portion and a variable camber flap (45, 46) depending therefrom. A first servomotor with linkages vary the camber of each pair of flaps (45, 46), so that the camber of the flaps (45, 46) of each pair is at all times the same amount but in opposite directions. Preferably, there are also four second vanes (41-44), one bisecting each quadrant, and a symmetric pair of spoilers (75-82) is mounted on each second vane (41-44). Each pair of spoilers (75-82) is independently movable, as a pair continuously between a position substantially blocking airflow through the outer portion of said quadrant and a position permitting substantially full airflow therethrough. A second servomotor with linkages symmetrically varies the position of its spoilers (75-82). There may be a radio receiver responsive to remote control signals for actuating each servomotor and its linkages.
Abstract:
A method of providing power information in a rotorcraft, the rotorcraft having a powerplant. The method comprising calculating a real-time power required and calculating a real-time power available, and orienting power required and power available indicators on a power safety instrument, the position of the power required indicator being dependent upon the calculated power required, and the position of the power available indicator being dependent upon the calculated power available.
Abstract:
A power safety system (301) is configured to provide power information in an aircraft (101). The power safety system (301) includes a power safety instrument (303) having a power required indicator (311) and a power available indicator (313), each being located on a display. A position of the power required indicator (311) and the power available indicator (313) represent the power available and power required to perform a hover flight maneuver. The power safety system (301) may be operated in a flight planning mode or in a current flight mode. The power safety system (301) uses at least one sensor (309) to measure variables having an effect on the power required and the power available.
Abstract:
The disclosed embodiments include a trailer for an autonomous vehicle controlled by a command and control interface. The trailer includes a trailer body configured to retain the autonomous vehicle in an undeployed configuration. The trailer also anchors the autonomous vehicle in a deployed configuration. A tether is provided having a first end coupled to the trailer body and a second end that is configured to couple to the autonomous vehicle. A winch is utilized to adjust a length of the tether to move the autonomous vehicle between the undeployed configuration and deployed configuration. Further, a communication system communicates with the command and control interface and the autonomous vehicle to control movement of the autonomous vehicle between the undeployed configuration and deployed configuration.
Abstract:
A method of providing power information in a rotorcraft, the rotorcraft having a powerplant. The method comprising calculating a real-time power required and calculating a real-time power available, and orienting power required and power available indicators on a power safety instrument, the position of the power required indicator being dependent upon the calculated power required, and the position of the power available indicator being dependent upon the calculated power available.
Abstract:
A power safety system (301) is configured to provide power information in an aircraft (101). The power safety system (301) includes a power safety instrument (303) having a power required indicator (311) and a power available indicator (313), each being located on a display. A position of the power required indicator (311) and the power available indicator (313) represent the power available and power required to perform a hover flight maneuver. The power safety system (301) may be operated in a flight planning mode or in a current flight mode. The power safety system (301) uses at least one sensor (309) to measure variables having an effect on the power required and the power available.
Abstract:
An apparatus, and a method performed by the apparatus, are disclosed wherein the apparatus can be mounted on an unmanned vehicle and arranged to act upon a payload. The payload can be mounted on the unmanned vehicle and, under an action of the apparatus, is able to be activated. The method can include receiving an activation instruction from an entity remote from the unmanned vehicle; determining whether or not the received activation instruction is valid by performing a validation process; and in response to determining that the received activation instruction is valid, activating the payload. In response to determining that the received activation instruction is not valid, activation of the payload may be prevented or opposed.
Abstract:
A power safety system (301) is configured to provide power information in an aircraft (101). The power safety system (301) includes a power safety instrument (303) having a power required indicator (311) and a power available indicator (313), each being located on a display. A position of the power required indicator (311) and the power available indicator (313) represent the power available and power required to perform a hover flight maneuver. The power safety system (301) may be operated in a flight planning mode or in a current flight mode. The power safety system (301) uses at least one sensor (309) to measure variables having an effect on the power required and the power available.
Abstract:
L'invention a pour objet une munition 10 ou composant de munition comprenant une charge utile associée à une structure 2 d'emport de la charge utile, une partie au moins de la structure 2 étant réalisée en un matériau énergétique comprenant au moins un composant énergétique mélangé à au moins un premier matériau de renfort structural. La munition ou le composant comporte au moins un dispositif d'amorçage 24a, 24b de la structure énergétique 2, ledit dispositif étant relié à un moyen de commande 16, la structure constituant une enveloppe 12 délimitant une cavité 22 recevant un chargement 23 inerte ou pyrotechnique.