| 摘要 |
<p>The invention relates to a method and an installation for parachuting a logic unitary active equipment of special and complex fast control meant to open the short and fast parachute for low-altitude drops by reverse launching for aircraft rescue. The claimed method consists in that the parachute is self-launched detecting the damage by movements and accelerations, guiding the landing and selecting the method adequate to the situation, the ballistic parachute being apparently reversely opened, and then vertically reoriented by the traction of the falling object, so that the parachute appears already opened beside the object, the launching of the bag being possible through the rotor in a synchronised manner with helicopter rotor, the parachute being anchored to the rotor, unwinding the cable from the bag in a tensioned and controlled manner above the moving blades. The claimed installation comprises two bags () for the parachutes that are installed in stand-by on the aircraft, each bag having two parachutes with two power stages, the first stage consisting in braking and orienting the aircraft, the second stage in additionally braking it, in cooperation with the first stage, and for launching the parachute bag () and passing it above the rotor, and in the point which has been selected as the most favourable, each bag () is installed on a launching minigun () by means of which the bag mass is detached from the aircraft and quickly and precisely launched in synchronism with the rotation of blades, the minigun () being oriented under an angle () adjustable depending on the situation, each bag () being provided with a remotely controlled carrying rocket () for transportation, with a possibility of correction of the initial launching direction while moving and with a limited propulsion at the finish of the estimated path and control stop, being guided in a programmed manner and assisted logically on a prolonged semi-circular path, as the case may be, while the path is traveled, the said path being generated by the rocket () which stretches the anchoring cable () above the blades of the main rotor, and having a radius limited by the momentary length of the anchoring cable () stretched in a tensioned manner.</p> |
