Aircraft parachute with bowden cables energized by the dynamic shock of the canopy

A ballistic parachute (40) for an aircraft (30) or for an unmanned aerial vehicle-(UAV) (70), comprising a pair of forward straps (20, 21) connected at forward sockets (46) provided proximally and on either side of the nose of the aircraft (30) or of the unmanned aerial vehicle-(UAV) (70) and a rearward strap (28) connected proximally to the tail of said aircraft (30) in the vicinity of a storage space of said parachute (40), the ballistic parachute being deployed and a canopy (41) thereof being inflated in an emergency situation, means of fixedly connecting said forward straps (20, 21) at said forward sockets (46), each of said forward straps (20, 21) comprising a folded extremity with a pair of folded sides that form a loop (35) with a frontal end and a rear end, transverse stitches (39, 39a) being provided at the rear end of said loop (35), an opening (36) being provided between said transverse stitches (39, 39a) at the rear end of said loop (35), an arm of said means of fixedly connecting said forward straps (20, 21) being confined within said opening (36) and an arm (27b) of a metallic snap hook (27) being confined at the frontal end of said loop (35), a main pretension device (50) of a Bowden cable being connected to said snap hook (27), said main pretension device (50) that is connected to said snap hook (27) comprising an inner cable (51) within a housing (52) being provided adjacently to said metallic snap hook (27), said housing (52) of said main pretension device (50) being fixedly mounted at points of anchorage (52a, 52b) of the frame of the aircraft (30) or of the UAV (70), a first end of said inner cable (51) of said main pretension device being provided with a terminal stake eye (51a) connected to a safety (27a) of said snap hook (27) and a second end of said inner cable (51) of said main pretension device being provided with a terminal stake eye (51b) adapted to function as a hook splitter, a plurality of terminal stake eyes (51a) of further pretension devices (50) of Bowden cables being connected to said terminal stake eye (51b) adapted to function as a hook splitter of said main pretension device (50) that is connected to said snap hook (27), each one of said further pretension devices (50) of Bowden cables being provided with a terminal stake eyes (51b) connected to a safety system of the aircraft (30) or (UAV) (70) and being adapted to transfer a pulling action therein with a scope of activation of said safety system during an emergency situation whereby, following deployment of the ballistic parachute (40) and inflating of said canopy (41) thereof, a dynamic shock is being exercised along said forward straps (20, 21) of the parachute (40), said dynamic shock resulting in tearing of said transverse stitches (39) and linear displacement of said metallic snap hooks (27) towards the rear end of said loop (35) of each one of said forward straps (20, 21) of the parachute (40), whereby a pulling action is being exerted onto said inner cable (51) of the main pretension device being connected to said safety (27a) of said snap hook (27), said pulling action being thereafter transferred to said further pretension devices (50) of Bowden cables thereby activating said safety systems of the aircraft (30) or (UAV) (70). said safety systems comprising any combination of the following:

• a safety system adapted to perform shutdown of the engine of the aircraft (30) or (UAV) (70) through setting at an off condition of a master switch (60), of an ignition switch (63), of a fuel supply switch (65) and pulling of a terminal (61a) of an ignition cable of the engine of the aircraft (30) or of the (UAV) (70);
• a safety system adapted to perform actuation of the doors and of the main landing system of the aircraft (30) or of the (UAV) (70);
• a safety system adapted to perform full flaps extension (92) of the aircraft (30) or of the (UAV) (70);
• a safety system adapted to perform drainage of liquid fuel tanks (90b) provided within the wings (90) and detachment and drop of a liquid fuel tank (95) within the fusealge of the aircraft (30) or of the (UAV) (70);
• a safety system adapted to perform pulling and tightening of safety belts (110) provided in each one of a plurality of seats (130) of the aircraft (30);
• and
• a safety system adapted to provide an anti-submerging function to each one of the plurality of seats (130) of the aircraft (30).