Aircraft parachute with bowden cables energized by the dynamic shock of the canopy
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-017/00
B64D-017/24
B64C-013/30
B64C-025/30
B64D-017/36
B64D-017/80
B64D-025/04
B64D-037/26
출원번호
US-0694334
(2012-11-21)
등록번호
US-9199742
(2015-12-01)
우선권정보
GR-20120100055 (2012-01-26)
발명자
/ 주소
Giannakopoulos, Pavlos
출원인 / 주소
Giannakopoulos, Pavlos
대리인 / 주소
Miltons IP/p.i.
인용정보
피인용 횟수 :
3인용 특허 :
5
초록▼
From the dynamic shock of the parachute canopy applied to an aircraft and unmanned aerial vehicle-(UAV) in an emergency, there is unlimited mechanical force available for exploitation through Bowden cables connected to the ends of the parachute straps, and transfer of the force in the form of a pull
From the dynamic shock of the parachute canopy applied to an aircraft and unmanned aerial vehicle-(UAV) in an emergency, there is unlimited mechanical force available for exploitation through Bowden cables connected to the ends of the parachute straps, and transfer of the force in the form of a pull onto the emergency safety systems of the aircraft for the safety of passengers, and onto the aerial vehicle-(UAV).
대표청구항▼
1. 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 r
1. 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); anda safety system adapted to provide an anti-submerging function to each one of the plurality of seats (130) of the aircraft (30). 2. A ballistic parachute (40) for an aircraft (30) or for an unmanned aerial vehicle-(UAV) (70) according to claim 1, wherein said means of fixedly connecting said forward straps (20, 21) at said forward sockets (46) are karabiners (26), a pair of mounting straps (23, 24) being provided for fixedly connecting each of said karabiners (26) to the frame of the aircraft (30) or of the unmanned aerial vehicle-(UAV) (70) and an arm (25) of said karabiners (26) being confined within said opening (36) between said transverse stitches (39, 39a) at the rear end of said loop (35) of each one of said forward straps (20, 21). 3. A ballistic parachute (40) for an aircraft (30) or for an unmanned aerial vehicle-(UAV) (70) according to claim 1, wherein said means of fixedly connecting said forward straps (20, 21) at said forward sockets (46) are metallic safety buckles (73) with an opening (71), a screw passing through the opening (71) being employed for fixedly connecting each one of said safety buckles (73) onto the frame of the aircraft (30) or of the unmanned aerial vehicle-(UAV) (70) and an arm (72) of said safety buckles (73) being confined within said opening (36) between said transverse stitches (39, 39a) at the rear end of said loop (35) of each one of said forward straps (20, 21). 4. A ballistic parachute (40) for an aircraft (30) or for an unmanned aerial vehicle-(UAV) (70) according to claim 1, wherein said means of fixedly connecting said forward straps (20, 21) at said forward sockets (46) are tubes (75) fixedly mounted onto the frame of the aircraft (30) or of the unmanned aerial vehicle-(UAV) (70), said tubes (75) being confined within said opening (36) between said transverse stitches (39, 39a) at the rear end of said loop (35) of each one of said forward straps (20, 21). 5. A ballistic parachute (40) for an aircraft (30) or unmanned aerial vehicle-(UAV) (70) according to claim 1, wherein said safety system adapted to perform shutdown of the engine of the aircraft (30) or (UAV) (70) through setting at an off condition of the master switch (60), of the ignition switch (63), of the fuel supply switch (65) and through pulling of the terminal (61a) of the ignition cable of the engine of the aircraft (30) or of the (UAV) (70) comprises a pretension device (50) of Bowden cable for the master switch (60), a pretension device (50) of Bowden cable for the ignition switch (63), a pretension device (50) of Bowden cable for the fuel supply switch (65) and a pretension device (50) of Bowden cable for pulling of the terminal (61a) of the ignition cable of the engine of the aircraft (30) or of the (UAV) (70), each one of said pretension devices (50) of Bowden cables being provided with a terminal stake eye (51a) 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), wherein the point of anchorage (52a) of the outer plastic housing (52) of said pretension devices (50) of the safety system adapted to perform shutdown of the engine of the aircraft (30) or (UAV) (70) is located onto the frame of the aircraft (30) or (UAV) (70), and said terminal stake eyes (51b) of said pretension devices (50) are connected directly onto said master switch (60), said ignition switch (63) said fuel supply switch (65) and said terminal (61a) of the ignition cable of the engine of the aircraft (30) or of the (UAV) (70) respectively, the second point of anchorage (52b) of the outer plastic housing (52) of said pretension devices (50) being located onto the frame of the aircraft (30) or (UAV) (70), adjacently to said master switch (60), said ignition switch (63), said fuel supply switch (65) and said terminal (61a) of the ignition cable (61) of the engine of the aircraft (30) or of the (UAV) (70) respectively, whereby, in response to the pulling action, resulting from the dynamic shock being exercised along said forward. straps (20, 21) of the parachute (40) during deployment thereof in an emergency situation, that is being transferred to said pretension devices (50) of said safety system adapted to perform shutdown of the engine of the aircraft (30) or (UAV) (70) in an emergency situation, said master switch (60), said ignition switch (63) and said fuel supply switch (65) are being set at an off condition and the terminal (61a) of the ignition cable (61) is detached from a socket (62a) of an ignition coil (62). 6. A ballistic parachute (40) for an aircraft (30) or unmanned aerial vehicle-(UAV) (70) according to claim 1, said aircraft (30) or unmanned aerial vehicle-(UAV) (70) comprising wheels (77b) mounted onto struts (77a) arranged within the wings (90) and a wheel (77b) with a mechanical actuation system (81) at the nose of said aircraft (30) or unmanned aerial vehicle-(UAV) (70), said struts (77a) being provided with hydraulic actuation mechanisms (78c) adapted to initiate rotation of said struts (77a) downwardly to extract the wheels (77b) through openings closed by doors (78), said doors (78) being actuated with actuation mechanisms (78a), wherein said safety system adapted to perform actuation of the doors and of the main landing system of the aircraft (30) or of the (UAV) (70) comprises pretension devices (50) of Bowden cables, each one of said pretension devices (50) of Bowden cables being provided with a terminal stake eye (51a) 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), the points of anchorage (52a, 52b) of the pretension devices (50) of said safety system adapted to perform actuation of the doors and of the main landing system of the aircraft (30) or of the (UAV) (70) being located onto the frame of the aircraft (30) or of the (UAV) (70), whereby, in response to the pulling action, resulting from the dynamic shock being exercised along said forward straps (20, 21) of the parachute (40) during deployment thereof in an emergency situation, that is being transferred to said pretension devices (50) of said safety system adapted to perform actuation of the doors and of the main landing system of the aircraft (30) or of the (UAV) (70) in an emergency situation, said doors (78) drop downwardly and said wheels (77b) on either side of the wings (90) and on the nose of the aircraft (30) are lowered to landing position. 7. A ballistic parachute (40) for an aircraft (30) or unmanned aerial vehicle-(UAV) (70) according to claim 1, wherein the aircraft (30) or (UAV) (70) comprises flaps (92) in the middle of the rear portion of a frame (90a) of each one of the wings (90) thereof, a trailing edge of said flaps (92) being oriented towards the fuselage of the aircraft (30) or (UAV) (70), extension of said flaps (92) providing an enhanced lift to the wings (90) during the descent of the aircraft (30) or (UAV) (70) with the parachute (40), said safety system adapted to perform full flaps extension (92) of the aircraft (30) or of the (UAV) (70) comprising a pretension device (50) of Bowden cable for said flaps (92) in each one of the wings (90) of the aircraft (30) or of the (UAV) (70), each one of said pretension devices (50) of Bowden cables being provided with a terminal stake eye (51a) 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), the points of anchorage (52a) of the pretension devices (50) being located onto the fuselage (30a) of the aircraft (30) or of the (UAV) (70) and the points of anchorage (52b) of the pretension devices (50) being located onto the frame (90a) of the wings (90) near the flaps (92), said inner cables (51) of the pretension devices (50) with Bowden cables having an end pivotally connected at points (92a, 92b) of said flaps (92), whereby said inner cables (51) of the pretension devices (50) with Bowden cables being adapted to rotate said flaps (92) at said points (92a, 92b) thereby altering the camber of the wings (90) of said aircraft (30) or (UAV) (70) and providing an enhanced lift during during descent of the aircraft (30) or (UAV) (70) in an emergency situation. 8. A ballistic parachute (40) for an aircraft (30) an unmanned aerial vehicle-(UAV) (70) according to claim 1, wherein a fuel tank (95) is mounted onto the fuselage of the aircraft (30) or (UAV) (70) and each wing (90) comprises a fuel tank section (90b) in between a pair of ribs (90a), said section (90b) covered with a covering (90c), said covering (90c) being delimited by a predetermined compressed and etched line (91), said 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 fuselage of the aircraft (30) or of the (UAV) (70) comprising a pretension device (50) of Bowden cable for each fuel tank section (90b) and a pretension device for the fuel tank (95) mounted onto the fuselage of the aircraft (30) or (UAV) (70), each one of said pretension devices (50) of Bowden cables being provided with a terminal stake eye (51a) 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), the points of anchorage (52a) of the pretension devices (50) being located onto the fuselage (30a) of the aircraft (30) or of the (UAV) (70) and the points of anchorage (52b) of the pretension devices (50) being located onto said fuel tank section (90b) and onto the fuselage for said fuel tank (95), said inner cables (51) of the pretension devices (50) with Bowden cables having an end connected at end points (90d) of said predetermined compressed and etched line (91), whereby, in response to the pulling action, resulting from the dynamic shock being exercised along said forward straps (20, 21) of the parachute (40) during deployment thereof in an emergency situation, that is being transferred to said pretension devices (50) of said safety system adapted to perform drainage of the liquid fuel tanks (90b) provided within the wings (90) and detachment and drop of the liquid fuel tank (95) within the fusealge of the aircraft (30) or of the (UAV) (70) in an emergency situation, said inner cables (51) of the pretension devices (50) with Bowden cables connected with said fuel tank sections (90b) perform tearing of said covering (90c) along said predetermined compressed and etched line (91) thereby allowing drainage of liquid fuel tanks (90b) and said inner cable (51) of the pretension device (50) with Bowden cable connected with said fuel tank (95) performs detachment of connecting tubes (95b) of said fuel tank (95) and opening of a bottom door (95a) thereby allow detachment and drop of the fuel tank (95) during descent of the aircraft (30) or (UAV) (70) in an emergency situation. 9. A ballistic parachute (40) for an aircraft (30) according to claim 1, wherein said aircraft comprises a plurality of seats (130) for an equivalent plurality of passengers, each one of said seats (130) being provided with a safety belt (110) comprising two shoulder straps (130a, 130b) extending above the shoulders of a passenger and at least one apron strap (130c) enclosing and retaining the pelvis of the passenger seated on one of said seats (130), a safety buckle (131) being employed to connect said apron strap (130c) to said shoulder straps (130a, 130b), wherein said safety system adapted to perform pulling and tightening of the safety belts (110) provided in each one of the plurality of seats (130) of the aircraft (30) comprises a first pretension device (50) of a Bowden cable for said shoulder straps (130a, 130b) and a second pretension device (50) of a Bowden cable for said apron strap (130c), wherein said first and second pretension devices (50) of Bowden cables are provided with a terminal stake eye (51a) 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), the point of anchorage (52a) of said first and of said second pretension device (50) being located at the bottom of the seat (130), whilst the point of anchorage (52b) of said first pretension device (50) of the shoulder straps (130a, 130b) is located onto a headrest of the seat (130) and the point of anchorage (52b) of said second pretension device (50) of the apron strap (130c) is located at the bottom of the seat (130), the terminal stake eye (51b) of said first pretension device (50) being connected at a point (134) of crossing of the shoulder straps (130a, 130b) and the terminal stake eye (51b) of said second pretension device (50) being connected at an end point of the apron strap (130c), wherein said first pretension device (50) of the shoulder straps (130a, 130b) and said second pretension device (50) of the apron strap (130c) are subject to tightening in response to the pulling action being exerted thereupon resulting from the dynamic shock being exercised along said forward straps (20, 21) of the parachute (40) during deployment thereof in an emergency situation, said first and second pretension devices (50) being released following landing of the aircraft (30). 10. A ballistic parachute (40) for an aircraft (30) according to claim 9, wherein each one of said seats (130) comprises a bottom (136) with a fixed portion (136) and a movable forward section (133), a rotating rod (135) bearing a cam mechanism being provided for rotation of the forward section (133), hinges (133b) being provided for connecting a rear side (133a) of said forward section (133) to a frontal side (136a) of the fixed section (136), wherein said safety system adapted to provide an anti-submerging function to each one of the plurality of seats (130) comprises a pretension device (50) of a Bowden cable, said pretension device (50) of Bowden cable being provided with a terminal stake eye (51a) 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), the points of anchorage (52a, 52b) of the pretension device (50) of said safety system adapted to provide an anti-submerging function to each one of the plurality of seats (130) being located at the bottom of the seat (130), and terminal stake eye (51b) of the pretension device (50) being connected at an end point (137) of said rotating rod (135), whereby, in response to the pulling action being exerted thereupon resulting from the dynamic shock being exercised along said forward straps (20, 21) of the parachute (40) during deployment thereof in an emergency situation, said rotating rod (135) is rotated and said movable forward section (133) is elevated by cams (135a) provided onto said rotating rod (135) thereby providing the anti-submerging function of retaining the body of a passenger seated onto the seat (130) averting sliding beneath the apron strap (130c) of the safety belt (110) and submerging forwardly from the seat (130), said pretension device (50) being released following landing of the aircraft (30).
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이 특허에 인용된 특허 (5)
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