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Machine translation
1. (WO1980000244) PROGRAMMED AIRCRAFT ARRESTING SYSTEM
Latest bibliographic data on file with the International Bureau   

Pub. No.:    WO/1980/000244    International Application No.:    PCT/US1979/000459
Publication Date: 21.02.1980 International Filing Date: 28.06.1979
IPC:
B64F 1/02 (2006.01)
Applicants:
Inventors:
Priority Data:
926451 20.07.1978 US
Title (EN) PROGRAMMED AIRCRAFT ARRESTING SYSTEM
(FR) SYSTEME PROGRAMME D"ARRET D"AVION
Abstract: front page image
(EN)An arresting system which is adaptable to arrest a wide range of aircraft weights and speeds. A variable K factor energy absorber (40) for an aircraft arresting system has a movable control element (32) which is moved into different positions to adjust the K factor. The movement of the control element (32) is programmed during payout of the arresting system in accordance with the speed of the arrested aircraft. The speed is sensed by a pump (17) driven by the arresting gear (40) tape reel. The program is provided by a cam (12, 12A). The control element (32) is moved by a hydraulic drive (15, 16) actuated by an electrical shifting switch (107), which is triggered when the detected speed of the arrested aircraft exceeds the predetermined speed established by a cam (12) during initial and final phases of payout. The control element (32) is thereby moved from an initial low K (A) to an intermediate K (B) position during the initial phase of payout if the predetermined speed established by the cam (12) is exceeded. During the final phase of payout, the switch (10) shifts the control (32) to the high K position (C), if the predetermined speed is exceeded. The cam (12A, 28) also causes the control element (32) to be driven to a high K position (C) at the end of payout if it is not already there. Rewind (35) is accomplished by actuating the drive system (15, 16) to set the control element (32) in the low K position (A) to minimize the required rewind force.
(FR)Un systeme d"arret permet d"arreter des avions dans une large gamme de masses et de vitesses. Un dispositif d"absorption d"energie a facteur variable (40) pour un systeme d"arret d"avion possede un organe de commande mobile (32) qui peut prendre des positions differentes pour regler le facteur K. Le mouvement de l"organe de commande (32) est programme pendant le deroulement du systeme d"arret en fonction de la vitesse de l"avion arrete. La vitesse est detectee par une pompe (17) entrainee par une bobine a bande du dispositif d"arret (40). Le programme est obtenu par une came (12, 12A). L"organe de commande (32) est deplace par un entrainement hydraulique (15, 16) actionne par un commutateur electrique (107) qui est declenche lorsque la vitesse detectee de l"avion arrete depasse la vitesse predeterminee etablie par une came (12) pendant les phases initiale et finale du deroulement. L"organe de commande (32) est ainsi deplace d"une position basse initiale K (A) a une position intermediaire K (B) pendant la phase initiale du deroulement si la vitesse predeterminee etablie par la came (12) est depassee. Pendant la phase finale du deroulement le commutateur (10) deplace la commande (32) en position haute K (C), si la vitesse predeterminee est depassee. La came (12A, 28) provoque egalement l"entrainement de l"organe de commande (32) en une position haute K (C) a la fin du deroulement si l"organe de commande (32) ne s"y trouve pas deja. Le rembobinage (35) est effectue par actionnement du systeme d"entrainement (15, 16) pour placer l"organe de commande (32) en position basse K (A) de maniere a reduire au minimum la force de rembobinage requise.
Designated States:
Publication Language: English (EN)
Filing Language: English (EN)