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Machine translation
1. (WO1999039149) METHOD FOR NAVIGATING A ROBOT AND ARRANGEMENT AT SAID ROBOT
Latest bibliographic data on file with the International Bureau   

Pub. No.:    WO/1999/039149    International Application No.:    PCT/SE1999/000070
Publication Date: 05.08.1999 International Filing Date: 20.01.1999
Chapter 2 Demand Filed:    14.06.1999    
IPC:
F41G 7/34 (2006.01)
Applicants: SAAB DYNAMICS AB [SE/SE]; S-581 88 Linköping (SE) (For All Designated States Except US).
HAGELIN, Hans-Ove [SE/SE]; (SE) (For US Only)
Inventors: HAGELIN, Hans-Ove; (SE)
Agent: WILLQUIST, Bo; Willquist & Partners Patentbyrå AB S:t Larsgatan 23 S-582 24 Linköping (SE)
Priority Data:
9800221-5 28.01.1998 SE
Title (EN) METHOD FOR NAVIGATING A ROBOT AND ARRANGEMENT AT SAID ROBOT
(FR) PROCEDE ET SYSTEME DE GUIDAGE D'UN MISSILE
Abstract: front page image
(EN)The present invention relates to an arrangement and a method for guiding a missile (1) towards a target (2). The missile has information on its own position, velocity vector and future velocity profile and continuously receives information on the position and velocity vector of the target. The invention is characterised in that from the information on the missile and the target a point of interception (A) is predicted at which the missile is expected to strike the target. A flight time is then calculated which indicates the time that it will take for the missile to travel to the predicted point of interception (A). In addition a fictitious point of interception (B) is calculated which is situated at a higher altitude than the predicted point of interception and the distance of which to that point is related to the calculated flight time. Finally the missile velocity vector is directed towards the said fictitious point.
(FR)L'invention concerne un système et un procédé permettant de guider un missile (1) vers une cible (2). Le missile a des informations sur sa propre position, son propre vecteur de vélocité et le profil de sa vélocité future et reçoit en continu des informations sur la position et le vecteur de vélocité de la cible. L'invention est caractérisée en ce que le point d'interception (A) où le missile devrait frapper la cible, est calculé à partir des informations sur le missile et la cible. Ensuite, un temps de vol correspondant au temps qu'il faut au missile pour atteindre le point d'interception prévu (A), est calculé. En outre, un point d'interception fictif (B) est calculé. Le point d'interception fictif est plus haut que le point d'interception prévu et la distance qui le sépare de ce dernier est en relation avec le temps de vol calculé. Finalement, le vecteur de vélocité du missile est dirigé vers le point fictif en question.
Designated States: US.
European Patent Office (AT, BE, CH, CY, DE, DK, ES, FI, FR, GB, GR, IE, IT, LU, MC, NL, PT, SE).
Publication Language: English (EN)
Filing Language: Swedish (SV)