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Machine translation
1. (WO2011019424) GUIDED MISSILE
Latest bibliographic data on file with the International Bureau   

Pub. No.:    WO/2011/019424    International Application No.:    PCT/US2010/035178
Publication Date: 17.02.2011 International Filing Date: 18.05.2010
Chapter 2 Demand Filed:    18.05.2011    
IPC:
F42B 10/64 (2006.01)
Applicants: RAYTHEON COMPANY [US/US]; 870 Winter Street Waltham, Massachusetts 02451 (US) (For All Designated States Except US).
UNGER, Michael P. [US/US]; (US) (For US Only).
WITHERSPOON, Stephen D. [US/US]; (US) (For US Only).
SCHLEINING, James T. [US/US]; (US) (For US Only)
Inventors: UNGER, Michael P.; (US).
WITHERSPOON, Stephen D.; (US).
SCHLEINING, James T.; (US)
Agent: PLATT, Jonathan A.; Renner, Otto, Boisselle & Sklar, LLP Nineteenth Floor 1621 Euclid Avenue Cleveland, Ohio 44115 (US)
Priority Data:
61/179,391 19.05.2009 US
Title (EN) GUIDED MISSILE
(FR) MISSILE GUIDÉ
Abstract: front page image
(EN)A missile (10) comprising a projectile body (20), a payload (60) contained within the nose portion (30), wings (70) stowed within the mid portion (40), and fins (80) stored within the tail portion (50). The wings (70) can be deployed during intermediate stages of the flight path when lift is advantageous, and re-stowed during terminal stages when an almost vertical angle-of-attack is desired. The fins (80) function as stabilizing components during the early ballistic stage of the flight path and function as guiding components thereafter.
(FR)Missile (10) comprenant un corps de projectile (20), une charge utile (60) contenue dans la partie nez (30), des ailes (70) repliées dans la partie centrale (40), et des ailerons (80) repliés dans la partie queue (50). Les ailes (70) peuvent être déployées au cours de phases intermédiaires de la trajectoire de vol où une portance s'avère avantageuse, et repliées au cours des phases terminales où un angle d'attaque quasi vertical s'avère souhaitable. Les ailerons (80) jouent le rôle de composants stabilisateurs au cours de la phase balistique initiale de la trajectoire de vol, puis de composants de guidage.
Designated States: AE, AG, AL, AM, AO, AT, AU, AZ, BA, BB, BG, BH, BR, BW, BY, BZ, CA, CH, CL, CN, CO, CR, CU, CZ, DE, DK, DM, DO, DZ, EC, EE, EG, ES, FI, GB, GD, GE, GH, GM, GT, HN, HR, HU, ID, IL, IN, IS, JP, KE, KG, KM, KN, KP, KR, KZ, LA, LC, LK, LR, LS, LT, LU, LY, MA, MD, ME, MG, MK, MN, MW, MX, MY, MZ, NA, NG, NI, NO, NZ, OM, PE, PG, PH, PL, PT, RO, RS, RU, SC, SD, SE, SG, SK, SL, SM, ST, SV, SY, TH, TJ, TM, TN, TR, TT, TZ, UA, UG, US, UZ, VC, VN, ZA, ZM, ZW.
African Regional Intellectual Property Organization (BW, GH, GM, KE, LR, LS, MW, MZ, NA, SD, SL, SZ, TZ, UG, ZM, ZW)
Eurasian Patent Organization (AM, AZ, BY, KG, KZ, MD, RU, TJ, TM)
European Patent Office (AL, AT, BE, BG, CH, CY, CZ, DE, DK, EE, ES, FI, FR, GB, GR, HR, HU, IE, IS, IT, LT, LU, LV, MC, MK, MT, NL, NO, PL, PT, RO, SE, SI, SK, SM, TR)
African Intellectual Property Organization (BF, BJ, CF, CG, CI, CM, GA, GN, GQ, GW, ML, MR, NE, SN, TD, TG).
Publication Language: English (EN)
Filing Language: English (EN)