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1. (WO2007005033) SYSTEM & METHOD OF FILTERING LOW ORDER OSCILLATION FROM NON-RIGID SUSPENSION SYSTEMS
Latest bibliographic data on file with the International Bureau

Pub. No.: WO/2007/005033 International Application No.: PCT/US2005/026640
Publication Date: 11.01.2007 International Filing Date: 27.07.2005
Chapter 2 Demand Filed: 24.01.2006
IPC:
B64C 13/50 (2006.01)
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
C
AEROPLANES; HELICOPTERS
13
Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
24
Transmitting means
38
with power amplification
50
using electrical energy
Applicants:
ATAIR AEROSPACE, INC. [US/US]; 499 Van Brunt Street Suite 3b Brooklyn, NY 11231, US (AllExceptUS)
PRESTON, Daniel, J. [US/US]; US (UsOnly)
CALISE, Anthony, J. [US/US]; US (UsOnly)
Inventors:
PRESTON, Daniel, J.; US
CALISE, Anthony, J.; US
Agent:
BOURQUE, Daniel, J. ; BOURQUE AND ASSOCIATES, P.A. 835 Hanover Street Suite 301 Manchester, NH 03104, US
Priority Data:
60/591,33427.07.2004US
Title (EN) SYSTEM & METHOD OF FILTERING LOW ORDER OSCILLATION FROM NON-RIGID SUSPENSION SYSTEMS
(FR) SYSTEME ET PROCEDE PERMETTANT DE FILTRER DE FAIBLES OSCILLATIONS ISSUES DE SYSTEMES DE SUSPENSION NON RIGIDES
Abstract:
(EN) A system and method of guiding an aircraft is disclosed. The aircraft includes at least one non-rigidly attached sensor for providing a signal indicative of the angular rate of turn of the aircraft. The signal includes an oscillation component and an angular rate of turn component. A filter receives the signal from the sensor and attempts to remove the oscillation component found in the signal. A guidance system provides a commanded turn rate signal. A stability augmentation system receives the filtered angular rate of turn signal and the commanded turn rate signal and processes those signals to provide an actuator command signal. The actuator command signal can best be used to control an air vehicle activation device. The method involves receiving at least one signal indicative of an angular rate of turn of the aircraft from the sensor not rigidly suspended from an aircraft , wherein the signal includes an oscillation component and an angular rate of turn component. The signal is filtered to attenuate the oscillation component while a command a turn rate signal is received. Finally, the filtered signal and the commanded turn rate signal are processed to determine an actuator command signal.
(FR) La présente invention se rapporte à un système et à un procédé permettant de guider un avion. Ledit avion possède au moins un capteur, fixé de manière non rigide et destiné à fournir un signal indiquant la vitesse angulaire de virage de l'avion. Ledit signal comprend une composante d'oscillation et une composante de vitesse angulaire de virage. Un filtre reçoit le signal issu du capteur, et tente d'éliminer la composante d'oscillation trouvée dans le signal. Un système de guidage fournit un signal de vitesse de virage commandé. Un système d'augmentation de la stabilité reçoit la vitesse angulaire filtrée du signal de virage et le signal de taux de virage commandé, et traite lesdits signaux afin de fournir un signal de commande d'actionneur. Le signal de commande d'actionneur est particulièrement utile pour commander un dispositif d'activation de véhicules aériens. Le procédé selon l'invention consiste : à recevoir, du capteur suspendu de manière non rigide depuis un avion, au moins un signal indiquant la vitesse angulaire de virage de l'avion, ledit signal contenant une composante d'oscillation et une composante de vitesse angulaire de virage ; à filtrer le signal, afin d'atténuer la composante d'oscillation, pendant la réception d'un signal de vitesse de virage commandé ; et enfin à traiter le signal filtré et le signal de vitesse de virage commandé, afin de déterminer un signal de commande d'actionneur.
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Designated States: AE, AG, AL, AM, AT, AU, AZ, BA, BB, BG, BR, BW, BY, BZ, CA, CH, CN, CO, CR, CU, CZ, DE, DK, DM, DZ, EC, EE, EG, ES, FI, GB, GD, GE, GH, GM, HR, HU, ID, IL, IN, IS, JP, KE, KG, KM, KP, KR, KZ, LC, LK, LR, LS, LT, LU, LV, MA, MD, MG, MK, MN, MW, MX, MZ, NA, NG, NI, NO, NZ, OM, PG, PH, PL, PT, RO, RU, SC, SD, SE, SG, SK, SL, SM, SY, TJ, TM, TN, TR, TT, TZ, UA, UG, US, UZ, VC, VN, YU, ZA, ZM, ZW
African Regional Intellectual Property Organization (ARIPO) (BW, GH, GM, KE, 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 (AT, BE, BG, CH, CY, CZ, DE, DK, EE, ES, FI, FR, GB, GR, HU, IE, IS, IT, LT, LU, LV, MC, NL, PL, PT, RO, SE, SI, SK, 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)
Also published as:
CA2583384