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1. WO2022251598 - ROLL-BIASED SKID-TO-TURN TERMINAL GUIDANCE WITH RUDDER INTEGRATOR FEEDBACK

Publication Number WO/2022/251598
Publication Date 01.12.2022
International Application No. PCT/US2022/031294
International Filing Date 27.05.2022
IPC
G05D 1/08 2006.1
GPHYSICS
05CONTROLLING; REGULATING
DSYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
1Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
08Control of attitude, i.e. control of roll, pitch, or yaw
B64C 13/18 2006.1
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
13Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
02Initiating means
16actuated automatically, e.g. responsive to gust detectors
18using automatic pilot
B64C 39/02 2006.1
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
39Aircraft not otherwise provided for
02characterised by special use
G05D 1/00 2006.1
GPHYSICS
05CONTROLLING; REGULATING
DSYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
1Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
G05D 1/10 2006.1
GPHYSICS
05CONTROLLING; REGULATING
DSYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
1Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
10Simultaneous control of position or course in three dimensions
G08G 5/04 2006.1
GPHYSICS
08SIGNALLING
GTRAFFIC CONTROL SYSTEMS
5Traffic control systems for aircraft
04Anti-collision systems
CPC
B64C 13/18
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
13Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
02Initiating means
16actuated automatically, e.g. responsive to gust detectors
18using automatic pilot
B64C 39/02
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
39Aircraft not otherwise provided for
02characterised by special use
F41G 7/00
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
41WEAPONS
GWEAPON SIGHTS; AIMING
7Direction control systems for self-propelled missiles
G05D 1/12
GPHYSICS
05CONTROLLING; REGULATING
DSYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
1Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
12Target-seeking control
G08G 5/04
GPHYSICS
08SIGNALLING
GTRAFFIC CONTROL SYSTEMS
5Traffic control systems for aircraft ; , e.g. air-traffic control [ATC]
04Anti-collision systems
Applicants
  • AEROVIRONMENT, INC. [US]/[US]
Inventors
  • MITCHNER, Drew, David
  • DAVIS, Scott, David
Agents
  • ZARRABIAN, Michael
  • YEDIDSION, Pejman
  • WEISS, Christopher
Priority Data
63/194,76228.05.2021US
63/314,59728.02.2022US
Publication Language English (en)
Filing Language English (EN)
Designated States
Title
(EN) ROLL-BIASED SKID-TO-TURN TERMINAL GUIDANCE WITH RUDDER INTEGRATOR FEEDBACK
(FR) GUIDAGE TERMINAL DE GLISSEMENT EN VIRAGE SOLLICITÉ EN ROULIS AVEC RÉACTION D'INTÉGRATEUR DE GOUVERNE DE DIRECTION
Abstract
(EN) Systems, devices, and methods for an aircraft autopilot guidance control system (100, 300) for guiding an aircraft having a body, the system comprising: a processor (101) configured to determine if a yaw angle difference and a pitch angle difference meet corresponding angle thresholds; a skid-to-turn module (105) configured to generate a skid-to-turn signal if the corresponding angle thresholds are met; a bank-to-turn module (102) configured to generate a bank-to-turn signal having a lower bandwidth than the generated skid-to-turn signal; a rudder integrator module (104) configured to add a rudder integrator feedback signal to the bank-to-turn signal, where the rudder integrator feedback signal is proportional to a rudder integrator; and a filter module (103) configured to filter the generated bank-to-turn signal, wherein the filter module (103) comprises a low-pass filter configured by a set of gains to pass the bank-to-turn signal if a side force on the body meets a side force threshold (111).
(FR) L'invention concerne des systèmes, des dispositifs et des procédés pour un système de commande de guidage d'aéronef par pilote automatique (100, 300) pour guider un aéronef présentant un corps, le système comprenant : un processeur (101) conçu pour déterminer si une différence d'angle de lacet et une différence d'angle de tangage satisfont des seuils d'angle correspondants ; un module de glissement en virage (105) conçu pour générer un signal de glissement en virage si les seuils d'angle correspondants sont satisfaits ; un module de virage incliné (102) conçu pour générer un signal de virage incliné ayant une largeur de bande inférieure à celle du signal de glissement en virage généré ; un module d'intégrateur de gouverne de direction (104) conçu pour ajouter un signal de réaction d'intégrateur de gouverne de direction au signal de virage incliné, le signal de réaction d'intégrateur de gouverne de direction étant proportionnel à un intégrateur de gouverne de direction ; et un module de filtre (103) conçu pour filtrer le signal de virage incliné généré, le module de filtre (103) comprenant un filtre passe-bas configuré par un ensemble de gains pour faire passer le signal de virage incliné si une force latérale sur le corps satisfait un seuil de force latérale (111).
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