SYSTEMS AND METHODS OF REDUNDANCY FOR AIRCRAFT INERTIAL SIGNAL DATA
First Claim
1. An aircraft inertial system, comprising:
- at least two inertial reference units (IRU) configured to provide a first set of inertial signal data for operating an aircraft;
at least two attitude heading reference systems (AHRS) configured to provide a second set of the inertial signal data for operating the aircraft;
at least one primary flight display configured to receive the first and the second sets of the inertial signal data;
a standby flight display configured to receive at least the second set of the inertial signal data from at least one of the AHRS;
wherein when a single fault condition occurs in the inertial system, the primary flight display continues to operate with fail-operational redundancy from at least three independent sources of the inertial signal data comprising one or more combinations of the at least two IRU and the at least two AHRS; and
wherein the standby flight display continues to operate using a different source of the inertial signal data than the source of the inertial signal data for the primary flight display
1 Assignment
0 Petitions
Accused Products
Abstract
An aircraft inertial system comprises at least two inertial reference units (IRU) that provide a first set of inertial signal data for an aircraft and at least two attitude heading reference systems (AHRS) that provide a second set of the inertial signal data for the aircraft. At least one primary flight display receives the first and the second sets of the inertial signal data, and a standby flight display receives at least the second set of the inertial signal data from at least one of the AHRS. When a single fault condition occurs, the primary flight display continues to operate with fail-operational redundancy from at least three independent sources of the inertial signal data comprising one or more IRU and AHRS combinations. The standby flight display will operate using a different source of the inertial signal data than the source of the inertial signal data for the primary flight display.
-
Citations
20 Claims
-
1. An aircraft inertial system, comprising:
-
at least two inertial reference units (IRU) configured to provide a first set of inertial signal data for operating an aircraft; at least two attitude heading reference systems (AHRS) configured to provide a second set of the inertial signal data for operating the aircraft; at least one primary flight display configured to receive the first and the second sets of the inertial signal data; a standby flight display configured to receive at least the second set of the inertial signal data from at least one of the AHRS; wherein when a single fault condition occurs in the inertial system, the primary flight display continues to operate with fail-operational redundancy from at least three independent sources of the inertial signal data comprising one or more combinations of the at least two IRU and the at least two AHRS; and wherein the standby flight display continues to operate using a different source of the inertial signal data than the source of the inertial signal data for the primary flight display - View Dependent Claims (2, 3, 4, 5)
-
-
6. A method for operating an aircraft with redundant inertial signal data, the method comprising:
-
determining aircraft state information from a first set of inertial signal data provided by a first inertial reference unit (IRU) and a second IRU for at least a flight control system and one or more primary flight displays of the aircraft; determining the aircraft state information from a second set of the inertial signal data provided by a first attitude heading reference system (AHRS) and a second AHRS of the aircraft to augment the first set of the inertial signal data; comparing at least three sources of the inertial signal data comprising one or more combinations of the first and the second IRU and the first and the second AHRS to determine which of the at least three sources of the inertial signal data are dedicated to the flight control system and the primary flight displays; and when a fault condition is detected in the inertial signal data, supplying valid inertial signal data to at least the flight control system and the primary flight displays of the aircraft such that the aircraft operates with a prescribed level of dispatchability and fault isolation from the at least three dedicated sources of the inertial signal data. - View Dependent Claims (7, 8, 9, 10)
-
-
11. An aircraft inertial system, comprising:
-
at least two inertial reference units (IRU) configured to provide a first set of inertial signal data for operating an aircraft; at least two attitude heading reference systems (AHRS) configured to provide a second set of the inertial signal data for operating the aircraft; a primary flight display configured to receive the first and the second sets of the inertial signal data; a standby flight display configured to receive at least the second set of the inertial signal data from at least one of the AHRS; and a flight control system configured to receive the first and second sets of the inertial signal data from one or more combinations of the at least two IRU and the at least two AHRS; wherein when a single fault condition occurs in the inertial system, the flight control system continues to function from at least three independent sources of the inertial signal data comprising the one or more IRU and AHRS combinations. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
-
Specification