Aircraft secondary electric load controlling system
First Claim
Patent Images
1. A secondary electrical load power management system for an aircraft comprising:
- a plurality of secondary electrical loads;
at least one aircraft flight condition sensor; and
a controller coupled to said plurality of secondary electrical loads and to said at least one aircraft flight condition sensor and determining engine secondary power extraction and current operating conditions of said air-craft, determining a engine secondary power extraction limit in response to said current operating conditions, and operating said plurality of secondary electrical loads in response to said engine secondary power extraction limit and said engine secondary power extraction.
1 Assignment
0 Petitions
Accused Products
Abstract
A method of controlling electrical load power consumption during operation of an aircraft (12) includes determining current operating conditions of the aircraft (12). An engine secondary power extraction limit is determined in response to the current operating conditions. Engine secondary power extraction is determined. Multiple secondary loads (18) are operated in response to the engine secondary power extraction limit and the engine secondary power extraction.
17 Citations
20 Claims
-
1. A secondary electrical load power management system for an aircraft comprising:
-
a plurality of secondary electrical loads;
at least one aircraft flight condition sensor; and
a controller coupled to said plurality of secondary electrical loads and to said at least one aircraft flight condition sensor and determining engine secondary power extraction and current operating conditions of said air-craft, determining a engine secondary power extraction limit in response to said current operating conditions, and operating said plurality of secondary electrical loads in response to said engine secondary power extraction limit and said engine secondary power extraction. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
-
- 9. A system as in 1 wherein said controller limits operation of said plurality of secondary electrical loads when said engine secondary power extraction is greater than said engine secondary power extraction limit.
-
11. A method of controlling electrical load power consumption during operation of an aircraft comprising:
-
determining current operating conditions of the aircraft;
determining an engine secondary power extraction limit in response to said current operating conditions;
determining engine secondary power extraction; and
operating a plurality of secondary loads in response to said engine secondary power extraction limit and said engine secondary power extraction. - View Dependent Claims (13)
-
-
20. A method of controlling electrical load power consumption during operation of an aircraft comprising:
-
determining current operating conditions;
determining an engine secondary power extraction limit in response to said current operating conditions;
determining engine secondary power extraction;
operating a plurality of secondary loads in response to said engine secondary power extraction limit and said engine secondary power extraction;
operating said plurality of secondary loads in priority when said engine secondary power extraction is less than said engine secondary power extraction limit; and
limiting operation of said plurality of secondary loads when said engine secondary power extraction is greater than said engine secondary power extraction limit.
-
Specification