[특허]Method and apparatus for real time estimation of aircraft center of gravity

The Boeing Company

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Method and apparatus for real time estimation of aircraft center of gravity

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G01M-001/12
미국특허분류(USC)	364/463; 073/065
출원번호	US-0470577 (1990-01-26)
발명자 / 주소	Orgun, Munir Flannigan, Sean J.
출원인 / 주소	The Boeing Company
대리인 / 주소	Christensen, O'Connor Johnson & Kindness
인용정보	피인용 횟수 : 10 인용 특허 : 5

초록
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Disclosed is a method of and an arrangement for real time estimation of the location of the center of gravity of an aircraft. The center of gravity estimate is utilized in an aircraft flight control system for effecting flight control laws in which the center of gravity is a parameter that at least in part establishes open loop compensation or feedback gain. The disclosed method and arrangement are specifically adapted for establishing stabilizer mistrim during a landing procedure in which an aircraft flight control system is automatically controlling the aircraft. The method generally comprises the steps of generating a signal that represents the product of the aircraft stabilizer position and a multiplicative factor, A 1 and adding to that product an additive factor, A 2 . The multiplicative factor, A 1, and the additive factor, A 2, both are determined on the basis of the angle of attack of the aircraft and the aircraft flap setting.

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1. A method of estimating the location of aircraft center of gravity in an aircraft flight control system of the type that employs aircraft center of gravity location for executing one or more control laws that establish the flight path of said aircraft, said method comprising: obtaining from said aircraft flight control system signals representative of the aircraft stabilizer position, the aircraft flap setting and the aircraft angle of attack; multiplying said signal representative of aircraft stabilizer position by a first multiplicative factor, which is based on said signal representative of said aircraft angle of attack and said signal representative of said aircraft flap setting; adding to the product of said signal representative of said aircraft stabilizer position and said first multiplicative factor a first additive factor which is based on said signal representative of said aircraft angle of attack and said signal representative of said aircraft flap setting; and supplying as said estimate of said location of said aircraft center of gravity a flight control signal representative of the value obtained from said steps of multiplying said signal representative of said aircraft stabilizer position by said first multiplicative factor and adding said first additive factor, said flight control signal being supplied to said aircraft flight control system for controlling a flight control surface. 2. The method of claim 1, wherein said one or more control laws executed by said flight control system includes a control law for establishing stabilizer mistrim during automatic landing procedures and wherein said estimate of said location of said center of gravity is multiplied by a multiplicative factor M 1 and the product of said multiplicative factor M 1 and said center of gravity estimate is added to an additive factor M 1 to provide an elevator control signal that results in said stabilizer mistrim. 3. The method of claim 1 wherein said first multiplicative factor is determined by the steps of multiplying said signal representative of said aircraft angle of attack by a second multiplicative factor and adding to the product of said signal representative of said aircraft angle of attack and said second multiplicative factor a second additive factor; and wherein said first additive factor is determined by the steps of multiplying said signal representative of said aircraft angle of attack by a third multiplicative factor and adding to the product of said signal representative of said aircraft angle of attack and said third multiplicative factor a third additive factor. 4. The method of claim 3 wherein said signal representative of said aircraft flap setting is indicative of whether said aircraft flap setting is a first or second predetermined flap setting; and wherein said method further comprises the steps of: determining from said signal representative of said aircraft flap setting whether said aircraft flap setting is said first or second predetermined flap setting; establishing a first set of values for said second and third multiplicative factors and said second and third additive factors when said flap setting is said first predetermined flap setting; and establishing a second set of values for said second and third multiplicative factors and said second and third additive factors when said flap setting is said second predetermined flap setting. 5. The method of claim 4 wherein: said values supplied as said second multiplicative factor and said second additive factor when said flap setting is said first predetermined flap setting are based on the slope values of at least two linear relationships that substantially define the relationship between aircraft center of gravity location and aircraft stabilizer setting as a function of said first flap setting and predetermined values of aircraft angle of attack; said values supplied as said second multiplicative factor and said second additive factor when said flap setting is said second predetermined flap setting are based on the slope values of at least two linear relationships that substantially define the relationship between aircraft center of gravity location and aircraft stabilizer position as a function of said second flap setting and predetermined values of aircraft angle of attack; said values supplied as said third multiplicative factor and said third additive factor when said flap setting is said first predetermined flap setting are based on the intercept values of said at least two linear relationships that substantially define the relationship between said aircraft center of gravity location and said aircraft stabilizer position as a function of said first flap setting and said predetermined values of said aircraft angle of attack; and said values supplied as said third multiplicative factor and said third additive factor when said flap setting is said second predetermined flap setting are based on the intercept values of said at least two linear relationships that substantially define the relationship between said aircraft center of gravity location and said aircraft stabilizer position as a function of said second flap setting and said predetermined values of said aircraft angle of attack. 6. The method of claim 5 wherein said one or more control laws executed by said flight control system includes a control law for establishing stabilizer mistrim during automatic landing procedures and wherein said estimate of said location of said center of gravity is multiplied by a multiplicative factor M 1 and the product of said multiplicative factor M 1 and said center of gravity estimate is added to an additive factor M 2 to provide an elevator control signal that results in said stabilizer mistrim. 7. An improved aircraft flight control system of the type that controls the flight of an aircraft by processing signals representative of aircraft attitude and signals representative of the condition of aircraft control surfaces, said signals including signals representative of the location of said aircraft center of gravity, the angle of attack of said aircraft and the aircraft flap setting, wherein said improvement comprises means for generating a signal representative of said location of aircraft center of gravity, said means including: first multiplier means for multiplying said signal representative of said aircraft stabilizer position by a first multiplicative factor A 1 ; first adder means operatively coupled to said multiplier means for receiving a signal representative of the product of said signal representative of said stabilizer position and said multiplicative factor A 1, said adder means adding to said signal representative of said product an additive factor A 2 ; and means operatively coupled to said adder means for utilizing the signal supplied by said adder means as an estimate of the aircraft center of gravity during the execution of at least one control law that controls said flight of said aircraft. 8. The improvement of claim 7 wherein said signal representative of said aircraft flap setting is indicative of whether said aircraft flap setting is a first predetermined setting or a second predetermined setting; and wherein said means for estimating the location of the aircraft center of gravity further includes: signal processing means responsive to said signal representative of said aircraft flap setting and said signal representative of said aircraft angle of attack, said signal processing means including means for supplying to said multiplier means a first value of said multiplicative factor A 1 when said flap setting is said first predetermined setting and for supplying a second value of said multiplicative value A 1 when said flap setting is said second predetermined setting, said signal processing means further including means for supplying to said adder means a first value of said additive factor A 2 when said flap setting is at said first predetermined setting and a second value of said additive factor A 2 when said flap setting is at said second predetermined setting. 9. The improvement of claim 8 wherein said first and second values of said first multiplicative factor A 1 respectively correspond to the expressions A 1 =B 1 AOA+B 2 and A 1 +B 3 AOA+B 4 and said first and second values of said additive factor A 2 respectively correspond to A 2 =C 1 AOA+C 2 and A 2 =C 3 AOA+C 4, where AOA represents the angle of attack of said aircraft, B 1, B 3, C 1 and C 3 respectively represent second, third, fourth and fifth multiplicative factors and B 2, B 4, C 2 and C 4 respectively represent second, third, fourth and fifth additive factors; and wherein said signal processing means includes: detection means responsive to said signal representative of said aircraft flap setting for supplying a signal indicative of whether said aircraft flap setting is said first predetermined setting or said second predetermined setting; second multiplier means responsive to said signal representative of said aircraft angle of attack and an applied multiplicative factor, said second multiplier means supplying a signal representative of the product of said applied multiplicative factor and sais signal representative of said aircraft angle of attack; first signal selection means responsive to said signal supplied by said detection means for supplying said second multiplicative factor B 1 to said second multiplier means when said aircraft flap setting is said first predetermined setting and for supplying said third multiplicative factor B 3 to said second multiplier means when said aircraft flap setting is said second predetermined setting; second adder means responsive to said signal supplied by said second multiplier means and an applied additive factor, said second adder means supplying a signal representative of the sum of said applied additive factor and said signal supplied by said second multiplier means; second signal selection means responsive to said signal supplied by said detection means for supplying said second additive factor B 2 to said second adder means when said aircraft flap setting is said first predetermined setting and for supplying said third additive factor B 4 to said second adder means when said aircraft flap setting is said second predetermined setting; third multiplier means responsive to said signal representative of said aircraft angle of attack and an applied multiplicative factor, said third multiplier means for supplying a signal representative of the product of said applied multiplicative factor and said signal representative of said aircraft angle of attack; third signal selection means responsive to said signals supplied by said detection means for supplying said fourth multiplicative factor C 1 to said third multiplier means when said aircraft flap setting is said first predetermined setting and for supplying said fifth multiplicative factor C 3 to said third multiplier means when said aircraft flap setting is said second predetermined setting; third adder means responsive to said signal supplied by said third multiplier means and an applied additive factor, said third adder means for supplying a signal representative of the sum of said applied additive factor and said signal supplied by said third multiplier means; fourth signal selection means responsive to said signal supplied by said signal detection means for supplying said fourth additive factor C 2 to said third adder means when said aircraft flap setting is said first predetermined setting and for supplying said fifth additive factor C 4 to said third multiplier means when said aircraft flap setting is said second predetermined setting; means for supplying said signal supplied by said second adder means to said first multiplier means as said first multiplicative factor A 1 ; and means for supplying said signal supplied by said third adder means to said first adder means as said first additive factor A 2 .

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Method and apparatus for real time estimation of aircraft center of gravity

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이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 10

IPC 상위 출원인

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Method and apparatus for real time estimation of aircraft center of gravity

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이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 10

IPC 상위 출원인

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원문조회

IPC 상세정보(version : 201201)

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