Aircraft nonlinear dynamic instability warning system
OwnerShaojie Tanginventor
Life of this patent
Estimating the term…
Abstract
A system and method for predicting aircraft nonlinear instability includes the steps of: (1) a pre-built aircraft state parameters for all possible flight conditions, (2) real time measuring flight parameters to determine aircraft state, (3) calculating the inertial coupling frequencies and periods as well as the nonlinear instability threshold based on the nonlinear instability theory recently developed by the inventor, (4) providing a first warning signal if the threshold is approached, (5) providing a second warning signal if the threshold has been exceeded.
Claims15
A method of predicting aircraft nonlinear pitch dynamic instability including:
- a. pre-obtained aircraft state parameter and coefficient data for all possible flight states;
- b. measuring current flight parameters to determine the aircraft state;
- c. calculating the inertial coupling frequencies and periods as
- ω1st=ω10+ω30 and T1st=2π/ω1st,
- ω2nd=|ω10−ω30| and T2nd=2π/ω2nd;
- d. displaying the 1st and 2nd inertial coupling frequencies and periods;
- e. calculating the pitch instability threshold as
- A
- T
- =
- max
-
- {
- 2
- ω
- 1
-
- st
-
- b
- 1
-
- b
- 3
- (
- I
- z
- -
- I
- y
- )
-
- (
- I
- y
- -
- I
- x
- )
- -
- β
- m
- ,
- β
- m
- }
- ;
- f. calculating the pitch response around the preset equilibrium flight state as
- AR|θ=γ0−αT|;
- g. providing a first warning signal under the following condition:
- λAT<AR<AT;
- h. providing a second warning signal under the following condition:
- AR≥AT.
A method of predicting aircraft nonlinear roll dynamic instability including:
- a. pre-obtained aircraft state parameter and coefficient data for all possible flight states;
- b. measuring current flight parameters to determine the aircraft state;
- c. Calculating the inertial coupling frequencies and periods as
- ω1st=ω20+ω30 and t1st=2π/ω1st,
- ω2nd=|ω20−ω30| and T2nd=2π/ω2nd,
- d. displaying the 1st and 2nd inertial coupling frequencies and periods;
- e. calculating the roll instability threshold as
- A
- T
- =
- max
-
- {
- 2
- ω
- 1
-
-
- st
-
- b
- 2
-
- b
- 3
- (
- I
- z
- -
- I
- z
- )
-
- (
- I
- x
- -
- I
- y
- )
- -
- β
- m
- ,
- β
- m
- }
- ;
- f. calculating the roll response around the preset equilibrium flight state as
- AR=|φ−φ0|;
- g. providing a first warning signal under the following condition:
- λAT<AR<AT;
- h. providing a second warning signal under the following condition:
- AR≥AT.
A method of predicting aircraft nonlinear yaw dynamic instability including:
- a. pre-obtained aircraft state parameter and coefficient data for all possible flight states;
- b. measuring current flight parameters to determine the aircraft state;
- c. calculating the inertial coupling frequencies as
- ω1st=ω10+ω20 and T1st=2π/ω1st,
- ω2nd=|ω10−ω20| and T2nd=2π/ω2nd;
- d. displaying the 1st and 2nd inertial coupling frequencies and periods;
- e. calculating the yaw instability threshold as
- A
- T
- =
- max
-
- {
- 2
- ω
- 1
-
-
- st
-
- b
- 1
-
- b
- 2
- (
- I
- y
- -
- I
- z
- )
-
- (
- I
- z
- -
- I
- x
- )
- -
- β
- m
- ,
- β
- m
- }
- ;
- f. calculating the yaw response around the preset equilibrium flight state as
- AR=ψ−ψ0|;
- g. providing a first warning signal under the following condition:
- λAT<AR<AT;
- h. providing a second warning signal under the following condition
- AR≥AT.
Dependencies are inferred from the claim text.