PATENT CLAIM ANALYSIS

Application Number: 16281962
Application Type: Utility
Filing Date: 2019-02
Publication Date: 2019-08
Patent Classification: ["315", "077000"]

Abstract:
A method for dynamic control of runway illumination on aircraft, suitable for controlling the illumination of a light equipment comprising a LED matrix and refraction optics during a flight phase. The method comprises the steps of a) determining predefined flight dynamic movement equations for the flight phase, b) obtaining real data from autonomous sensors independent from the aircraft sensors, c) using extended Kalman Filter and algorithm taking into account the data from the autonomous sensors to obtain the aircraft dynamics data. This step c) comprises the c1) predict phase and c2) update phase, and d) applying the obtained aircraft dynamics data to light control laws affecting the light equipment.

Claim (Index 2):
The method for dynamic control of runway illumination on aircraft, according to  claim 1 , applicable during the take-off flight phase, comprising the following steps:\n a) determining predefined flight dynamic movement equations for the take-off flight phase: T \ue89e \ue89e cos \ue89e \ue89e \u03b1 - D - W \ue89e \ue89e sin \ue8a0 ( \u03b3 - a ) = W g \ue89e dV dt T \ue89e \ue89e sin \ue89e \ue89e \u03b1 + L - W \ue89e \ue89e cos \ue8a0 ( \u03b3 - \u03b1 ) = W g \ue89e V \ue89e d \ue8a0 ( \u03b3 - \u03b1 ) dt \ue89e \n \ue89e L = 1 2 \ue89e \u03c1 \ue89e \ue89e SC L \ue89e V 2 = 1 2 \ue89e \u03c1 \ue89e \ue89e S \ue8a0 ( C L D + C L \u03b1 \ue89e \u03b1 ) \ue89e V 2 \ue89e \n \ue89e D = 1 2 \ue89e \u03c1 \ue89e \ue89e SC D \ue89e V 2 = 1 2 \ue89e \u03c1 \ue89e \ue89e S \ue8a0 ( C D 0 + kC L 2 ) \ue89e V 2 where the following parameters are considered:\n \u03c1 is an air density, \n S is a wing surface for the aircraft, \n g is gravitational acceleration, \n C L0  is a lift coefficient for 0 angle of attack for the aircraft, \n C L\u03b1  is a lift coefficient parameter dependent on angle of attack for the aircraft, \n C D0  is a constant drag coefficient for the aircraft, \n k is a polar coefficient for the aircraft, \n where the following forces are considered:\n D: drag, \n L: lift, \n T: thrust, \n W: weight, \n b) obtaining real data from a y-axis gyroscope, an x-axis accelerometer and a z-axis accelerometer as autonomous sensors independent from aircraft sensors:\n a pitch rate being obtained from the y-axis gyroscope, \n accelerations in x and z being obtained from the two corresponding accelerometers, \n c) using extended Kalman Filter and algorithm taking into account data from the autonomous sensors to obtain an aircraft pitch angle \u03b3 and an aircraft speed V, wherein phases considered in a process in a sequential phase for an iterative process are as follows:\n c1) predict phase,\n (1) predicted (a priori) state estimate from previous state:\n x t =f ( x t\u22121 ) \n \n (2) predicted (a priori) estimate error covariance:\n P t =F t\u22121 P t\u22121 F t\u22121 T +Q t\u22121  \n \n \n c2) update phase\n (3) measurement residual:\n y t =z t \u2212h ( x t ) \n \n (4) innovation covariance:\n S t =H t P t H t T R t  \n \n (5) optimal Kalman gain:\n K t =P t T t T S t \u22121  \n \n (6) updated (a posteriori) state estimate:\n x t+1 =x t +K t y t  \n \n (7) updated (a posteriori) estimate error covariance:\n P t\u22121 ( I\u2212K t H t ) P t  \n \n \n wherein components used for the Kalman filter are as follows:\n state of the system vector for instant x t , \n vector of sensor measurements: z t , \n state transition model: function f( ) for the process and F t  for a Jacobian matrix based on the process for instant t, \n observation model: function h( ) for the model and H t  for a Jacobian matrix based on the model for instant t, \n estimated error covariance: P t , \n covariance of process noise: Q t , \n covariance of observation noise: R t , \n wherein the following state variables are used for vector x t :\n aircraft ground speed: V, \n angle between wind and ground axis: \u03b2=\u03b3\u2212\u03b1 \n angle of attack: \u03b1 \n d) applying an obtained pitch angle \u03b3 and the aircraft speed V to determine an intensity, direction and light distribution of LEDs in the light equipment.

Metadata:
- Claim Count in Document: 5.0
- Percentile: 99.0
- Lexical Diversity: 1.86364
- Patent Class: 315.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: True
- Related Applications: ['10436936', '13563357', '10779365', '13956736', '14808646']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.6865590040044977
- 35 USC 102 Novelty (BERT): 0.4987132139087373
- Combined Prediction Score: 0.6677744249949216
- Mean Citation Score: 171.538208
- Max Citation Score: 204.6668
- Similarity Product: 131.365018514204

Labels:
- Claim Label 101: 1
- Claim Label 102: 1
- Claim Label 103: 1
- Claim Label 112: 1
- Combined Label: 1
- Label 101 Adjusted: 1

Dataset: test