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公开(公告)号：US10935984B2
公开(公告)日：2021-03-02
申请号：US16037234
申请日：2018-07-17
发明人： David Michael Lax , Reza Ghaemi , Pierino Gianni Bonanni , Nicholas Race Visser , Owen Michael O'Keefe
摘要： A method and system of determining or predicting a climb profile for an aircraft, includes receiving, by a controller module, an initial climb profile defining a portion of a flight plan for the aircraft between takeoff and a cruise profile, and an altitude climb constraint defining at least one altitude limitation of the aircraft, determining, by the controller module, that the initial climb profile does not satisfy the altitude constraint, and determining an updated climb profile based on a set of subsequent climb models.
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公开(公告)号：US20190304314A1
公开(公告)日：2019-10-03
申请号：US15943258
申请日：2018-04-02
摘要： A flight management system and method of updating flight calculations includes flying an aircraft along a current flight path, collecting real-time weather data from a network of aircraft operating in a nearby region, and predicting a trajectory for completion of the flight. The prediction can be based on the collected real-time weather data.
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公开(公告)号：US20180067480A1
公开(公告)日：2018-03-08
申请号：US15651276
申请日：2017-07-17
摘要： Systems and methods for determine a cost-improved set of control commands for an aircraft based at least in part on deterioration costs are provided. One example computing device is configured to iteratively: input a candidate set of control commands for the aircraft into the deterioration cost model; receive, as an output of the deterioration cost model, an estimated deterioration cost associated with the candidate set of control commands; input the estimated deterioration cost into a cost function to obtain a total estimated cost associated with the candidate set of control commands; and determine an improved set of control commands based at least in part on the total estimated cost and the cost function.
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4.发明申请公开(公告)号：US20170121028A1
公开(公告)日：2017-05-04
申请号：US14927788
申请日：2015-10-30
CPC分类号： B64D31/06 , B64D2013/0618 , F01D21/003 , F02C9/00 , F02C9/18 , F02C9/28 , F02C9/52 , F05D2270/096 , F05D2270/311 , F05D2270/313 , F05D2270/805 , G01S13/953 , G01S17/95 , Y02A90/18 , Y02A90/19 , Y02T50/56 , Y02T50/671
摘要： Systems and methods for enhancing engine performance based on atmospheric ice particles are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a reflectivity measurement for each of the one or more points obtained using a device located on the aircraft. The method can further include determining an estimate of ice water content for each of the one or more points based at least in part on the reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable bleed valve) based at least in part on the estimate of ice water content for at least one of the plurality of points.
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公开(公告)号：US11302204B2
公开(公告)日：2022-04-12
申请号：US15943258
申请日：2018-04-02
摘要： A flight management system and method of updating flight calculations includes flying an aircraft along a current flight path, collecting real-time weather data from a network of aircraft operating in a nearby region, and predicting a trajectory for completion of the flight. The prediction can be based on the collected real-time weather data.
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公开(公告)号：US20210327284A1
公开(公告)日：2021-10-21
申请号：US17306805
申请日：2021-05-03
发明人： David Michael Lax , Mark Darnell
摘要： Methods, apparatus, and articles of manufacture to provide improved engine load models are disclosed. An example apparatus includes a model generator to generate an engine load model for an engine using flight information, weather information, and manifest information to predict a load on the engine from an engine subsystem utilization modeled for a flight. The example model generator is to incorporate the engine load model into an engine model, the engine model representing engine behavior for the flight. The example model generator is to determine a first measure of thrust from the engine and a second measure of fuel flow to the engine using the engine model with the engine load model, the engine load model to modify engine behavior by the predicted load on the engine from the engine subsystem utilization. The example model generator is to generate flight parameters for a flight path using the first measure of thrust and the second measure of fuel flow for the predicted load on the engine based on the engine load model.
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公开(公告)号：US20200026307A1
公开(公告)日：2020-01-23
申请号：US16037234
申请日：2018-07-17
发明人： David Michael Lax , Reza Ghaemi , Pierino Gianni Bonanni , Nicholas Race Visser , Owen Michael O'Keefe
摘要： A method and system of determining or predicting a climb profile for an aircraft, includes receiving, by a controller module, an initial climb profile defining a portion of a flight plan for the aircraft between takeoff and a cruise profile, and an altitude climb constraint defining at least one altitude limitation of the aircraft, determining, by the controller module, that the initial climb profile does not satisfy the altitude constraint, and determining an updated climb profile based on a set of subsequent climb models.
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公开(公告)号：US20170361941A1
公开(公告)日：2017-12-21
申请号：US15184196
申请日：2016-06-16
发明人： Steven Louis Kiebles , David Michael Lax , Otto Y. Darias , Mark Lawrence Darnell , Sean Sanghyun Hwang , Christopher Daniel Holbert , Harry Kirk Mathews, JR. , Sridhar Adibhatla , Jeffrey Russell Bult , Thomas Charles Swager
CPC分类号： B64D31/06 , B64C15/02 , B64D45/00 , G05D1/0808 , G05D1/0816
摘要： Systems and methods for stabilizing an aircraft in response to a yaw movement are provided. In one embodiment, a method includes detecting a yaw movement of the aircraft. The yaw movement can cause a front portion of the aircraft to move towards a first side of the aircraft. The method can further include, in response to the yaw movement, initiating a trim process resulting in a thrust differential. The trim process can include increasing thrust in one or more engines on the first side of the aircraft and decreasing thrust in one or more engines on a second side of the aircraft. The method can include controlling the trim process based at least in part on a detected yaw movement of the aircraft.
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9.发明申请公开(公告)号：US20170121027A1
公开(公告)日：2017-05-04
申请号：US14927709
申请日：2015-10-30
CPC分类号： B64D31/06 , F02C9/00 , F02C9/20 , F02C9/28 , F02C9/54 , F05D2270/096 , F05D2270/311 , F05D2270/805 , G01S13/02 , G01S13/953 , Y02A90/18 , Y02T50/671
摘要： Systems and methods for enhancing engine performance based on atmospheric rain conditions are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a radar reflectivity measurement for each of the one or more points obtained using a radar device located on the aircraft. The method can further include determining an estimate of liquid water content for each of the one or more points based at least in part on the radar reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable stator vane) based at least in part on the estimate of liquid water content for at least one of the plurality of points.
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公开(公告)号：US11651695B2
公开(公告)日：2023-05-16
申请号：US17306805
申请日：2021-05-03
发明人： David Michael Lax , Mark Darnell
CPC分类号： G08G5/003 , B64D27/02 , B64D31/00 , G01C21/20 , G06Q40/12 , G08G5/0021 , G08G5/0034 , G08G5/0091
摘要： Methods, apparatus, and articles of manufacture to provide improved engine load models are disclosed. An example apparatus includes a model generator to generate an engine load model for an engine using flight information, weather information, and manifest information to predict a load on the engine from an engine subsystem utilization modeled for a flight. The example model generator is to incorporate the engine load model into an engine model, the engine model representing engine behavior for the flight. The example model generator is to determine a first measure of thrust from the engine and a second measure of fuel flow to the engine using the engine model with the engine load model, the engine load model to modify engine behavior by the predicted load on the engine from the engine subsystem utilization. The example model generator is to generate flight parameters for a flight path using the first measure of thrust and the second measure of fuel flow for the predicted load on the engine based on the engine load model.
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