公开(公告)号：US10346585B2

公开(公告)日：2019-07-09

申请号：US15049555

申请日：2016-02-22

Applicant: Hamilton Sundstrand Corporation

Inventor： Thomas M. Zywiak ,  Tony Ho ,  Nathan Haggerty

IPC: G06F17/50 ,  G05B23/02 ,  B64F5/60

Abstract: A method and system for predicting heat exchanger blockage in an aircraft is provided. The method includes generating a reduced order model (ROM) that predicts a ram air fan (RAF) surge margin that correlates to a heat exchanger blockage parameter, calculating, using the ROM, a predicted RAF surge margin value using a sensor signal received from a sensor connected to a ram air fan (RAF), calculating the heat exchanger blockage parameter using at least the predicted RAF surge margin value, and reporting, to a user, the heat exchanger blockage parameter that indicates when a heat exchanger blockage condition is present.

公开(公告)号：US20170242956A1

公开(公告)日：2017-08-24

申请号：US15049555

申请日：2016-02-22

Applicant: Hamilton Sundstrand Corporation

Inventor： Thomas M. Zywiak ,  Tony Ho ,  Nathan Haggerty

IPC: G06F17/50

CPC classification number: G06F17/5095 ,  B64F5/60 ,  G05B23/0254 ,  G05B23/0283

Abstract: A method and system for predicting heat exchanger blockage in an aircraft is provided. The method includes generating a reduced order model (ROM) that predicts a ram air fan (RAF) surge margin that correlates to a heat exchanger blockage parameter, calculating, using the ROM, a predicted RAF surge margin value using a sensor signal received from a sensor connected to a ram air fan (RAF), calculating the heat exchanger blockage parameter using at least the predicted RAF surge margin value, and reporting, to a user, the heat exchanger blockage parameter that indicates when a heat exchanger blockage condition is present.

公开(公告)号：US20170293710A1

公开(公告)日：2017-10-12

申请号：US15095357

申请日：2016-04-11

Applicant: Hamilton Sundstrand Corporation

Inventor： Nathan Haggerty ,  Tony Ho

IPC: G06F17/50 ,  G05B15/02

CPC classification number: G06F17/5086 ,  G05B15/02 ,  G05B17/02

Abstract: A system includes a plurality of sensors, a controller and a component. The plurality of sensors are configured to obtain sensed data indicative of characteristics of an environment. The controller is configured with a reduced order model to output a predicted parameter based on the sensed data. The reduced order model is generated on an external computer system using a high-fidelity physics-based model. The controller is configured to control the component based on the predicted parameter.

公开(公告)号：US20170243413A1

公开(公告)日：2017-08-24

申请号：US15049562

申请日：2016-02-22

Applicant: Hamilton Sundstrand Corporation

Inventor： Nathan Haggerty ,  Tony Ho

IPC: G07C5/08 ,  B64D45/00 ,  G06F17/11

CPC classification number: G07C5/0808 ,  B64D45/00 ,  B64D2045/0085 ,  G05B13/04 ,  G05B17/02 ,  G05B23/0232 ,  G05B23/0254 ,  G05B2219/37205 ,  G05B2219/42329 ,  G06F17/11 ,  G07C5/0816 ,  G07C5/0841

Abstract: A computer implemented method to determine aircraft sensor failure and correct aircraft sensor measurement in an aircraft system is provide. The computer implemented method includes determining, using a physics-based high-fidelity model, a high-fidelity system response over operating conditions during which sensor drift of a sensor of interest can be detected, creating, using an aircraft system controller, a reduced order model (ROM) using the high-fidelity system response, wherein the ROM correlates with the sensor of interest when operating normally, calculating, using the ROM, at least one reduced order sensor value, determining an error value between the reduced order sensor value and a sensor measurement reading from the sensor of interest, and comparing the error value to an error threshold, wherein the sensor of interest has failed when the error value is greater than the error threshold.