阅读说明：本技术 控制系统 (Control system ) 是由 V.基里齐斯 M.布里斯托 于 2019-06-20 设计创作，主要内容包括：本发明题为“控制系统”。本发明提供了一种能够操作以为飞行器提供经修改的主控制参数的控制系统(100),该控制系统(100)包括：主控制参数支路,该主控制参数支路被配置为输出该飞行器的主控制参数(103)中的需求；主控制参数补偿支路,该主控制参数补偿支路被配置为接收涡流角和/或风扇压力在相对于参考的主控制参数下的绝对水平和/或空间分布的检测到的变化(107),并将该检测到的变化(107)转换为该主控制参数(106)的变化；和处理器,该处理器适于：接收从该主控制参数支路输出的该主控制参数(103)中的需求和从该主控制参数补偿支路输出的该主控制参数(106)的变化；比较从该主控制参数支路输出的该主控制参数(103)中的该需求和从该主控制参数补偿支路输出的该主控制参数(106)的该变化；以及为该飞行器生成经修改的主控制参数(105)。(The invention provides a control system. The invention provides a control system (100) operable to provide an aircraft with modified master control parameters, the control system (100) comprising: a main control parameter branch configured to output a demand in a main control parameter (103) of the aircraft; a main control parameter compensation branch configured to receive a detected change (107) of the swirl angle and/or of the absolute horizontal and/or spatial distribution of the fan pressure at a main control parameter relative to a reference and to convert the detected change (107) into a change of the main control parameter (106); and a processor adapted to: receiving a demand in the main control parameter (103) output from the main control parameter branch and a change in the main control parameter (106) output from the main control parameter compensation branch; comparing the demand in the main control parameter (103) output from the main control parameter branch with the change in the main control parameter (106) output from the main control parameter compensation branch; and generating modified master control parameters for the aircraft (105).)

1. A control system operable to provide an aircraft with modified master control parameters, the control system comprising:

a main control parameter branch configured to output a demand in a main control parameter of the aircraft;

a main control parameter compensation branch configured to receive detected changes in the absolute level and/or spatial distribution of the swirl angle and/or fan pressure at a main control parameter relative to a reference and convert the detected changes to changes in the main control parameter; and

a processor adapted to:

receiving the demand in the main control parameter output from the main control parameter branch and the change in the main control parameter output from the main control parameter compensation branch;

comparing the demand in the main control parameter output from the main control parameter branch with the change in the main control parameter output from the main control parameter compensation branch; and

generating modified master control parameters for the aircraft.

2. The control system of claim 1, wherein a thrust demand generates the demand in the main control parameters.

3. The control system of claim 1, wherein deriving and detecting accordingly any change in the absolute level and/or spatial distribution of the swirl angle and/or fan pressure comprises tracking or detecting one or more changes in the absolute level and/or spatial distribution of the measured value of one or more properties of the fluid flowing in the bypass duct of the aircraft engine.

4. A control system according to claim 1, wherein deriving and hence detecting any change in the absolute level and/or spatial distribution of the swirl angle and/or fan pressure comprises tracking or detecting one or more changes in the absolute level and/or spatial distribution of the derived value of a parameter of the fluid flowing in the bypass duct of the aircraft engine.

5. A control system according to claim 1 wherein deriving and hence detecting any change in the absolute level and/or spatial distribution of swirl angle and/or fan pressure comprises utilising an estimate of a parameter of fluid flowing in a bypass duct of the aircraft engine.

6. The control system of claim 1, the system comprising a device for estimating a parameter of fluid flowing in the bypass conduit, the device comprising:

a plurality of instruments operable to measure one or more properties of the fluid flowing in the bypass duct, the plurality of instruments being disposed in the bypass duct and arranged in a common measurement plane.

7. Control system according to claim 6, wherein the common measurement plane is located within the bypass duct (22) downstream of the pusher fan (13).

8. The control system of claim 6, wherein the common measurement plane is located in the region of one or more outlet guide vanes within the bypass duct.

9. The control system of claim 6, wherein the plurality of instruments are arranged in a regular or irregular pattern within the common measurement plane.

10. The control system of claim 6, wherein the plurality of instruments are arranged in one or more rings, each ring comprising a plurality of spaced apart instruments.

11. The control system of claim 6, wherein the plurality of instruments are circumferentially and/or radially spaced at intervals.

12. The control system of claim 6, wherein the one or more properties of the fluid measured by the plurality of instruments include one or more of: pressure, such as static pressure or total pressure; (ii) temperature; a fluid flow rate; fluid flow rate and/or fluid flow direction, such as yaw angle of flow.

13. A control system according to claim 6, wherein each instrument comprises a pressure sensor, a sensor operable to measure or derive a fluid flow rate, such as a pitot tube, and/or a sensor operable to measure or derive an airflow direction, such as a yaw probe.

14. A control system according to claim 6, comprising one or more data storage devices, such as a data logger, adapted to store the measured values measured by the instrument and/or the derived values calculated using the measured values.

15. The control system of claim 6, comprising:

a computer adapted to communicate with the plurality of instruments and to:

receiving measurements of the one or more properties of the fluid measured by the plurality of instruments;

assigning flow tubes to each instrument, wherein each flow tube represents a spatial region in the common measurement plane that is within the bypass conduit and each flow tube surrounds one instrument of the plurality of instruments, wherein the flow tubes together correspond to the cross-sectional shape and area of the bypass conduit in the common measurement plane;

calculating a derived value for each flow tube using the measured values for each flow tube;

summing said derived values over all of said flow tubes.

16. A gas turbine engine or aircraft comprising the control system of claim 1.

17. A method of operating an aircraft, comprising:

providing a demand in a master control parameter of the aircraft;

receiving a detected change in the absolute level and/or spatial distribution of the swirl angle and/or fan pressure at a primary control parameter relative to a reference;

converting the detected change to a change in the primary control parameter;

comparing the demand in the primary control parameter to the change in the primary control parameter; and

generating modified master control parameters for the aircraft.