CN110884653A - System and method for aircraft propeller control - Google Patents
System and method for aircraft propeller control Download PDFInfo
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- CN110884653A CN110884653A CN201811055718.5A CN201811055718A CN110884653A CN 110884653 A CN110884653 A CN 110884653A CN 201811055718 A CN201811055718 A CN 201811055718A CN 110884653 A CN110884653 A CN 110884653A
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- 235000014676 Phragmites communis Nutrition 0.000 claims abstract description 105
- 230000004044 response Effects 0.000 claims abstract description 10
- 230000008859 change Effects 0.000 claims description 18
- 238000005259 measurement Methods 0.000 claims description 15
- 238000012545 processing Methods 0.000 claims description 14
- 239000012530 fluid Substances 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 description 12
- 230000007246 mechanism Effects 0.000 description 7
- 238000010586 diagram Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 210000003746 feather Anatomy 0.000 description 3
- 239000003570 air Substances 0.000 description 2
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- 239000000567 combustion gas Substances 0.000 description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/56—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
- B64C27/57—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Abstract
A system and method for controlling an aircraft propeller is provided. Anticipating a situation in which a parameter related to an angle of a plurality of blades of the propeller reaches a value that exceeds a predetermined threshold, outputting a first control signal comprising a command to actuate a reed valve operatively coupled to an actuator configured to adjust the angle in response to hydraulic pressure, thereby causing the reed valve to provide the hydraulic pressure to the actuator, and adjusting the angle to urge the parameter toward the threshold. Outputting a second control signal when the parameter reaches the predetermined threshold, the second control signal including a command to hold the reed valve at a position in which the hydraulic pressure is inhibited by the actuator, causing the angle to remain unchanged.
Description
Technical Field
The present application relates generally to aircraft propeller control.
Background
In current aircraft propeller systems, a propeller flying ball overspeed governor (fly ball over governor) is typically provided to limit the speed of the propeller. This hardware acts as a secondary propeller control mechanism independent of the primary mechanism, which may be a mechanical flyweight governor or an electro-hydraulic control system. To protect the propeller from becoming below the minimum blade angle, an auxiliary low pitch stop solenoid system is also typically integrated in the Propeller Control Unit (PCU). However, these mechanisms add weight, additional parts, and complexity to the PCU hardware.
In other applications, a reed valve (foil valve) of the propeller is modulated to avoid overspeed. However, this method is only applicable to reed valves whose position can be controlled by bandwidth modulation of its command, such as spring-loaded reed valves. This therefore imposes a certain hydraulic design on the PCU hardware.
Accordingly, there is a need for an improved aircraft propeller control system and method.
Disclosure of Invention
In one aspect, a system for controlling a propeller of an aircraft is provided. The system comprises: an actuator responsive to hydraulic pressure to adjust an angle of a plurality of blades of the aircraft propeller; a reed valve operatively coupled to the actuator and configured to selectively provide the hydraulic pressure to the actuator; a memory; and a processing unit coupled to the memory and configured to: outputting a first control signal comprising a command to actuate the reed valve, thereby causing the angle and the parameter to be adjusted towards a predetermined threshold value, in anticipation of a situation in which a propeller parameter related to the angle reaches a value that exceeds the threshold value; and outputting a second control signal when the parameter reaches the threshold, the second control signal including a command to hold the reed valve at a position in which the hydraulic pressure is inhibited by the actuator, thereby causing the angle to remain unchanged.
In another aspect, a method is provided for controlling an aircraft propeller having a plurality of blades, the propeller including an actuator responsive to hydraulic pressure to adjust an angle of the plurality of blades and a reed valve operatively coupled to the actuator and configured to selectively provide the hydraulic pressure to the actuator. The method comprises the following steps: outputting a first control signal comprising a command to actuate the reed valve, thereby causing the angle and the parameter to be adjusted towards a predetermined threshold, in anticipation of a situation in which a propeller parameter related to the angle reaches a value that exceeds the predetermined threshold; and outputting a second control signal when the parameter reaches the threshold, the second control signal including a command to hold the reed valve at a position in which the hydraulic pressure is inhibited by the actuator, thereby causing the angle to remain unchanged.
In a further aspect, a computer-readable medium is provided, having stored thereon program code executable by a processor for: in anticipation of a situation in which a parameter relating to an angle of a plurality of blades of an aircraft propeller reaches a value that exceeds a predetermined threshold, outputting a first control signal comprising a command to actuate a reed valve operatively coupled to an actuator configured to adjust the angle in response to hydraulic pressure, thereby causing the reed valve to provide the hydraulic pressure to the actuator, and adjusting the angle to urge the parameter towards the threshold; and outputting a second control signal when the parameter reaches the predetermined threshold, the second control signal including a command to hold the reed valve at a position in which the hydraulic pressure is inhibited by the actuator, thereby causing the angle to remain unchanged.
Drawings
Referring now to the drawings wherein:
FIG. 1 is a schematic cross-sectional view of a gas turbine engine in accordance with an illustrative embodiment;
FIG. 2 is a block diagram of a system for controlling an aircraft propeller in accordance with an illustrative embodiment;
FIG. 3 is a block diagram of the on-off pulse controller of FIG. 2;
FIG. 4 is a block diagram of a reed valve model unit of FIG. 2;
FIG. 5 is a block diagram of a computing device for implementing the controller of FIG. 2, in accordance with an illustrative embodiment; and is
FIG. 6 is a flowchart of a method for controlling an aircraft propeller, according to an illustrative embodiment.
Detailed Description
FIG. 1 illustrates a gas turbine engine 10 of the type typically provided for subsonic flight, comprising: an inlet 12 through which ambient air is propelled; a compressor section 14 for pressurized air; a combustor 16 in which compressed air is mixed with fuel and ignited to generate an annular flow of hot combustion gases; and a turbine section 18 for extracting energy from the combustion gases. Turbine section 18 illustratively includes: a compressor turbine 20 that drives the compressor assembly and accessories; and at least one power or free turbine 22 that rotatably drives a rotor shaft 24 about a propeller shaft axis a independently of the compressor turbine 20 and through a reduction gearbox 26. The hot gases may then be evacuated through a short exhaust pipe (stub) 28. A gas generator (not shown) of engine 10 illustratively includes a compressor section 14, a combustor 16, and a turbine section 18. The rotor 30 in the form of a propeller through which ambient air is propelled is housed in a propeller hub 32. The rotor 30 may, for example, comprise a propeller of a fixed wing aircraft or a main (or tail) rotor of a rotary wing aircraft (e.g., a helicopter). The rotor 30 may include a plurality of circumferentially arranged blades (not shown) connected to and extending radially from a hub (not shown) by any suitable means. The blades may also each rotate about their own radial axis through a plurality of blade angles, which may be varied to achieve several modes of operation, such as feathering (feather), full reverse, and forward thrust.
Referring now to fig. 2, a system 100 for controlling the rotor 30 (i.e., the aircraft propeller) will now be described. In one embodiment, the propeller 30 is a hydro-mechanical propeller, and the system is an electronic control system for protecting the propeller 30 from overspeeding and/or from becoming below a minimum blade angle. The control system 100 may include a digital computer or an Engine Control Unit (ECU) (not shown) using a Central Processing Unit (CPU) (not shown). As will be discussed further below, the control system 100 may then be implemented as a processor-based system, where the term processor may refer to a microprocessor, an Application Specific Integrated Circuit (ASIC), a logic circuit, or any other suitable processor or circuit known to those skilled in the art.
As will be discussed further below, to control the propeller speed and/or blade angle, the control system 100 modulates a reed valve 102 provided in a propeller control unit (PCU, not shown) in order to provide more controllability over the propeller system. The reed valve 102 is illustratively in fluid communication with a pitch actuator (pitch actuator) 103, the pitch actuator 103 being configured to adjust the angle of the propeller blades in response to hydraulic pressure. Using the control system 100, the reed valve 102 is bandwidth modulated open and closed to control the flow of fluid (e.g., oil) through the propeller, and the propeller speed and/or blade angle is adjusted accordingly. It should be appreciated that since the control system 100 relies on the reed valve dynamics (dynamics) of the PCU and the hydraulic circuit to control the reed valve 102, the control system 100 may be applied to various types of reed valves 102, including but not limited to spring-loaded valves, two-port solenoid valves, three-port solenoid valves, and so forth.
In operation, when actuated in response to a control signal from control system 100, also referred to herein as a feather command (feather command) generated as a pulse width modulated signal, reed valve 102 moves (e.g., winds) between a fully closed position and a fully open position to selectively provide hydraulic pressure to pitch actuator 103. To this end, the reed valve 102 is operatively coupled to a servo valve (not shown) arranged in selective fluid communication with the pitch actuator 103. When in the fully closed position, the reed valve 102 allows the flow of metering oil from the servo valve to the pitch actuator 103, providing hydraulic pressure and causing the blade angle to be adjusted accordingly. When the reed valve 102 has traveled halfway between the fully closed position and the fully open position (i.e., has reached a position referred to herein as a pitch locked position), the reed valve 102 restricts oil flow from the servo valve, thereby dampening hydraulic pressure and preventing further adjustment of the blade angle. The reed valve 102 also begins to direct the propeller 30 through a propeller pitch change mechanism (e.g., pitch change actuator 103), causing the propeller blades to move toward a feathered angle. When the reed valve 102 reaches the fully open position, maximum piloting (Drainage) is achieved when the servo valve path is fully closed.
In one embodiment shown in fig. 2, the control system 100 includes an on-off pulse controller unit 104 configured to generate a feathering command for actuating the reed valve 102 and an optional reed valve model unit 106 configured to estimate a current position of the reed valve 102 based on the feathering command. The on-off pulse controller unit 104 generates an initial feathering command in anticipation of (i.e., before occurrence of) a condition in which a propeller parameter (e.g., propeller speed or blade angle) exceeds a predetermined threshold. In this way, the reed valve 102 can be actuated at the correct time to prevent this from occurring. For example, and as will be discussed further below, the on-off pulse controller unit 104 generates an initial feathering command when it is determined that the desired propeller speed exceeds a maximum speed threshold or the desired propeller blade angle is below a minimum blade angle threshold. An initial feathering command is then sent to the reed valve 102, and the reed valve 102 is actuated accordingly, causing the propeller parameters to be adjusted toward the threshold. For example, actuation of the reed valve 102 causes the propeller to reach a large pitch (coarse pitch) and the propeller speed drops and falls within a desired band.
Propeller parameters and reed valve positions were continuously monitored in real time. As will be discussed further below, in one embodiment, the initial feathering command is used by the reed valve model unit 106 to estimate the current position of the reed valve 102. However, it should be understood that the current position of the reed valve 102 may be obtained from a sensor (not shown) configured to take one or more measurements indicative of the current position and output a position feedback signal accordingly. Once determined, the current reed valve position is then fed back to the on-off pulse controller unit 104, which may generate a new feathering command accordingly. In particular, the on-off pulse controller unit 104 illustratively generates a new feathering command when the propeller speed or blade angle has reached a desired threshold (e.g., within a desired threshold). The new feathering command may then include instructions to cause reed valve 102 to remain at the pitch lock position, thereby inhibiting hydraulic pressure to pitch actuator 103 and preventing further adjustment of the blade angle.
Still referring to fig. 2, the control system 100 further comprises a protection mode enabler unit 108 for enabling or disabling a protection mode of operation of the control system 100 based on the propeller speed and/or the blade angle. When the protection mode of operation is disabled (or "off"), the on-off pulse controller unit 104 does not generate a feathering command. When the protected mode of operation is enabled (or "on"), the reed valve 102 is actuated in response to one or more feathering commands generated by the on-off pulse controller unit 104, as will be discussed further below. In one embodiment, to avoid interference with the normal operating mode of the propeller, the protection mode of operation is only enabled when the main (or normal) operating mode of the propeller system is degraded by a fault (e.g., a servo valve fault, etc.) and the propeller system is unable to clear the fault. As described herein, the mechanisms implemented by the control system 100 thus act as a secondary (or backup) control mechanism for operating the propeller pitch change mechanism in the event of a failure or other undesirable propeller condition.
As discussed above, the protection mode is typically enabled when parameters of the propeller 30, such as propeller speed (Np) and/or propeller blade angle (also referred to as β), are predicted to reach values outside of a desired threshold range in the example of FIG. 2, the protection mode is enabled when the desired propeller speed is between 102% and 106% outside of the predetermined speed threshold range, in particular, when the desired propeller speed exceeds 106%, a feathering command is generated by the on-off pulse controller unit 104 (i.e., the protection mode is enabled), and when the desired propeller speed is equal to or below 102%, a feathering command is not generated (i.e., the protection mode is disabled), also when the desired blade angle is between 4 and 7 degrees outside of the predetermined blade angle threshold range, in particular, when the desired blade angle is below 4 degrees, a feathering command is generated by the on-off pulse controller unit 104, and when the desired propeller speed is equal to or above 7 degrees, no feathering command is generated.
Referring now to fig. 3, the on-off pulse controller unit 104 illustratively includes an overspeed limiter unit 202, β a limiter unit 204 and a pitch lock logic unit 206. the overspeed limiter unit 202 is used to predict overshoot of the propeller speed and, accordingly, generate a feathering command that will cause an adjustment of the propeller speed toward a desired speed threshold value β the limiter unit 204 is used to predict a decrease in the blade angle below a minimum blade angle threshold value and, accordingly, generate a feathering command that will cause an adjustment of the blade angle toward the desired blade angle threshold value, the pitch lock logic unit 206 is used to generate an on/off command that will cause the reed valve (reference numeral 102 in fig. 3) to remain at a pitch lock position.
The speed measurement received at overspeed limiter unit 202 is also sent to speed threshold monitoring unit 218, and speed threshold monitoring unit 218 evaluates whether the current propeller speed is within a desired speed threshold or band. This may be accomplished by comparing the current speed measurement to upper and lower propeller speed thresholds. If the current propeller speed is within the desired speed threshold, the Boolean output of the speed threshold monitoring unit 218 is set to logic 1. Otherwise, the boolean output of the speed threshold monitoring unit 218 is set to logic 0. The AND gate 220 then performs a logical AND of the output of the speed threshold monitoring unit 218 and the input generated by the Pitch Lock logic 206 (referred to as "Pitch _ Lock _ Enable" in FIG. 3). The logical OR of the outputs of the logical retard speed unit 216 and AND gate 220 is then computed at OR gate 222.
As can be seen in FIG. 3, the Pitch Lock logic 206 is used to generate an on/off command based on the reed valve position such that it dithers the reed valve 102 within a narrow band of Pitch Lock positions where the reed valve 102 will remain once the propeller speed or blade angle has reached a desired threshold, the Pitch Lock logic 206 includes a logical hysteresis valve position unit 224, the logical hysteresis valve position unit 224 taking as input the current reed valve position (e.g., from the reed valve model unit 106), the upper threshold of the Pitch Lock position (referred to as the "Pitch Lock position upper band" in FIG. 3), and the lower threshold of the Pitch Lock position (referred to as the "Pitch Lock position lower band" in FIG. 3). the Pitch Lock logic 206 then compares the current reed valve position to the upper and lower thresholds of the Pitch Lock position to determine if the reed valve 102 has reached the Pitch Lock position. based on the comparison, the Pitch Lock logic 206 outputs a Boolean value (referred to as "Pitch _ Lock _ Enable" in FIG. 3) which is fed to the overspeed limiter 202 and β if the Pitch Lock logic is not within the Pitch Lock position, the logical valve position is otherwise 0 output as a logical hysteresis unit 206.
The β limiter unit 204 operates similar to the overspeed limiter unit 202. in particular, the β limiter unit 204 receives a measurement of the current blade angle from any suitable means the blade angle measurement is then fed to the lead module 226, the lead module 226 performs a lead adjustment on the propeller blade angle signal, i.e., calculates a predicted rate of change of the propeller blade angle to predict a potential situation in which the propeller blade angle is below a minimum blade angle threshold. to this end, the lead module 226 uses the derivative unit 228 to calculate a derivative of the blade angle, uses the β derivative gain unit 230 to represent the amount of predicted time, and uses the multiplier 232 to multiply the blade angle derivative by a gain.the output of the multiplier 232 is then added to the value of the current blade angle to generate a value representing the predicted change of the propeller blade angle over predicted time. this value is then fed to the logical lag blade angle unit 234, the logical lag blade angle unit 234 also uses an upper threshold value for the propeller blade angle (referred to the "β upper band" in FIG. 3) and a lower threshold value for the logical lag blade angle (referred to the "β lower band" as an input in FIG. the logical lag angle unit 234) to determine if the predicted blade angle is below the minimum blade angle and the predicted blade angle is not set to the logical lag angle as the predicted blade angle by the logical lag angle unit 234 if the predicted blade angle is below the logical lag angle and the predicted blade angle is less than the predicted blade angle by the logical lag angle threshold value of the predicted blade angle.
The blade angle measurement received at β limiter unit 204 is also sent to β angle threshold monitoring unit 236, β angle threshold monitoring unit 236 evaluates whether the current blade angle is within the desired blade angle threshold, if this is the case, the Boolean output of blade angle threshold monitoring unit 236 is set to logic 1, otherwise, the Boolean output of blade angle threshold monitoring unit 236 is set to logic 0, AND gate 238 then performs a logical AND of the output of β angle threshold monitoring unit 236 and the pitch lock logic input, thus, blade angle threshold monitoring unit 236 and AND gate 238 are used to determine whether the reed valve (reference numeral 102 in FIG. 2) will remain at the pitch lock position, then a logical OR of the outputs of logical lag β angle unit 234 and AND gate 238 is calculated at OR gate 240, then a logical OR of the output of overspeed limiter unit 202 and the output of β limiter 204 is calculated at OR gate 242 to generate a feathering command.
Referring now to fig. 4, the reed valve model unit 106 illustratively includes a solenoid dynamics unit 302, the solenoid dynamics unit 302 using reed valve dynamics, particularly the dynamics of a reed solenoid (not shown) associated with the reed valve (reference numeral 102 in fig. 2), to estimate the current position of the reed valve 102. As understood by those skilled in the art, the reed valve 102 does include a reed solenoid (reed) that is energizable (e.g., by a pulse width modulated signal) to actuate the reed valve 102. In particular, once a feathering command is generated, the reed solenoid is energized after a certain period of time (i.e., a given charging time). The reed solenoid then moves the reed valve and experiences inertia.
Thus, the solenoid dynamics unit 302 takes as input the feathering command generated by the on-off pulse controller unit 104 and feeds it to the charge time unit 302. A charge time unit 302 is provided to take into account the time required to charge the reed solenoid after the reed valve (reference numeral 102 in fig. 2) command is output. A slew rate calculation unit 304 is also provided to take into account the slew rate of the reed valve 102 (i.e. the rate at which the reed valve 102 winds once actuated). At multiplier 306, the output of slew rate calculation unit 304 is multiplied by the output of charge time unit 302. A first order dynamic cell 308 is provided to account for the inertia of the reed solenoid after it is energized. A first order dynamics unit 308 receives the output of the multiplier 306 and calculates the instantaneous slew rate, which is in turn fed to an integrator module 310. The output of the integrator module 310, which is an estimate of the current reed valve position, is fed back to the pitch lock logic 206 of the on-off pulse controller unit 104. As discussed above, the current reed valve position may be used by the on-off pulse controller unit 104 to generate a new feathering command that will cause the reed valve 102 to remain at the pitch locked position.
Fig. 5 is an exemplary embodiment of a computing device 400 for implementing the control system 100 described above. Computing device 400 includes a processing unit 402 and a memory 404, with computer-executable instructions 406 stored in memory 404. The processing unit 402 may include any suitable means for: the apparatus is configured to cause a series of steps to be performed such that the instructions 406, when executed by the computing apparatus 400 or other programmable device, may cause the functions/acts/steps specifically illustrated in the methods described herein to be performed. Processing unit 402 may include, for example, any type of general purpose microprocessor or microcontroller, a Digital Signal Processing (DSP) processor, a CPU, an integrated circuit, a Field Programmable Gate Array (FPGA), a reconfigurable processor, other suitable programmed or programmable logic circuitry, or any combination thereof.
Referring now to FIG. 6, an exemplary method 500 for controlling an aircraft propeller will now be described. The method 500 may be implemented by the computing device 400 of fig. 5. The method 500 includes receiving a measurement of a current value of a propeller parameter (e.g., propeller speed or blade angle) at step 502. The next step 504 is to predict a situation in which the propeller parameters reach values exceeding a predetermined threshold. As discussed above, this may be accomplished by calculating an expected rate of change of a propeller parameter and comparing the predicted rate of change to a threshold to assess whether the parameter is expected to exceed the threshold. An initial feathering command is then output at step 506 to actuate the reed valves and adjust the blade angles accordingly, causing the propeller parameters to be adjusted towards the threshold. The propeller parameters are then monitored at step 508 and evaluated at step 510 for whether the propeller parameters are within a threshold. If this is not the case, the method 500 returns to step 508 of monitoring propeller parameters. If it is determined at step 510 that the propeller parameter is within the threshold value, a new feathering command is output at step 512 to cause the reed valve to remain at the pitch lock position, preventing further adjustment of the blade angle.
The above description is intended to be exemplary only, and those skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. Still other modifications that fall within the scope of the invention will be apparent to those skilled in the art from a review of this disclosure, and such modifications are intended to fall within the appended claims.
Claims (16)
1. A system for controlling a propeller of an aircraft, the system comprising:
an actuator responsive to hydraulic pressure to adjust an angle of a plurality of blades of the aircraft propeller;
a reed valve operatively coupled to the actuator and configured to selectively provide the hydraulic pressure to the actuator;
a memory; and
a processing unit coupled to the memory and configured to:
outputting a first control signal comprising a command to actuate the reed valve, thereby causing the angle and the parameter to be adjusted towards a predetermined threshold value, in anticipation of a situation in which a propeller parameter related to the angle reaches a value that exceeds the threshold value; and is
Outputting a second control signal when the parameter reaches the threshold, the second control signal including a command to hold the reed valve at a position in which the hydraulic pressure is inhibited by the actuator, thereby causing the angle to remain unchanged.
2. The system of claim 1, wherein the reed valve is operatively coupled to a servo valve disposed in selective fluid communication with the actuator, the reed valve being movable between a first position in which the reed valve allows fluid flow from the servo valve to the actuator to provide the hydraulic pressure and a second position in which the reed valve restricts the fluid flow to inhibit the hydraulic pressure.
3. The system of claim 1, wherein the processing unit is configured to:
receiving a measurement of a current value of the parameter;
calculating a rate of change of the parameter based on the measurement;
comparing the calculated rate of change to the threshold; and
predicting a condition if the calculated rate of change exceeds the threshold.
4. The system of claim 1, wherein the processing unit is configured to output the first control signal in anticipation of a situation in which propeller speed exceeds a predetermined speed threshold.
5. The system of claim 1, wherein the processing unit is configured to output the first control signal in anticipation of a situation in which the angle is below a predetermined angle threshold.
6. The system of claim 1, wherein the processing unit is configured to output each of the first and second control signals as a bandwidth modulated signal to a reed solenoid that is energizable to actuate the reed valve.
7. The system of claim 1, wherein the processing unit is configured to apply a reed valve model to estimate a current position of the reed valve in response to the first control signal, the reed valve model representing dynamics of the reed valve, and to generate the second control signal for causing the reed valve to move from the current position to a position in which the hydraulic pressure is inhibited by the actuator.
8. The system of claim 1, wherein the processing unit is configured to receive a position feedback signal from a sensor including a measurement of a current position of the reed valve in response to the first control signal, and to generate the second control signal for causing the reed valve to move from the current position to a position in which the hydraulic pressure is inhibited by the actuator.
9. A method for controlling an aircraft propeller having a plurality of blades, the propeller including an actuator responsive to hydraulic pressure to adjust an angle of the plurality of blades and a reed valve operatively coupled to the actuator and configured to selectively provide the hydraulic pressure to the actuator, the method comprising:
outputting a first control signal comprising a command to actuate the reed valve, thereby causing the angle and the parameter to be adjusted towards a predetermined threshold, in anticipation of a situation in which a propeller parameter related to the angle reaches a value that exceeds the predetermined threshold; and is
Outputting a second control signal when the parameter reaches the threshold, the second control signal including a command to hold the reed valve at a position in which the hydraulic pressure is inhibited by the actuator, thereby causing the angle to remain unchanged.
10. The method of claim 9, further comprising:
receiving a measurement of a current value of the parameter;
calculating a rate of change of the parameter based on the measurement;
comparing the calculated rate of change to the threshold; and
predicting a condition if the calculated rate of change exceeds the threshold.
11. The method of claim 9, wherein the first control signal is output in anticipation of a situation in which propeller speed exceeds a predetermined speed threshold.
12. The method of claim 9, wherein the first control signal is output in anticipation of a situation in which the angle is below a predetermined angle threshold.
13. The method of claim 9, wherein each of the first and second control signals is output as a bandwidth modulated signal to a reed solenoid that is energizable to actuate the reed valve.
14. The method of claim 9, further comprising applying a reed valve model to estimate a current position of the reed valve in response to the first control signal, the reed valve model representing dynamics of the reed valve, and generating the second control signal for causing the reed valve to move from the current position to a position in which the hydraulic pressure is inhibited by the actuator.
15. The method of claim 11, further comprising receiving a position feedback signal from a sensor comprising a measurement of a current position of the reed valve in response to the first control signal, and generating the second control signal for causing the reed valve to move from the current position to a position in which the hydraulic pressure is inhibited by the actuator.
16. A computer readable medium having stored thereon program code executable by a processor for:
in anticipation of a situation in which a parameter relating to an angle of a plurality of blades of an aircraft propeller reaches a value that exceeds a predetermined threshold, outputting a first control signal comprising a command to actuate a reed valve operatively coupled to an actuator configured to adjust the angle in response to hydraulic pressure, thereby causing the reed valve to provide the hydraulic pressure to the actuator, and adjusting the angle to urge the parameter towards the threshold; and is
Outputting a second control signal when the parameter reaches the predetermined threshold, the second control signal including a command to hold the reed valve at a position in which the hydraulic pressure is inhibited by the actuator, causing the angle to remain unchanged.
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| CN201811055718.5A CN110884653A (en) | 2018-09-11 | 2018-09-11 | System and method for aircraft propeller control |
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