The subject matter disclosed herein relates to enhanced engine load demand anticipation and, more particularly, to using angle of attack data in enhanced engine load demand anticipation in a helicopter.
In a rotary-wing aircraft application, engine anticipation may be part of the engine control system to maintain rotor speed within a relatively narrow range in response to demanded torque from the rotary-wing aircraft rotor system. The capability of the engine control algorithm to correctly anticipate changes in power required directly impact rotor speed governor performance.
Conventional engine power anticipation algorithms include collective pitch based anticipators, predictive anticipators and lookup-table based anticipation algorithms that add atmospheric variation, reference rotor speed and airspeed data to collective anticipation concepts. In some cases, tail rotor power requirement data is also added.
Collective pitch based anticipators are most commonly utilized on current generation rotary-wing aircraft. The engine power anticipation algorithm utilizes changes in collective control displacement as collective pitch change has a significant effect on power required. The collective control position is monitored and fuel flow is adjusted based on collective control displacement. This type of an algorithm is typically implemented via mechanical or electronic feedback. Collective pitch based anticipator performance may be imperfect, however, since power required depends on a multitude of factors, such as air speed, gross weight, maneuver, etc.
Predictive anticipators are currently under development. This category of engine power anticipation algorithms monitor various states of the aircraft and attempt to predict changes in power required with a neural-network which must be trained on each particular engine and aircraft. There are known certification issues with predictive anticipators, however, since the neural network is not deterministic.
According to one aspect of the invention, a flight control system of an aircraft is provided and includes modules configured to shape one or more flight control commands through a flight control system to provide a shaped flight control command and to determine expected power required data for the shaped flight control command. The flight control system further includes an architecture configured to determine enhanced engine load demand anticipation utilizing data reflective of an angle of attack of the aircraft for use in a determination of the expected power required data.
According to another aspect of the invention, a flight control system of an aircraft is provided and includes modules configured to shape one or more flight control commands through a flight control system to provide a shaped flight control command and to determine expected power required data for the shaped flight control command. The flight control system further includes an architecture configured to determine enhanced engine load demand anticipation utilizing data reflective of a collective setting and angle of attack of the aircraft for use in a determination of the expected power required data.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
The description provided below relates to enhanced anticipation of aircraft power demand changes for a rotary wing aircraft, utilizing angle of attack data for more accurate estimation of power required by the main rotor system in steady and maneuvering flight.
Power required by a helicopter main rotor varies tremendously with both collective pitch setting and angle of attack. Existing helicopter engine anticipation algorithms predict power required as a function of collective position but assume level flight conditions. In a hybrid helicopter with multiple control surfaces allowing additional flexibility in setting the trim angle of attack of the main rotor in level flight, or a conventional or hybrid helicopter in climbing/descending flight, collective position alone is insufficient to reasonably predict main rotor power demand.
Torque and power coefficients provide non-dimensional expressions of a power required by an aircraft and are expressed in terms of rotor speed, rotor radius, density and torque as shown in the following equation.
Cq=Q/(ΠρΩ2R5)=Cp
The power coefficient of the main rotor in a typical rotary wing design of an aircraft is a function of advance ratio, collective setting, and angle of attack. As long as the collective setting is reasonably high, the angle of attack sensitivity is reduced as shown in
PwrComp=(NrREFERENCE/NrNOMINAL)3*ρ/ρ0
With reference to
In detail, as shown in
The at least one action is performed in the engine controller. Fuel flow to the engine module is regulated through an electronic engine control unit utilizing the engine controller's rotor speed governor algorithm and anticipation data from the flight control system. The at least one action may be operative to modify at least a pitch axis of the aircraft, a roll axis of the aircraft, a yaw axis of the aircraft and/or a lift axis of the aircraft. The at least one action may be initiated prior to an application of the flight control command to an aircraft flight control unit or prior to generation of a resultant aircraft response.
As shown in
The first LUT 11 receives as an input data reflective of an angle of attack α of the aircraft, collective setting position θc of the main rotor blades and an air speed TAS of the aircraft and provides for a determination from that data a relationship between required power P and the collective setting position θc (dP/dθc). Thus, the first LUT 11 permits the capturing of high frequency power changes due to changes in the collective setting position θc. The first derivative lag filter 12 receives as an input data reflective of a collective setting pilot input and provides for a determination from that data a relationship between the collective setting position θc and time (dθc/dt). The second LUT 13 receives as an input data reflective of the angle of attack α of the aircraft, collective setting position θc of the main rotor blades and the air speed TAS of the aircraft and provides for a determination from that data a relationship between required power P and the angle of attack α of the aircraft (dP/dα). Thus, the second LUT 13 permits the capturing high frequency power changes due to changes in the angle of attack α. The second derivative lag filter 14 receives as an input data reflective of the angle of attack α and provides for a determination from that data a relationship between the angle of attack α and time (dα/dt). The third LUT 15 receives as an input data reflective of the angle of attack α of the aircraft, collective setting position θc of the main rotor blades and the air speed TAS of the aircraft and provides for a determination from that data a steady state required power P as a function of the angle of attack α, the collective setting position θc of the main rotor blades and the air speed TAS of the aircraft f(α, θ, TAS). An output of the third LUT 15 is provided to the lag filter 16.
The respective outputs of the first LUT 11 and the first derivative lag filter 12 are summed at the first summation unit 17 and provide for a reading of power required per second (HP/sec) due to rapid changes in collective setting pilot input. The respective outputs of the second LUT 13 and the second derivative lag filter 14 are summed at the second summation unit 18 and provide for a reading of power required per second (HP/sec) due to rapid changes in the angle of attack α. These summed results are then combined at the third summation unit 19 and output to the first gain compensation unit 20. An output of the first gain compensation unit 20 is thus reflective of a high frequency power demand of the aircraft that takes into account the collective setting pilot input data and the angle of attack α data. The output of the lag filter 16 is in turn output to the second gain compensation unit 21 and then output from the gain compensation unit 21 as a low frequency power demand.
In accordance with further embodiments, possible alternate methods of implementation may be feasible. In some case, an estimate of angle of attack that is derived from other aircraft state data may be made rather than utilizing a direct sensor measurement of angle of attack. For example, a relationship between the angle of attack and time may be modeled based on a commanded pitch rate and air speed. Another possible alternate method of implementation would be to model the power required as an empirical or physics-based model that doesn't utilize lookup tables.
With reference to
Use of angle of attack data and collective setting data in determining an engine load demand is expected to yield improved anticipation of load demand transients due to changes in flight condition. This, in turn, is expected to yield tighter rotor governing. The improved anticipation will also reduce the severity of maneuvers and flight conditions previously considered “uncompensated for,” thus simplifying engine control design.
While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
This application is a National Phase Application of Patent Application PCT/US15/52899 filed on Sep. 29, 2015, which claims the benefit of and priority to U.S. Provisional Patent Application Ser. No. 62/057,611 filed on Sep. 30, 2014, the contents of which are incorporated herein by reference in their entirety.
Filing Document | Filing Date | Country | Kind |
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PCT/US2015/052899 | 9/29/2015 | WO | 00 |
Publishing Document | Publishing Date | Country | Kind |
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WO2016/054014 | 4/7/2016 | WO | A |
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