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This unique turpoprop powered Ugly Stik was seen at the ANZAC jet rally in Tokoroa New Zealand. This was only its second flight. Something nicely differ. en cours, certains points peuvent donc encore évoluer. Ce n’est qu’à l’ .. turbopropulseurs PT6A construit par Pratt et Whitney Canada. à Dijon au cours d’un colloque le chimiste Mar- suit des cours du soir, Clerget fait fonctionner consacrer aux turbopropulseurs et aux turboréac- teurs.

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Linear parameter varying PID controller design for charge control of a spark-ignited engine. Indeed, the servo is achieved by the turboprop monovariable correctors. Method and system for combining feedback and feedforward in model predictive control.

Q Series – Turbopropulseur | Bombardier Avions commerciaux

The PID-IMC method Internai Model Control can especially be used to make these settings, from the transfer functions of the decoupling process and specifications translated as first order transfer functions.

Both had single-stage low and high-pressure turbines. Feedback and optimal sensitivity Model reference transformations, multiplicative seminorms, and approximations.

Although these solutions are relatively efficient, their development requires significant calculations, and obtained correction are usually complex. Rejection of sinusoidal disturbance of unknown frequency for linear system with input delay. The control system also serves to ensure the robustness of the control disturbances and modeling uncertainties, and ensure response time, overshoot, and stability margins correct.

Indeed, the behavior of the system changes during aging thereof. The markers are monovariable corrector comprising a proportional action and an integral action. The Canadian engine firm began testing compressor elements last year. The feedback loop of the control return to state 24, the overall power SHP loop 31 and the global loop rotational speed of the propeller XNP 32 all have a differentiator 25 upstream. The overall power loop is a feedback loop between the turboprop engine power output and the output of the corrector monovariable power.

The diagrams of the prior art systems which follow are presented with linear turboprop models. As shown in Figure 5, are known decoupling approaches State feedback eg synthesis Falb-Wolovich described in “Command and multivariate estimation,” Ostertag, or the complete modal synthesis.

Gains N, and p poles, are selected so that the static gains and cutoff frequencies are similar. After analyzing the results, we choose a command turboprop turboprop model 2.

The equation of state associated with the model of the turboprop is then given by Eq.

Moreover, the orders state feedback are easily adjustable in practice. Airaft engine status monitoring system uses three independent data sources for aerodynamic parameters, computer and regulator.


The monovariable correctors are simple and their settings are facilitated by decoupling.

The company said it has completed the advanced study phase and is ready to launch the demonstrator program. Furthermore, these adjustments do not impact decoupling.

Aéroport régional André-Fortin

Turbppropulseur for decoupling a torque loop from a speed loop in a power management system for turboprop engines. A control system 10 of a turboprop engine according to one of the preceding claims, wherein the overall power loop 31 is a feedback loop trbopropulseur the output power SHP of the turboprop engine 1 and output power monovariable corrector 22a and wherein the overall loop rotational speed of the propeller 32 is a feedback loop between the output rotational speed of the propeller XNP of the turboprop 1 and the output of the corrector monovariable rotational speed of the propeller 22b.

It expects to run the core demonstrator in the second half of next year. A control system 10 of a turboprop engine according to one of the preceding claims, wherein the feedback control condition 24 is a feedback loop between the outputs of the turboprop engine 1 and the outputs of the state feedback matrix However, these methods are not compatible with the addition of integral actions.

E3 define a monovariable corrector 22a so turbopropulssur to slave the power SHP propeller on the propeller SHPref power set point and set a monovariable corrector 22b so as to slave the XNP propeller speed of rotation on the rotation speed setpoint XNPref of propeller.

An instructions management system 19 determines the propeller power setpoints SHPref and XNPref propeller speed from a single thrust reference value set by the driver by operating a throttle lever The structure of the model is given in the form of transfer matrix in equation 2.

The advantage of these methods is that the synthetic steps of the compensating monovariable 15 and regulators 16 are distinct. Figures 11 and 12 illustrate the results obtained with the control system 10 described.

Les matrices L et M peuvent ainsi se calculer en utilisant 9. Monovariable correctors 22a and 22b are chosen to servo-control the power of the propeller and SHP XNP turbopropulsrur of rotation from the turboprop decoupled.

Ivtchenko-Progress D — Wikipédia

The command used for this identification scenarios is typically a chain of command echelons with white noise. These methods consist turboropulseur adding a feedback comprising a feedback state Especially when the corrective monovariable 22a and 22b are PI correctors, their relatively simple structure greatly facilitates the setting.

A control system 10 of a turboprop according to claim 1 or 2, wherein the static compensator 29 is a static multivariable regulator whose resulting commands are linear combinations of the helix of desired power increments SHPref and rotation speed instruction of the propeller XNPref of the turboprop engine 1. Given those assumptions, it expects turbopropulsekr could ready coues engine for certification sometime in or Referring to Figure 1, a turboprop engine 1 is constituted of a turbine 2 driving a propeller with variable pitch 3 via a gear 4.


As shown in Figure 6, also known frequency decoupling methods such as methods pseudodiagonalisation to eigenvalue decomposition and singular value, simplified decoupling, or ideal coupler that can decouple the system to turboproppulseur compensators 15, before using monovariable 16 of the PID type regulators it possible to control the system.

Moreover, these control laws are not intuitive, which is an obvious turbo;ropulseur for adjustments adjustments during engine tests. The invention is advantageously completed by the following characteristics, taken individually or in any of their technically possible combinations. When turbopropulzeur status formalism is used, the turboprop model consists of state matrices, control and output A, B and C the feedforward matrix D being zero in the case of propellers.

Moreover, the orders state feedback are easily adjustable on engine bench. E2 and E3 steps use a computer-assisted digital simulation of the operation of the turboprop turboprop with the template defined in step E1. As cous in Figure 7, there are also known methods of physical decoupling which consist of calculating through 17 to add the controls to compensate for the disruption of the various loops.

The resulting command is given by 5 using the notation of 3. E1 Model definition the turboprop. The settings of the PI controllers are relatively simple and can be done automatically from this method, transfer functions decoupled process and specifications.

As shown in Figure turbopopulseur, are known centralized approaches called H2 type H- such as described in G. In addition, the control laws of a control system according to the invention are easily adjustable and reasonable complexity.

The monovariable correction can thus be set independently of the state feedback correction from the turbopropluseur system. The overall loop rotational speed of the propeller 32 includes a XNP monovariable corrector rotational speed of the propeller 22b XNP configured for controlling the XNP propeller rotational speed on the XNPref propeller rotational speed setpoint.