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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Furthermore, these adjustments do not impact decoupling. The speed is controlled XNP around several speed ranges, defined with respect to flight conditions and relative to the state of the turboprop. A control system 10 of a turboprop engine according to one of the ccours claims, wherein: These allow to take into account the interactions between SHP and XNP loops during synthesis corrective but are more complex than traditional control methods. It is relatively simple to adjust the settings post regulators monovariable Indeed, the behavior of the system changes during aging turbopropluseur.

The structure of the desired transfer matrix of the closed loop system is given in 4 using the notation of 3. These methods consist in adding a feedback comprising a feedback state 14 and a static compensation M 14b to decouple the system. An turboprkpulseur of the invention is therefore to provide a control system for a turboprop engine for obtaining an effective decoupling of the power of the propeller P SH and the speed of rotation of the propeller XNP with control laws and relatively simple synthesis methods.

As shown in Figure 3, are known centralized approaches called H2 type H- such as described in G. Figures 11 and 12 illustrate the results obtained with the control system 10 described. They cause particularly important overtorque damaging components fatigue, especially the gear 4. Gains N, p and the poles are chosen to best approach the diagonal transfer of the expression 2using model reduction techniques, such as truncation technique turbopropulsejr comparing the frequency responses the original transfer and reduced those transfers, emphasizing conservation static gain and the cutoff frequency.

These adjustments can be made in the upstream design phases, during tests on test benches, but also during the life of the turboprop. The problem with these methods is that through 17 are difficult to calculate and not always accurate enough.

### PW remplacement de la série PW

Les performances obtenues sont alors insuffisantes, notamment en termes de rejet de perturbations. Monovariable correctors 22a, 22b may in particular be PI controller having a proportional action and an integral action. Saabas said the new engine will not be aimed at increasing the cruising speed of regional turboprops, typically knots. 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.

Quelques vieux liens http: A method of setting a control system 10 according to claim 8 or claim 9, further comprising an interpolation step turrbopropulseur correctors 22a, 22b depending on flight conditions of variables C1, C2, C3, In particular, when the correction monovariable 22a, couts are PI correction, interpolation gains is simple since it is a sum of different weighted shares turbopropulsehr gains.

E3 define a monovariable corrector 22a so as 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. A differentiator 26a is placed at the input of the overall power SHP loop 31, and a differentiator turboprkpulseur is placed at the input of the global loop rotational speed of the turboprppulseur 32 XNP.

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 model of the turboprop for performing the steps E2 and E3 is generally a linear model identified around operating points. The feedback control condition is a static multivariable regulator whose resulting commands are linear combinations of the power of the propeller and the rotation speed of the propeller of the turboprop.

## Douglas A2D Skyshark

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 using compensators 15, before using monovariable 16 of the PID type regulators it possible to control the system.

These characteristic operating points courw characterized by flight conditions Mach, altitude and states of the turboprop. Overall, the company has established a comprehensive testing program for this year.

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. The model therefore has two state variables, the order of the system equals the number of state variables. It expects to run the core demonstrator in tutbopropulseur second half of next year.

A suitable or perfect decoupling can only be achieved by using complex compensators, hardly implementable and interpolated.

## PW remplacement de la série PW100

The model has two poles common to all transfers, but the zeros are different for each of them. In these approaches, the control laws are synthesized from a linear model identified around operating points. The SVC is a static multivariable regulator which the resulting commands are linear combinations of the power set increments of cous propeller and rotational speed setpoint of the propeller turboprop.

C’est un peu se remettre enfin, au niveau des nouveaux turbo-fan. Moreover, these control laws are not intuitive, which is an obvious problem for adjustments adjustments during engine tests.