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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Once it reaches that milestone, the engine maker hopes to officially launch the program and test the demonstrator core next year. The model has two poles common to all transfers, but the zeros are different for each of them. The invention is advantageously completed by the following characteristics, taken individually or in any of their technically possible combinations. The state feedback corrector and static compensator are configured so that the control system of the transfer function have poles and gains corresponding to those of the transfer function of the turboprop model.

It is found that SHP power and speed of the propeller XNP perform well in terms setpoint tracking, decoupling and disturbance rejection.

## Réacteur et APU du B737-800

Let L be the state feedback matrix M and the static compensation matrix. Similarly, the state feedback equalizer 24 and SVC 29 are matrices gains size 2×2 L and M, so it is relatively easy to interpolate the coefficients of the matrices. The performances obtained are insufficient, especially in terms of disturbance rejection. 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.

The advantage of these methods is that the synthetic steps of the compensating monovariable 15 and regulators 16 are distinct. The parameters monovariable correctors are interpolated individually by sequencing gains. The PW models featured trbopropulseur, two-stage centrifugal high-pressure compressors, the more powerful PW moving to a three-stage axial design. Tkrbopropulseur airframers have got to decide the size of airplane they want.

A control system 10 turbpropulseur a turboprop engine according to one of the preceding claims, wherein the feedback control condition 24 is a feedback loop turbopgopulseur the outputs of the turboprop engine 1 and the outputs of the state feedback matrix Les performances obtenues sont alors insuffisantes, notamment en termes de rejet de perturbations.

The gain of sequencing is to determine a family of linear systems approaching the nonlinear system in a given number of operating points, and propose control laws in each region of the state space associated to finally realize a global control law. The proposed setting method used to separate the phases of design and decoupling of the drive. A number of characteristics operating points are defined. Indeed, the behavior of turboproopulseur system changes during aging thereof.

The company said it has completed the advanced study phase and is ready to launch the demonstrator program. E1 Model definition the turboprop.

The structure of the model is given in the form of transfer matrix in equation 2. A validation test was applied to validate control laws on the complete model of the turboprop. Gains N, p and the poles are chosen to turbopropulseurr approach the diagonal transfer of the expression 2using model reduction techniques, such as truncation technique and comparing the frequency responses the original transfer and reduced those transfers, emphasizing conservation static gain and the cutoff frequency.

The structure of the desired transfer matrix of the closed loop system is given in 4 using the notation of 3.

### Douglas A2D Skyshark — Wikipédia

Tyrbopropulseur permet d’obtenir 8. The control feedback state 24 is a feedback loop between the states that correspond to the helix power outputs SHP and propeller rotational speed XNP the turboprop engine 1 and outputs the return of 24 state.

The ratings of the equation 3 are subsequently adopted: The monovariable 22a corrector has as input variable the error of the servo SHP and corrector monovariable 22b has as input variable the error of the servo XNP. Instructions and outputs are derived which allows to work with error increments, and the control increments are integrated.

The overall power loop is a feedback loop between the turboprop engine power output and the output of the corrector monovariable power.

Monovariable correctors 22a, 22b may in particular be PI controller having a proportional action and an integral action. The diagrams of the prior art systems which follow are presented with linear turboprop models.

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 A method of setting a control system 10 according to one of claims 8 to 11, further comprising an interpolation step of state feedback equalizer 24 and the static compensator 29 according to flight conditions variables C1, C2, C3, Experimentation With a T-Inverted Pendulum. The speed is controlled XNP around several speed ranges, defined with respect to flight conditions and relative to the state of the turboprop.

As shown in Figure 5, turbopropu,seur known decoupling approaches State feedback eg synthesis Falb-Wolovich described in “Command turboprlpulseur multivariate estimation,” Ostertag, or the complete modal synthesis.

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