Aircraft and rotorcraft system identification : engineering by Mark Tischler, Robert Remple

By Mark Tischler, Robert Remple

Even supposing many books were written at the concept of procedure id, few can be found that offer an entire engineering therapy of approach identity and the way to effectively use it on flight cars. This booklet offers the original standpoint of over twenty years of flight-test functions to either plane and rotorcraft and is a priceless source for college kids, operating engineers, and others drawn to atmospheric flight mechanics, modeling and simulation, and try and review. It offers confirmed equipment, sensible directions, and real-world flight-test effects for a variety of cutting-edge flight automobiles, from small uncrewed aerial automobiles (UAVs) to giant manned aircraft/rotorcraft.

Beginning with the elemental recommendations of procedure identity, each one bankruptcy strains an easy simulation instance and actual flight examples during the step by step strategy from instrumentation and knowledge checking to version extraction and version verification. The frequency-response technique, that's distinctive to this ebook, is principally like minded for procedure id of airplane and rotorcraft dynamics types from flight-test information. an entire bankruptcy is dedicated to higher-order modeling of helicopters. Many functions are incorporated to illustrate how the goods due to process id are used. particular purposes comprise flight mechanics and handling-qualities analyses, balance margin choice, structural mode choice, and simulation version constancy assessment.

The e-book assumes wisdom of the elemental suggestions of aeronautics, Laplace transforms, and flight dynamics and classical keep an eye on. Emphasis is put on engineering equipment and interpretation of flight-test effects and every key process or research software is illustrated with photographs got from the process id software program (CIFERÆ) supplied with the booklet. Case reports in response to actual flight-test initiatives are integrated besides! as difficulties for college kids to unravel utilizing the supplied CIFERÆ software.

A ideas guide, written by means of Christina M. Ivler and Mark B. Tischler is out there from the writer.

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Extra resources for Aircraft and rotorcraft system identification : engineering methods with flight-test examples

Sample text

These transfer-function models provide the key dynamic modes and control sensitivities. Transfer-function models of the bare-airframe response can be used directly for control system synthesis based on root-locus techniques, whereas equivalent system models of the closed-loop response with the automatic flight-control system (AFCS) active are widely used for handling-qualities analyses. In some applications, it might be necessary to proceed to the ultimate identification step of extracting a state-space description in terms of identified stability and control derivatives.

There is strong coupling between the dynamics of the rotor blades and the dynamics of the air flow passing through the rotor (inflow) with those of the fuselage, control system, and engine, so that as many as 13 degrees of freedom (or even more) are often necessary to model the dynamic response accurately. The planar symmetry of a fixedwing aircraft also leads to considerable simplification of system-identification model structures, decoupling into a three-DOF model for the longitudinal dynamics and a separate three-DOF model for lateral/directional dynamic characteristics.

6 Simulation vs system identification. that this can be done before the aircraft has been built. In some cases the agreement between the predicted and measured dynamic behavior is unsatisfactory, at least initially, before “tuning,” because of the accumulated uncertainties and modeling simplifications. The approach is less suitable for small unmanned air vehicles (UAVs), which often have unique designs that are not similar to any existing database. System identification and simulation modeling can be seen as inverse procedures, as shown in Fig.

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