A project-oriented introduction to flight test engineering

Ward, D. T.

doi:10.2514/6.1988-2116

Cited by 21 publications

(34 citation statements)

References 1 publication

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“…These data are summarized in Table 6. The phugoid damping ratio ζ Ph is calculated using the transient-peak-ratio (TPR) method suggested by Ward and Strganac [18]. This method consists in measuring the transient peak ratio from the time histories and then through a chart the damping ratio can be read (see Ref.…”

Section: Dynamic Longitudinal Stabilitymentioning

confidence: 99%

Stability, flying qualities and longitudinal parameter estimation of a twin-engine CS-23 certified light aircraft

Nicolosi

Marco

Vecchia

2013

Aerospace Science and Technology

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Section: Dynamic Longitudinal Stabilitymentioning

confidence: 99%

Stability, flying qualities and longitudinal parameter estimation of a twin-engine CS-23 certified light aircraft

Nicolosi

Marco

Vecchia

2013

Aerospace Science and Technology

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“…APM programme is used by airliners to monitor the trend of fuel consumption and specific air range (SR) during time in service. Main method for SR determination is the method for cruise flight drag estimation [15,16]. More details of cruise performance monitoring method are given in the third part of this paper.…”

Section: Performance Evaluation Methodsmentioning

confidence: 99%

Aircraft performance monitoring from flight data

2015

Teh. vjesn.

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Preliminary notesTo ensure timely maintenance and efficient aircraft operations, it is necessary to know and keep track of aircraft's actual performance. Flight performance is determined by aircraft's physical characteristics. Theoretical aircraft performance, obtained after manufacturing and flight testing, are described in flight manual. Transport aircraft in operation is usually exposed to standard operational conditions. Despite the standard operational conditions and regular aircraft maintenance, structure aging and high dynamic loads due to high subsonic Mach number could lead to changes of main physical factors that determine flight performance. For this reason actual aircraft performance often differs from theoretical. Commercial airlines monitor true performance of aircraft in operation. This paper presents an overview of existing performance monitoring methods as well as first indications for new research possibilities regarding physical characteristics determination for aircraft in operation using flight data. Keywords: aerodynamic coefficients; flight performance; flight testing; system identification Praćenje stvarnih performansi zrakoplova prema podacima iz letaPrethodno priopćenje Poznavanje stvarnih performansi zrakoplova bitno je za učinkovitu eksploataciju i pravovremeno održavanje. Performanse su određene fizikalnim karakteristikama zrakoplova. U Priručniku za letenje opisane su teorijske performanse određene od proizvođača nakon proizvodnje zrakoplova i testiranja u letu. Komercijalni zrakoplovi su tijekom svog operativnog ciklusa uglavnom izloženi predviđenim uvjetima eksploatacije. Unatoč predviđenim uvjetima eksploatacije i redovnom održavanju, starenje materijala i velika opterećenja na strukturu zrakoplova kod leta visokim podzvučnim Machovim brojem, mogu dovesti do promjene temeljnih fizikalnih faktora koji određuju performanse. Zbog toga se stvarne performanse zrakoplova nerijetko razlikuju od teorijskih. Zračni prijevoznici prate stanje zrakoplova i njegove stvarne performanse tijekom korištenja. U ovom radu prikazan je pregled dosadašnjih metoda praćenja performansi i mogućnosti istraživanja na području određivanja fizikalnih parametara zrakoplova u eksploataciji prema podacima iz leta.Ključne riječi: aerodinamički koeficijenti; identifikacija sustava; ispitivanje u letu; performanse leta

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“…At a given bank angle, the steady state, straight line lateral-directional equation of mo written as follows: (14) If the C.G. of the aircraft is located at the neutral point, i.e.…”

Section: Estimation Of Static Stability and Control Derivativesmentioning

confidence: 99%

“…Once the aircraft is stabilized in a 60 degree left bank with zero roll rate, the pilot abruptly moves the stick to the right and holds it until the aircraft is rolled to a 60 degree right bank. The pilot then moves the stick to the neutral position and maintains 425-436 (2015) the aircraft at 60 degrees of the right bank angle [13][14], as shown in Fig. 6. …”

Section: Prediction Of Aerodynamic Derivativesmentioning

confidence: 99%

A Study on Parameter Estimation for General Aviation Canard Aircraft

Kim¹,

Seong²,

Kim³

2015

International Journal of Aeronautical and Space Sciences

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This paper presents the procedures used for estimating the stability and control derivatives of a general aviation canard aircraft from flight data. The maximum likelihood estimation method which accounts for both process and measurement noise was used for the flight data analysis of a four seat canard aircraft, the Firefly. Without relying on the parameter estimation method, several aerodynamic derivatives were obtained by analyzing the steady state flight data. A wind tunnel test, a flight test of a 1/4 scaled remotely controlled model aircraft, and the prediction of aerodynamic coefficients using the USAF Stability and Control Digital Data Compendium (DATCOM), Advanced Aircraft Analysis (AAA), and Computer Fluid Dynamics (CFD) were performed during the development phase of the Firefly and the results were compared with flight determined derivatives of a full scaled flight prototype. A correlation between the results from each method could be used for the design of the canard aircraft as well as for building the aerodynamic database.

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A project-oriented introduction to flight test engineering

Cited by 21 publications

References 1 publication

Stability, flying qualities and longitudinal parameter estimation of a twin-engine CS-23 certified light aircraft

Stability, flying qualities and longitudinal parameter estimation of a twin-engine CS-23 certified light aircraft

Aircraft performance monitoring from flight data

A Study on Parameter Estimation for General Aviation Canard Aircraft

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