Lotniczo-rakietowy system wynoszenia ładunków na niską orbitę okołoziemską – studium realizowalności

Olejnik, Aleksander; Zalewski, Piotr; Kiszkowiak, Łukasz; Rogólski, Robert; Borcuch, Dominik; Milczarczyk, Jarosław; Radomski, Michal; Dziubiński, Adam

doi:10.15632/ml2020/227-239

Cited by 1 publication

(1 citation statement)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Sometimes it happens that professional research institutions are trying to focus on reasons influenced the crash and employ their human and equipment resources for explaining what had happened. A good example of such the activity can be found in Olejnik (2017).…”

Section: Boundary and Initial Conditionsmentioning

confidence: 99%

Simulation of a passenger aircraft flight with the wing tip cut

Goraj

Kowalski

Kiszkowiak

et al. 2021

AEAT

Self Cite

View full text Add to dashboard Cite

Purpose The purpose of this paper is to present the result of simulations that were performed to assess the uncontrolled motion of the passenger aircraft following its wing tip was suddenly cut. Such a simulation can help to understand the tendencies of aircraft behaviour after wing tip cut, assess how fast this phenomenon is going on and estimate the values of angles of attack, sideslip and pitch angle basing on given aerodynamic characteristics. Also, answer the question if pilot can counteract high deviations from flight path initially planned during the final phase of approach to landing. Design/methodology/approach Simulation is based on the full non-linear equations of motion derived from generalised equations of change of momentum and moment of momentum of rigid body. Dynamic equations of motion in the so-called normal mode are solved in the so-called stability frame of reference. Findings It was found that asymmetric rolling moment must be compensated by essential increase of pitching moment. Moreover, it appeared that aircraft goes into high angles of attack and high pitch angle and, therefore, for reliable simulation, the available aerodynamic characteristics must include angles of attack till 90 degrees when total flow separation occurs. Practical implications For accurate simulation, it is strongly recommended to perform to perform first the wind tunnel testing in the range of +20o ÷ 120o and use it in flight simulation. Originality/value The presented methodology is an original for numerical simulation of flight trajectory during the final phase of approach to landing in a hazardous state of flight. For reliable simulation, the available aerodynamic characteristics must include angles of attack till 90 degrees when total flow separation occurs, whereas usually maximum angles of attack used in wind tunnel experiments for passenger aircraft are not higher than 25 degrees. The influence of limited range of experimental data on results of simulation is another value which can be adopted in the future investigations of hazardous states of flight.

show abstract

Section: Boundary and Initial Conditionsmentioning

confidence: 99%