Stability analysis using SDSA tool

Goetzendorf‐Grabowski, Tomasz; Mieszalski, Dawid; Marcinkiewicz, Ewa

doi:10.1016/j.paerosci.2011.08.007

Cited by 37 publications

(31 citation statements)

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“…shows computed characteristic of the lift coefficient vs. angle of attack for the airfoil. Simple Newton-Rapson gradient algorithm was used to find the angle of attack for the maximum lift coefficient (1). The method finds zero value of the objective function.…”

Section: Simple Example Of Encountering Optimization Problemsmentioning

confidence: 99%

Practical problems of numerical optimization in aerospace sciences

Mieloszyk

2017

AEAT

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Design processes of aircrafts are well established today and described by numerous positions in literature. This well understood and safe path leads to aircraft designs, which become very similar. It is harder then ever to achieve competitive construction. This is why numerical optimization is becoming standard tool during the design process. Although, optimization procedures are becoming more mature, in the industry practice still fairly simple examples of optimization are present. The more complicated is the task to solve the harder it is to implement automated optimization procedures. The paper presents practical examples of optimization in aerospace sciences. Encountered problems during the optimization are presented, solutions of the problems are shown and resulting consequences are discussed.

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Section: Simple Example Of Encountering Optimization Problemsmentioning

confidence: 99%

Practical problems of numerical optimization in aerospace sciences

Mieloszyk

2017

AEAT

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“…In order to quantify the impact of CG position on performance, we performed the evaluations shown below. First of all, plots of elevator deflection to trim the airplane in steady level powered flight versus the airspeed and angle of attack were defined using the SDSA software developed by Warsaw University of Technology, Poland [56,57] as shown in Figure 13a,b, respectively. Calculations were made for the baseline propulsion configuration (see Figure 2) and five different CG positions were staggered by 10% of MAC.…”

Section: Center Of Gravity Position Impact On the Airplane Performancementioning

confidence: 99%

“…Based on this, the numeric model as shown in Figure 17 was created to assess the airplane aerodynamic characteristics in sideslip cases using the PANUKL software developed by Warsaw University of Technology, Poland [58]. Using results from PANUKL, input data for the analysis was updated and the stability computation was performed in SDSA [56][57][58] for geometry with a new vertical stabilizer position and most aft CG position. The basic results are presented in Figure 18 and compared with the properties of the airplane with the initial geometry and most forward CG position.…”

Section: Center Of Gravity Position Impact On the Airplane Performancementioning

confidence: 99%

“…It is a bit different in terms of lateral-directional stability because a combination of dihedral and wing sweep angles together with side connecting plates and usually a relatively small area of vertical stabilizer makes it difficult to predict airplane qualities. That is why the results presented in [59] revealed spiral instability and a satisfactory level of Dutch roll Using results from PANUKL, input data for the analysis was updated and the stability computation was performed in SDSA [56][57][58] for geometry with a new vertical stabilizer position and most aft CG position. The basic results are presented in Figure 18 and compared with the properties of the airplane with the initial geometry and most forward CG position.…”

Section: Center Of Gravity Position Impact On the Airplane Performancementioning

confidence: 99%

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Electric Propulsion Concepts for an Inverted Joined Wing Airplane Demonstrator

2017

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Abstract:One of the airplane design concepts that potentially allows for significantly increased efficiency, but has not yet been investigated thoroughly, is the inverted joined wing configuration, where the upper wing is positioned in front of the lower one. We performed wind tunnel and flight testing of a demonstrator of this concept, first by applying electrical propulsion to simplify wind tunnel testing, and then the same electrical-propulsion demonstrator performed several flights. As the chosen propulsion method proved to be too cumbersome for an intensive flight campaign and significant loss of battery performance was also observed, the electrical propulsion was then replaced by internal combustion propulsion in the second phase, involving longer-duration flight testing. Next we identified and analyzed two potentially beneficial modifications to the design tested: one involved shifting the center of gravity towards the aft, the other involved modifying the thrust vector position, both with the assumption that electric motors can be applied for propulsion. On this basis, the paper finishes with some conclusions concerning a new concept of electrical propulsion for an inverted joined wing design, combining two ideas: hybridization and distribution along the aft wing leading edge.

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“…The dynamic stability analysis was performed by the SDSA package (Goetzendorf-Grabowski 2008). The analysis of eigenvalues was made by a linearized nonlinear model (Goetzendorf-Grabowski 2008;Goetzendorf-Grabowski et al 2011) by computing the Jacobian matrix (Goetzendorf-Grabowski 2008;Goetzendorf-Grabowski et al 2011) around a trim point. Equation 1presents the general form of the eigenvalue solutions computed by the SDSA package.…”

Section: The Dynamic Stability Analysismentioning

confidence: 99%

Study on the Static and Dynamic Stability of a Modular Airplane System

Kwiek

2016

Aviation

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The purpose of this research is an analysis of the static and dynamic stability of the Modular Airplane System (MAS). The MAS is designed to perform suborbital space flights. The concept assumes that two tailless vehicles bonded together form a conventional aircraft where the wing of the second one is used as the horizontal tail of the whole system. The CFD calculations, and the stability and control derivatives were conducted by the PANUKL package, which uses a low order panel method for the aerodynamic analysis. The analysis of the static and dynamic stability was performed by the SDSA package. Only the selected part of the MAS mission was investigated. The results that will be presented have been divided into three parts: static stability, longitudinal dynamic stability and lateral dynamic stability. The MAS has a few possible applications. The first one is a suborbital space tourism flight. Moreover, it can be used as a lunching vehicle for micro satellites or as a testing platform for new space technology to improve their TRL level. Finally, in the far future, it could be used as a fast point-to-point travel system. The paper presents the results of the static and dynamic stability of a unique aircraft configuration which consists of two tailless vehicles. The research focuses on a situation where the vehicles are just before separation and their mass is similar. Moreover, the influence of the second vehicle’s position with respect to the first one is included.

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Stability analysis using SDSA tool

Cited by 37 publications

References 1 publication

Practical problems of numerical optimization in aerospace sciences

Practical problems of numerical optimization in aerospace sciences

Electric Propulsion Concepts for an Inverted Joined Wing Airplane Demonstrator

Study on the Static and Dynamic Stability of a Modular Airplane System

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