Determination of Dynamic Stability Information Through Simulation of a Tumbling Tailless Aircraft

2006 ◽  
Author(s):  
Syta Saephan ◽  
C.P. van Dam
Keyword(s):  
Dynamic Stability ◽  
Tailless Aircraft

scholarly journals A numerical study into the longitudinal dynamic stability of the tailless aircraft

2019 ◽  
Vol 91 (3) ◽  
pp. 428-436 ◽  
Author(s):  
Agnieszka Kwiek
Keyword(s):  
Stability Analysis ◽  
Dynamic Stability ◽  
Numerical Study ◽  
Aircraft Design ◽  
Content Type ◽  
Preliminary Stage ◽  
Longitudinal Dynamic ◽  
Stability Derivatives ◽  
The Impact ◽  
Tailless Aircraft

Purpose The purpose of this research is a study into a mathematical approach of a tailless aircraft dynamic stability analysis. This research is focused on investigation of influence of elevons (elevator) on stability derivatives and consequently on the aircraft longitudinal dynamic stability. The main research question is to determine whether this impact should be taken into account on the conceptual and preliminary stage of the analysis of the longitudinal dynamic stability. Design/methodology/approach Aerodynamic coefficients and longitudinal stability derivatives were computed by Panukl (panel methods). The analysis of the dynamic stability of the tailless aircraft was made by the Matlab code and SDSA package. Findings The main result of the research is a comparison of the dynamic stability of the tailless aircraft for different approaches, with and without the impact of elevator deflection on the trim drag and stability derivatives. Research limitations/implications This paper presents research that mostly should be considered on the preliminary stage of aircraft design and dynamic stability analysis. The impact of elevons deflection on the aircraft moment of inertia has been omitted. Practical implications The results of this research will be useful for the further design of small tailless unmanned aerial vehicles (UAVs). Originality/value This research reveals that in case of the analysis of small tailless UAVs, the impact of elevons deflection on stability derivatives is bigger than the impact of a Mach number. This impact should be taken into consideration, especially for a phugoid mode.

scholarly journals Conceptual design of an aircraft for Mars mission

2019 ◽  
Vol 91 (6) ◽  
pp. 886-892
Author(s):  
Agnieszka Kwiek
Keyword(s):  
Stability Analysis ◽  
Dynamic Stability ◽  
Conceptual Design ◽  
Design Stage ◽  
Content Type ◽  
Mars Mission ◽  
Longitudinal Dynamic ◽  
Short Period ◽  
The Impact ◽  
Tailless Aircraft

Purpose The purpose of this paper is to present the results of a conceptual design of Martian aircraft. This study focuses on the aerodynamic and longitudinal dynamic stability analysis. The main research questions are as follows: Does a tailless aircraft configuration can be used for Martian aircraft? How to the short period characteristic can be improved by side plates modification? Design/methodology/approach Because of a conceptual design stage of this Martian aircraft, aerodynamic characterises were computed by the Panukl package by using the potential flow model. The longitudinal dynamic stability was computed by MATLAB code, and the derivatives computed by the SDSA software were used as the input data. Different aircraft configurations have been studied, including different wing’s aerofoils and configurations of the side plate. Findings This paper presents results of aerodynamic characteristics computations and longitudinal dynamic stability analysis. This paper shows that tailless aircraft configuration has potential to be used as Martian aircraft. Moreover, the study of the impact of side plates’ configurations on the longitudinal dynamic stability is presented. This investigation reveals that the most effective method to improve the short period damping ratio is to change the height of the bottom plate. Practical implications The presented result might be useful in case of further design of the aircrafts for the Mars mission and designing the aircrafts in a tailless configuration. Social implications It is considered by the human expedition that Mars is the most probable planet to explore. This paper presents the conceptual study of aircraft which can be used to take the high-resolution pictures of the surface of Mars, which can be crucial to find the right place to establish a potential Martian base. Originality/value Most of aircrafts proposed for the Mars mission are designed in a configuration with a classic tail; this paper shows a preliminary calculation of the tailless Martian aircraft. Moreover, this paper shows the results of a dynamic stability analysis, where similar papers about aircrafts for the Mars mission do not show such outcomes, especially in the case of the tailless configuration. Moreover, this paper presents the results of the dynamic stability analysis of tailless aircraft with different configurations of the side plates.

The Tightening Accuracy of Workpieces in the Multiple Clamping Devices

2014 ◽  
Vol 657 ◽  
pp. 524-528 ◽  
Author(s):  
Neculai Eugen Seghedin ◽  
Dragoş Florin Chitariu
Keyword(s):  
Dynamic Stability ◽  
Machine Tools ◽  
Machining Time ◽  
Number Of Components ◽  
The Subject

Fixtures are used for orientation-positioning-tightening of workpieces during machining on machine tools. Multiple clamping fixtures are intended to clamp several workpieces for simultaneous or successive machining. Multiple clamping is characterized by a series of economical advantages, due to the reduction of total machining time. These advantages are more important once the number of workpieces is higher or if the machining is made with compound tools. Due to the complexity, overall size and the high number of components, the multiple clamping fixtures have diminished accuracy than simple fixture due to elastic and contact deformations of fixtures housing, of supports etc. Also, multiple clamping fixtures present diminished rigidity and dynamic stability. From the analysis of the specialized literature results that there are a few paper on the subject of multiple clamping. In the paper there are presented the causes that can lead to the diminish of the accuracy of multiple fixture. The modalities for the determination of fixtures precision are presented, also, for the parallel and serial multiple clamping fixtures.

Determination of dynamic stability derivatives using forced oscillation technique

2002 ◽  
Author(s):  
N. Alemdaroglu ◽  
I. Iyigun ◽  
M. Altun ◽  
H. Uysal ◽  
F. Quagliotti ◽  
...  
Keyword(s):  
Dynamic Stability ◽  
Forced Oscillation ◽  
Forced Oscillation Technique ◽  
Stability Derivatives

Determination of excitation parameter limits for generator dynamic stability

1989 ◽  
Vol 72 (5) ◽  
pp. 357-362 ◽  
Author(s):  
C. D. Vournas ◽  
A. V. Machias ◽  
J. L. Souflis
Keyword(s):  
Dynamic Stability ◽  
Excitation Parameter

Design Guidelines for Dynamic Stability of Tainter Gates

2017 ◽  
Author(s):  
Keiko Anami ◽  
Noriaki Ishii ◽  
Charles W. Knisely ◽  
Tatsuya Oku
Keyword(s):  
Dynamic Stability ◽  
Fem Analysis ◽  
Design Guidelines ◽  
Design Stage ◽  
Actual Structure ◽  
Analysis And Design ◽  
Coupled Mode ◽  
Excited Vibration ◽  
Vibration Tests

To ensure the long-term safe operation of newly constructed Tainter gates, methods of analysis and design criteria are needed in the design stage to assure the dynamic stability of any new Tainter gate. For this purpose, the present study provides a detailed procedure for the dynamic design of Tainter gates that can be applied to preliminary designs by gate engineers to assure the dynamic stability of their gate designs. The dynamic stability of the gate can be determined using the natural vibration characteristics ascertained by finite element method (FEM) analysis, reasonable values of actual structure damping actually measured by the field vibration tests, and theoretical analysis of the coupled-mode self-excited vibration that has been previously established by authors. The procedure and the important points of each step are detailed in an example determination of the dynamic stability of a practical Tainter gate.

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