Flight dynamics of unconventional configurations

Goetzendorf‐Grabowski, Tomasz

doi:10.1016/j.paerosci.2023.100885

Cited by 10 publications

(4 citation statements)

References 41 publications

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“…The next step in any aircraft design is the stability analysis. For such an unconventional layout, this step is particularly important [40]. Dynamic stability analysis was carried out for longitudinal modes.…”

Section: Dynamic Stabilitymentioning

confidence: 99%

The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory

Kwiek

Figat

Goetzendorf‐Grabowski

2023

Aerospace

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The article presents the results of preliminary studies of the parameters of the return flight trajectory of a rocket plane for suborbital tourist flights into space. The rocket plane is designed as a tailless vehicle and has an unconventional arrangement of control surfaces: elevons and side plates that can rotate. The main aim of the research presented in this paper is to investigate the dynamic stability of the rocket plane and the response to control in the return suborbital flight. The secondary objective is to study the behavior of the rocket plane with respect to the initial state of the return flight. The key parameters taken into account in this study are the Mach number and G-load. Moreover, a study of the trim condition, dynamic stability and response to control of a rocket plane in the low part of the stratosphere is presented. The tests were carried out using a numerical simulation of the flight of a rocket plane. Dynamic stability was determined on the basis of time history analysis, and the results were compared with the results obtained by solving the eigenvalues problem. The results revealed that the rocket plane should be equipped with a Stability Augmentation System to improve short period damping at supersonic speeds at moderate altitudes. It can also be concluded that the maximum load G and Ma do not occur at the same height of flight. In terms of the effectiveness of the control surfaces, they start working at an altitude of 55 km. Due to the speed regime, the obtained results can be useful in the design of such objects as rocket planes, highly maneuverable and supersonic aircraft.

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Section: Dynamic Stabilitymentioning

confidence: 99%

The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory

Kwiek

Figat

Goetzendorf‐Grabowski

2023

Aerospace

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“…Moreover, further enhancement of a conventional configuration from the aerodynamic point of view seems to be exhausted. Therefore, lots of researchers are searching for a more effective configuration by turning to non-conventional configurations (Bravo-Mosquera et al, 2022;Goetzendorf-Grabowski, 2023) like biplane (Goraj et al, 2001), tandem wing (Goetzendorf-Grabowski and Figat, 2017), joined wing (Galinski et al, 2018), flying wing (Mieloszyk et al, 2020), three surfaces configuration (Goetzendorf-Grabowski and Antoniewski, 2016), delta wing (Gudmundsson, 2014), etc. One of the more interesting, but not very popular, aircraft configurations is a tandem wing configuration.…”

Section: Introductionmentioning

confidence: 99%

Analysis of longitudinal dynamic stability of tandem wing aircraft

Figat

Kwiek

2023

AEAT

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Purpose Tandem wing aircrafts belong to an unconventional configurations group, and this type of design is characterised by a strong aerodynamic coupling, which results in lower induced drag. The purpose of this paper is to determine whether a certain trend in the wingspan impact on aircraft dynamic stability can be identified. The secondary goal was to compare the response to control of flaps placed on a front and rear wing. Design/methodology/approach The aerodynamic data and control derivatives were obtained from the computational fluid dynamics computations performed by the MGAERO software. The equations of aircraft longitudinal motion in a state space form were used. The equations were built based on the aerodynamic coefficients, stability and control derivatives. The analysis of the dynamic stability was done in the MATLAB by solving the eigenvalue problem. The response to control was computed by the step response method using MATLAB. Findings The results of this study showed that because of a strong aerodynamic coupling, a nonlinear relation between the wing size and aircraft dynamic stability proprieties was observed. In the case of the flap deflection, stronger oscillation was observed for the front flap. Originality/value Results of dynamic stability of aircraft in the tandem wing configuration can be found in the literature, but those studies show outcomes of a single configuration, while this paper presents a comprehensive investigation into the impact of wingspan on aircraft dynamic stability. The results reveal that because of a strong aerodynamic coupling, the relation between the span factor and dynamic stability is nonlinear. Also, it has been demonstrated that the configuration of two wings with the same span is not the optimal one from the aerodynamic point of view.

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“…The potential advantages of such a system come with various problems, mainly in the area of handling qualities, unless the issues of stability and controllability are taken into account at the earliest possible stage of the design. These issues are covered extensively in books (Gudmundsson, 2016) and articles (Goraj, 2014; Rodzewicz et al , 2018; Tomaszewski and Goraj, 2019; Esteban, 2001; Goetzendorf-Grabowski, 2023). The design of a small-sized unmanned aerial vehicle requires a special approach, primarily considering low Reynolds numbers at the aerodynamic design stage, but also solving many seemingly minor problems resulting from the small size of components and the need to keep the low weight of the aircraft.…”

Section: Introductionmentioning

confidence: 99%

Designing aerodynamic devices for UAV – lessons learned

Mieloszyk,

Tarnowski,

Goetzendorf-Grabowski

2023

AEAT

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Purpose Designing new aircraft that are state-of-the-art and beyond always requires the development of new technologies. This paper aims to present lessons learned while designing, building and testing new UAVs in the configuration of the flying wing. The UAV contains a number of aerodynamic devices that are not obvious solutions and use the latest manufacturing technology achievements, such as 3D printing. Design/methodology/approach The design solutions were applied on an airworthy aircraft and checked during test flights. The process was first conducted on the smaller UAV, and based on the test outcomes, improvements were made and then applied on the larger version of the UAV, where they were verified. Findings A number of practical findings were identified. For example, the use of 3D printing technology for manufacturing integrated pressure ports, investigation of the adverse yaw effect on the flying wing configuration and the effectiveness of winglet rudders in producing yawing moment. Practical implications All designed devices were tested in practice on the flying aircraft. It allowed for improved aircraft performance and handling characteristics. Several of the technologies used improved the speed and quality of aerodynamic device design and manufacturing, which also influences the reliability of the aircraft. Originality/value The paper presents how 3D printing technology can be utilized for manufacturing of aerodynamic devices. Specially developed techniques for control surface design, which can affect adverse yaw problem and aircraft handling characteristics, were described.

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Flight dynamics of unconventional configurations

Cited by 10 publications

References 41 publications

The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory

The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory

Analysis of longitudinal dynamic stability of tandem wing aircraft

Designing aerodynamic devices for UAV – lessons learned

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