Three surface aircraft (TSA) configuration – flying qualities evaluation

Goetzendorf‐Grabowski, Tomasz; Antoniewski, Tomasz

doi:10.1108/aeat-02-2015-0055

Cited by 19 publications

(14 citation statements)

References 7 publications

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“…The input data are provided as discrete values which are interpolated by the software. In the case of the flight at low AoA, the relation is usually linear, therefore, the prediction of aerodynamic forces and moments with this kind of approach should give good results what was proven and confirmed in the flight tests presented in (Goetzendorf-Grabowski et al, 2013;Goetzendorf-Grabowski and Antoniewski, 2016). However, in the case of the rocket plane, which flies at high AoA, the characteristics are nonlinear and feeding the data even with many points might not guarantee satisfactory results.…”

Section: Methodsmentioning

confidence: 76%

“…Previously it was proven that the SDSA could be applied successfully to the simulation of flight characteristics of airplanes flying at angles of attack lower than stall angles (Goetzendorf-Grabowski et al, 2011;Goetzendorf-Grabowski et al, 2013;Goetzendorf-Grabowski and Antoniewski, 2016;Goetzendorf-Grabowski and Figat, 2016). In the presented research the package was used in the simulation of the post-stall characteristics.…”

Section: Simulation and Dynamic Stability Analysismentioning

confidence: 96%

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Results of simulation and scaled flight tests performed on a rocket-plane at high angles of attack

Kwiek

Galiński

Bogdański

et al. 2021

AEAT

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Purpose According to the study of the space flight market, there is a demand for space suborbital flights including commercial tourist flights. However, one of the challenges is to design a mission and a vehicle that could offer flights with relatively low G-loads. The project of the rocket-plane in a strake-wing configuration was undertaken to check if such a design could meet the FAA recommendation for this kind of flight. The project concept assumes that the rocket plane is released from a slowly flying carrier plane, then climbs above 100 kilometers above sea level and returns in a glide flight using a vortex lift generated by the strake-wing configuration. Such a mission has to include a flight transition during the release and return phases which might not be comfortable for passengers. Verification if FAA recommendation is fulfilled during these transition maneuvers was the purpose of this study. Design/methodology/approach The project was focused on the numerical investigation of a possibility to perform transition maneuvers mentioned above in a passenger-friendly way. The numerical simulations of a full-scale rocket-plane were performed using the simulation and dynamic stability analyzer (SDSA) software package. The influence of an elevator deflection change on flight parameters was investigated in two cases: a transition from the steep descent at high angles of attack to the level glide just after rocket-plane release from the carrier and an analogous transition after re-entry to the atmosphere. In particular, G-loads and G-rates were analyzed. Findings As a result, it was found that the values of these parameters satisfied the specific requirements during the separation and transition from a steep descent to gliding. They would be acceptable for an average passenger. Research limitations/implications To verify the modeling approach, a flight test campaign was performed. During the experiment, a rocket-plane scaled model was released from the RC model helicopter. The rocket-plane model was geometrically similar only. Froude scales were not applied because they would cause excessive technical complications. Therefore, a separate simulation of the experiment with the application of the scaled model was performed in the SDSA software package. Results of this simulation appeared to be comparable to flight test results so it can be concluded that results for the full-scale rocket-plane simulation are also realistic. Practical implications It was proven that the rocket-plane in a strake-wing configuration could meet the FAA recommendation concerning G-loads and G rates during suborbital flight. Moreover, it was proven that the SDSA software package could be applied successfully to simulate flight characteristics of airplanes flying at angles of attack not only lower than stall angles but also greater than stall angles. Social implications The application of rocket-planes in a strake-wing configuration could make suborbital tourist flights more popular, thus facilitating the development of manned space flights and contributing to their cost reduction. That is why it was so important to prove that they could meet the FAA recommendation for this kind of service. Originality/value The original design of the rocket plane was analyzed. It is equipped with an optimized strake wing and is controlled with oblique, all moving, wingtip plates. Its post-stall flight characteristics were simulated with the application of the SDSA software package which was previously validated only for angles of attack smaller than stall angle. Therefore, experimental validation was necessary. However, because of excessive technical problems caused by the application of Froude scales it was not possible to perform a conventional test with a dynamically scaled model. Therefore, the geometrically scaled model was built and flight tested. Then a separate simulation of the experiment with the application of this model was performed. Results of this separate simulation were compared with the results of the flight test. This comparison allowed to draw the conclusion on the applicability of the SDSA software for post-stall analyzes and, indirectly, on the applicability of the proposed rocket-plane for tourist suborbital flights. This approach to the experimental verification of numerical simulations is quite unique. Finally, a quite original method of the model launching during flight test experiment was applied.

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Section: Methodsmentioning

confidence: 76%

Section: Simulation and Dynamic Stability Analysismentioning

confidence: 96%

Results of simulation and scaled flight tests performed on a rocket-plane at high angles of attack

Kwiek

Galiński

Bogdański

et al. 2021

AEAT

View full text Add to dashboard Cite

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“…The stability constraints can play a significant role in case of unconventional configuration. 19 Such problems are presented in several papers and concern configurations such as flying wing, 20 three surface aircraft, 21 or box wing. 22 Figure 6 presents the change of the body shape of the aircraft in the box wing configuration and Figure 7 presents the result of convergence of the trim, stability and stress constraints.…”

Section: Practical Applicationsmentioning

confidence: 99%

Multi-disciplinary optimization in aeronautical engineering

Goetzendorf‐Grabowski

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Nowadays, optimization is a very popular tool used to improve existing projects. The optimization covers different disciplines by linking them into multidisciplinary process of design. Existing software tools allow to very effectively solve particular problems giving high quality solutions which were previously very hard to achieve. Aeronautical engineering is a domain/field which links many disciplines: aerodynamics, stability, control, structural analysis, materials, propulsion systems, avionics, etc. Therefore, the multidisciplinary optimization results in very significant progress not only in aircraft design but also in air transport, which links technical aspects with economical questions. The paper presents selected aspects of using the multidisciplinary optimization in aeronautical engineering with special focus on multidisciplinary aircraft design.

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“…Initial conceptual analyses were performed and included: recognizing potential needs of the future user, propulsion type selection and sizing and estimation of the basic parameters of the aircraft. To improve the design numerical optimization was performed based but not limited to enhanced cruse duration Mieloszyk et al (2016) and Goetzendorf-Grabowski and Antoniewski (2016).…”

Section: Reference Aircraftmentioning

confidence: 99%

Morphing wing with skin discontinuity – kinematic concept

Tarnowski

2017

AEAT

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This paper describes novel discontinuous morphing flying wing concept, which despite its relatively simple design, has not been previously used. Potentially it can combine advantages of wing morphing without challenges of structure elastic deformation. Proposed wing structure has modular construction formed by rigid, separate segments, pivoted around swept spar. This paper presents preliminary investigation of wing kinematics on conceptual design level. Project assumptions, next steps and expected results are briefly presented.

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Three surface aircraft (TSA) configuration – flying qualities evaluation

Cited by 19 publications

References 7 publications

Results of simulation and scaled flight tests performed on a rocket-plane at high angles of attack

Results of simulation and scaled flight tests performed on a rocket-plane at high angles of attack

Multi-disciplinary optimization in aeronautical engineering

Morphing wing with skin discontinuity – kinematic concept

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