The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory
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...
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| Format: | Article |
| Language: | English |
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MDPI AG
2023-05-01
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| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/10/5/489 |
| _version_ | 1827742498361966592 |
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| author | Agnieszka Kwiek Marcin Figat Tomasz Goetzendorf-Grabowski |
| author_facet | Agnieszka Kwiek Marcin Figat Tomasz Goetzendorf-Grabowski |
| author_sort | Agnieszka Kwiek |
| collection | DOAJ |
| description | 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. |
| first_indexed | 2024-03-11T04:02:47Z |
| format | Article |
| id | doaj.art-835d5f8dd43845288233bbfbee307cdd |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-11T04:02:47Z |
| publishDate | 2023-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-835d5f8dd43845288233bbfbee307cdd2023-11-18T00:01:05ZengMDPI AGAerospace2226-43102023-05-0110548910.3390/aerospace10050489The Study of Selected Aspects of the Suborbital Vehicle Return Flight TrajectoryAgnieszka Kwiek0Marcin Figat1Tomasz Goetzendorf-Grabowski2Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, Nowowiejska 24, 00-665 Warsaw, PolandInstitute of Aeronautics and Applied Mechanics, Warsaw University of Technology, Nowowiejska 24, 00-665 Warsaw, PolandInstitute of Aeronautics and Applied Mechanics, Warsaw University of Technology, Nowowiejska 24, 00-665 Warsaw, PolandThe 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.https://www.mdpi.com/2226-4310/10/5/489suborbital flightflight simulationresponse to controlrocket plane |
| spellingShingle | Agnieszka Kwiek Marcin Figat Tomasz Goetzendorf-Grabowski The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory Aerospace suborbital flight flight simulation response to control rocket plane |
| title | The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory |
| title_full | The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory |
| title_fullStr | The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory |
| title_full_unstemmed | The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory |
| title_short | The Study of Selected Aspects of the Suborbital Vehicle Return Flight Trajectory |
| title_sort | study of selected aspects of the suborbital vehicle return flight trajectory |
| topic | suborbital flight flight simulation response to control rocket plane |
| url | https://www.mdpi.com/2226-4310/10/5/489 |
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