Evaluation of Aerodynamic Performance of Mars Airplane in Scientific Balloon Experiment

Anyoji, Masayuki; Okamoto, Masato; Fujita, Koji; Nagai, Hiroki; Oyama, Akira

doi:10.15406/fmrij.2017.01.00012

Cited by 13 publications

(9 citation statements)

References 10 publications

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“…Early designs such as the NASA High-flying Mini-Sniffer [4] and Canyon-Flyer ( 20 kg ) [5] looked at airplane designs that would perform a single exploration mission after deploying mid-air from the entry capsule. The Mini-Sniffer and more recent concepts such as the NASA ARES ( 127 kg ) [6] and a Japanese mars airplane ( 3.5 kg ) [7] have been tested in Earth upper atmosphere but none have been deployed on Mars. For repeated near-surface exploration, as required for the VaMEx mission, rotorcraft have become a focus of research since landing on the rough Martian terrain requires vertical take-off and landing (VTOL) capabilities.…”

Section: Abbreviationsmentioning

confidence: 99%

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Evaluation of aerial vehicle configurations for high-range Mars missions

et al. 2023

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As part of an envisioned autonomous swarm exploration mission in Valles Marineris on Mars a design investigation of a high-range scout UAV is performed in this work. Two VTOL configurations, a coaxial helicopter and a transition tailsitter, are examined to assess their suitability. A preliminary design framework using Python and the optimization framework OpenMDAO is created using the preliminary design software NDARC. To model the rotor performance, comprehensive analysis simulations are executed using CAMRAD II. Structural 2D-FEM beam models are created for the rotor blades and the wing for weight modeling. Design sizings are executed for operation in the extremely thin atmosphere and the mission performance for a scouting mission as part of the robotic Valles Marineris Explorer (VaMEx) swarm is examined. A behavioral model is created to evaluate the controllability of the configurations. The results for a mission with a cruise flight of 30 km and 1.4 kg of payload show that for such a mission the transition configuration does not offer advantages over a more conventional coaxial helicopter design. To understand design sensitivities and to evaluate the respective effects on vehicle performance parameter sweeps are conducted.

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Section: Abbreviationsmentioning

confidence: 99%

“…non-constant mean section drag coefficient c d,mean (7) including surrogate models for flow detachment, Mach, and Reynolds number effects [21]. F P considers effects of varying relative flow conditions at the blade elements.…”

Section: Ndarcmentioning

confidence: 99%

Evaluation of aerial vehicle configurations for high-range Mars missions

et al. 2023

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“…A few different concepts have been investigated, for example, the NASA project (Guynn et al , 2003) for ARES mission, a solar aircraft (Noth et al , 2004) and rotorcraft (Young et al , 2005). Moreover, the study on Martian aircraft aerodynamic (Anyoji et al , 2017; Naoya Fujioka et al , 2014) is also conducted. All listed aircraft concepts are assuming designing the aircraft in classic configuration.…”

Section: Introductionmentioning

confidence: 99%

Conceptual design of an aircraft for Mars mission

Kwiek

2019

AEAT

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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.

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“…In this research, the aerodynamic deformation of the airplane for a high-altitude flight test named "Mars Airplane Balloon Experiment-1 (MABE-1)" [5] [6] [7] was directly measured in a large wind tunnel using a video grammetry technique. Then, the effects of the deformation on the aerodynamic performance were estimated using the wing element theory to evaluate the impact on the entire aerodynamic performance.…”

Section: Introductionmentioning

confidence: 99%

Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

Fujita¹,

Oyama²,

Kubo³

et al. 2019

JFCMV

Self Cite

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This paper reports the results of the aerodynamic deformation measurements of the meter-scale, entire shape, actual UAV in the wind tunnel using a video grammetry technique. The measured airplane was the airplane for Mars exploration being developed by Japan Aerospace Exploration Agency (JAXA) and Japanese universities. Its main wing span length was 2.4 m. The video grammetry measurement was performed using VICON's system. Retroactive markers and stickers were put on the airplane. JAXA's 6.5 m × 5.5 m Low-Speed Wind Tunnel was used. The airplane was mounted on the strut support with pitch-free or pitch-locked conditions. The deformations of the main wing bending, the main wing twisting, the tail boom bending, and the elevator deflection angle change were revealed quantitatively. The bending stiffness of a main wing spar that was designed as a safety factor of 2.8 at load factor of 5 was sufficient. The main wing spar was located around a center of pressure of an airfoil and it showed enough stiffness for twisting at nominal condition. The effects of the main wing bending and twisting, and the tail boom bending on the aerodynamic performance were estimated but they were in an acceptable range from the standpoint of the controllability of the aerodynamic performance using control surfaces. Even though the servo motor was located near the elevator and the linkage between the servo motor and the elevator was short, the measured elevator deflection angle was at most 4% smaller than the angle at no-wind condition. The obtained results and presented method are useful for control, flight data analysis, and design of lightweight airplanes.

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Evaluation of Aerodynamic Performance of Mars Airplane in Scientific Balloon Experiment

Cited by 13 publications

References 10 publications

Evaluation of aerial vehicle configurations for high-range Mars missions

Evaluation of aerial vehicle configurations for high-range Mars missions

Conceptual design of an aircraft for Mars mission

Wind Tunnel Test for Videogrammetric Deformation Measurement of UAV for Mars Airplane Balloon Experiment-1 (MABE-1)

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