Proceedings of the Vertical Flight Society 78th Annual Forum
Pit craters on Mars are assumed to be used as manned exploration bases and it is highly possible ... more Pit craters on Mars are assumed to be used as manned exploration bases and it is highly possible that life signature would be discovered there since its temperature is appropriate and it is less affected by radiation. Regarding pit crater exploration, helicopter which can climb and descend quickly is expected to be utilized. This paper introduces blade shape optimization of Mars helicopter exploring pit craters. Definition of a mission, selection of aircraft types, conceptual design, optimization of blade twist angle and airfoil, and rotor test are conducted. As a result, hexa-rotor which has robustness, resistance to gust, and fault tolerance is proposed. Moreover, it is confirmed that the mission can be accomplished, carrying instruments on the helicopter within payload weight. Hovering performance of the helicopter is improved by optimizing blade twisting angle and airfoil. And it is found that there is a good correlation between experiment and numerical simulation with respect t...
Design information in practical engineering problems is briefly classified into two groups: globa... more Design information in practical engineering problems is briefly classified into two groups: global and local design information. Global design information is easy to physically construct but mostly trivial. In contrast, local design information is difficult to physically interpret because of mechanical acquisition but potentially worth for innovative design. This research deals with a recent data mining be named Correlation-based Information Hierarchical Structuring Method; we apply it to a practical engineering problem to physically construct local design information. As a result, our approach has successfully functioned as intuitive visual mining to generate latent hierarchical structure of the design space. Moreover, local design information regarding sweet spots was consequently revealed although the former mining techniques did not obtain them; physical construction could be also implemented by handling it.
The demand for the economic and dedicated space launchers for vast amount of lightweight, so-call... more The demand for the economic and dedicated space launchers for vast amount of lightweight, so-called nano-/microsatellites, is now growing rapidly. There is a strong rationale for the usage of the hybrid propulsion for economic space launch as suggested by the assessment conducted here. A typical concept of development of such an economic three-stage launcher, in which clustering unit hybrid rocket engines are employed, is described with a development scenario. Thanks to the benefits of hybrid rocket propulsion, assuring and safe, economic launcher dedicated to lightweight satellites can be developed with a reasonable amount of quality assurance and quality control actions being taken in all aspects of development such as raw material, production, transportation, storage, and operation. By applying a multi-objective optimization technique for such a launch system, examples of possible launch systems are obtained for a typical mission scenario for the launch of lightweight satellites. Furthermore, some important technologies that contribute strongly to economic space launch by hybrid propulsion are described. They are the behavior of fuel regression rate, the swirling-oxidizer-flow-type hybrid rocket, the liquid oxygen vaporization, the multi-section swirl injection, the low-temperature melting point thermoplastic fuel, the thrust and O/F simultaneous control by altering-intensity swirl-oxidizer-flow-type (A-SOFT) hybrid, the numerical simulations of the internal ballistics, and so on.
A time-series flight trajectory technique was developed for use in a civil aircraft during descen... more A time-series flight trajectory technique was developed for use in a civil aircraft during descent. The three-degree-of-freedom (3-DoF) equations of motion were solved via time-series prediction of aerodynamic forces. In the present evaluation, the microburst effect during the descent was considered. The single-objective optimization problem, in which the cost function indicating the trajectory efficiency was minimized, was solved by means of a Kriging model based genetic algorithm (GA) which produces an efficient global optimization process. The optimal trajectory results were compared with those without the microburst condition during the descent. The minimization solution converged well in each case for both conditions plus the differences in flight profiles based on the trajectory history were smaller than those of the solutions before optimization. An analysis of variance and parallel coordinate plot were applied to acquire the quantitative information for the initial condition...
2021 18th International Conference on Electrical Engineering/Electronics, Computer, Telecommunications and Information Technology (ECTI-CON)
In the aircraft design methodology, there are many methods to measuring the UAVs performance, suc... more In the aircraft design methodology, there are many methods to measuring the UAVs performance, such as, the minimize drag, the lift required or the take-off/landing performance etc. The multi-objective optimization is one of the popular method for UAVs design problem. In addition, in the UAVs design problem is required for high computational cost such as computation of fluid dynamics. The solution to the said problem could be reached through the method of the Efficient Global Optimization algorithm (or abbreviated, the EGO). However, the EGO was, in the first instant, intended for very limited use; namely, it was utilized as a solution for a single-objective optimization problem with just one additional sampling. Then, the EGO method must be required for long computational time for single-additional sampling procedure. The objective of this particular research was to study the EGO with multi-objective multi-additional sampling as a solution to the UAVs airfoil design problem. The Expected Hypervolume Improvement (EHVI) is applied with the EGO process with an intention to find a solution to the multi-objective optimization problem. Furthermore, there was a proposal to use multiple additional sampling methods in the efficiency improvement of the additional sampling process in EGO, and at the same time, keeping the performance of exploration based on EHVI maximization at the same constant There are two main goals in the application of this algorithm to UAVs airfoil design optimization, which include minimizing aerodynamic drag and maximizing UAVs airfoil thickness at the trailing edge. The Reynolds-averaged Navier-Stokes simulation is applied for aerodynamic evaluation. By adopting the airfoil design, the results were the reduction in the aerodynamic drag, as well as 5% improvement of the thickness of the airfoil at the trailing edge when compared with the airfoil initial design.
Proceedings of the Vertical Flight Society 78th Annual Forum
Pit craters on Mars are assumed to be used as manned exploration bases and it is highly possible ... more Pit craters on Mars are assumed to be used as manned exploration bases and it is highly possible that life signature would be discovered there since its temperature is appropriate and it is less affected by radiation. Regarding pit crater exploration, helicopter which can climb and descend quickly is expected to be utilized. This paper introduces blade shape optimization of Mars helicopter exploring pit craters. Definition of a mission, selection of aircraft types, conceptual design, optimization of blade twist angle and airfoil, and rotor test are conducted. As a result, hexa-rotor which has robustness, resistance to gust, and fault tolerance is proposed. Moreover, it is confirmed that the mission can be accomplished, carrying instruments on the helicopter within payload weight. Hovering performance of the helicopter is improved by optimizing blade twisting angle and airfoil. And it is found that there is a good correlation between experiment and numerical simulation with respect t...
Design information in practical engineering problems is briefly classified into two groups: globa... more Design information in practical engineering problems is briefly classified into two groups: global and local design information. Global design information is easy to physically construct but mostly trivial. In contrast, local design information is difficult to physically interpret because of mechanical acquisition but potentially worth for innovative design. This research deals with a recent data mining be named Correlation-based Information Hierarchical Structuring Method; we apply it to a practical engineering problem to physically construct local design information. As a result, our approach has successfully functioned as intuitive visual mining to generate latent hierarchical structure of the design space. Moreover, local design information regarding sweet spots was consequently revealed although the former mining techniques did not obtain them; physical construction could be also implemented by handling it.
The demand for the economic and dedicated space launchers for vast amount of lightweight, so-call... more The demand for the economic and dedicated space launchers for vast amount of lightweight, so-called nano-/microsatellites, is now growing rapidly. There is a strong rationale for the usage of the hybrid propulsion for economic space launch as suggested by the assessment conducted here. A typical concept of development of such an economic three-stage launcher, in which clustering unit hybrid rocket engines are employed, is described with a development scenario. Thanks to the benefits of hybrid rocket propulsion, assuring and safe, economic launcher dedicated to lightweight satellites can be developed with a reasonable amount of quality assurance and quality control actions being taken in all aspects of development such as raw material, production, transportation, storage, and operation. By applying a multi-objective optimization technique for such a launch system, examples of possible launch systems are obtained for a typical mission scenario for the launch of lightweight satellites. Furthermore, some important technologies that contribute strongly to economic space launch by hybrid propulsion are described. They are the behavior of fuel regression rate, the swirling-oxidizer-flow-type hybrid rocket, the liquid oxygen vaporization, the multi-section swirl injection, the low-temperature melting point thermoplastic fuel, the thrust and O/F simultaneous control by altering-intensity swirl-oxidizer-flow-type (A-SOFT) hybrid, the numerical simulations of the internal ballistics, and so on.
A time-series flight trajectory technique was developed for use in a civil aircraft during descen... more A time-series flight trajectory technique was developed for use in a civil aircraft during descent. The three-degree-of-freedom (3-DoF) equations of motion were solved via time-series prediction of aerodynamic forces. In the present evaluation, the microburst effect during the descent was considered. The single-objective optimization problem, in which the cost function indicating the trajectory efficiency was minimized, was solved by means of a Kriging model based genetic algorithm (GA) which produces an efficient global optimization process. The optimal trajectory results were compared with those without the microburst condition during the descent. The minimization solution converged well in each case for both conditions plus the differences in flight profiles based on the trajectory history were smaller than those of the solutions before optimization. An analysis of variance and parallel coordinate plot were applied to acquire the quantitative information for the initial condition...
2021 18th International Conference on Electrical Engineering/Electronics, Computer, Telecommunications and Information Technology (ECTI-CON)
In the aircraft design methodology, there are many methods to measuring the UAVs performance, suc... more In the aircraft design methodology, there are many methods to measuring the UAVs performance, such as, the minimize drag, the lift required or the take-off/landing performance etc. The multi-objective optimization is one of the popular method for UAVs design problem. In addition, in the UAVs design problem is required for high computational cost such as computation of fluid dynamics. The solution to the said problem could be reached through the method of the Efficient Global Optimization algorithm (or abbreviated, the EGO). However, the EGO was, in the first instant, intended for very limited use; namely, it was utilized as a solution for a single-objective optimization problem with just one additional sampling. Then, the EGO method must be required for long computational time for single-additional sampling procedure. The objective of this particular research was to study the EGO with multi-objective multi-additional sampling as a solution to the UAVs airfoil design problem. The Expected Hypervolume Improvement (EHVI) is applied with the EGO process with an intention to find a solution to the multi-objective optimization problem. Furthermore, there was a proposal to use multiple additional sampling methods in the efficiency improvement of the additional sampling process in EGO, and at the same time, keeping the performance of exploration based on EHVI maximization at the same constant There are two main goals in the application of this algorithm to UAVs airfoil design optimization, which include minimizing aerodynamic drag and maximizing UAVs airfoil thickness at the trailing edge. The Reynolds-averaged Navier-Stokes simulation is applied for aerodynamic evaluation. By adopting the airfoil design, the results were the reduction in the aerodynamic drag, as well as 5% improvement of the thickness of the airfoil at the trailing edge when compared with the airfoil initial design.
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Papers by Masahiro Kanazaki