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Background. The defining trends of technical progress are the development of information technologies and revolutionary approaches to the practical use of space. In aviation, there are breakthroughs in the creation of a variety of technical implementations of aviation equipment and its application. Increasingly close interaction between aviation and space systems at the level of service provision, joint problem solving. The transition to large aerospace systems connected into a single entity on the basis of information technologies and having the function of supplying information technologies is not far away. The training of specialists in the creation and operation of aerospace systems is becoming an increasingly urgent task and should be several steps ahead of the latest achievements in this direction. Objective: conceptual developments regarding the creation of an aerospace system and educational programs for training specialists in solving the problems of managing its aircraft and their target equipment, this system management, application and production of information technologies in the system. Methods. Results. On the basis of the analysis of the development of tasks and technologies in the field of space and aviation technology and the prospects of their combination, the concept of a single aerospace system is proposed with an emphasis on the complex of issues of managing such a system, on information technologies in this system. In the context of the creation, development and operation of the aerospace system, the features and common features of three types of educational programs are highlighted, grouped by preparation for the corresponding groups of tasks: management in space systems; management in aviation systems; provision of the aerospace system with information technologies and (or) providing information technology by the system. The content of the educational material within the framework of the mentioned educational programs is generally considered. Conclusions. The materials of the article are aimed at improving the mentioned educational programs., Проблематика. Визначальні тренди технічного прогресу ˗ розвиток інформаційних технології і революційні підходи до практичного застосування космосу. В авіації є проривні здобутки у створенні різноманіття технічних реалізації авіаційної техніки і її застосуванні. Все більш тісна взаємодія між авіаційними і космічними системами на рівні надання послуг, спільного вирішення задач. Недалеко перехід до великих авіакосмічних систем, зв’язаних в єдине ціле на основі інформаційних технологій і маючих функції постачання інформаційних технологій. Підготовка фахівців зі створення та експлуатації авіакосмічних систем стає все більш актуальною задачею та має на декілька кроків передувати новітнім здобуткам у цьому напрямку. Мета дослідження: концептуальні розробки щодо створення авіакосмічної системи і освітніх програм підготовки фахівців з вирішення задач управління її літальними апаратами і їх цільовою апаратурою, управління цією системою, застосування і продукування інформаційних технологій в системі. Методика реалізації та результати досліджень. На основі аналізу розвитку задач і технологій в галузі космічної і авіаційної техніки та перспектив їх поєднання запропонована концепції єдиної авіакосмічної системи з акцентом на комплексі питань управління такою системою, на інформаційні технології в цій системі. У контексті створення, розвитку і експлуатації авіакосмічної системи виділені особливості і спільне для трьох видів освітніх програм, згрупованих за підготовкою до відповідних груп задач: управління в космічних системах; управління в авіаційних системах; забезпечення авіакосмічної системи інформаційними технологіями та (або) постачання системою інформаційних технологій. Узагальнено розглянутий зміст навчального матеріалу рамках названих освітніх програм. Висновки. Матеріали статті спрямовані на роботу щодо вдосконалення названих навчальний програм.&nbsp

The exploration and trade-off analysis of different aerodynamic design configurations requires solving optimization problems. The major bottleneck to assess the optimal design is the large number of time-consuming evaluations of high-fidelity computational fluid dynamics (CFD) models, necessary to capture the non-linear phenomena and discontinuities that occur at higher Mach number regimes. To address this limitation, we introduce an original non-myopic multifidelity Bayesian framework aimed at including expensive high-fidelity CFD simulations for the optimization of the aerodynamic design. Our scheme proposes a novel two-step lookahead policy to maximize the improvement of the solution quality considering the rewards of future steps, and combines it with utility functions informed by the fluid dynamic regime and the information extracted from data, to wisely select the aerodynamic model to interrogate. We validate the proposed framework for the case of a constrained drag coefficient optimization problem of a NACA 0012 airfoil, and compare the results to other popular multifidelity and single-fidelity optimization frameworks. The results suggest that our strategy outperforms the other approaches, allowing to significantly reduce the drag coefficient through a principled selection of limited evaluations of the high-fidelity CFD model.

Prognostics and health management aim to predict the remaining useful life (RUL) of a system and to allow a timely planning of replacement of components, limiting the need for corrective maintenanc...

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Purpose: The purpose of this article is to present the algorithm for calculating the path of two-stage hypersonic unmanned aerial vehicle consisting of unmanned carrier aircraft and unmanned orbital aircraft. Methods: The article describes a method of theory of discontinuous dynamical systems optimal control used to optimize the branching trajectory of a two-stage hypersonic unmanned aerial vehicle. Results: The optimal values of phase coordinates and controls at points of structural transformations of the branching path of a two-stage hypersonic unmanned aerial vehicle are calculated. Discussion: The proposed algorithm allows to optimize the path of two-stage hypersonic unmanned aerial vehicle in any section of the path, including the phase of separation and initial disengagement of orbital stage from air launch aircraft, taking into account the mutual influence of stages.

In the aerospace industry contactless measurement has been a very versatile and adaptable in recent years, mainly because of its diverse applications. Usually ultrasonic measurement requires acoustic contact media which may disserve the sample and varies for different materials. In the operational hand, acoustic contact media like water is also not preferred for on-aircraft inspection. The air coupled inspection technique among other nondestructive testing techniques is often not enticing due to acoustic mismatch and wave propagation. Though, acoustical mismatch of the transducers can be reduced by application of a matching layer and also by using different corresponding transducers. Air-coupled transducers are the captivating alternatives for the inspection. This paper comprises different air coupled inspection techniques i.e. through transmission and guided wave generation as well as its working modes. Various transducer arrangements, the advantages of air-coupled ultrasonic guided wave inspection over other NDT techniques and their specifications are discussed revolving around the materials. Composite materials have superior properties like tensile strength, better heat resistance which cannot be materialized in single. The utilization of composite materials like CFRP, GFRP, other polymers and ceramic composites seeks the improvement in lift to weight ratio. An overall review deals with air coupled techniques and scrutiny of different materials concerning this technique, which includes characteristics of various composite materials used in aerospace industry.

The work objective is the synthesis of simple analytical formula of the optimal roll angle of hypersonic gliding vehicles for conditions of quasi-horizontal motion, allowing its practical implementation in onboard control algorithms.The introduction justifies relevance, formulates basic control tasks, and describes a history of scientific research and achievements in the field concerned. The author reveals a common disadvantage of the other authors’ methods, i.e. the problem of practical implementation in onboard control algorithms.The similar tasks of hypersonic maneuvers are systemized according to the type of maneuver, control parameters and limitations.In the statement of the problem the glider launched horizontally with a suborbital speed glides passive in the static Atmosphere on a spherical surface of constant radius in the Central field of gravitation.The work specifies a system of equations of motion in the inertial spherical coordinate system, sets the limits on the roll angle and optimization criteria at the end of the flight: high speed or azimuth and the minimum distances to the specified geocentric points.The solution.1) A system of equations of motion is transformed by replacing the time argument with another independent argument – the normal equilibrium overload. The Hamiltonian and the equations of mated parameters are obtained using the Pontryagin’s maximum principle. The number of equations of motion and mated vector is reduced.2) The mated parameters were expressed by formulas using current movement parameters. The formulas are proved through differentiation and substitution in the equations of motion.3) The Formula of optimal roll-position control by condition of maximum is obtained. After substitution of mated parameters, the insertion of constants, and trigonometric transformations the Formula of the optimal roll angle is obtained as functions of the current parameters of motion.The roll angle is expressed as the ratio of the sine of the latitude by the cosine of the suborbital inclination with correction for the speed.The spherical diagram shows the geometric illustration of the trajectory and control parameters. In conclusion the paper shows the essence and the solution novelty, describes the flight model, which allowed us to conduct numerical tests of the Formula. Besides, it concludes that the formula is valid and can be used in practical implementation in on-Board algorithms to control the hypersonic gliding vehicles.

Autonomy in space systems is a promising way not only to expand performance and functions of systems but also to achieve cost reduction, particularly in large and complicated systems and constellations. Now a day, a number of constellation systems are proposed or under development which provide advanced services in earth observations, tele-communication and satellite based navigations. This spacecraft autonomy research area was newly organized in 2002, and two target missions, constellation for Earth observation and rendezvous spacecraft such as HTV were defined. It was started to study on three themes related with the target missions, autonomous orbit maneuvering function, intelligent vision and AI based ground support systems for rendezvous operations from fiscal year 2003. Major results of these studies are reported., 資料番号: AA0048129013, レポート番号: JAXA-RM-04-011

The fuel cell, which has a high energy-conversion efficiency, a high power-density and a pollution free characteristics, is anticipated to be one of the future main energy sources for terrestrial, mobile and automotive applications. These characteristics are very attractive for several power plants, so a lot of governments and manufactures invest their fund to the R&D activities of the fuel cell technology. This advanced technology is also expected to be applied to the future space and aerospace systems including the launch vehicle, the space station, the lunar base etc., because of its higher performance. This paper introduces the fuel cell power system concept for the planetary probe application. The electric power sources for the space systems are usually defined based on the power and operation term requirements. The fuel cell power plant was utilized in Gemini and Apollo program, and one of the highly reliable fuel cell power plant is operated in the Space Shuttle Orbiter because of its higher performance characteristics compared with the chemical batteries. And in case of a long life operation for several months or years, the photovoltaics or the RTG is selected as the power sources. Especially for the planetary probe the light weight and long term operable electric power system is essential to the mission feasibility. The RTG power plant cannot be utilized in the planetary probes of this country, so the alternatives are being required. The integrated propulsion and power system concept is considered as one of the solution for this issue. The common fuel and oxidizer selection, with propulsion makes the fuel cell power plant simplicity and is estimated to bring a dramatic electric power system weight reduction. Additionally this concept has a benefit that the residual propellant for the propulsion can be used effectively for the planetary mission., 資料番号: AA0045915001

宇宙エネルギーシンポジウム 宇宙科学研究所 20030312 神奈川 日本, ISAS Space Energy Symposium Institute of Space and Astronautical Science 20030312 Kanagawa Japan, 資料番号: AA0045915000