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The formula ∂Lᵣ/∂r∣ᵣ₌₁/₂ = 2T in Hata and Yamaguti [1], where Lr is Salem’s singular function and T is the Takagi function, was generalized to the formula ∂ᵏLᵣ/∂rᵏ = k!Tᵣ,ₖ in Sekiguchi and Shiota [17] by using the measure theoretic method, where Tᵣ,ₖ is the k-th order Takagi function. In this paper we reconsider these functions fromthe viewpoint of de Rham’s functional equation, and by investigating such functional equation on a directed network we expand the above formula without the measure theoretic method.

形態: 図版あり, Physical characteristics: Original contains illustrations, Accepted: 2016-12-26, 資料番号: PA1710085000

In this paper, we first give an explicit formula of the exponential sum of sum of digits with complex coefficients. As an application of this formula, we obtain a simple expression of Newman-Coquet summation formula related to the number of binary digits in a multiple of three.

JAXA has been developing Next Generation Star Tracker (STT). STT is the attitude sensor, which consists of hood, lenses, CCD, and some electric circuits. In acquisition mode, images of stars detected by CCD are compared with a star catalogue to determine the absolute orientation of a spacecraft without a-priori attitude information. STT is more accurate attitude sensor than earth sensor plus sun sensor system. Advanced Land Observation Satellite (ALOS) mounts large size Star Tracker to fulfill its high attitude accuracy requirement. On the other hand, we have been developing an autonomous Star Tracker whose size, power and mass is smaller than ALOS/Star Tracker., 資料番号: AA0049054046, レポート番号: JAXA-SP-05-008

This is the report of a study of high performance maneuver for artificial satellite. Especially, CMG (Control Moment Gyro) aiming to agile reorientation maneuver is discussed in this report. The number and the arrangement of the CMG cluster were examined, for Rest-to-Rest maneuvering. The performance presumption parameter to the first design estimate was derived. The CMG assembly design for agile maneuver is determined by requirement of angular momentum and the moment of inertia of satellite. The result of the CMG assembly arrangement should be discussed from the point of electrical energy consumption, precise weight estimation and cost., 資料番号: AA0049054045, レポート番号: JAXA-SP-05-008

The objective of this research was to investigate the effects of beef extract on fat metabolism, muscle mass and muscle fiber types in rats. We also investigated the synergetic effect of endurance exercise. Twenty-four male rats weighing about 270 g were assigned to two diets containing 0 or 6% beef extract (BE). Half the rats fed each diet were subjected to compulsory exercise (CE) for 30 min every other day. After 4 weeks feeding, the blood was collected and various organs were dissected. The muscle fiber type of the soleus and extensor digitorum longus (EDL) muscles were evaluated by histochemical and electrophoretical analyses. Rats supplemented with BE showed a decrease in fat content in liver and abdomen and an increase in the activity of carnitine palmitoyl transferase II in liver. BE as well as exercise increased the relative weights of both soleus and EDL. BE alone and BE plus CE did not affect the distribution of muscle fiber types in soleus. BE without exercise decreased in type IIb of EDL from 54% to 44% with compensatory increase in type IIa from 41% to 49% and type I from 5% to 7% compared with the nonsupplemented, nonexercised control group. No synergetic effect on a fast to slow fiber conversion due to the combination of BE and CE was detected. Thus, BE supplement increased muscle mass and slow type fiber in EDL. The effects of BE supplement on muscle characteristics were similar to those of exercise. beef extract, fat metabolism, muscle fiber type, muscle mass, L-carnitine

科学衛星は、他の衛星と同様に、ミッションを達成するためにその姿勢を所望の方向へ制御する必要がある。最近の科学衛星においては、ミッションの高度化に伴い、姿勢制御系に対する要求も高まっている。本稿では、ミッション側からの要求をまとめ、それに対するJAXAとしての取り組みを紹介する。また、2004年度に再編された科学衛星専門研究委員会姿勢班の活動、および総合技術研究本部との協力体制について紹介する。, 資料番号: AA0049122100

編隊飛行する太陽発電衛星システム(FF-SSPS)は、静止軌道上にあって地球指向する発送電部と、太陽輻射圧を揚力として利用して赤道面から一定の距離に保たれつつ太陽指向する反射鏡によって構成される。本稿では、まず、円軌道近傍におけるHill方程式で表される系に対してLQRを適用し、反射鏡の発送電部に対する相対軌道制御則を導く。続いて、静止軌道上で想定される摂動源を組み込んだ軌道制御シミュレーションを実施し、制御則の有効性を検証する。, A space solar power satellite system using a formation-flying reflector (FF-SSPS) consists of the main body and two formation-flying reflectors. The main body is located on geostationary orbit. Two reflectors are located north and south of the main body. Their orbital planes are parallel to the main body's orbital plane. First set is the control law to maintain the relative position of the reflector for the main body, which is an applied linear quadratic regulator (LQR) for the system expressed in Hill's equation around a circular orbit. Then the efficiency of the control law is confirmed using an orbit control simulation that incorporates the perturbations that are assumed on geostationary orbit., 資料番号: AA0047897011

Control technology of the Large Space Structure (LSS) is supposed to be one of the key technology in the future space activity, however, there are many problems which have not been solved. This research aims to solve such problems and to establish the basic technology of the LSS. In this research, Space Solar Power System (SSPS) is focused on as the very Large Space Structure, and the assembly and maintenance technique is studied. In this report, the result of this study in the FY2003 activity is described., 資料番号: AA0048129011, レポート番号: JAXA-RM-04-011

JAXA has been developing Next Generation Star Tracker. Star Tracker (STT) is an attitude sensor, which consists of hood, lenses, CCD, and some electric circuits. In acquisition mode, images of the stars detected by CCD are compared with a star catalogue to determine its absolute orientation of a spacecraft without a-priori attitude information. STT can be more accurate attitude sensor than earth sensor plus sun sensor system. Advanced Land Observation Satellite (ALOS) mounts STT of large size to fulfill its high attitude accuracy requirement. On the other hand, an autonomous STT has been developed whose size, power and mass is smaller than ALOS/STT. It is named Next Generation Star Tracker., 資料番号: AA0048057011, レポート番号: JAXA-RM-04-010

Results of research on large-scale, flexible space structures are reported. In this study, it is aimed to develop a lightweight inflatable structure by applying the thermoplastic composite. An inflatable tube is manufactured using a newly developed bundle of the thermoplastic composite. Through some experiments, the feasibility of its stowing, development, and rigidization are demonstrated. An innovative control system is also developed for the structural control of large and flexible structures. To accommodate the structural vibration of a very long period, the control system uses the fiber Bragg grating to measure the strain of the structure, and the piezo actuators to cancel the structural deformation. Architectures of distributed control systems are also discussed. Through experiments, the effectiveness of the control system is clearly demonstrated. Because these are promising fundamental technologies for the future spacecraft, it is important to continue the research and development and to have opportunities of space demonstration in the near future., 資料番号: AA0048129009, レポート番号: JAXA-RM-04-011