Nec Toshiba Space Systems, Ltd.

Nichias Corporation

Japan Aerospace Exploration Agency

Astroscale Japan Inc.

Ken Maeda

Toshio Kamiya

Yuki Seto

Yoshihiko Goto

Yasuo Ito

Akifumi Sakamoto

Keita Ogo

Tatsuaki Hashimoto

Shinichiro Sakai

Simplify, downsize and reduce power of devices which comprise the satellite navigation system used in approach and docking in space. The navigation systemwhich estimates an attitude of a target object T in space comprises: an optical markerthat is attached to the target T and reflects light; a lighting devicethat irradiates the target object T with light of a predetermined wavelength band; an image acquisition devicethat acquires an image of the optical markerwhich has reflected the light of the predetermined wavelength band; and an image processing devicethat processes the image acquired by the image acquisition deviceand thereby estimates the attitude of the target object T. The lighting deviceand the image processing deviceare loaded on an aerospace vehicle

Navigation system, aerospace vehicle and optical marker

A thermal insulator with both excellent heat insulation and strength and a method of manufacturing the thermal insulator are provided. A thermal insulator according to the present invention includes metal oxide fine particles with an average particle diameter equal to or smaller than 50 nm and a reinforcing fiber, wherein the thermal insulator has a bridge structure between the metal oxide fine particles which is formed by elution of part of the metal oxide fine particles. A method of manufacturing a thermal insulator according to the present invention includes a curing step of curing a dry pressed compact including metal oxide fine particles with an average particle diameter equal to or smaller than 50 nm and a reinforcing fiber under a pressurized vapor saturated atmosphere at a temperature equal to or higher than 100&#xb0; C. for four hours and a drying step of drying the cured dry pressed compact.

Thermal insulator and method of manufacturing the same

In order to control an attitude of a movable object having a flexible member () through an attitude maneuver, first, based on vibration of the flexible member at the time of the attitude maneuver, for example, a sampling function including no frequency components equal to or higher than a particular frequency is obtained. With the use of the sampling function, a control target value is created as a previously-frequency-shaping-type feedforward control law. Based on the control target value, attitude control data is created. The attitude control data can be used for the attitude maneuver with respect to the movable object.

Attitude control data creating method, and attitude control system applying the method

Disclosed is an attitude change control system that is designed to efficiently output a torque for attitude change of a space craft using CMGs and realizes a real time CMG driving rule. A CMG gimbal steering lawgenerates target profiles for setting angle and angular velocity for each gimbal by applying an anisotropic weighted gradient method based upon the necessary torque calculated by a feed back controllerand a feed forward controllerfrom the angle and angular velocity in the target direction from the attitude navigatorand the current angle and angular velocity of the space craft estimated by the attitude estimatoras well as the current condition of each gimbal from the CMG, thereby controlling the CMGfor changing the attitude of the space craft dynamicsto the target direction.

Attitude change control method, attitude change control system, attitude change control program and program recording medium

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Tokyo, Japan

Ken Maeda