公开(公告)号：JPH01258142A

公开(公告)日：1989-10-16

申请号：JP8666088

申请日：1988-04-08

Applicant: NAT SPACE DEV AGENCY ,  TOSHIBA CORP

Inventor： ICHIKAWA SHINICHIRO ,  ITSUKAICHI ATSUSHI

IPC: G06F11/30

Abstract: PURPOSE:To detect an error even when the same error is generated in central processing units operated in parallel by checking the program execution step of the central processing unit by history check, and prohibiting the execution of the next processing step when the error not passing a prescribed step is generated. CONSTITUTION:The output signal of a sensor part 100 is supplied to a posture control operation part 101. The posture control operation part 101 is provided with a function to discriminate whether an arithmetic step passes the prescribed step, that is, history identification, history data update, the history check, an abnormality processing, and the function by the loop of the history identification. In other words, in a case where a result by the addition or subtraction of a constant value on history data does not arrive at a prescribed value in the history check, it means that an arithmetic processing is not processed in a normal route, and it follows that the present arithmetic data for posture control is incorrect. In such a case, a start command is issued by an abnormality processing function, then, abnormality check is started. In such a way, an accident can be prevented from occurring.

公开(公告)号：JPH07223598A

公开(公告)日：1995-08-22

申请号：JP1622494

申请日：1994-02-10

Applicant: NAT SPACE DEV AGENCY ,  TOSHIBA CORP

Inventor： ICHIKAWA SHINICHIRO ,  SOGA HIROSHI

IPC: B64G1/24 ,  B64G1/36 ,  G05D1/08

Abstract: PURPOSE:To provide an external turbulence torque estimating device for an artificial satelite which can estimate the external turbulence torque applied to the artificial satelite and carry out the active attitude control. CONSTITUTION:An external turbulence torque estimating device is equipped with a profile registering means which approximation-represents the external turbulence torque applied to an artificial satelite which turns around the earth by the n-th order (n is a natural number) Fourier series, and registers the approximate Fourier series as a profile, wheel speed measuring means which measures the wheel speed which varies according to the attitude change of the artificial satelite at 2n+1 points on the orbit of the artificial satelite, and a parameter calculating means 14 which obtains the parameter of the Fourier series from the measurement values of the wheel speed at 2n+1 points which are obtained by the wheel speed measuring means. Further, an external turbulence torque estimating means 15 which inputs the parameter obtained by the parameter calculating means into the Fourier series, and estimates the external turbulence torque at an arbitrary position on the orbit, from the Fourier series into which the above-described parameter is inputted, is provided.

公开(公告)号：JPH01186497A

公开(公告)日：1989-07-25

申请号：JP842388

申请日：1988-01-20

Applicant: NAT SPACE DEV AGENCY

Inventor： SHIMODAIRA KATSUYUKI ,  ICHIKAWA SHINICHIRO ,  ODA MITSUSHIGE ,  WAKABAYASHI YASUSHI ,  NAKAMURA HIROYUKI

IPC: B64G1/44

Abstract: PURPOSE:To maintain the performance of the blade of a solar sail by rotatably supporting a pair of blade retainers in opposed state and easily fixing and supporting the blade of the solar sail by a simple mechanism. CONSTITUTION:Since a solar battery panel is in folded state when a satellite is launched up, a solar sail outer frame 1 installed onto an upper surface panel and an undersurface panel 8 are closely attached. Therefore, a blade retainer 6 rotatably installed onto the undersurface panel 8 by a supporting shaft 9 nips and fixes a blade 2 by a damper 7 installed onto a bent part 6a, since the basic plate part 6b is pressed by a solar sail outer frame 1 through a damper 11, and locked state is generated. Therefore, the blade 2 having a low rigidity is fixed by a blade retainer 6 through the damper 7, the blade 2 can sufficiently withstand the environment on launching.

公开(公告)号：JPS63212812A

公开(公告)日：1988-09-05

申请号：JP4522587

申请日：1987-03-02

Applicant: NAT SPACE DEV AGENCY

Inventor： WAKABAYASHI YASUSHI ,  NAKAMURA HIROYUKI ,  ICHIKAWA SHINICHIRO

IPC: G05D1/08 ,  B64G1/36 ,  G01C1/00 ,  G01C21/24 ,  G01S3/78 ,  G01S3/781

Abstract: PURPOSE:To enable the improvement of measuring precision without increasing the weight while maintaining reliability, by narrowing an opening angle of line-of-sight channels used for measurement and by using all informations of the line-of-sight channels in a plurality for measurement of the direction of a scanning axis. CONSTITUTION:An oscillation mechanism system 11 consists of a scan mechanism element and an angle encoder element, and it is constructed in such a manner that a plane mirror is rotated to oscillate by a non-sliding bearing for which two torsion bars are employed, for instance. An infrared photoelectric system 12 comprises a main optical system formed of Ge, for instance, an infrared optical element constituted by a filter, a pyroelectric infrared detector, etc., and it is so constructed as to detect the radiation from the earth through the intermediary of the mechanism system 11. An analog signal processing element 13 amplifies and shapes an output of the photoelectric system 12 and generates a horizon measuring pulse signal. A digital signal processing element 14 is so constructed as to generate an output of an attitude angle (pitch, roll) by using a pulse from the mechanism system 11 and a pulse signal from the processing element 13.

公开(公告)号：JPS62299499A

公开(公告)日：1987-12-26

申请号：JP14269686

申请日：1986-06-20

Applicant: NAT SPACE DEV AGENCY ,  TOSHIBA CORP

Inventor： ICHIKAWA SHINICHIRO ,  KISHIMOTO HITOSHI

IPC: B64G1/38 ,  B64G1/24 ,  G05D1/08

公开(公告)号：JPH0457208B2

公开(公告)日：1992-09-10

申请号：JP13930086

申请日：1986-06-17

Applicant: NAT SPACE DEV AGENCY

Inventor： SHIMODAIRA KATSUYUKI ,  ICHIKAWA SHINICHIRO ,  WAKABAYASHI YASUSHI ,  NAKAMURA HIROYUKI

IPC: B64G1/36 ,  G01C1/00 ,  G01J1/02 ,  G01S3/78 ,  G01S3/782

公开(公告)号：JPH01297399A

公开(公告)日：1989-11-30

申请号：JP12709288

申请日：1988-05-26

Applicant: NAT SPACE DEV AGENCY ,  TOSHIBA CORP

Inventor： ICHIKAWA SHINICHIRO ,  HO MASAYA

IPC: B64G1/36 ,  B64G1/24 ,  B64G1/38

Abstract: PURPOSE:To secure the high precision of the attitude precision by obtaining the attitude control signal by converting the attitude error of a satellite dynamics to the values on the coordinate system of a developed structure body such as solar battery paddle and converting said signal to the values on the coordinate system of the satellite dynamics and controlling the attitude of the satellite dynamics. CONSTITUTION:In the application to a satellite dynamics 12 in which a developed structure body 11 is arranged in rotatable ways around the pitch (Y) axis of the satellite body 10 of an artificial satellite, a roll detecting sensor 13 and a yaw detecting sensor 14 for detecting the roll attitude error around the roll (X) axis of the satellite dynamics 12 and the yaw attitude error around a yaw (Z) axis are installed. The output signals of the sensors 13 and 14 are inputted into the first coordinate conversion part 16, and converted to the values on the coordinate system of the developed structure body 1, and outputted into the Xp and Zp control calculation parts 17 and 18. The roll and yaw control signals in the coordinate system are obtained and sent into the second coordinate conversion part 19, and converted to the values on the coordinate system of the satellite dynamics 12, and the drive control for an actuator 15 for attitude drive is carried out.

公开(公告)号：JPS63154500A

公开(公告)日：1988-06-27

申请号：JP30130886

申请日：1986-12-19

Applicant: NAT SPACE DEV AGENCY

Inventor： WAKABAYASHI YASUSHI ,  ICHIKAWA SHINICHIRO ,  ODA MITSUSHIGE ,  SHIMODAIRA KATSUYUKI

IPC: B64G1/24

公开(公告)号：JPH02291927A

公开(公告)日：1990-12-03

申请号：JP11211689

申请日：1989-05-02

Applicant: NAT SPACE DEV AGENCY

Inventor： FUKUDA MINORU ,  ICHIKAWA SHINICHIRO

IPC: G01J1/02 ,  G01J5/06 ,  G01S3/781

Abstract: PURPOSE:To make it possible to block only the passage of harmful electro-magnetic waves effectively without decreasing the transmittance for an incident light signal by providing a shield plate having an opening part whose size is smaller than the specified ratio of the wavelength of an electromagnetic wave whose transmission should be blocked. CONSTITUTION:A sensor has the following parts: a shield plate 3 which is arranged in an optical-sensor main body 1 and has an opening 4 whose size is about 1/2 or less of the wave length of an electromagnetic wave whose transmission should be blocked; and an optical system which condenses a light signal inputted from an opening part 4 of the sensor main body to the size of the opening of the shield plate 3 and passes the signal through the opening 4. An incident light signal 6 is condensed through an objective lens 2 and reaches a detecting and processing part 5 through the opening 4 of the shield plate 3 without attenuation. The electromagnetic wave which is intruded through the opening 4 of the sensor main body is drastically attenuated when the electromagnetic wave passes through the opening 4 of the shield plate which is set at the value that is about 1/2 or less of the wavelength of the electro magnetic wave. The reaching of the electromagnetic wave to the detecting and protecting part 5 in the sensor main body 1 is effectively blocked. Thus, interference on the detecting and processing part 5 is prevented.

公开(公告)号：JPH01186498A

公开(公告)日：1989-07-25

申请号：JP842288

申请日：1988-01-20

Applicant: NAT SPACE DEV AGENCY

Inventor： SHIMODAIRA KATSUYUKI ,  ICHIKAWA SHINICHIRO ,  WAKABAYASHI YASUSHI ,  NAKAMURA HIROYUKI

IPC: B64G1/44 ,  B64G1/24

Abstract: PURPOSE:To improve reliability by removing a movable part and a sliding part by generating a three-axis control torque by selectively changing the optical characteristics of the surface element divided in the vertical and horizontal directions for the center of gravity of a solar sail. CONSTITUTION:Two solar sails 1 and 2 arranged in the pitch axis YS direction are constituted of a plurality of divided surface elements 1-11-1-22 and 2-11-2-22 arranged in two rows. Each surface element is formed from the elec tric optical effect substance in which the optical characteristics such as transmissivity can be changed by applying a voltage onto a liquid crystal plate, light adjusting glass, etc. The optical characteristics are changed by applying a voltage only onto the surface elements 1-11 and 1-21 at the position separated by (y1) from the center G of gravity of the solar sail 1 in the reverse direction to the pitch axis YS, and when the mirror surface reflection rate and dispersion reflection rate are changed, a roll axis torque TXS is generated. Therefore, a three-axis torque is generated by selectively changing the optical characteristics of the divided surface element.