I found a webpage that provides more detailed info. Highlights: http://god.tksc.nasda.go.jp/lr/top.html 50-centimeter diameter, 86-kilogram (smaller than EGP/Ajisai) GTO -- 36198 km apogee, 251 km perigee, 28.5 deg inclination 24 "metal mirror plate(s)", 126 "laser retroreflector(s)" Mirrors: 85% albedo, Aluminum (20) - 10.5 x 9.4 x 1.0 cm / 5.3 kg (4) - 8.4 x 5.6 x 1.0 cm / 0.5 kg (quite a mass difference) Launch date 2001 August 25 Lifetime "over a month" Epoch 2001/8/25 04:39:35.00UT (Launch Window : 04:00-09:00) Semi-Major Axis 24597.741880764 km Eccentricity 0.730481992 Inclination 28.491633373 deg Argument of Perigee 179.065695554 deg Right Ascension of Ascending Node 69.870582954 deg Mean Anomaly 7.117897857 deg Cross Sectional Area 0.173 m2 Satellite Drag Coefficient : 2.5 Solar refrectivity coefficient : 1.5 Mission Objective: To evaluate the Initial trajectory determination of JAPANESE Rocket H2A using SLR. SLR Mission Objectives: - To evaluate the Initial trajectory determination of JAPANESE Rocket H2A accuarately. - Verification of the SLR station performance. We use this as target for wide dynamic range of transmitting/receiving test up to geosynchronous orbit for optical communication and SLR. - Air drug [sic] model could be modified using SLR data. This page appears to have a rough mission timeline: http://god.tksc.nasda.go.jp/lr/method.html -- Sean Sullivan ----------------------------------------------------------------- Unsubscribe from SeeSat-L by sending a message with 'unsubscribe' in the SUBJECT to SeeSat-L-request@lists.satellite.eu.org http://www2.satellite.eu.org/seesat/seesatindex.html
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