The aim of this study was to investigate the effect of Maitland mobilization and Kaltenborn-Evjenth mobilization on the SLR angle. Subjects randomly divided into Kaltenborn-Evjenth group(n=8) and Maitland group(n=7). The mean height, age, body weight was 176.00±5.10 cm, 22.75±1.83 years, 72.63±10.65 kg respectively in Kaltenborn-Evjenth group. The mean height, age, body weight was 175.00±5.60 cm, 22.29 ±3.68 years, 78.00±12.36 kg respectively in Maitland group. Hip joint accessary movements with Grade Ⅲ or IV were applied depend on the patient’s condition to the restricted direction for 1 minute each set, and performed 5 set in a Maitland group. Hip joint anteroposterior gliding with Grade Ⅲ were applied 60 for 1 minutes each set, and performed 5 set in a Kaltenborn-Evjenth group. The angle of first pain was referred to as P1 and subjects were pointed out that they could not bend the knee anymore, then examiner measure SLR angle. The SLR was significantly increased in the Maitland group compared to the Kaltenborn- Evjenth group after intervention(p<.05). In a within group difference, SLR significantly increased in the both groups(p<.05). These results indicated that Maitland mobilization could be recommended the excellent technique to increase the hip flexion in patient with hip hypo-mobility.

In this study, we present the results of orbit determination (OD) using satellite laser ranging (SLR) data for the Science and Technology Satellite (STSAT)-2C by a short-arc analysis. For SLR data processing, the NASA/GSFC GEODYN II software with one year (2013/04 – 2014/04) of normal point observations is used. As there is only an extremely small quantity of SLR observations of STSAT-2C and they are sparsely distribution, the selection of the arc length and the estimation intervals for the atmospheric drag coefficients and the empirical acceleration parameters was made on an arc-to-arc basis. For orbit quality assessment, the post-fit residuals of each short-arc and orbit overlaps of arcs are investigated. The OD results show that the weighted root mean square post-fit residuals of short-arcs are less than 1 cm, and the average 1-day orbit overlaps are superior to 50/600/900 m for the radial/cross-track/along-track components. These results demonstrate that OD for STSAT-2C was successfully achieved with cm-level range precision. However its orbit quality did not reach the same level due to the availability of few and sparse measurement conditions. From a mission analysis viewpoint, obtaining the results of OD for STSAT-2C is significant for generating enhanced orbit predictions for more frequent tracking.

In this study, we present results of precise orbital geodetic parameter estimation using satellite laser ranging (SLR) observations for the International Laser Ranging Service (ILRS) associate analysis center (AAC). Using normal point observations of LAGEOS-1, LAGEOS-2, ETALON-1, and ETALON-2 in SLR consolidated laser ranging data format, the NASA/ GSFC GEODYN II and SOLVE software programs were utilized for precise orbit determination (POD) and finding solutions of a terrestrial reference frame (TRF) and Earth orientation parameters (EOPs). For POD, a weekly-based orbit determination strategy was employed to process SLR observations taken from 20 weeks in 2013. For solutions of TRF and EOPs, loosely constrained scheme was used to integrate POD results of four geodetic SLR satellites. The coordinates of 11 ILRS core sites were determined and daily polar motion and polar motion rates were estimated. The root mean square (RMS) value of post-fit residuals was used for orbit quality assessment, and both the stability of TRF and the precision of EOPs by external comparison were analyzed for verification of our solutions. Results of post-fit residuals show that the RMS of the orbits of LAGEOS-1 and LAGEOS-2 are 1.20 and 1.12 cm, and those of ETALON-1 and ETALON-2 are 1.02 and 1.11 cm, respectively. The stability analysis of TRF shows that the mean value of 3D stability of the coordinates of 11 ILRS core sites is 7.0 mm. An external comparison, with respect to International Earth rotation and Reference systems Service (IERS) 08 C04 results, shows that standard deviations of polar motion XP and YP are 0.754 milliarcseconds (mas) and 0.576 mas, respectively. Our results of precise orbital and geodetic parameter estimation are reasonable and help advance research at ILRS AAC.