2007-051A
Chang'e is the Chinese moon goddess.
Chang'e-1 (chang'e yihao weixing) lunar probe. Based on its DFH-3 communication satellite, Chang'e-1 will be launched into geostationary transfer orbit by the Long March 3A rocket from the Xichang spaceport and then use its own engine to head out to the Moon and enter a 200 kilometer polar orbit around it. According to Chinese astronomer Renjiang Xie, the launch of Chang'e-1 is now set for April 2007, and a 50-meter deep space network antenna has been inaugurated in Beijing to support the mission. The probe will have a low-resolution imager, a gamma-ray spectrometer and microwave radiometer to study surface composition and temperature, and a laser altimeter to measure the height of topographical features. Although Chang'e-1 is just a test mission, the altimeter will be competitive with those flown on previous missions.
Leading the Chinese lunar program is Ouyang Ziyuan, seen here in front of the new Beijing deep space antenna.
Notes: the mass of Chang'e is about 2350 kg full 1000 kg empty; it is probably a box 2.2 x 1.7 x 2.0m in size with solar panel span 18m. It most likely uses the FY-25 engine with 490N thrust for course corrections and lunar orbit insertion.
- A stereo camera and integrated spectrometer with three CCDs. Its ground resolution will be a rather low 120 m (compare to about 1 meter for Lunar Orbiter and 13 m for Clementine) - A laser altimeter with 120 m accuracy - A gamma and X-ray spectrometer. This particular instrument will be mounted inside the body of the probe, which in my opininion could create some problem since measures will be contaminated by the presence of the spacecraft structure. Gamma-ray spectrometers are usually carried at the end of long booms for this reason. - A 4 band microwave radiometer to measure the temperature of the regolith and infer its depth. - Various deep space environment monitors (particle detectors etc.)
Control from BACC - Beijing Aerospace control center.
China's lunar probe, Chang'e-1, was deorbited at 0736 UTC on Mar 1 and impacted the lunar surface at 1.50S 52.36E at 0813 UTC. The impact site in Mare Fecunditatis is south-east of the crater Taruntius P and west of the Luna-16 landing site.
| CE-1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Oct 24 | 1005:04 | Launch by CZ-3A | XSC |
| T+2:25 Stage 1 MECO | |||
| 1007:40 | T+2:27 Stage 2 MES, Stage 1 sep | ||
| 1009:09 | T+3:52 Fairing sep | ||
| T+4:15 St 2 MECO | |||
| T+4:20 St 2 VECO | |||
| 1009:40 | T+4:21 St 2 sep, St 3 MES | ||
| 1015:05? | T+10:00? St 3 MECO-1 | 200 x 212 x 30.9? | |
| 1026 | MES-2 | ||
| 1028:04 | T+23:00 MECO-2 | ||
| 1029:39 | T+24:34 St 3 sep | 212 x 50584 x 30.9 | |
| 1955 | 173 x 50432 x 30.9 | ||
| 2007 Oct 25 | 0955 | OTM-1 130s raise peri | 600 x |
| 2007 Oct 26 | 0944 | OTM-2 | 24h x 70000 |
| 2007 Oct 29 | 1001 | OTM-3 | 48h x 120000 |
| 2007 Oct 30 | 1000 | At apogee | |
| 2007 Oct 31 | 0915 | OTM-4 10.916 km/s | 600? x 380000 |
| 0928 | OTM-4 complete | ||
| 2007 Nov 1 | 0042? | Pass EL1:4 | |
| 2007 Nov 2 | MCC-1 | ||
| 2007 Nov 4 | 2205? | Enter L sphere | |
| 2007 Nov 5 | 0100 | Despin | |
| 0145 | Attitude control for LOI | ||
| 0315 | LOI burn begins, 300 km alt | ||
| 0337 | LOI 1.948 km/s | 210 x 8600 | |
| 2007 Nov 6 | 0300s | LOI-2 1.80 km/s | 200 x 1700 |
| 2007 Nov 7 | 0000s | LOI-3 1.59 km/s 127 min circ | 200 x 200 |
| 2008 Jan 27 | 1550:48 | Orbit raise 2 km to shorten eclipse | |
| 2008 Feb 21 | Eclipse 2 hr | ||
| 2008 Oct 24 | Primary mission complete | ||
| 2008 Dec 5 | 200 x 200 km | ||
| 2008 Dec 6 | OTM | 100 x 200 | |
| OTM | 100 x 100 | ||
| 2008 Dec 18 | 1800 | OTM | 17 x 100 |
| 2008 Dec 19 | 0400 | After mascon drift | 15 x 100 |
| 2008 Dec 20 | 0000 | OTM | 100 x 100 |
| 2008 Dec? | Inclination change | ||
| 2009 Mar 1 | 0736 | Deorbit burn | |
| 0813 | Impact at 1.50S 52.36E | ||
