Auto Credit Based on JoãoV's Long March 4B CBERS-1 [RSS]

Long March 4B

The Long March 4B, also known as the Chang Zheng 4B, CZ-4B, and LM-4B, is a Chinese expendable orbital launch vehicle. Launched from Launch Complex 1 at the Taiyuan Satellite Launch Center, it is a 3-stage launch vehicle, used mostly to place satellites into low Earth orbit and Sun-synchronous orbits. It was first launched on 10 May 1999, with the FY-1C weather satellite, which would later be the target in the 2007 Chinese anti-satellite missile test.
The Chang Zheng 4B experienced its only launch failure on 9 December 2013, with the loss of the CBERS-3 satellite.

Characteristics:

Heigth: 47.2 meters
Mass: 249 Tons
Payload to GTO: 1.5 Tons

CBERS-1

China-Brazil Earth Resources Satellite-1 was a remote sensing satellite which was operated as part of the China–Brazil Earth Resources Satellite program between the China National Space Administration and Brazil's National Institute for Space Research. The first CBERS satellite to fly, it was launched by China in 1999

CBERS-1 was a 1,450 kg (3,200 lb) spacecraft built by the China Academy of Space Technology and based on the Phoenix-Eye 1 satellite bus. The spacecraft was powered by a single solar array, providing 1,100 watts of electricity for the satellite's systems. The instrument suite aboard the CBERS-1 spacecraft consisted of three systems: the Wide Field Imager (WFI) produced visible-light to near-infrared images with a resolution of 260 metres (850 ft) and a swath width of 890 km (550 mi); a high-resolution CCD camera was used for multispectral imaging at a resolution of 20 metres (66 ft) with a swath width of 113 km (70 mi); the third instrument, the Infrared Multispectral Scanner (IMS), had a resolution of 80 metres (260 ft) and a swath width of 120 kilometres (75 mi).

Orbit:

Apogee: 785km
Perigee: 779Km
Inclination: 98.34°

Credits:

CAAA logo
CASC, LM and stripes logos

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GENERAL INFO

  • Predecessor: Long March 4B CBERS-1 [RSS]
  • Created On: Android
  • Game Version: 1.3.204.1
  • Price: $16,163k
  • Number of Parts: 226
  • Dimensions: 47 m x 5 m x 5 m

PERFORMANCE

  • Total Delta V: 11.9km/s
  • Total Thrust: 4.7MN
  • Engines: 14
  • Wet Mass: 2.51E+5kg
  • Dry Mass: 18,129kg

STAGES

Stage Engines Delta V Thrust Burn Mass
1 4 3.8km/s 3.3MN 2.6m 2.51E+5kg
2 4 16m/s 414kN 2s 53,272kg
3 5 3.2km/s 883kN 2.1m 53,272kg
7 1 4.9km/s 102kN 6.1m 15,458kg

6 Comments

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  • Profile image
    885 JoãoV

    @CCCP0000001 Now I've seen these solid engines. Honestly I had never seen them before on LM-3 I only thought it may have them because I had seen them in LM-5. And how I didn't know that the LM-3 do a hot staging I used them tho separate the S1 an S2.

    +1 22 days ago
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    @JoãoV you can see https://ru.scribd.com/document/533517995/LM-3A-Series-Launch-Vehicles-User-s-Manual-Issue-2011-1 p 2-14 If the rocket has three stages, then the four solid engines on the downward facing end of the second stage appear to be pointing upward and are used to separate the second stage away from the third stage.

    +1 23 days ago
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    @JoãoV On the one hand, the Long March 7 uses liquid oxygen and kerosene, while the previous rockets used UDMH/N2O4 fuel. This may be due to the difference in fuel. On the other hand, there was always a jam during separation before that launch, so it is not clear what happened.

    23 days ago
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    885 JoãoV

    @CCCP0000001 About the inlet:
    Anteriorly they were connected to the first stage, but after I watched this LM-7 launch (https://youtu.be/_fsGewECMy0?t=1056) I thought they were all like this(separate after), but now I have seen this (https://youtu.be/250uBKv7j9Q?t=63).

    +1 23 days ago
  • Profile image
    885 JoãoV

    @CCCP0000001 It makes sense. I had thought about this because of the interstage style (like the Soyuz), but I never saw it happen in the launches I watched.

    23 days ago
  • Profile image

    bro,the first and second stages of Chinese rockets, with the exception of the Long March-5, Long March-7 and Long March-8, are thermally separated (the second stage ignites before the first stage runs out of fuel, which is where the successive V-shaped structure at the top of the first stage comes from) (like the Soyuz), but their inlets are connected to the first stage and separated together, not a second time

    +1 23 days ago

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