CERES-1

SOLID PROPELLANT LAUNCH VEHICLE

中文 | EN

FAIRING

Von Karman Shaped, Composite Material

LOAD MASS

350kg To LEO

230kg To SSO(700km)

LOAD SPACE

1.28m Diameter

2.6m Height

Advanced liquid upper stage

One-rocket-multiple-satellites,Space ferry,Active derailment

Third stage

Single Light Year GS-3 solid engine

8.8t Thrust

69s Burn time

Second stage

Single Light Year GS-2 solid engine

28t Thrust

70s Burn time

First stage

Single Light Year GS-1 solid engine

60t Thrust

74s Burn time

  • CERES-1 is a 4-stage launch vehicel independently designed by Galactic Energy, Solid engine are used in the first, second and third stages, advanced liquid upper stage as the fourth stage , the rocket diameter is 1.4 m, total length is 19m, lift-off weight 30 t, LEO orbital capacity 350 kg, 700 km SSO ,orbit capacity 230 kg, which is committed to provide high-quality, cheap and fast launch services for low-orbit small satellites.
  • FLIGHT ENVIRONMENT

    Maximum longitudinal overload≤9g

    Maximum lateral overload≤0.6g

    INJECTION ACCURACY

    Deviation of half length axis≤5km

    Orbital tilt Angle deviation≤0.1 °

    Eccentricity deviation ≤ 0.002

    SATELLITE SEPARATION ATTITUDE ANGLE AND ANGULAR RATE DEVIATION

    Attitude angle deviation ≤1 °

    Attitude angle rate deivation≤0.3°/s  

  • INTERFACE

    Military standard GJB4228 (GJB/Z200) type 300 and 660 type wrap belt spring type satelliteand launch vehicel connection separation unit.

    The international general CubeSat release mechanism, with 1U (100mm 100mm 100mm) as the basic unit for modular expansion, can load the common volume of 1U, 2U, 3U, 6U, 12U CubeSat.

    Lightweight wrap belt, interface sizes range from 8 to 38 inch in diameter.

    Explosive bolts, 3-point or 4-point interface.

    Other interface types.

  • Quick launch
    Ample space
    Multiple interfaces