CSES-02:
In a Nutshell

Pending launch
Type Satellite
Start 14/06/2025
Target Earth
Objectives Ionosphere - Magnetosphere - Eliosphere

The second satellite in the mission, CSES-02, is scheduled for launch with a planned operational lifespan of at least six years. It carries nearly the same suite of scientific payloads as CSES-01, each featuring specific technological upgrades, along with two additional instruments to enhance observational capabilities.

Diagram of CSES-02 and some of its onboard instruments.

Diagram of CSES-02 and some of its onboard instruments.

How it works

CSES satellite operation

The onboard payloads include:

  • Two particle detectors:
    The High-Energy Particle Detector (HEPD-02), developed by the Italian Limadou Collaboration;
    The Medium Energy Electron Detector (MEED), which replaces the High Energy Particle Package (HEPP) used in CSES-01;
  • A High-Precision Magnetometer (HPM);
  • A Search-Coil Magnetometer (SCM);
  • The Electric Field Detector (EFD-02), also developed by the Italian Limadou Collaboration;
  • Two new instruments:
    A Coherent Population Trap (CPT) system;
    An Ionospheric Photometer (IP);
  • A Global Navigation Satellite System (GNSS) Occultation Receiver (GOR);
  • A Tri-Band Beacon (TBB) transmitter;
  • A Langmuir Probe (LP);
  • A Plasma Analyzer Package (PAP).

Both HEPD-02 and EFD-02 incorporate several technological improvements over their counterparts flown on CSES-01.

Details about each payload and their observational targets are reported in the table below.

Category Payload Name Observation Target
Energy Particle High Energy Particle Detector (HEPD) Proton: 30 Mev ~ 200 Mev
Electron: 3 ~ 100 Mev
Medium Energetic Electron Detector (MEED) Electron: 25 KeV ~ 3.2 MeV
Electro-Magnetic Field Electric Field Detectors (EFD) Electric Field DC ~ 3.5 MHz
High Precision Magnetometer (HPM)
• Vector Magnetic Field: FGM1, FMG2.
• Scalar Magnetic Field: CDSM, CPT.
Magnetic Field: 10 Hz ~ 20 kHz
Search Coil Magnetometer (SCM) Magnetic Field: 10 Hz ~ 20 kHz
In Situ Plasma Plasma Analyzer Package (PAP) Composition: H+, He+, O+
Ni: 5×10² ~ 1×10⁷ cm⁻³
Ti: 500K ~ 10000 cm⁻³
Langmuir Probe (LP) Ni: 5×10² ~ 1×10⁷ cm⁻³
Ti: 500K ~ 10000 cm⁻³
Plasma Profile Construction GNSS Occultation Receiver TEC by transmit VH/U/L Signal
Tri-Band Beacon TEC by transmit VH/U/L Signal
Ionospheric O₂ 135.6 nm and N₂ LBH airglow

CSES-02 is built on the same CAST2000 satellite platform as CSES-01, developed by DFH Satellite Co., Ltd., with several enhancements.

Key specifications include:

  • Total mass: ~900 kg
  • Peak power consumption: ~900 W
  • Data storage: 512 GB
  • Data transmission rate: 150 Mbps

CSES-02 will operate in a Sun-synchronous polar orbit, identical to that of CSES-01:

  • Altitude: ~507 km
  • Inclination: 97°
  • Orbital period: 94.6 minutes
  • Local Time of Descending Node (LTDN): 14:00.

CSES-02 relies on an Earth oriented 3-axis stabilization system with an Attitude Pointing Accuracy  ≤0.1°(3σ).

It will be injected into the same orbital plane with a 180° phase shift, enabling a complementary ground track. This configuration effectively reduces the revisit time from 5 days to 2.5 days, significantly improving temporal resolution and correlation capabilities, and establishing a new dual-satellite system for ionospheric monitoring.

Unlike CSES-01, whose payload operations were initially limited to latitudes between ±65° (later expanded to ±70°), CSES-02 will enable full-orbit payload operation, greatly enhancing coverage and broadening the range of scientific investigations.

Satellite CSES-02

in depth