CSES-02:
In a Nutshell

Pending launch
Type Satellite
Start 13/06/2025
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-01 and the onboard instruments.

Diagram of CSES-01 and the 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).

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
High Energy Particle Detector (HEPD) 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

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

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