Space Brief 9 Mar 2025
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ARCADE (57485)
COSPAR: 2023-109E | Alt Name: INSPIRESat-4
Image
Additional Sources
Launch Details
Launch Date
January 1, 45137
Launch Site
Satish Dhawan Space Centre, Sriharikota, India
Launch Pad
First Launch Pad (FLP)
Launch Vehicle
PSLV-C56
Orbital Elements
NORAD ID
57485
International Designator
2023-109E
Epoch
Sat, 23 Dec 2023 20:42:38 GMT
Apogee
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Perigee
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Inclination
5.00°
Right Ascension
247.63°
Eccentricity
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Argument of Perigee
53.83°
Period
95.07 min
Mean Motion
15.15 rev/day
Latitude
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Longitude
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Altitude
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Velocity
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Polar Plot
3D Visualization
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Basic Satellite Info
Name
ARCADE
Alternative Name
INSPIRESat-4
Type
Payload
Status
Operational
Owner
Nanyang Technological University (NTU)
Country
Singapore
Constellation
N/A
Related Satellites
Major Events
Launched on 30 July 2023; deployment into initial orbit; planned altitude reduction to 350 km using electric propulsion for VLEO operations.
Latest TLEs
1 57485U 23109E 23357.86294789 .00014481 00000+0 70660-3 0 9996
2 57485 4.9977 247.6344 0009185 53.8335 306.2623 15.14746534 22250
Source: Celestrak
Summary
ARCADE (also known as INSPIRESat-4) is a CubeSat 27U scientific microsatellite developed by the Satellite Research Centre at Nanyang Technological University (NTU). Launched on July 30, 2023, from Satish Dhawan Space Centre in Sriharikota, India using PSLV-C56 launch vehicle, it aims to study equatorial ionosphere and mesosphere-lower thermosphere region. Weighing 26.4 kg at launch, the satellite is equipped with instruments including a Compact Ionosphere Probe (CIP), Spatial Heterodyne Interferometer (SHI), and an imager for atmospheric gravity waves among others. ARCADE operates in low Earth orbit with plans to lower its altitude using ThrustMe electric propulsion system for Very Low Earth Orbit (VLEO) operations, designed for a mission duration of one year. The satellite is powered by deployable solar panels providing 100W peak power and has an ADCS comprising sun sensors, IMUs, magnetorquers, reaction wheels, and a star tracker.
Physical Characteristics
Length
0.32
Diameter
0.32
Span
0.32
Dry Mass
26.4
Launch Mass
26.4
Shape
Box-shaped with deployable solar panels
Radar Cross Section
Unknown
Visual Magnitude
Unknown
Color
Unknown
Material Composition
Constructed from aluminum and magnesium alloys; includes experimental materials for atomic oxygen exposure studies.
Technical Details
Payload
The primary payloads include the Compact Ionosphere Probe (CIP) for ionospheric measurements and a Spatial Heterodyne Interferometer (SHI) for imaging the MLT region.
Purpose
Technology
Mission
ARCADE (Atmospheric Coupling and Dynamics Explorer) is a scientific microsatellite developed to study the equatorial ionosphere and mesosphere-lower thermosphere (MLT) region. It aims to provide insights into atmospheric coupling processes and the dynamics of the equatorial ionosphere.
Manufacturer
Satellite Research Centre, Nanyang Technological University (NTU)
Life Expectancy
The mission is designed for a duration of one year in low Earth orbit, with plans to utilize its electric propulsion system to lower its altitude from 530 km to 350 km for Very Low Earth Orbit (VLEO) operations.
Bus
CubeSat 27U
Configuration
CubeSat (27U)
Motor
ThrustMe electric propulsion system
Equipment
The satellite is equipped with four instruments: an imager for atmospheric gravity waves, a plasma probe for measuring ionospheric plasma density and velocity, an atomic oxygen instrument to study material degradation in low Earth orbit, and an optical imager for Earth observation.
Power System
The satellite is powered by three deployable solar panels and one body-mounted solar panel, providing a total of 100W peak power at Beginning of Life (BOL). Energy is stored in two 24 Ah lithium-ion batteries.
ADCS
The Attitude Determination and Control System (ADCS) comprises 12 coarse sun sensors, Inertial Measurement Units (IMUs), a star tracker, three magnetorquers, and three reaction wheels.
Transmitter Frequency
UHF uplink at 9600 bps GFSK; X-band downlink at 50 Mbps
Map
Next Pass
Azimuth Elevation Time (Local)
Start Azimuth
Max Elevation
Stop Azimuth
Time Until
Pass Duration
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