LEAP-TD Mission

Dhruva Space tested and Space-qualified of its 'Launching Expeditions for Aspiring Payloads - Technology Demonstrator' (LEAP-TD) platform onboard ISRO’s PSLV-C55 POEM-3 mission.

The launch took place at 09:10 IST on 01 January 2024, from the First Launch Pad at Satish Dhawan Space Centre (SDSC) in Sriharikota, Andhra Pradesh.

Mission success was confirmed by the way of reception of Telemetry & Beacon data at the Ground Station of Indian Institute of Space Science & Technology (IIST), Trivandrum, and through the data received from the POEM platform itself as well.

ISRO's PSLV-C58 DL lifting off from the First Launch Pad at Satish Dhawan Space Centre (SDSC)  in Sriharikota, Andhra Pradesh.
(Photo Credit: Indian Space Research Organisation)

Launching Expeditions for Aspiring Payloads (LEAP)

Dhruva Space’s Launching Expeditions for Aspiring Payloads or (LEAP) is the company's full-fledged hosted payload solutions for Space missions, signifying Dhruva Space’s readiness to offer hosted payload services to the world.

A hosted payload service comprises a portion of a satellite, such as a sensor, instrument or a set of communications transponders that are owned by an entity other than the primary satellite operator. The hosted portion of the satellite operates independently of the main spacecraft, but shares the satellite’s power supply, transponders, and in some cases, ground systems.

POEM has standard interfaces and packages for power generation, telemetry, telecommand, stabilisation, orbit keeping and orbit manoeuvring and hence can be used to design, develop and validate experimental payloads.

The LEAP-TD mission featured a derivative of the Dhruva Space P-30 satellite platform integrated to ISRO’s PSLV Orbital Experimental Module 3 (POEM-3), which enabled in-orbit scientific experiments using the spent PS4 stage as an orbital platform.

This mission has validated the P-30 platform and its various subsystems in-orbit.  

On-board Computer;
Ultra High Frequency (UHF) TT&C Module;
Beacon in UHF;
Attitude Control System with a Reaction Wheel from Comat; and
Power Distribution Board.



Compact & Modular
Satellite Bus Volume
Available on
Satellite mass
20 - 50 kg
Payload power
Available on
Nominal mission Lifetime
Upto 5 years
Pointing Accuracy
Upto 0.1
Dhruva Space
  • LEO Optimised
  • Scalable for Earth Observation Constellations
  • Multi-Payload Configurations
  • Pre-Qualified and assembled (Mechanical, Electrical) and ready for Payload Integration
  • Body-mounted and Deployable Solar Arrays
  • 3 axis stabilized customized configurations available
  • Suitable for medium resolution remote-sensing payloads
  • Electric Propulsion for Orbit maneuverability