ISRO Qualifies Gaganyaan Crew Module Systems

ISRO is conducting qualification of the Gaganyaan Crew Module (CM) systems by successfully carrying out 3 major qualification tests to validate astronaut safety and system performance. The news focuses on qualified subsystems, the CM’s selected truncated sphere-cone configuration, and key life-support, re-entry, and recovery mechanisms.

Gaganyaan Crew Module (CM):

Dimension	Key Details
Qualified subsystems	Proven subsystems comprise the Crew Module Uprighting System (CMUS), the separation of the Crew-Service Umbilical mechanism (CSU-2), and the structural integrity during the Apex Cover Separation.
Spacecraft outer shape	The outer shape of a spacecraft dictates how it behaves physically when hitting the atmosphere at orbital velocities.
Design choice: spherical capsule	A spherical capsule comprises maximum internal volume for minimum structural mass, and it generates no aerodynamic lift, falling straight down and exposing astronauts to extreme G-forces.
Design choice: conical body	A conical body provides for high lift and aerodynamic stability for a controlled descent, and it is less volume-efficient.
Gaganyaan CM configuration	The Gaganyaan Crew Module comprises a truncated sphere-cone configuration weighing approximately 5.3 tonnes.
Environmental Control & Life Support (ECLSS)	ECLSS regulates oxygen supply, cabin pressure at 0.8 atm, temperature at 20–26°C, and humidity between 30% and 70%, and it comprises carbon dioxide scrubbing and waste control.
Thermal Protection System (TPS)	TPS comprises a thermal shield on the module’s exterior that safeguards the metallic pressure hull and the crew from re-entry heat loads exceeding thousands of degrees Celsius.
Deceleration system	The deceleration system comprises a highly redundant system utilising 10 different parachutes.
Crew Escape System (CES)	CES provides for a high-speed lifeboat function, and in case of catastrophic booster failure on the launchpad or during ascent, 5 quick-firing solid fuel motors pull the crew module away to safety.
De-orbit and CSU-2 separation sequence	The Service Module fires its propulsion system to decelerate the vehicle, and the Crew Module Umbilical (CSU-2) system executes separation by detaching the Service Module, which burns up in the atmosphere while the Crew Module proceeds alone.
Apex cover separation	Before the main parachutes deploy, the protective apex cover is cleanly jettisoned.
Parachute deployment and splashdown	The parachute sequence triggers to slow the module to terminal velocity before it splashes down in the ocean.
Active uprighting (CMUS)	CMUS comprises stored high-pressure cold-gas that inflates flotation devices to rotate the module back to an upright position to protect the crew and secure communication antennas.