July 12, 2026
Recently ISRO has successfully accomplished three major qualification tests for Crew Module (CM) systems of Gaganyaan mission viz. Float inflation test for Crew Module Up-righting System (CMUS), umbilical separation testing of Crew module Service module Connect & Disconnect System (CSCDS) and Crew Module Structure qualification test for Apex Cover separation loads.
Ensuring up-right position for Crew Module after splashdown in the sea is one of the important crew safety requirements. A stored cold gas based up-righting system has been developed to meeting this requirements.
A system level qualification test setup consisting of all the elements of CMUS was realised and successfully conducted inflation tests for the primary inflation module where in stored gas in the high pressure gas bottle was made to inflate the floatation by operating the control valves. The tests demonstrated the inflation module meeting the functional and performance requirements for deployment of the primary flotation. The test also demonstrated the inflation time requirements over the complete operating range of gas bottle pressures.
The Crew Module Service Module - Connect Disconnect System (CS-CDS) is one of the major systems that serves as an electrical / hydro-pneumatic umbilical link between Crew Module (CM) and Service Module (SM). All the electrical communication between CM and SM as well as the fluid communication for Environment Control & Life Support System (ECLSS) takes place through CS-CDS. This system consists of two parts, Crew module - Service module Umbilical (CSU-1 & CSU-2) one each at CM and SM side. After separation of SM from CM at CSU-1, CSU-2 on CM side is separated before re-entry of CM.
Separation test of CSU-2 from simulated Crew Module was carried out. The test demonstrated the clean separation of CSU-2 as well as structural stability of the Crew Module panel and their interfaces. The test validated the functionalities of integrated CSU-2 system and demonstrated the required design margins.
Apex cover of Crew Module protects the parachutes and associated subsystems during the mission. Before deployment parachutes in sequence to decelerate the Crew Module, the apex cover is separated at a predetermined altitude operating pyrotechnically actuated thrusters.
To validate the structural integrity of the Crew Module during apex cover separation event, an instrumented test rig along with simulated crew module and associated systems were realised and approximately 1.75 times of estimated reaction loads were applied to simulated crew module at identified locations. All the measured strain and deformations during the tests confirmed the design margins and also validated the structural integrity of crew module for the apex cover separation event in the flight.