Successful Test Flight Sets Gaganyaan Mission on Course with Crew Safety Assurance

Mission Description: The mission, known as the "In-flight Abort Demonstration of Crew Escape System (CES)," involved a test flight of the newly developed Test Vehicle. The primary objectives of this mission were to: 1. Demonstrate and evaluate the performance of various sub-systems of the Test Vehicle. 2. Validate the effectiveness of the Crew Escape System (CES) and its associated separation systems. 3. Showcase the behavior and deceleration systems of the Crew Module (CM) at higher altitudes and ensure its safe recovery. Key Mission Highlights: - Test Vehicle (TV) reached a maximum speed of Mach 1.2. - The altitude reached during the mission was 11.7 kilometers. - The flight path angle was maintained at 60 degrees. - The dynamic pressure experienced was 22.6 kilopascals. - CM-CES separation occurred at Mach 0.5 at an altitude of 17 kilometers with a dynamic pressure of 2-3 kilopascals. - Drogue parachute deployment took place at an altitude of 16.7 kilometers. - The main parachute was deployed at an altitude below 2.5 kilometers. Test Vehicle (TV-D1) Specifications: - The TV-D1 is a single-stage liquid-propelled vehicle equipped with a modified VIKAS engine, with the Crew Module (CM) and Crew Escape System (CES) mounted at the front. Vehicle Configuration: - Length: 34.954 meters - Diameter: Ø 2.1 meters (stage), Ø 4.05 meters (CES) - Liftoff mass: 44 metric tons - TV inert mass: 7 metric tons - CES inert mass: 12.5 metric tons - CM inert mass: 4.5 metric tons Propulsion System: - TV: VIKAS Engine with AR6, N2O4 – 12 metric tons, UH-25 – 7 metric tons - CES: HEM (4 units) + CJM TV-D1 Crew Module (CM) Specifications: - Structure: Single-walled unpressurized aluminum structure with a simulated thermal protection system using cork. - Dimensions: Ø3.1 meters x 2.97 meters - Mass: 4520 kilograms - Avionics: Equipped with launch vehicle heritage avionics featuring dual redundancy. - Navigation: Supported by Mini Advanced INS augmented by NavIC/GPS. - Deceleration System: Utilizes a total of 10 parachutes with pyro systems, with parachute deployment initiated at 17 kilometers altitude. Separation Systems: - CM/Service Module (SM) separation - CM/CES separation - Apex cover separation - CES - CMF separation Touchdown Velocity: - Nominal touchdown velocity is 8.5 meters per second. Floatation System: - Utilizes a buoyancy augmentation system using PUF blocks. Recovery Aids: - Includes sea markers and location transmitters to aid in recovery operations.