Chandrayaan-2 Lunar Rover Prototype design update

ISRO Mars Orbiter Update

We all are eagerly waiting for the launch of ISRO's Mars Orbiter Mission (MOM), in the meanwhile here are some more infos about the orbiter. 

Credits: Anil Bhardwaj, ISRO

ISRO Mars Orbiter.

ISRO Launch Vehicles: PSLV & GSLV

ISRO's Reusable Technology Demonstration Programs

In the quest of developing a reusable launch vehicle to enable low cost access to space, ISRO has been working on three technology development programs. These programs strive to demonstrate necessary technologies like high temperature reusable materials, hypersonic aerodynamics etc., that will form building blocks of ISRO's future RLVs. The three technology demonstration programs are following: 1) Space capsule Recovery Experiment (SRE), 2) Dual Mode Ram Jet Flight Technology Demonstrator (DMRJ-FTD) and Reusable Launch Vehicle Technology Demonstrator (RLV-TD).

ISRO Semi-cryogenic Engine update

ISRO's Semi-cryo Engine illustration. (credit ISRO)

 ISRO's Semi-cryogenic Engine specifications are following:

• Thrust (vacuum) - 2000 kN
• Isp (vacuum) - 3285 N-s/kg
• Chamber Pressure - 18 MPa
• Mixture Ratio - 2.65
• Thrust Throttling - 65-105 (% of nominal thrust) 
• Engine gimbal - 8 degrees (in two planes)

LVM3 Update: Vehicle subsytem status

GSLV MK2 Vehicle latest modifications

Latest developments related to GSLV MK2 (credit: ISRO)

ISRO Semi-cryogenic engine update

Status of SC2000

The Preliminary Design Review (PDR) for Semi-cryogenic engine development has been completed. Preparation of fabrication drawings of subsystems have been completed. 

A MOU has been signed with NFTDC for the realisation of copper alloy for Thrust chamber. 

Single element Pre-Burner (PB) injector realised and injector spray charaterisation using PIV was carried out. Test facility for single element pre-burner commissioned at PRG facility, VSSC. Semi Cryo Test facility design by M/s Rolta has been completed. 

Design of Semi Cryo Engine including heat exchanger and ejector is competed. Fabrication drawings and documents are generated based on the PDR and joint reviews. Configuration design of subscale engine is completed. Preliminary Design Review (PDR) of Hydraulic Actuation System

(HAS) and Hydraulic Power System (HPS) for Engine Gimbal control is completed and Technical specifications are finalized.

Single Element Pre-Burner injector element has been hot tested successfully. Ignition of LOX/Isrosene propellant with hypergolic slug igniter and flame holding, demonstration of safe handling of pyrophoric fluid TEA, validation of start sequence, characterization of injector elements and qualification of Hayness-214 material are the major achievements of the tests.

CUS-5 at High Altitude Test facility (HAT)

ISRO cryogenic engine for GSLV D5 at HAT(credits: ISRO)

The image is of CUS-5 engine for the GSLV D5 mission. The engine underwent a simulated vacuum ignition test at ISRO's High Altitude Test facility near Mahendragiri. The test demonstrated the successful simulated vacuum ignition and further build up of required operating parameters for high altitude atmospheric flight. Success of the HAT test will further boost India's cryogenic engine development program.