ISRO General News and Updates

[Karthi]

Crew access arm hinge mechanism scheme

The hinge part of CAA is machined item which will be interfaced with the structural boom. The shaft of the hinge is EN24T and will be heat-treated to achieve required strength and hardness. Involute teeth Splines will be prepared on shaft to interface with the actuator. The shafts will be rotated through bearings. The approx. weight of machining part of boom is:8000Kg (8t)..

 

[Karthi]

Locking arrangement using turn buckles

The proposed Modification is minor in nature which involves trimming the corner of existing platform and addition of new members. The existing elements of the locking arrangement like turn buckle, supporting pedestal etc. will be used as it is by fixing in required direction. The approximate weight for the above work:
1t.

 

[Karthi]

Locking arrangement using turn buckles

 

[Karthi]

SCVRP 3 auto- locking is proposed at 46m on the top of girder and on 46m platform. This proposed auto-locking is designed to lock SCVRP at 102O instead of current locking of 135O. The auto locking and unlocking will be operated remotely from the control room. Major features of the proposed scheme are as following-

1. SCVRP 3A & 3B both will be locked at 102degree.
2. Striking arm is placed on the top SCVRP girder which will hold the locking.
3. The locking system at 46m platform will be remotely operated.
4. The locking system is operated by a flameproof electrical motor which will serve the function of both locking and unlocking. ( This work is in scope of department). However the scope of tenderer is to demonstrate the free rotation lever around the hinge shaft


Total 3 number of this auto-locking system has to be realized for Both SCVRP-3A, SCVRP-3B and CAA (one for each system). This involves the machining works like brackets, rotating pin with keys, swing arm, Striker plates, etc. The bought items like bearings etc. within the scope of supplier. The incorporation of drive system for auto locking system will be carried out by department. The approximate weight for this is around: 5t

 

[Akula]

Where is the article/source?

Please post.................

Check out Isro Reddit, there you can find the article source.

 

[Karthi]

Human Rated Launch vehicle and Crew Escape System

 

[Karthi]

SSLV D1 Acceptance testing of second stage (SS2) flight motor case completed.

 

[Karthi]

SSLV static test of first stage solid motor

 

[Karthi]

SSLV Third stage motor is under propellant processing

 

[Indx TechStyle]

View attachment 45031


The schematic layout of modifications to be carried out at launch pad as part of crew ingress & egress system

View attachment 45035

Crew access arm (CAA) view

The crew access arm is rotating cantilever structure arm connected from hinge being supported on 46m extension platform. The hinge will be rotated through a hydraulic actuator. The CAA is a 12m long cantilever boom having opening of 1.25m width and 2.3m height opening for crew entry. The structure of the boom is made up of MS pipes and the floor is cover with chequired plate. The approximate weight of boom is: 4t

Tender link for this stuff?
.............

 

[scatterStorm]

IAD stands for Inflatable Aerodynamic Decelerator, otherwise known as Aerodynamic Decelerator Atmospheric-entry Module (ADAM). The system is being designed jointly by VSSC and IIST for deployment off of a Mars orbiter. More about ADAM :

1. ADAM is an atmospheric entry module that delivers safely micro/mini probes/payloads to Martian surface, weighing from minimum 5 kg to 15 kg net weight relevant for small scale researchers and explorers.
2. Conceptualized as a stretched sphere (tear drop shape during its atmospheric entry) and the rear cone separates out during the parachute deployment transforming the module to a sphere.
3. This sphere drops down decelerating, aided with three thrusters to bring down the velocity to near zero value for a safer touchdown.
4. Visco-elastic damping materials serves as shock absorbers to prevent impact load transfer to the payload inside.

Additional details :

1. Outer aeroshell in the shape of a stretched sphere (tear drop shape)
2. Multiple layer of Thermal Protection System (TPS)
3. Visco-elastic shock absorbing layer
4. Decelerator system consisting of parachute and thrusters
5. Concept is analogous to advent of mini-satellites when larger spacecrafts of agencies reign the space arena.
6. Small scale space enthusiasts can enter planetary exploration via such small payload delivery systems
7. Maximum deceleration: 11.5 m/s (3.28 ‘g’)
8. Altitude of maximum deceleration: 20.40 km from surface
9. Velocity at maximum deceleration: 491.93 m/s
10. Maximum dynamic pressure: 880 Pa
11. Drag force at maximum deceleration: 180 N
12. Altitude of maximum heating: 8.20 km from surface
13. Maximum heating rate: 3033 Watt/sqm (lesser than the space capsule recovery experiment heating rate as achieved by ISRO in earth atmosphere)

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If only we would've tried on our Vikram lander. I am more interested in the aerogel part. If Nasa Isn't using it then why we are doing it?

 

[scatterStorm]

View attachment 45041


Human Rated Launch vehicle and Crew Escape System

Any news on reusable booster phase rocket from ISRO, are we doing it, or in pipelines?

 

[Karthi]

Any news on reusable booster phase rocket from ISRO, are we doing it, or in pipelines?

Don't know much details , the only thing I know is work is going on.

 

[Karthi]

If only we would've tried on our Vikram lander. I am more interested in the aerogel part. If Nasa Isn't using it then why we are doing it?

Moon don't have atmosphere so decelerating won't work only thrusters can do the job

 

[saketkr]

What happened to the launch plan of GISAT-1? It is unusually eerie in media, no one is talking anymore about it, neither ISRO nor Media or the Community here. Does anyone on the forum know what happened !

 

[Indx TechStyle]

What happened to the launch plan of GISAT-1? It is unusually eerie in media, no one is talking anymore about it, neither ISRO nor Media or the Community here. Does anyone on the forum know what happened !

ISRO is closed for a couple of weeks just like rest of India due to SARS CoV-2.
It will still be first and immediate launch of ISRO as soon as lockdown is lifted.

 

[Karthi]

Crew Module Integration Mock up model

 

[Karthi]

Structural Testing of RLV EM

 

[Karthi]

Structural Testing of RLV EM

 

[Karthi]

X band Radar at NARL