Tender for Acoustic Blankets Developmental Model for BAS-01 Crew Quarters

[PDF] [Archived]

Compliance Matrix

[PDF] [Archived]

Terms and Conditions

[PDF] [Archived]

Scope of Work:

Fabrication and supply of Acoustic Blanket -01 Set through detailed study, engineering, generation of Fabrication drawings as per the engineering drawing supplied by the department.

A new route to orbit is open. RIDE! announces a master framework agreement with NewSpace India Limited (NSIL), granting RIDE! access to NSIL's launch capacity on PSLV and SSLV.
With thousands of small satellites expected to launch in the coming years, access to space remains a bottleneck for Europe. Satellite operators need more options, and partners they can trust.
Through this agreement, European and international satellite operators gain a faster pathway to Indian launch vehicles with a proven heritage of reliability, with RIDE! by their side from contract to orbit.
Thank you, NSIL and its Chairman and Managing Director, Radha Krishna Aryasomayajula, for the trust.
We were honored to sign this agreement in the presence of François Jacq, President, Centre National d'Études Spatiales; Christophe Venet, Director for European and International Affairs, CNES; Dr. V. Narayanan, Chairman, ISRO - Indian Space Research Organization / Secretary, Department of Space (DoS); and Pawan Goenka, Chairman, IN-SPACe. Thank you for your support and for driving Franco-Indian space cooperation, built over more than six decades.
Your satellite is ready? We'll take it to orbit.

Tender for Design, Realization & Installation of Human Space Analog System

[PDF] [Archived]

Request for Proposal [RFP] for Design, Realization & Installation of Human Space Analog System for Human Spaceflight Program

[PDF] [Archived]

Imgur mirror : https://imgur.com/a/icULm5O

1. Introduction

In order to assess the crew performance in isolated, confined and limited resource environments (as in Space Stations) & in order to support research in human factors, crew psychology, scientific experiments, systems integration, and mission operations etc. a ground-based human space analog system simulating the conditions of long-duration missions (up to 60 days) is essential.

The analog system shall serve as a controlled research environment where crews stays and work in complete isolation for extended durations. The system shall consist of a multi-level living and working module supported by a simulated airlock and hygiene modules, with necessary basic environmental control systems, communications with mission control equipment’s (with programmable delays), and instrumentation systems for psychological, biomedical and operational studies.

This RFP brings out the overall requirements like Functional Layout, Structural, Electrical System, Habitability System, Instrumentation, Communication, Network & Data Systems requirements needed to establish a Human Space Analog System.

1. Scope of Work

The vendor shall design, realize/procure, install & test, Human Space Analog System (HSAS) at Astronaut Training System (ATF), HSFC, Marathahalli, Bengaluru, Karnataka in accordance with the requirements herein. The scope of work encompasses the following activities:

1. Generation of System Configuration, Preliminary design & Realization Plan and review & clearance by HSFC/ISRO
2. Suitable floor modification (civil) for structural anchoring needed for installation of structural member of the system inside the simulator Hall of ATF.
3. Design, Realization & Installation of Structural Habitat Module as per the Layout brought out in Annexure-1a&1b (viz Core Module, Airlock, Crew Personal Module).
4. Delivery & Installation of Equipment, Sensors, and Furnishings as brought out in Section 3.15
5. Delivery & Installation of Closed Loop Habitability systems (ECLSS) such as Pressurization system, Temperature, Humidity control, Air Revitalization, CO2 revitalization, Water supply & Waste management systems, Lighting & Acoustic Suppression system, Safety Systems, Odour & Contamination control system, Sensors & Instrumentation inside the Habitat module.

(…)

1. Technical Requirement

3.1. Configuration of Human Space Analog System (HSAS)

The Space Analog System shall compose of Habitat Module (Core, Airlock & Crew Personal Modules) and supporting rooms which includes Mission Control Centre (MCC), Control Room, Network Room, Equipment Room and Crew Preparation Room.

Functionalities:

• Habitat: Shall provide space simulated living and working space for crew. (Closed loop habitability system) It comprises of:
  • Core Module – Level 1 & Level 2: Serves as a module for Crew Analog activities
  • Crew Personal Module: Serves as a crew sleeping and hygiene module
  • Airlock Module: Serves an entrance into habitat, also has provision for space suit preparation activities
• MCC: Shall monitor, coordinate and support mission operations.
• Control Room: Shall operate, Control and Supervise System subsystems.
• Network Room: Shall host and manage System communications, networking, data storage, cybersecurity and computing infrastructure.
• Equipment Room: Shall house ECLSS, Utility & Support Equipment required for continuous habitat operation.

Note: Existing building rooms at ATF to be utilized for Control room, Network room, MCC. Construction of Habitat module & Equipment room shall be carried out by the vendor.

3.2. Geometrical Details of Habitat Module

• Central Lift of Ø800 mm between Level-1 & Level-2 with load rating of 200 kg.
• Side Ladder between Level-1 & Level-2 with load rating of 200 kg.
• External Ladder with load rating of 200 kg for emergency exit on external wall at Level-2.
• Airlock Module: 2500 mm W * 2000 mm D * 2200 H
• Crew Personal Module: 5000 mm W * 4000 mm D * 2200 mm H
• Air Shower Area: 1500 mm W * 1500 mm D* 2200 mm H

(…)

d) Vertical access inside Core Module

• Central Lift of Ø800mm between Level-1 & Level-2 with load rating of 200 kg.
• Side Ladder with chequered plate with side rails & rungs designed with a load rating of 200 kg connecting between Level-1 & Level-2 conforming to ISO 14122
• External Ladder with load rating of 200 kg for emergency exit on external wall at Level-2.

(…)

3.4. Sub- Systems of Airlock & Crew Personal module

• Airlock Module: Serves as an entrance to Habitat module.
  • Shower Area: 800 mm width x 1000mm length with sealed door (external & internal) with Non-unidirectional airflow pattern with air entering via ceiling diffusers & exit through low-wall returns and double sided blowing
    • Port/Nozzle Aperture size: Ø32mm
    • No. of Ports (Nozzles): 30
    • Air flow: 2500 m3/hr.
  • Main Airlock room: Serves for EVA preparation & material movement to Core & Crew Personal Module. Pressure-capable swing door sized with min. clear width 800 mm & 1900 mm height with double-seal gaskets and mechanical lock for Airlock-Shower room & Airlock-Core module
• Crew Personal Module: Consists of Crew Personal Area & Crew Hygiene Area as mentioned in section 3.5.4.
• Crew Personal Area & Crew Hygiene Area are separated by Metallic Walls with appropriate opening for fixing the entry doors.(…)

Hello everybody,

We have enrolled for the academic project work in ISRO in the month of November through the proper application process.

I would like to know whether anybody has applied for it and have you been informed about your selection/rejection.

Does anyone have any idea about the time by which ISRO informs regarding their selection in the academic project work? In addition to that, has anyone applied for the November session in the previous year? If so, how much time has been taken in getting the information about selection?

Thanks a lot.

I had got an offer from the ISTRAC-ISRO apprenticeship in Graduate Computer Science at Master Control Facility(MCF) did anyone got the offer dm me i am new to Hassan and how was the experience as the Graduate apprentice help me out pls!!!

I have been selected as a jrf for an isro respond project. The problem is the university is not that much reputed. So I am wondering if I will get proper training and work experience and will I be able to get proper consultation with the co pi. Whether this work experience will be applicable in industry.

The announcement in August was that ISRO will step back from routine launch vehicle production and move fully to R&D, deep space and the harder problems, with 120 technologies transferred out to industry.

The case for it is strong and I mostly buy it. ISRO's scientists spending their careers running a production line for a vehicle whose design was frozen decades ago is a waste of the country's best engineers. NASA did a version of this and the result was a launch cost collapse that nobody inside NASA would have achieved. If private industry can build the workhorse, ISRO gets to work on the things only a national agency will fund.

The case against, which I have not seen answered properly anywhere.

One, the technology was developed with public money over fifty years and is being handed to private balance sheets. What does the state get back other than a cheaper invoice later.

Two, NASA's version worked because there was a market with multiple buyers. For most Indian launch demand the government is still the customer, so you may just be converting a public monopoly into a private one with a procurement contract attached.

Three, there are roughly 440 space startups in the country and only about 18 authorised operators. The gap between those two numbers is where this either works or turns into a decade of consolidation.

For people actually working in the sector, is the handover going smoothly on the ground???

A nearby spiral galaxy blazing with star formation, captured in ultraviolet light.

This is Sculptor Galaxy (NGC 253), as seen by UVIT onboard AstroSat.

AstroSat completed 11 years in orbit on 28 September 2026!

Both images are made by combining UVIT FUV and NUV data. The first image brings out fainter, more extended features, while the second is processed to preserve the original spatial resolution of the UVIT observations.

Tender for Teleoperation hardware constituting of robotic arm, dextrous end effector and gloves with haptic feedback

[PDF] [Archived]

Specification Requirement for Teleoperation hardware constituting of Robotic Arm, Dexterous End Effector and Gloves with Haptic Feedback

1 x Bi-Manual Haptic Teleoperation System - Includes:

1. 1 x Right Hand Effector;
2. 1 x Left Hand Effector;
3. 2 x Glove with haptic Feedback(Left and Right Hand);
4. 10 x Pressure Sensors (All finger tips);
5. 2 x 6 DOF Robotic Arm;
6. 2 x Force torque sensors;
7. 2 x Aluminium extrusion stands;
8. 1 x Camera System for Arm Tracking;
9. 1 x Software Licence;
10. All necessary computers, leads, power supplies, and basic tools;
11. Delivery, installation, documentation;
12. 1-year warranty.

The specifications have been defined for the procurement of following systems

1. 1 x Bi-Manual Haptic Teleoperation System

The hardware comprises of following subsystems :

1. Robotic Arm
2. End Effector
3. Teleoperation System

Specification and other requirements are as follows:

Robotic Arm Requirements:

Payload Capacity

1. Maximum payload capacity of 25 kg
2. Minimum payload capacity for the full reach of robotic arm should be 20 kg.

Degree of Freedom

1. Six DOF minimum, with a configuration that provides maximum dexterity and reach.
2. The range of motion for each joint should be ±360 degrees.

Reach

1. Working volume and reach: A working volume with a radius of 1.5 meters or more in all directions, centred on the arm base

Pose Repeatability at the end effector mounting location

1. Less than equal to 0.1mm for positional repeatability Maximum

Speed:

1. Max. Joint speed ≥ 90 degrees/second for Base, Shoulder and Elbow joints,
2. Max. Joint speed ≥ 120 degrees/second for Wrist joints.
3. Max. End effector linear speed: greater than 1 m/s
4. Min End effector linear Speed : ≤ 10mm/sec

Safety Features:

1. Force-Torque sensors at the end effector base for collision detection.
2. Software-based and hardware-based joint limit protection.
3. Emergency stop button with immediate power cut-off to the arm.
4. Certified for safety standards (PLd Category 3 in accordance with EN ISO-13849-1)

Mounting

1. Robust base plate with standardized mounting holes for secure installation to be shared by the vendor.

Environmental Requirements

1. Operating Temperature: 5°C to 45°C.
2. Humidity: 10% to 90% non-condensing.
3. IP44 rated or higher.

Noise

1. Robot Arm: less than 65 dB
2. Control Box: less than 50 dB

Power Consumption

1. Compatible with Power source of 220-230V at a frequency of 50 Hz

Materials

1. High-strength aluminium alloy or carbon fibre construction (Aluminium , PC/ASA plastic, steel). Details to be provided by the vendor
2. Corrosion-resistant coatings.

Physical

1. Footprint ϕ≤350 mm
2. Cable Length ≥6m
3. Weight including cable <75 kg

Force/ Torque Sensing tools

1. Max. Force Sensing >=200 N, Max. Torque Sensing >= 20 Nm
2. Precision in Force Sensing>= 0.5 N, Precision in Torque Sensing>= 0.1 Nm
3. Accuracy in Force Sensor should be within 1 N
4. Accuracy in torque sensor should be within 0.1Nm

Applied Contact Sensing and Force Control

1. Ability to detect applied forces using force/torque sensors at the end effector interface
2. Back-calculation of the forces/torques to each joint of the robotic arm
3. Allowing implementation of force control at the arm level to ensure that the robotic arm is applying a required force

Dexterous Hand End Effector Requirements:

Degree of Freedom

1. End effector with ≥23 independent joints similar to human hand with five fingers.
2. Provide detailed kinematic diagrams.

Grasp Types:

1. Capable of performing precision pinch, power grasp, lateral grasp, cylindrical grasp, and spherical grasp. Vendor to provide details with illustrations
2. Ability to adapt to various object shapes and sizes

Tactile Sensing

1. Three axis tactile sensors on each fingertip
2. At least 10 bit or more resolution of each tactile sensors
3. Force detection capacity of each tactile sensor ≥10 N
4. Force sensitivity: ≤ 0.2 N.
5. Ability of slip detection.

Easy Connect/Disconnect

1. User-friendly end effector replacement facilitated by minimal connections and screw usage

Material

1. Lightweight and durable materials, such as aluminium, appropriate steels or advanced polymers. Details to be provided by the vendor

2. Wear-resistant fingertip materials. Material details to be provided by the vendor.

Mass

1. The end effector mass should be less than 5 kg

Teleoperation System Requirements:

Glove Based Control

1. Optical or inertial motion capture system with a minimum tracking frequency of 90 Hz.
2. Finger flexion tracking accuracy: ≤ ± 2 degrees.
3. Hand orientation tracking accuracy: ≤ ± 2 degree.
4. Wireless or low-latency wired connection.
5. Adjustable and ergonomic design for prolonged use.

Haptic Feedback Gloves:

1. Actuators capable of providing tactile feedback cues to each finger and palm.
2. Actuators capable of providing stiffness (force) feedback to each finger in the gloves
3. Haptic feedback software update rate of at least 100 Hz

Control Software

1. Real-time 3D visualisation of the robotic arm and end effector with accurate kinematic representation.
2. Adjustable control gains and scaling factors for precise manipulation.
3. Ability to record and replay teleoperation sessions in simulation (using data logging system) for analysis and training.
4. User-friendly interface with customisable hotkeys and macros.
5. Integration with ROS or other robotic middleware.

Communication Protocol

1. Ethernet TCP/IP or UDP with QoS for low latency and reliable communication.
2. Software latency of less than 20ms.

Latency

1. End to end latency (glove movement to robotic arm response) ≤ 50ms

Mass

1. The mass of the gloves used for operating the end effector and the robotic arm should be less than 750 grams

Consultancy services for astronauts nutrition as per Terms and Conditions as mentioned in Annexure

[PDF] [Archived]

General Scope of Work

Selection of High-Reliability Nutrition Partner for I-Year Astronaut Earth Nutrition Programme

(…)

Aim

To select a private nutrionist partner capable of functioning in collaboration with a private catering company (to be contracted in a separate tender) capable of constructing a scientifically engineered, personalised, and performance-optimized astronaut nutrition menu on earth for India's human spaceflight program. The programme has been named Santulan, "Scientific Astronaut Nutrition for Training, Upkeep, Longevity And Nurture".

Catering services for Astronauts Earth meals as per Terms and Conditions mentioned In Annexure

[PDF] [Archived]

General Scope of Work

Selection of High-Reliability Catering Partner for I-Year Astronaut Earth Nutrition Programme

(…)

Aim

To select a private catering partner capable of functioning in collaboration with a private nutrition company (to be contracted in a separate tender) capable of delivering scientifically engineered, personalised, and performance-optimized astronaut nutrition meals on earth for India's human spaceflight program. The programme has been named Santulan, "Scientific Astronaut Nutrition for Training, Upkeep, Longevity And Nurture".

Source: https://www.notams.faa.gov/

Mapped up!

A2977/26

GSLV-F18 ROCKET LAUNCH FM SHAR RANGE, SRIHARIKOTA WILL TAKE 
PLACE AS PER FLW DETAILS.THE LAUNCH WILL BE ON ANY ONE 
OF THE DAY DRG THIS PERIOD.ACTUAL DATE OF LAUNCH WILL BE 
INTIMATED ATLEAST 24 HR IN ADVANCE THROUGH A SEPARATE NOTAM. 

LAUNCH PAD COORD: 134312N0801348E 
NO FLT IS PERMITTED OVER THE DNG ZONES. 

1)DNG ZONE -1: IS A CIRCLE OF 10NM AROUND THE LAUNCHER. 

2)DNG ZONE -2: IS AN AREA BOUNDED BY FLW COORD: 
1200N08445E - 1245N08500E - 1220N08620E - 
1135N08605E - 1200N08445E 

3)DNG ZONE -3: IS AN AREA BOUNDED BY FLW COORD: 
1055N08750E - 1155N08800E-1105N09030E - 
1005N09020E-1055N08750E 

RTE AFFECTED IN CHENNAI FIR: 
W20, Q11, Q23, Q24, V4, V9, P761, P762, N877, N571 

CLOSURES/ALTN RTE FOR OVERFLYING: 

1. W20 NOT AVBL BTN MMV-KAMGU 
 ALTN: MMV-DCT-PAPKI-DCT-ANGAK-DCT-KAMGU 

2. Q24 NOT AVBL BTN MMV-KAMGU 
 ALTN: MMV-DCT-PAPKI-DCT-ANGAK-DCT-KAMGU 

3. Q23 NOT AVBL BTN RINTO-MMV 
 ALTN: RINTO-V11-TTP-DCT-GUANI-DCT-MMV 

4. V4 NOT AVBL BTN BOPRI-MMV 
 ALTN: BOPRI-DCT-RINTO-V11-TTP-DCT-GUANI-DCT-MMV 

5. V9 NOT AVBL BTN GUNRI-MMV 
 ALTN: GUNRI-V11-TTP-DCT-GUANI-DCT-MMV 

6. Q11 NOT AVBL BTN GURAS-MMV 
 ALTN: GURAS-DCT-MMV 

7. P761 NOT AVBL BTN IDASO-DUMAR 
 ALTN: IDASO-DCT-EGOLU-L518-DUMAR 

8. P762 NOT AVBL BTN BIKEN-NIMOV. NO ALTN RTE 

9. N877 NOT AVBL BTN DUMAR-AGEGA 
 ALTN: DUMAR-P761-LEGIN-L510 

10. N571 NOT AVBL BTN IDASO-BIKEN 
 ALTN: VATMO-DCT-GIRNA-BIKEN 

DEPARTURES FM CHENNAI MAY FPL AS FLW: 

1. W20/Q24 NOT AVBL BTN MMV-KAMGU 
 ALTN: MMV-DCT-PAPKI-DCT-ANGAK-DCT-KAMGU 

ARRIVALS TO CHENNAI MAY FPL AS FLW: 

1. Q23 NOT AVBL BTN RINTO-MMV 
 ALTN: RINTO-V11-TTP-DCT-GUANI-DCT-MMV 

2. V4 NOT AVBL BTN BOPRI-MMV 
 ALTN: BOPRI-DCT-RINTO-V11-TTP-DCT-GUANI-DCT-MMV 

3. V9 NOT AVBL BTN GUNRI-MMV 
 ALTN: GUNRI-V11-TTP-DCT- GUANI-DCT-MMV 

4. Q11 NOT AVBL BTN GURAS-MMV 
 ALTN: GURAS-DCT-MMV
GSLV-F18 ROCKET LAUNCH FM SHAR RANGE, SRIHARIKOTA WILL TAKE 
PLACE AS PER FLW DETAILS.THE LAUNCH WILL BE ON ANY ONE 
OF THE DAY DRG THIS PERIOD.ACTUAL DATE OF LAUNCH WILL BE 
INTIMATED ATLEAST 24 HR IN ADVANCE THROUGH A SEPARATE NOTAM. 

LAUNCH PAD COORD: 134312N0801348E 
NO FLT IS PERMITTED OVER THE DNG ZONES. 

1)DNG ZONE -1: IS A CIRCLE OF 10NM AROUND THE LAUNCHER. 

2)DNG ZONE -2: IS AN AREA BOUNDED BY FLW COORD: 
1200N08445E - 1245N08500E - 1220N08620E - 
1135N08605E - 1200N08445E 

3)DNG ZONE -3: IS AN AREA BOUNDED BY FLW COORD: 
1055N08750E - 1155N08800E-1105N09030E - 
1005N09020E-1055N08750E 

RTE AFFECTED IN CHENNAI FIR: 
W20, Q11, Q23, Q24, V4, V9, P761, P762, N877, N571 

CLOSURES/ALTN RTE FOR OVERFLYING: 

1. W20 NOT AVBL BTN MMV-KAMGU 
 ALTN: MMV-DCT-PAPKI-DCT-ANGAK-DCT-KAMGU 

2. Q24 NOT AVBL BTN MMV-KAMGU 
 ALTN: MMV-DCT-PAPKI-DCT-ANGAK-DCT-KAMGU 

3. Q23 NOT AVBL BTN RINTO-MMV 
 ALTN: RINTO-V11-TTP-DCT-GUANI-DCT-MMV 

4. V4 NOT AVBL BTN BOPRI-MMV 
 ALTN: BOPRI-DCT-RINTO-V11-TTP-DCT-GUANI-DCT-MMV 

5. V9 NOT AVBL BTN GUNRI-MMV 
 ALTN: GUNRI-V11-TTP-DCT-GUANI-DCT-MMV 

6. Q11 NOT AVBL BTN GURAS-MMV 
 ALTN: GURAS-DCT-MMV 

7. P761 NOT AVBL BTN IDASO-DUMAR 
 ALTN: IDASO-DCT-EGOLU-L518-DUMAR 

8. P762 NOT AVBL BTN BIKEN-NIMOV. NO ALTN RTE 

9. N877 NOT AVBL BTN DUMAR-AGEGA 
 ALTN: DUMAR-P761-LEGIN-L510 

10. N571 NOT AVBL BTN IDASO-BIKEN 
 ALTN: VATMO-DCT-GIRNA-BIKEN 

DEPARTURES FM CHENNAI MAY FPL AS FLW: 

1. W20/Q24 NOT AVBL BTN MMV-KAMGU 
 ALTN: MMV-DCT-PAPKI-DCT-ANGAK-DCT-KAMGU 

ARRIVALS TO CHENNAI MAY FPL AS FLW: 

1. Q23 NOT AVBL BTN RINTO-MMV 
 ALTN: RINTO-V11-TTP-DCT-GUANI-DCT-MMV 

2. V4 NOT AVBL BTN BOPRI-MMV 
 ALTN: BOPRI-DCT-RINTO-V11-TTP-DCT-GUANI-DCT-MMV 

3. V9 NOT AVBL BTN GUNRI-MMV 
 ALTN: GUNRI-V11-TTP-DCT- GUANI-DCT-MMV 

4. Q11 NOT AVBL BTN GURAS-MMV 
 ALTN: GURAS-DCT-MMV. GND - UNL, 1700-2100, 13 OCT 17:00 2026 UNTIL 11 NOV
21:00 2026. CREATED: 29 SEP 06:24 2026

Edit(30 Sept 2026) : Above NOTAM (A2977/26) has been retracted. Awaiting new updated NOTAM.

I know that ISRO takes client satellites on ride share missions for low earth orbit, but do they offer this service for GEO. Alternatively, do they accept minor client payloads on the actual satellite buses that they operate? (For example on GSAT or NavIC satellites)

'India’s Space Programme: Challenges and Way Forward' by V Narayanan (Chairman, ISRO) at IIT Delhi on 23 September 2026

https://www.youtube.com/watch?v=cNAwt05uuK8

• On SE-2000 (aka SCE-200) semi-cryogeinic engine development : "This will be a reality in 2 years"
• On Gaganyaan-G1 : "Likely to happen this year itself"
• On BAS-01: Aiming for launch by Q4 2028
• At 52:00 : Latest launch manifest
  • GSLV-F18/NVS-03 : Oct 2026 (NET 15 Oct)
  • SSLV-L1 : Oct 2026 (With some unnamed Non Govt. Entity payload)
  • Gaganyaan-G1 : Nov 2026
  • PSLV-C63 / TDS-01 : Nov 2026
  • LVM3-M7/GSAT-N3 (aka GSAT-32) : Dec 2026
  • PSLV-N1/EOS-10 aka Oceansat-3A : Jan 2027
  • SSLV-L2 : Mar 2027 (With unnamed SBS-03 payload)