u/Ohsin

Design & Development of Radar Altimeter for landing experiments (C-Band and X-Band)

> Introduction

> Space Applications Centre (SAC), one of the principal centers of Indian Space Research Organization (ISRO), is responsible for design and development activities related to Space Programs like earth and planetary observation, communication and navigation and also responsible for design and development of radar altimeters for landing experiments. Radar Altimeter is envisaged to be part of multiple landing experiments being planned by ISRO, which requires a large number of units on production scale. These altimeters are now required to be designed and developed from the industry resources

Main document (X-Band): [PDF] [Archived]

RFP : [PDF] [Archived]

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> Introduction > > Space Applications Centre (SAC), one of the principal centers of Indian Space Research Organization (ISRO), is responsible for design and development activities related to Space Programs like earth and planetary observation, communication and navigation. A Radar Altimeter has been successfully designed, realized and utilized in lunar missions of ISRO. Radar Altimeter is envisaged to be part of multiple missions being planned by ISRO, which requires a large number of units on production scale. These altimeters are now required to be designed and developed from the industry resources.

Main document (C-Band) : [PDF] [Archived]

RFP : [PDF] [Archived]

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Table-1: Specifications of Radar Altimeter

Parameter	Specification
Altitude of operation	1.5 km to 0.5m
Operating velocity regime	Up to 100 m/s
Attitude (Roll,Pitch )	Better than (±20 degrees,±20 degrees_
Altitude Accuracy (3σ)	≤40 cm or 0.3% of altitude, whichever is higher.
Altitude Update Rate to Platform	40 ms

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!

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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

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Edit(30 Sept 2026) : Above NOTAM (A2977/26) has been retracted.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

Following up on previous thread by /u/guru-yoda

Excerpt from 'Minutes of the 102nd meeting of the Radio Regulations Board' (29 June to 3 July 2026) [PDF] [Archived]

From Page 30 and onward.

> Submission by the Administration of Liechtenstein (Principality of) requesting an extension of the second milestone period (M2) for the 3ECOM-1 satellite system

> (…) He explained that, with the second milestone period for the 3ECOM-1 system expiring on 10 June 2026, and NewSpace India Limited, the provider that the operator had originally planned to entrust with the launch, having grounded its fleet following a launch failure on 12 January 2026, the Administration of Liechtenstein had outlined what it viewed as reasons justifying an extension until 30 June 2027 on grounds of force majeure. According to the administration, the launch service disruption had prevented the planned launch and deployment of 24 satellites intended to contribute to meeting the 50 per cent deployment requirement for the system.

> (…) While the 12 January 2026 launch failure might be classed as a force majeure event, it was far from certain that any satellites could have been launched by 10 June 2026, taking into account the need for final testing and for transport from the manufacturing facility in the United Kingdom to the launch site in India. By December 2025, no formal contract had been signed with the potential launch service provider; Attachment MR-2 referred only to a “bilateral letter of intent”. On that basis, he did not consider that the conditions for granting an extension on grounds of force majeure had been satisfied and could not accede to the administration’s request.

> * The M2 regulatory time-limit for the 3ECOM-1 satellite system had been 10 June 2026; > * The satellite operator had been in discussion with a launch service provider to finalize a contract for the launch of 24 satellites via two dedicated launches to take place in May 2026 when the launch vehicle intended to be used to launch the satellites had suffered a failure on 12 January 2026; > * The satellite operator had made efforts to find alternative launch options before the M2 regulatory time-limit, but without success; > * A contract with a new launch service provider had been signed on 12 June 2026 for four launch service missions to launch the 24 satellites between September 2026 and June 2027; > * The administration was seeking an extension of the M2 regulatory time-limit to 30 June 2027 owing to force majeure; > * By 5 June 2026, 28 satellites had been either completed or at a very late stage of manufacture (subject to final launch-specific testing); however, no details had been provided on the status of the satellites’ construction and the project milestones before and after the force majeure event.

> Based on the information provided, the Board concluded that the situation might qualify as a case of force majeure but that additional information was required to demonstrate that all conditions of force majeure had been satisfied. > > Consequently, the Board was not in a position to accede to the request from the Administration of Liechtenstein at that meeting and invited the Administration of Liechtenstein to submit to the 103rd meeting of the Board the following information: > > * The project milestones for the construction and launch of the satellites in sufficient detail to demonstrate that 24 satellites could have been deployed in time to meet the M2 regulatory time-limit if not for the force majeure event; > * The status of the satellites’ construction prior to the failure of the launch vehicle on 12 January 2026; > * A description of the satellite project and deployment plan and a rationale for the differences with the one presented at the 93rd meeting.

From their previous ITU filings the orbit of 3ECOM-1 deployment is 1057 km (circular orbit) with 89° inclination. Two satellites MR-1 and MR-2 were launched by RocketLab in Jan 2026.

Not sure if they actually signed the contract with NSIL and if they did whether it is still on or not.

Realization of Rate Gyro Package based on MEMS Gyroscope (RGPM)

[PDF] [Archived]

> (…) > > 2.2 Need of the Expression of Interest (EoI) > > The aim is to develop parties for realization of Rate Gyro Packages based on MEMS gyroscopes after due understanding of the technological challenges, risks, investments and returns. > > 2.3 Scope of RGPM Realization > > Scope of the project includes end-to-end realization of 25 sets of RGPMs (50 no.s). Activities related to initial 1 set (2 no.s) will be carried out with essential minimal guidance from IISU in order to make the party familiar with the technology. Once the familiarization is complete the party will be responsible of the following activities. > > * Procurement of raw materials & electronic components > * Printed Circuit Boards (PCB) fabrication > * Mechanical hardware fabrication > * Wiring of electronic cards > * Quality Control (QC) inspection – Electrical and Mechanical > * Card level testing including development of test station > * System integration & integrated level tests > * Final QC & QA clearance certificates > * Presentation of test results to review forum in IISU > * Delivery to IISU with log files of production & test results > > 2.4 Description of RGPM > > Rate Gyro Package – MEMS (RGPM) is designed with ISRO Coriolis Resonator Gyroscope – Digital for control applications of Launch Vehicle (LV). System is configured to meet the objectives of faster development, cost effectiveness, production friendliness, miniaturization and mass reduction. > > RGPM system consist of > > a. Sensors (Three nos. of gyros) : FIM - will be supplied by IISU. 3 iCRGDs hard mounted on chassis in orthogonal direction > > b. Mechanical h/w : Housing + 4 covers > > c. RGPM Electronics Card (REC)1 no. card. 1553B i/f to NGC bus through HOLT device. Power & Signal routing of iCRGDs through RGPM electronics card. > > d. DC-DC 1 no. : PCB based DC-DC Redundancy is achieved in LV by using 2 no.s of RGPM. > > Redundancy is achieved in LV by using 2 no.s of RGPM. > > Overall size, mass and power of the system is given below. > > * Size : 136 mm x 120 > > * Mass : 1.3 kg > > * Power : 4 W > > The party shall be responsible for the safe custody of FIMs issued.

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* FIM = Free Issue Material

* iCRGD = ISRO Coriolis Resonator Gyroscope - Digital

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See also:

• ISRO Coriolis Resonator Gyro on Pg.7 [PDF] (Source)
• EoI for SSLV's MINS-6S