Frequently asked questions

The different types of payloads that can be integrated on Team Indus Lunar Lander is defined as follows Basic Operations on lunar surface, more data intensive with higher uplink/downlink volumes.
  • The minimum mass and volume for the different classes of payload is as follows and is also given in the PUG
  • Basic: Mass – 1 kg, Volume – 1U (1U – 10 x 10 x 11.35 cm)
  • Standard: Mass – 1 kg, Volume – 1U (1U – 10 x 10 x 11.35 cm)
  • Observatory: Mass – 2 kg, Volume – 2U (1U – 10 x 10 x 11.35 cm)
  • Exploration: Mass – 3.5 kg, Volume – 4U (1U – 10 x 10 x 11.35 cm)
  • Any increment for the above categories are allowed subject to a maximum mass growth of 1 kg and envelope evaluation.
The landing site planned for TI lunar lander is 20 km x 16 km centered at 35.25 deg N and 29.23 deg W in Mare Imbrium. Data for this landing site is available publicly from Planetary Data System. There are no alternate landing sites planned.
The lunar landing is planned to occur at dawn + 12hrs at the landing site. Surface operations will continue for 1 lunar day (14 Earth days). Payload operations can begin as early as day 2 (36 hrs post landing).
All payloads are expected to be non-operational during flight. Payloads will be commissioned post touchdown on lunar surface. Operations during orbit if needed can be requested and will be evaluated as per operations plan.
The Lander is capable of 1 Mbps downlink in X-band. This link will be shared amongst all payloads and Team Indus Rover. The telemetry from payloads will be scheduled for offline delivery. Real-time telemetry can be requested for Observatory and Exploration class payloads.
The payload will be delivered to Team Indus office in Bangalore, India for integration onto the lander and carrying out Integrated Spacecraft Testing by June, 2017. The payload has to be pre-qualified for the test levels and duration as mentioned in the Payload User Guide only after which the payload will be accepted for integration.
The qualification tests required for the payload are vibration, thermo-vacuum and EMI/EMC testing. EMI/EMC test will be taken up case to case basis. The levels and duration for these qualification tests are detailed in the Payload Users Guide.
The compliances and declarations required for payload integration are qualification test reports for vibration, thermos-vacuum, EMI/EMC. Compliances for operational power consumption and material declaration needs to be provided to ascertain no out gassing.
There is no provision for payload software update during flight.
The ground checkout operations for payloads will be done during integrated spacecraft testing at integration facility.
Team Indus Mission Operations Center will forward telecommand and telemetry to and from the payload operations center (PC at customer end, on VPN) to the spacecraft as per operations schedules agreed upon post sign-off. Provision for carrying out payload operations at Team Indus Mission Operations Center by the customer can also be requested.
Request can be made for the qualification tests to be done by Team Indus. This will be a separate engagement and the pricing for this can be provided later.
The payload can have 1 or more degree of freedom; in such cases the acceptable field of view requirement has to be conveyed to Team Indus. The onstraints will only be mass, volume and qualification tests.
There is no provision for payload on the Rover for TeamIndus GLXP mission.