Company Name: ispace, inc., Japan
Potentially available for future missions
Planned Mission(s): ispace Mission 2
First Mission Launch: 2024
Payload Delivery Locations: To Be Announced
First Mission Lander: HAKUTO-R Lander
Rover Mass: To Be Announced
Rover Dimensions: 53 X 60 cm, Height - 35 cm
Rover Mobility: Speed - Up to 0.1 m/s, Rove up to 500 m from the landing site & Cover more than 2 km in one lunar day
Payload Bay - Available Mass: 3.5 kg
Power Source Type: Solar panels
Power Generation and Usage: Generates up to 20 W.
When stationary - uses approximately 5 W of power for housekeeping and communications.
When moving - uses approximately 40 W of power.
Power distribution (for payload): On rover - 1.0 W/kg. The rover provides a total of 18 W of power for Payloads.
Interfaces Available for Payload: Ethernet, RS422 and 3.3V UART.
Rates during surface operations - 50 kbps per kg of payload for downlink
Rates for check-out during the cruise - 2 kbps per kg of payload for downlink,
X band for lander-Earth uplink and downlink. Wi-Fi and sub-Ghz communications between mobile payloads and lander.
Expected Working Duration: Flight duration is a Maximum of 4 months & The duration of nominal surface operations is 12 sunlit days
First Mission Rover Manifest:
It will be equipped with high-definition, colour photo and video, and terrain mapping capabilities, among other data acquisition technologies. Its design is universal in nature, consisting of a “rover bus” comprising standard structural, thermal management and mobility systems with basic functionality for imaging, near-real-time video and near-real-time teleoperation. Depending on customer needs, this can be made up of several payloads from different customers, or from a tailored suite of payloads for a dedicated, customer-specific mission.