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SpaceRadar | Payload Selection Tool

Micro Rover

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: ~ 5 kg

Rover Dimensions: 26 cm tall, 31.5 cm wide, and 54 cm long

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. 

Communications Available: 

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.

Last Updated on August 2022

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