Hardware

Mission Space develops ultra-compact instruments for radiation monitoring, including charged particle flux spectrometry, surface charge investigations, and lunar environmental monitoring. Sensors are designed for space-origin missions: onboard satellites and spacecraft, from LEO to lunar orbiters and landers.

Leemr Lunar Dust and
Surface-Charging Monitor

LEEMR unit combines a surface charge sensor with a dust-sensitive module, enabling simultaneous measurement of both ambient electrostatic conditions and the specific contribution of dust to local charging. Intended for deployment as a part of ground-based lunar weather monitoring stations, it provides real-time data on surface charging dynamics, supporting operational safety and prolonging the lifespan of lunar exploration equipment. Accurate monitoring of dust-induced charging is essential for informed decision-making during infrastructure deployment and ongoing lunar activities.

Capabilities:

1
Charged lunar dust detection
1
Surface charge accumulation monitoring
1
Dust density variation measurement
1
Dust charging level measurement
1
Active and passive dust-sensing configurations
1
Real-time local electrostatic environment data
1
Compact, low-power modular form factor

Heritage / Development Status:

1
Selected by NASA
1
Developed in collaboration with NASA Goddard Space Flight Center
1
TRL 7 in 2027
1
Built on Mission Space ZOHAR electronics and autonomous measurement software heritage

Leemr Lunar Dust and
Surface-Charging Monitor

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Capabilities:

1
Charged lunar dust detection
2
Surface charge accumulation monitoring
3
Dust density variation measurement
4
Dust charging level measurement
5
Active and passive dust-sensing configurations
6
Real-time local electrostatic environment data
7
Compact, low-power modular form factor

Heritage:

1
Selected by NASA
2
Developed in collaboration with NASA Goddard Space Flight Center
3
TRL 7 in 2027
4
Built on Mission Space ZOHAR electronics and autonomous measurement software heritage

ZOHAR-I Sensors

(Flight-Proven)

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Capabilities:

1
Electron, proton, and alpha-particle spectra via silicon telescopes
2
Cosmic rays and SEP flux via Cherenkov detectors
3
Sub-second measurement cadence
4
<1 W power, compact form factor

Heritage:

1
Flight proven
2
Pathfinder mission launched in March 2025 on Transporter-13
3
Global Tech Award 2025 recipient

SOLARIS Suite

The SOLARIS suite is a ruggedized, ultra-compact radiation monitoring suite engineered for high-fidelity space weather investigations in the solar system’s harshest environments.

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Capabilities:

1
Advanced Multi-Sensor Payload
2
Deep-Space Hardened Design
3
High-Cadence Dynamics
4
Ultra-Low SWaP Footprint
5
Modular Scalability

Development Status:

1
Flight-ready configurations available for integration starting 2028
Pipeline
PL-3
Surface Charge Monitor
Pipeline
PL-4
Solar UV / X-Ray Monitor
Pipeline
PL-4
X-Ray / Soft Gamma-Ray / Electron Spectrometer

Proposed Sets Of Instruments

Orbiter set

1
PL-1f, 2 x units (Zenith- and Nadir-oriented)
1
PL-2, 2 x units coaxial to PL-1
1
Mass: <2kg

Lander set

1
PL-1m unit (Looking sideways)
1
PL-2 unit
1
Mass: <1kg

Payload specifications

Parameters
PL-1f
PL-1m
PL-2
PL-3m
Dimension I x w x h, mm
85 x 50 x 70
85 x 50 x 75
147 x 95 x 30
85 x 50 x 60**
Mass, no more than, kg
<0.6
<0.6
<0.7
< 1**
Power consumption, W
< 1
< 1
< 1
< 1.5**
Charged particles ranges, MeV: electrons protons
0.1 … 10 1… 250
0.1 … 10 1 … 250
>5 >450
Collected excess charge; Induced potential; Dust density
Data produced, MiB/day *
1…75
10…250
1…70
1…50
FoV
25…50
90…110
Omni
Hemisphere
Delivery time, m
3
5**
3
Parameters
PL-1f
PL-1m
PL-2
PL-3m
Dimension I x w x h, mm
85 x 50 x 70
85 x 50 x 75
147 x 95 x 30
85 x 50 x 60**
Mass, no more than, kg
<0.6
<0.6
<0.7
< 1**
Power consumption, W
< 1
< 1
< 1
< 1.5**
Charged particles ranges, MeV: electrons protons
0.1 … 10 1… 250
0.1 … 10 1… 250
>5          >450
Collected excess charge; Induced potential; Dust density
Data produced, MiB/day *
1…75
10…250
1…70
1…50
FoV
25…50
90…110
Omni
Hemisphere
Delivery time, m
3
5**
3
-
Auxiliary parameters: 9-axis sensor*
PL-1: Silicon telescope; PL-2:Cherenkov detector;    PL-3m: Flat Langmuir probe + Capacitance sensor


Closing the LEO Sensing Gap

Real-Time Multi-Point SW Monitoring

Download our white paper:

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