Sampie Booysen
Co-founder and CTO
We deeply value their personalized service. From facilitating valuable connections within the global space industry, to providing valuable market insight reports, working with satsearch has significantly influenced our sales processes.
The platform allows us to present our communication systems to the right audiences at the right time. We are especially grateful for how the program has accelerated our business growth.
Astrid Kjeldal
Sales Manager & Team Lead
When working on the commercialization of space, it is essential to make the procurement process as easy and uncomplicated as possible, and this is where satsearch offers an excellent marketplace for the space industry and helps give a great overview for the customer of what the market has to offer.
As a satellite supplier and a satsearch partner, we have had many sales inquiries through satsearch, many of whom are our customers today.
Alberto Ordaz Acero
BD Manager
Satsearch is a must for satellite products and services suppliers to showcase their catalogue effectively, resulting in increased visibility and sales opportunities.
The great team behind satsearch also helps connecting with a global network of potential customers and bringing great monthly reports.
Thomas Yen
CEO
We have worked with satsearch since the early days of Tensor Tech and it has always been an important partner for us.
Unlike how sales traditionally works in the space industry, satsearch provides a transparent way for buyers to look for suitable suppliers and products.
I believe they have truly fostered the growth of the industry.
Tensor Tech, as a user, has also enjoyed the way we update our information, monitor the traffic for data analysis, and attract more international clients.
Ronnie Nader
Chief Designer and Director of Space Operations
Ever since we signed up for satsearch back in 2019 it was an immediate hit and it has been a game changer for us.
The people involved really want their users to succeed, they do understand the industry and the market and not only that, but for providers, the relationship has been a constant feedback about what works and what does not, who is who in the landscape and all that knowledge serves to improve the platform and the quality of the leads.
We also have other leads providers, so we can compare, and none gets to the level of satsearch. In short, satsearch works, period.
Struan Johnston
Director
It has become a well known supply chain platform for the industry and a great place to find and compare different suppliers in a fraction of the time.
As a manufacturer of satellite components, we have grown our reach and audience using satsearch as a marketing channel, and met many of our customers via satsearch for the first time.
Sampie Booysen
Co-founder and CTO
We deeply value their personalized service. From facilitating valuable connections within the global space industry, to providing valuable market insight reports, working with satsearch has significantly influenced our sales processes.
The platform allows us to present our communication systems to the right audiences at the right time. We are especially grateful for how the program has accelerated our business growth.
Astrid Kjeldal
Sales Manager & Team Lead
When working on the commercialization of space, it is essential to make the procurement process as easy and uncomplicated as possible, and this is where satsearch offers an excellent marketplace for the space industry and helps give a great overview for the customer of what the market has to offer.
As a satellite supplier and a satsearch partner, we have had many sales inquiries through satsearch, many of whom are our customers today.
Alberto Ordaz Acero
BD Manager
Satsearch is a must for satellite products and services suppliers to showcase their catalogue effectively, resulting in increased visibility and sales opportunities.
The great team behind satsearch also helps connecting with a global network of potential customers and bringing great monthly reports.
Thomas Yen
CEO
We have worked with satsearch since the early days of Tensor Tech and it has always been an important partner for us.
Unlike how sales traditionally works in the space industry, satsearch provides a transparent way for buyers to look for suitable suppliers and products.
I believe they have truly fostered the growth of the industry.
Tensor Tech, as a user, has also enjoyed the way we update our information, monitor the traffic for data analysis, and attract more international clients.
Ronnie Nader
Chief Designer and Director of Space Operations
Ever since we signed up for satsearch back in 2019 it was an immediate hit and it has been a game changer for us.
The people involved really want their users to succeed, they do understand the industry and the market and not only that, but for providers, the relationship has been a constant feedback about what works and what does not, who is who in the landscape and all that knowledge serves to improve the platform and the quality of the leads.
We also have other leads providers, so we can compare, and none gets to the level of satsearch. In short, satsearch works, period.
Struan Johnston
Director
It has become a well known supply chain platform for the industry and a great place to find and compare different suppliers in a fraction of the time.
As a manufacturer of satellite components, we have grown our reach and audience using satsearch as a marketing channel, and met many of our customers via satsearch for the first time.
Browse the latest capabilities that qualified buyers
are looking for on satsearch right now
| # | Parameter | Requirement | Response |
| 1 | Physical Properties | Payload Mass (kg) | < 15 kg |
| 2 | Payload Volume (U or m3) | 200 x 300 x 200 mm | |
| 3 | General | Payload type e.g. RF, EO (RGB, HS, MS IR) | Optical Payload |
| 4 | Desired orbits e.g. SSO, near-equatorial | SSO | |
| 5 | Desired altitudes e.g. 550 km | 500 km | |
| 6 | EPS | Payload continuous power (W) | < 25 W |
| 7 | Payload peak power (W) | < 50 W | |
| 8 | Payload duty cycle per orbit (%) | 70 | |
| 9 | Payload voltage supply e.g. 3V3, 5V, 12V | 12 V | |
| 10 | RF | High-speed downlink required e.g. > 5 Mbps? | < 15 Mbps |
| 11 | Daily data budget (Mb or Gb) | < 5 Gb | |
| 12 | Encryption required on TTC or payload data e.g. AES-256? | no | |
| 13 | Interfaces | Bus to payload interfaces required e.g. CAN, I2C, SPI, UART, RS422, RS485, PPS | CAN |
| 14 | On-board data storage requirements? | yes | |
| 15 | ADCS | Payload Pointing Modes when active e.g. Nadir | Nadir |
| 16 | Pointing Accuracy | No requirements | |
| 17 | Pointing Knowledge | No requirements | |
| 18 | Slew Rate (°/s) requirements? | No requirements | |
| 19 | GPS required for position, velocity knowledge? | No requirements | |
| 20 | Propulsion | Propulsion Required? | Yes |
| 21 | Propulsion type requirement e.g. electric, chemical? | Electric. Which type of electric propulsion is used and what are the parameters? We need to understand the impact on the optical system. | |
| 22 | Propulsion system use e.g. orbit maintenance | Orbit maintenance, De-orbit | |
| 23 | Propulsion thrust or delta V requirements? | 3-5 mN | |
| 24 | Operations | Operations duration e.g. 6 months, 12 months | 3-4 years |
| 25 | Summary of payload operations or CONOPS? | 26 months | |
| 26 | Other | Any other comments or notes? E.g. ITAR restrictions, ground station requirements. | No ITAR restrictions |
| 27 | Other | Anything else? E.g. budgetary or lead time requirements. | Lead time: 12 months |
| Category | Requirement Parameter | Buyer Target Value | Units / Options | Criticality / Description |
| MISSION ARCHITECTURE | ||||
| MISSION ARCHITECTURE | Target Orbit Altitude | 500 km | km (e.g., 500 km) | Directly influences ground sampling distance (GSD) |
| MISSION ARCHITECTURE | Orbit Type | LEO | SSO / LEO / Equatorial | Sun-Synchronous Orbit (SSO) is standard for optical imaging |
| MISSION ARCHITECTURE | Local Time of Ascending Node (LTAN) | 10:30 | HH:MM (e.g., 10:30) | Determines solar illumination angles on target areas |
| MISSION ARCHITECTURE | Design Lifetime Target | 5 | Years | Determines radiation shielding and component screening levels |
| OPTICAL & IMAGING PERFORMANCE | ||||
| OPTICAL & IMAGING PERFORMANCE | Panchromatic GSD (Nadir) | 30cm | meters (e.g., 0.3m - 0.5m) | Ground Sampling Distance at lowest point of orbit |
| OPTICAL & IMAGING PERFORMANCE | Multispectral GSD (Nadir) | 50cm - 80cm | meters (e.g., 1.2m - 2.0m) | Typically 4x coarser than Panchromatic band |
| OPTICAL & IMAGING PERFORMANCE | Swath Width | 10km | km (e.g., 10 km - 15 km) | Cross-track imaging coverage width per pass |
| OPTICAL & IMAGING PERFORMANCE | Spectral Bands Required | PAN + MS (6 configurable bands) | Text List (e.g., PAN, R, G, B, NIR) | Define VNIR, SWIR, or Thermal requirements |
| OPTICAL & IMAGING PERFORMANCE | Modulation Transfer Function (MTF) | >10% | Value @ Nyquist (e.g., > 0.15) | Measures image sharpness and optical quality |
| OPTICAL & IMAGING PERFORMANCE | Signal-to-Noise Ratio (SNR) | >200 at 100% albedo | Ratio (e.g., > 150) | Specified at a reference solar radiance level |
| OPTICAL & IMAGING PERFORMANCE | Quantization Bit Depth | 12 | bits (e.g., 12-bit / 14-bit) | Dynamic range and radiometry resolution |
| ELECTRICAL & DATA INTERFACES | ||||
| ELECTRICAL & DATA INTERFACES | Instrument Peak Power | 275 | Watts | Maximum power consumption during imaging operations |
| ELECTRICAL & DATA INTERFACES | Instrument Standby Power | Watts | Power consumed between imaging passes (e.g., thermal maintenance) | |
| ELECTRICAL & DATA INTERFACES | Raw Payload Data Interface Protocol | Spacewire | SpaceWire / SpaceFibre / LVDS / SerDes | High-speed data bus from camera unit to satellite mass memory |
| ELECTRICAL & DATA INTERFACES | Command & Telemetry Interface | RS-422 / MIL-STD-1553 | CAN Bus / RS-422 / I2C / MIL-STD-1553 | Low-speed command link to the main On-Board Computer (OBC) |
| ELECTRICAL & DATA INTERFACES | Payload Core Voltage Supply | 28V regulated | V (e.g., 28V regulated / unregulated) | Spacecraft main power bus compliance standard |
| MECHANICAL, STRUCTURAL & THERMAL | ||||
| MECHANICAL, STRUCTURAL & THERMAL | Payload Maximum Mass Allocated | 130 | kg | Strict ceiling for telescope + focal plane array + electronics |
| MECHANICAL, STRUCTURAL & THERMAL | Maximum Envelope Allocations | 0.5 x 0.5 x 0.85 m | X x Y x Z mm | Volumetric constraints inside launch vehicle fairing |
| MECHANICAL, STRUCTURAL & THERMAL | Optical Alignment Stability | Arcseconds / μrad | Max structural distortion allowed due to thermal gradients | |
| MECHANICAL, STRUCTURAL & THERMAL | Operational Temperature Range | 0°C to 50°C | °C to °C | Narrow thermal windows are often required for optical optics |
| MECHANICAL, STRUCTURAL & THERMAL | Thermal Control Responsibility | Host controlled | Autonomous / Host-controlled | Does payload feature own heaters or rely on platform? |
| PRODUCT ASSURANCE & QUALITY | ||||
| PRODUCT ASSURANCE & QUALITY | Quality Standard Compliance | AS9100 | AS9100 / ECSS / NASA-STD | Space agency or aerospace quality system standard |
| PRODUCT ASSURANCE & QUALITY | Radiation Tolerance (TID) | 30 | krad (Si) | Total Ionizing Dose minimum resilience based on orbit |
| PRODUCT ASSURANCE & QUALITY | Calibration Strategy | Solar | On-board Lamp / Solar / Vicarious | Requirement for radiometric and geometric calibration |
We are a graduate research team in South Korea, developing
a 6U CubeSat for an advanced-track CubeSat competition. We are looking for an
ONBOARD AI PAYLOAD PROCESSOR and would like to gather options and approximate
pricing from multiple suppliers.
Mission summary:
- 6U CubeSat, LEO (~500–600 km)
- Primary mission: optical observation of resident space objects / debris
- Imaging triggered by TLE predictions (event-based capture, no active tracking)
- Onboard AI task: detection + coarse classification of space objects from
captured monochrome images (batch / event-based inference, NOT continuous
real-time processing — so heavy compute is not required)
Requirements / preferences for the AI processor:
- CubeSat-compatible form factor, within ~1U, low power (6U power budget)
- Capable of running a lightweight CNN for detection + coarse classification
- Data interface able to receive images from a monochrome CMOS camera
- Radiation mitigation suitable for a short LEO mission
- LOW COST is a priority — please indicate the most budget-friendly option
and any academic / research / student-competition discount
- Engineering model (EM) availability for ground testing is a plus
For each suggested product, we would like:
1. Approximate unit price (+ academic/research discount if any)
2. Lead time
3. AI performance (TOPS), power consumption, size, mass, interfaces
4. Flight heritage / TRL and radiation-mitigation approach
5. Export-control status for shipping to South Korea
Expected timeline: [launch around 2027 /delivery date]. Quantity: [e.g. 1 EM + 1 FM]
RFQ for Reaction wheels with at least 4Nms momentum storage and max torque of at least 250 mNm
| Category | Parameter | Mission Requirement | Expected Unit / Format | Notes & Testing Conditions |
| Volume | Number of units | 20-50 | pcs | Possibility to scale up if price is good |
| Electrical (AM0) | BOL Efficiency | ≥ 28% (ideally 29–30% | % | Measured at AM0, 28°C |
| EOL Efficiency | ≥ 24% after mission | % | At mission-specific radiation dose | |
| Max Power Voltage (Vmp) | ≥ 2.2 V | V | Measured at AM0, 28°C | |
| Max Power Current (Imp) | As high as possible | mA/cm² or A | Measured at AM0, 28°C | |
| Open-Circuit Voltage (Voc) | ≥ 2.5 V | V | Measured at AM0, 28°C | |
| Short-Circuit Current (Isc) | As high as possible | mA/cm² or A | Measured at AM0, 28°C | |
| Mechanical | Cell Architecture | Triple Junction (GaInP/GaAs/Ge) or high-end IBC Mono Si | Text | e.g., 3J (InGaP/InGaAs/Ge) |
| Cell Dimensions | 40 × 80 mm (±0.5 mm) or similar | mm x mm | Width x Length | |
| CIC Assembly | Coverglass Thickness | 100 – 300 µm | µm or mils | |
| Coverglass Coatings | AR + UV Rejection | Text | e.g., AR, UV Rejection | |
| Interconnect Design | Standard with stress relief | Text | Material and stress relief type | |
| Bypass Diode Type | External Si diode | Text | Monolithic or Discrete | |
| Contact Layout | Front-to-Back or All-Back | Text | e.g., Front-to-Back, All-Back | |
| Heritage & QA | Flight Heritage | LEO preferred | Orbit / Mission List | Proven in LEO/MEO/GEO? |
| Space Standard Auth. | ECSS or equivalent | Text | e.g., ECSS, AIAA | |
| LAT Documentation | Yes | Yes/No | Lot Acceptance Test reports |
1. Educational Satellite Development Kit
• For teaching spacecraft subsystems, embedded systems, communications, power management, and mission operations Qty: 1
2. Single Axis Reaction Wheel Module
• For attitude determination and control experiments
• Compatible with educational satellite platforms Qty: 1
3. Satellite Test Bench – FlatSat Configuration
• Hardware in the loop (HIL) test bench
• For subsystem integration, verification, validation, and FlatSat testing Qty: 1
4. 2U Satellite Structure Expansion Kit
• Modular structure for additional payloads and subsystems Qty: 1
5. Satellite Storage & Transport Case
• Protective case for satellite hardware and accessories Qty: 1
6. Motor Control Development Kit (Dual DC Motors)
• Controls two DC motors
• Uses external power source Qty: 1
7. Microcontroller Based Motor Control Development Kit
• Python programmable
• Wireless IoT connectivity
• Embedded control applications Qty: 1
8. Dual Axis Robotics Educational Kit
• Wireless communication
• 9 DOF IMU
• Ultrasonic distance sensor
• Programmable microcontroller Qty: 2
9. Python Programmable Microcontroller Educational Kit
• Wireless IoT connectivity
• Ultrasonic distance sensor
• Infrared sensing modules
• Plug in expansion capability Qty: 2
| Category | Parameter Name | Target Value | Unit |
| Programmatic | 1. Quantity & Schedule | 1FM asap (<1 Month) | Qty / Date |
| Electrical | 2. Nominal Voltage | 5V,12V | V |
| 3. Total Energy Capacity | 100 | Wh | |
| 4. Max Continuous Current | 5 | A | |
| 5. Peak Current & Duration | 7A for 200ms | A / ms | |
| Mechanical | 6. Maximum Mass | 1.4 | kg |
| 7. Max Envelope (X x Y x Z) | 100x100x200 | mm | |
| Environmental | 8. Operational Temp Range | -45to +65 | °C |
| 9. Launch Vibration (Random) | 5.57 | g rms | |
| Mission Life | 10. Orbit Type & Design Life | LEO, 2 Years | Orbit / Yrs |
| 11. Max Depth of Discharge | 30 | % | |
| Quality | 12. Mission Class / Standard | Space qualified TRL9 |
We need a small solar cell for a distributed lunar science mission. Final mission may need 50-150 of the cells, however we want to understand the pricing and availability of 3J or 4J cells to test and integrate before possible launch. We aim for smaller than 70mm max length, however we may go with an 80 mm by x mm model if needed.
