Leads
Bid on open business opportunities for space products or services
We'll do the rest of the work for you!
Do you often struggle getting in touch with potential customers for your ground, launch, or satellite products and services?
Well struggle no more!
Our lead engine is set up to streamline the process of engaging with customers from all over the world.
We'll work closely with you to showcase your bid to customers. Simply browse the list of leads below and submit bids for the ones that you can offer solutions for.
you submit a bid
Send us all of the details of your offer to the customer for the lead you've chosen.
we contact the buyer
We check with the buyer if they are interested to learn more about your bid.
you talk to the buyer
We introduce you to the buyer so you can mature the opportunity further.
Don't want to spend time browsing for leads and want them to be delivered to your inbox directly?
status
Satellite Bus
| # | 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 |
Status:
Open
S&X Feed
S&X Feed mono pulse for 5.4 Mt dia Reflector with .4 mm F/d
Status:
Open
VHR Payload
| 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 |
Status:
Open
PAYLOAD PROCESSOR
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]
Status:
Open
Reaction wheels
RFQ for Reaction wheels with at least 4Nms momentum storage and max torque of at least 250 mNm
Status:
Open
Need help?
If you need help with submitting your bid, click here to chat with us.