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
X-band feed assembly
Please use this information to identify suitable manufacturers or products for a complete matched X-band feed assembly and provide budgetary pricing, lead time, RF performance data and mechanical/interface information where available.
Main reflector diameter: 5 m
Surface profile: paraboloid
F/D: approximately 0.317
X-band receive frequency: 8.025–8.400 GHz
Polarisation: dual circular RHCP/LHCP, simultaneous preferred
Axial ratio: ≤0.75 dB across band, ≤0.50 dB preferred
Cross-pol isolation: ≥25 dB, ≥30 dB preferred
Rx/Rx isolation: ≥30 dB, ≥35 dB preferred
VSWR: ≤1.35:1, ≤1.25:1 preferred
Insertion loss: ≤0.35 dB, ≤0.20 dB preferred
Edge illumination taper: -10 to -12 dB, preferably matched to the reflector optics
Preferred Rx interface: WR-112 / CPR-112G, or suitable alternative
Maximum feed mass target: <12 kg
Quantity: 1 evaluation/prototype unit, with an option for production units
Status:
Open
Ka-band SSPA
5U SSPA with 34GHz-36GHz output power greater than 53dBm
Status:
Open
OCT
| Section | Parameter | Minimum Buyer Requirement / Value | Notes / Document Reference |
| Project / Mission Requirements | Required Delivery Date (Flight) | 2028 | e.g., Q3 2028 |
| Quantity Required | TBD | e.g., 2 Flight Units + 1 Engineering Model | |
| Target Cost Per Unit | - | e.g., $400,000 | |
| Mission Lifetime | 5 Years | e.g., 5 Years | |
| Target Orbit / Altitude | LEO / 600-800 km | e.g., LEO / 550 km Sun-Synch | |
| 2. Technical - Optical | Laser Wavelength | 1550 nm | e.g., 1550 nm (C-band) |
| Interoperability Standard | SDA Tranche 1 | e.g., SDA Tranche 1 / CCSDS | |
| 2. Technical - Performance | Data Rate (Tx / Rx) | 1- 10 Gbps | e.g., 2.5 Gbps / 2.5 Gbps |
| Link Distance (Range) | Up to 5,000 km | e.g., Up to 5,000 km | |
| 2. Technical - SWaP-C | Mass (Weight) | ≤ 10 kg | e.g., < 15 kg |
| Power Consumption (Peak) | < 75 W | e.g., < 80 W (Operational) | |
| Volume / Envelope Dimensions | < 250 x 250 x 250 mm | e.g., 300 x 250 x 200 mm | |
| 2. Technical - Interfaces | Data Interface | Ethernet | e.g., SpaceWire / OIF / Ethernet |
| Electrical / Power Input | 28 VDC regulated | e.g., 28V DC regulated | |
| Mechanical Mounting | TBD | e.g., 4x M5 bolts, nadir-facing | |
| 2. Technical - Pointing | Field of Regard (FoR) | TBD (Optics will be decided later) | e.g., Azimuth: ±90°, Elevation: ±45° |
| 3. Environmental | Technology Readiness Level (TRL) | at least TRL 6-7 | Minimum TRL 6 (Flight proven preferred) |
| Operational Temperature | LEO conditions | -20°C to +55°C | |
| Survival Temperature | -40°C to +75°C | ||
| Random Vibration (Launch) | TBD (Launch Vehicle specs) | e.g., 14.1 grms (or specific launch vehicle spec) | |
| Radiation Tolerance (TID) | TBD (Will be similar for LEO 600 - 800 km) | e.g., 30 krad (Si) absorbed dose | |
| Component Screening Level | TBD | e.g., NASA Level 2 / ECSS Class 2 | |
| 4. Deliverables | 3D CAD Model (STEP format) | Yes | Required at Preliminary Design Review (PDR) |
| Electrical Interface Control Document (ICD) | Yes | Required at Critical Design Review (CDR) | |
| Software/Firmware ICD | Yes | Required at Critical Design Review (CDR) | |
| Thermal / Structural FEA Models | Yes | Required at Critical Design Review (CDR) | |
| End-of-Line Test Reports | Yes | Required prior to shipment | |
| Certificate of Conformance (CoC) | Yes | Required at delivery |
Status:
Open
Payload hosting
| # | Parameter | Requirement | Response |
| 1 | Physical Properties | Payload Mass (kg) | 2.3 kg |
| 2 | Payload Volume (U or m3) | 1.5U | |
| 3 | General | Payload type e.g. RF, EO (RGB, HS, MS IR) | SSA |
| 4 | Desired orbits e.g. SSO, near-equatorial | Mid-Inclination (preferred), or SSO | |
| 5 | Desired altitudes e.g. 550 km | 500-550 km | |
| 6 | EPS | Payload continuous power (W) | 25W |
| 7 | Payload peak power (W) | 40W | |
| 8 | Payload duty cycle per orbit (%) | TBD with the provider | |
| 9 | Payload voltage supply e.g. 3V3, 5V, 12V | 12-36 V | |
| 10 | RF | High-speed downlink required e.g. > 5 Mbps? | X-Band (preferred), S-Band (minimum requirement) |
| 11 | Daily data budget (Mb or Gb) | TBD | |
| 12 | Encryption required on TTC or payload data e.g. AES-256? | ||
| 13 | Interfaces | Bus to payload interfaces required e.g. CAN, I2C, SPI, UART, RS422, RS485, PPS | CSP 1.6 over CAN & UART
|
| 14 | On-board data storage requirements? | No on-board data storage required | |
| 15 | ADCS | Payload Pointing Modes when active e.g. Nadir | Nadir Pointing, Satellite Tracking (optional) |
| 16 | Pointing Accuracy | Better than 1 deg/s | |
| 17 | Pointing Knowledge | Better than 0.5 deg/s | |
| 18 | Slew Rate (°/s) requirements? | ||
| 19 | GPS required for position, velocity knowledge? | GNSS log is required during operation |
Status:
Open
Pre-heating
Pre-heating solutions for thruster propellant
Status:
Open
Need help?
If you need help with submitting your bid, click here to chat with us.