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We are looking for suitable S-band transceiver/transponder options for a CubeSat communication subsystem.
The unit should be suitable for a CubeSat mission and support S-band communication with two wideband full-duplex S-band antennas. We are exploring an antenna-selection architecture where the communication subsystem can select the antenna with better received-link quality during operation.
S-band uplink and downlink capability suitable for CubeSat TT&C / data communication.
Full-duplex operation preferred, or clear details on supported half-duplex/full-duplex modes.
Compatibility with two wideband S-band antennas.
Support for single-antenna and/or dual-antenna configuration.
Ability to support antenna selection using either:
1. internal RF switching,
2. transceiver-controlled external RF switch,
3. configurable GPIO / antenna-select output, or
4. OBC-controlled external RF switch.
Ability for the OBC to read RX QoS metrics and command antenna selection, if supported.
Clear RF interface information:
1. single common RF antenna port or separate TX/RX RF ports,
2. RF connector type,
3. output power,
4. receiver sensitivity,
5. required duplexer/diplexer/filtering, if any.
OBC interface details: UART, SPI, CAN, RS-422, RS-485, or other supported digital interface,
Flight heritage, qualification status, environmental test levels, and radiation information.
Availability of engineering model, qualification model, and flight model units.
Current lead time, approximate cost, and procurement options.
Datasheet, ICD, user manual, and application notes. If detailed documents require NDA, please mention the process.
We are currently performing a high-level trade study and would like suppliers to recommend suitable products or configurations, including any required external hardware such as RF switch, duplexer/diplexer, filters, power amplifier, or interface boards.
Technical KPIs:
- Current Mission Phase (Phase 0, A, B, ...) -> A
- Expected Satellite Mass (Kg) -> 4 kg
- Expected Satellite Orbital Average Power (OAP) (W) ->
- Allowed OAP power diverted to thruster (W) -> 5 W
- Peak power diverted to thruster (W) -> 15 W
- EMC requirements or standards used in the Satellite -> None
- Minimum thrust requirement (mN) -> 1mN
- Minimum Isp requirement (s) -> 40s
- Minimum dV (m/s) or Total Impulse (kNs) requirement -> 150 m/s
- Maximum allowed total (wet) propulsion system mass (kg) -> 1
- Maximum allowed system volume (cm3) -> 1U
- Intended manoeuvres (orbit injection, station keeping, deorbiting, collision avoidance) -> we need to lower our orbit of 170 Km in order to perform experiments in VLEO time for manuevering maximum 1 month
- Intended Space segment (LEO, MEO, GEO, far-earth, etc.) -> LEO /VLEO
- Minimum required radiation tolerance (in kRad) ->
Supply chain questions:
- Specific Propulsion Technology requirements (HET, GIT, others) -> Cold Gas
- Specific Propellant requirements -> no
- Thrust Vectoring Requirements -> no
- Required Number of Thrusters (EM and FM) ->
- Expected qualification status at delivery (ground qualified or flight qualified) -> flight qualified we can accept even ground qualified if really convenient
- Initial delivery date -> Q3 20274
- Bulk delivery or batch delivery allowed? ->
- Maximum budget per propulsion system -> 40 000 $
Looking for a spherical propellant tank that can hold 75kg water. Needs to be within 21-22" OD. Need this tank to act as a structural dynamic mass simulator for a vibration test on secondary structures that support the tank. Does not need to be flight qualified, tank can be used or a mockup. No pressure qualification required.
| Parameter | Specifications |
| Mass / Weight | Preferably < 1 kg |
| PC104, Suitable for CubeSat Integration (< 0.5U preferred) | |
| Mounting Configuration | CubeSat frame compatible |
| Input Voltage Range | 3.3V, 5V, 12V |
| Power Consumption (TX) | Preferably < 15 W peak |
| Power Consumption (RX) | Preferably < 10 W |
| Power Consumption (Idle) | Preferably < 3 W |
| Frequency Range (TX/RX) | S band preferred. Interested in X band specs also |
| Duplexing | Full Duplex Preferred |
| Instantaneous Bandwidth | Minimum 5 MHz |
| RF Output Power (TX) | +30 to +33 dBm preferred depending upon PA capabilities Minimum +7 dBm without seperate PA |
| Receiver Sensitivity / Noise Figure | Preferably < 5 dB |
| Number of Channels | 2 x 2 MIMO preferred |
| Modulation Schemes | BPSK, QPSK, OQPSK, QAM |
| Command & Telemetry Interface | I2C, SPI, CAN bus,RS-422, UART |
| High-Speed Payload Interface | Spacewire, LVDS, Ethernet |
| RF Connectors | SMA or SMP preferred |
| FPGA / SoC Specifications | Xilinx Zynq or equivalent FPGA-SoC Architecture |
| Onboard Storage | Minimum 512 MB RAM and 512 MB – 4 GB onboard flash/eMMC preferred |
| ADC/DAC Resolution | Minimum 12-bit preferred |
| Radiation Tolerance (TID) | Space-compatible / LEO mission Suitable 10 – 50 krad |
| Single Event Effects (SEE) | SEU mitigation preferred |
| Operating Temperature | -30 to +80 °C preferred |
| Vibration & Shock | Launch vibration compatible |
| Vacuum Operation | Suitable for vacuum operation in LEO orbit |
| Waveform Support | CCSDS preferred |
| Development Environment | GNU radio, C/C++, VHDL/Verilog |
| In-Flight Reprogrammability | Not mandatory |
| Parts Class / Grade | Space-compatible COTS or EEE Parts Class 2/3 preferred |
| Space Heritage (TRL) | TRL 6-9 preferred |
| Mission Lifetime | 1 – 3 years LEO |
| Export Compliance | Non-ITAR / EAR99 preferred. |
| Lead Time | Preferably 2 to 3 months |
| Regulatory Compatibility | shall comply any RF regulatory Standards equivalent to ITU |
| Category | Parameter | Specification |
| 1. Test Object Details | Dimensions & Volume | 200*200*220 mm |
| Mass | 8kg or lower | |
| Center of Gravity (CoG) | ||
| Handling & Lifting | NA | |
| Cleanliness/Contamination | NA | |
| Operational State | Active | |
| 2. Vibration & Shock Testing | Test Profile / Spectrum | Constant |
| Frequency Range | 5Hz | |
| Amplitude / Acceleration | ||
| Sweep Rate & Duration | 168h | |
| Test Axes | ||
| Mounting Fixture | Customer Provided | |
| Control & Response Channels | ||
| 3. Thermal Vacuum (TVAC) Testing | Vacuum/Pressure Level | 03. Oct |
| Temperature Extremes | -150 | |
| Temperature Ramp Rate | ||
| Number of Cycles | Contant -150°C | |
| Dwell Time | ||
| Thermal Dissipation | ||
| Heating/Cooling Method | ||
| Feedthrough Requirements |
| RF & Signal Performance | ||
| Downlink Frequency | (e.g., 8025–8400 MHz / X-Band) | X/S band |
| Uplink Frequency | (e.g., 2025–2110 MHz / S-Band) | S Band |
| Minimum G/T | (e.g., 22 dB/K @ 5° Elevation) | |
| Maximum EIRP | (e.g., 45 dBW) | |
| Polarization | (e.g., RHCP / LHCP Switchable) | Switchable |
| IF Interface | (e.g., 70 MHz, 140 MHz, or DIFI) | |
| Target Link Margin | (e.g., 3 dB @ worst-case rain) | |
| Mechanical & Tracking System | ||
| Antenna Aperture | (e.g., 3.7 Meter) | |
| Mount Geometry | (e.g., X-Y Mount for LEO) | Yes |
| Azimuth Travel | (e.g., Continuous or +/- 270°) | Yes |
| Elevation Travel | (e.g., 0° to 180° / Over-the-top) | Yes |
| Max Slew Rate | (e.g., 10° / second) | Yes |
| Pointing Accuracy | (e.g., ≤ 0.05° RMS) | |
| Tracking Mode | (e.g., Program Track / Autotrack) | |
| Baseband & Network Infrastructure | ||
| Modem Type | (e.g., Software Defined / Virtual IF) | Software Defined |
| Max Data Rate | (e.g., 1.2 Gbps Downlink) | |
| Modulation Support | (e.g., BPSK, QPSK, 16APSK) | BPSK/QPSK |
| Encoding/FEC | (e.g., CCSDS, LDPC, Turbo) | CCSDS, others optional |
| M&C Interface | (e.g., SNMP v3 / REST API) | REST API |
| Data Backhaul | (e.g., Dual 10GbE Fiber) |
S band transceiver for low data rate TC/TM for GEO orbit. Frequency range would be 2025 MHz – 2110 MHz UL and 2200 MHz to 2300 MHz for DL.
Rigid modular solar panel designed for CubeSat applications, consisting of six (6) space-qualified triple-junction (InGaP/InGaAs/Ge) solar cells connected in series to form a single output string. Solar cells shall have a minimum efficiency of 29.5%. The panel shall provide functional capability for coarse sun sensing and temperature monitoring (integrated or equivalent). The system shall include integrated bypass diodes for reverse-bias protection. The panel shall be fully compatible with standard 6U CubeSat mechanical structure and Electrical Power System (EPS) interfaces without requiring modification. Suitable for operation in space environment with demonstrated spaceflight heritage. Operating temperature range: –40°C to +85°C.























































































