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Used by engineers from:
ST Engineering
Iceye
Reflex Aerospace
Pixxel
ESA
NASA
Northrop Grumman
Kepler Communications
GISTDA
ATMOS Space Cargo
Azista
egSA
Azista
egSA
L3Harris
UAE Space Agency
Exotrail
Link
Fleet
OHB
DLR
Eutelsat
Satellogic
Lockheed Martin
ST Engineering
Iceye
Reflex Aerospace
Pixxel
ESA
NASA
Northrop Grumman
Kepler Communications
GISTDA
ATMOS Space Cargo
Azista
egSA
Azista
egSA
L3Harris
UAE Space Agency
Exotrail
Link
Fleet
OHB
DLR
Eutelsat
Satellogic
Lockheed Martin

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S-band transceiver

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.

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Open
Thruster

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 $
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Open
spherical propellant tank

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.

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Open
SDR
ParameterSpecifications
Mass / WeightPreferably < 1 kg 
 PC104, Suitable for CubeSat 
Integration (< 0.5U preferred) 
Mounting ConfigurationCubeSat frame compatible 
Input Voltage Range3.3V, 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
DuplexingFull Duplex Preferred
Instantaneous BandwidthMinimum 5 MHz
RF Output Power (TX)+30 to +33 dBm preferred 
depending upon PA capabilities
Minimum +7 dBm without seperate PA
Receiver Sensitivity / Noise FigurePreferably < 5 dB
Number of Channels2 x 2 MIMO preferred
Modulation SchemesBPSK, QPSK, OQPSK, QAM
Command & Telemetry InterfaceI2C, SPI, CAN bus,RS-422, 
UART 
High-Speed Payload InterfaceSpacewire, LVDS, Ethernet
RF ConnectorsSMA or SMP preferred
FPGA / SoC SpecificationsXilinx Zynq or equivalent FPGA-SoC Architecture 
Onboard StorageMinimum 512 MB RAM and 
512 MB – 4 GB onboard flash/eMMC preferred
ADC/DAC ResolutionMinimum 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 & ShockLaunch vibration compatible 
Vacuum OperationSuitable for vacuum operation in  LEO orbit
Waveform SupportCCSDS preferred
Development EnvironmentGNU radio, C/C++, VHDL/Verilog
In-Flight ReprogrammabilityNot mandatory
Parts Class / GradeSpace-compatible COTS or 
EEE Parts Class 2/3 preferred 
Space Heritage (TRL)TRL 6-9 preferred
Mission Lifetime1 – 3 years LEO
Export ComplianceNon-ITAR / EAR99 preferred. 
Lead TimePreferably 2 to 3 months
Regulatory Compatibilityshall comply any RF regulatory
Standards equivalent to ITU
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Open
TVAC testing
CategoryParameterSpecification
1. Test Object DetailsDimensions & Volume200*200*220 mm 
 Mass8kg or lower
 Center of Gravity (CoG) 
 Handling & LiftingNA
 Cleanliness/ContaminationNA
 Operational StateActive
2. Vibration & Shock TestingTest Profile / SpectrumConstant 
 Frequency Range5Hz
 Amplitude / Acceleration 
 Sweep Rate & Duration168h
 Test Axes 
 Mounting FixtureCustomer Provided
 Control & Response Channels 
3. Thermal Vacuum (TVAC) TestingVacuum/Pressure Level03. Oct
 Temperature Extremes-150
 Temperature Ramp Rate 
 Number of CyclesContant -150°C
 Dwell Time 
 Thermal Dissipation 
 Heating/Cooling Method 
 Feedthrough Requirements 
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Open
Ground Station
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) 
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Open
LoRa/IoT

LoRa/IoT device that can work on UHF/S-band frequencies

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Open
12U CubeSat Structure

RFQ for 12U CubeSat Structure

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Open
S band transceiver

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.

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Open
Solar Panel (6U CubeSat Compatible)

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.
 

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