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.
 

Provision of thermal shock test services (Two-zone elevator thermal shock chamber):
-Device under test:
-6 units of sandwich panels (35 x 16cm x 2cm)
-Test conditions:
-Hot temperature: +115 deg (+-5deg)
-Cold temperature: -110 deg (+-5deg) (flexible, -70deg is the minimum requirement)
-1 min dwell time
-Test cycles:
-Total 30k
-Inspection points:
-One visual inspection after 5k cycles since start
-One visual inspection after 15k cycles since start
-One visual inspection after 30k cycles since start
Expected response to the tender
-Response deadline: 20/07/2026
-Response content:
-FFP price for the mentioned campaign
-If applicable, 2 prices can be quoted, one for the -110 deg temp and another for the -70 deg temp
-Proposed schedule
-Including, at least, 2 days window for a 4h visual inspection
-Thermal shock chamber technical description
-Accommodation of the DUTs (Device Under Test)

We are seeking a quotation for a lightweight cryogenic pressure vessel / bottle for gaseous helium service. Please review the requirements below and confirm your capability to supply or fabricate a suitable vessel.
Technical requirements
- Minimum internal volume: approximately 30 litres
- Maximum outer radius: approximately 0.30 m
- Maximum expected operating pressure: approximately 300 bar
- Service: gaseous helium
- Exposure: liquid oxygen
- Cryogenic compatibility over temperature range: 90 K to 330 K
- Preference: minimum mass, subject to safe design, qualification, and compliance requirements

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 $