Conmoly | CM-SPACE-SPACEWIRE | SpaceWire Data Cables
Shenzhen Xinju New Materials Technology Co., Ltd.
https://conmoly.com

Selection reference; third-party published figures are not Conmoly guaranteed specifications or certifications. Final specifications require configuration review. Images illustrate product form.
Reference configuration: LVDS serial point-to-point links carry bidirectional data up to 400 Mbps with low crosstalk, loss and skew plus lightweight shielding for critical spacecraft interconnects.

Values apply to the traditional-space SpaceWire configuration; choose 26 or 28 AWG against link and mass budgets.
Data rate: 400 Mbps | Bidirectional LVDS link
Maximum operating voltage: 200 Vrms | Traditional-space configuration
Time delay: 4.30 ns/m | Pair
Intra-pair skew: ≤ 150 ps/m | Specification limit
Dielectric withstand: 1400 Vrms | Conductor-conductor/shield
Temperature / radiation: −200 to +180 °C · 10+ MRad | Traditional-space configuration
Vacuum stability: VCM < 0.1% · TML < 1.0% | ASTM 595 / ECSS-Q-70-02
Source: https://www.gore.com/products/spacewire

26 AWG SpaceWire: Balances link loss, mechanical strength and termination.
28 AWG lightweight type: Reduces diameter and mass for dense routing.
Terminated assembly: Connector, length and shield grounding form the complete channel.
Space-grade conductor: Material, stranding and plating are selected for resistance, strength, flex and termination.
Low-outgassing insulation: Dielectric, thermal, vacuum-stability and processing requirements guide material selection.
Controlled functional unit: Single, twisted, shielded, coaxial or multicore signal geometry is formed.
Lightweight shield and cover: EMI, atomic oxygen, protection and mass are optimized together.
Termination and traceability: Connector, branch, strain relief, material lot and process records remain controlled.
Mission and orbit: LEO, GEO, deep space, launch phase and mission duration
Electrical function: Voltage, current, protocol, frequency, impedance and core count
Mass and space: Mass per meter, diameter, bend radius and route
Environment: Vacuum, thermal cycle, radiation, ATOX, vibration and shock
Harness interface: Connector, branch, lacing, ground and installation process
Verification level: Applicable ESCC/NASA documents, first article, lot and traceability

Electrical baseline before and after thermal cycling
Vibration, shock, flex and termination retention
Mission-defined outgassing, radiation or atomic-oxygen evidence
First article, lot consistency and material/process traceability
High-resolution cameras
Radar and sensor equipment
Memory and telemetry subsystems
Spacecraft high-speed backbone
Single, multicore or shielded space cable
Space connector and lightweight harness
Fixed-length assembly, branch or pigtail
Page values do not constitute mission qualification or approval. Applicable standards, lot screening and verification levels are confirmed per project.