CONMOLY / ENGINEERING & CONNECTIVITY
Reference configuration: Low-loss coax, lightweight shielding, low-profile connectors and thermomechanical ruggedization operate as one assembly to maintain signal integrity and phase stability through 40 GHz during launch and orbit.
Space Cables
CM-SPACE-RF
Spaceflight Microwave RF Assemblies
Reference configurations only; specifications and certifications require confirmation.
Selection reference. Published third-party figures below describe specific reference configurations; they are not Conmoly guaranteed values or certifications. Confirm the final construction and test requirements with engineering.
Frequency, insertion loss, diameter and connector vary by cable type; phase/time-delay matching is available by project.
Scroll the table horizontally to view all configuration conditions.
| Parameter | Reference value | Configuration / condition |
|---|---|---|
| Maximum frequency | 40 GHz | Spaceflight RF assembly family |
| Frequency families | 18 · 22 · 29.5 · 32 · 40 GHz | By cable type |
| Standard impedance | 50 ± 1 Ω | Type 8S example |
| Velocity / delay | 85% · 4.0 ns/m | Family typical values |
| Shielding effectiveness | > 90 dB | Through 18 GHz |
| Diameter families | 2.2–8.1 mm | 0.085–0.320 in |
| Phase / time-delay matching | Through 40 GHz | Sub-picosecond tolerances available |
Reference source: www.gore.com
| Traditional-space assembly | ESCC/NASA verification path for high-reliability missions. |
|---|---|
| NewSpace and launch assembly | Balances schedule, mass and mission environment validation. |
| High-power/high-density assembly | Frequency, diameter, power and connector are combined. |
| 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 |
Page values do not constitute mission qualification or approval. Applicable standards, lot screening and verification levels are confirmed per project.
Reference configuration: Conductive or semi-conductive covers continuously drain static charge and provide lightweight, flexible, atomic-oxygen-resistant 600 Vrms power interconnects for moving LEO and GEO systems.
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Reference configuration: ESCC 3901/025 lightweight GEO cable delivers 600 Vrms power and analog/low-frequency signals with smaller diameter, lower mass and tighter bending.
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Reference configuration: ePTFE, PTFE and PFA combine in a chemical- and cut-through-resistant, low-springback wide-temperature space cable covering 12–30 AWG and multicore constructions.
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