Conmoly | CM-SPACE-ASW | Type ASW Anti-Static Space Wire
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: 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.

GEO and LEO versions use different jacket and insulation systems; select the part number against the orbit environment.
Maximum operating voltage: 600 Vrms | Type ASW space wire
Temperature range: −200 to +200 °C | GEO / LEO range
GEO jacket: Conductive film | Antistatic construction
LEO jacket: Semi-conductive fluoropolymer | Antistatic / ATOX direction
Conductor: Silver-plated copper or copper | Version dependent
Wire gauges: 20 · 22 · 24 AWG | Standard part numbers
Source: https://www.gore.com/products/space-cables-type-asw

GEO conductive-film type: Conductive-film covering for moving geostationary-orbit systems.
LEO semiconductive type: Semiconductive fluoropolymer for low-orbit atomic oxygen.
20–24 AWG single core: Standard gauge selected for resistance, mass and termination.
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
Ion thrusters
Solar-array wiring
Stationary plasma thrusters
LEO/GEO moving mechanisms
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.