ESD Materials for Space: Why Surface Resistance Alone Is Not Enough

Satellite manufacturers do not care about ESD-safe materials because a data sheet says "10^7 ohm." They care because uncontrolled charging can interrupt communications, damage power systems, disturb attitude control, create solar-array arcs, contaminate critical surfaces, corrupt science measurements, and in documented cases contribute to total loss of mission.

NASA's spacecraft charging handbook opens with the point plainly: spacecraft charging is a known source of serious spacecraft-system damage and has been blamed for total spacecraft loss.1 NASA's NESC article on spacecraft charging describes Galaxy 15 losing command capability and drifting uncontrolled for eight months after a suspected charging event, and ADEOS-II losing its power system in 2003 after charging and ESD in a high-inclination low Earth orbit.2 A NASA spacecraft-charging workshop summary lists additional anomalies and losses of mission attributed to charging, including DSCS II, GOES 4, MARECS A, Telstar 401, INSAT 2, Tempo-2, PAS-6, ADEOS-II, and others.3 These are not edge cases; they are part of the anomaly history that motivates modern spacecraft-charging guidance and standards.

That is the starting point for material selection. Space ESD is not just about making plastic conductive. It is about creating a stable charge-dissipative material that survives the full orbital environment, in the actual molded geometry, for the full mission life.

For satellite OEMs, LEO component designers, spacecraft materials engineers, and space electronics packaging teams, the better question is not:

What is the surface resistance?

The better question is:

Will this material dissipate charge at the right rate, in the final geometry, after vacuum exposure, thermal cycling, radiation, atomic oxygen exposure, mechanical wear, and mission-specific grounding conditions?

Surface resistance is part of that answer. It is not the answer.

How Static Charge Builds Up In Orbit

Exterior spacecraft surfaces usually do not charge for the same reason a polymer fixture charges in a factory. In orbit, charging is dominated by exchange currents with plasma, radiation, illumination, emitted electrons, biased conductors, and local grounding conditions. At a given initial potential those currents generally do not balance, so the surface charges until it reaches a current-balance potential.

The balance is not simple. Ambient electrons and ions arrive from the plasma. Higher-energy electrons can penetrate materials and deposit charge below the surface. Sunlight can pull electrons out of sunlit surfaces through photoemission. Incoming particles can knock secondary electrons out of a material. Conductive surfaces, dielectric coatings, thermal blankets, solar arrays, sensors, booms, and shielded internal conductors all respond differently. NASA's MSFC Space Environmental Effects Team summarizes spacecraft charging as a complex interaction among environmental conditions, intrinsic material properties, and design choices, including electron flux and energy, solar illumination, temperature, electrical resistivity, secondary-electron emission yield, photoemission yield, dielectric breakdown strength, dielectric geometry, and placement of conductive surfaces.4

The useful way to think about the problem is current balance. Every exposed element on the spacecraft acts as a small electrode in a plasma. If more negative charge arrives at a surface than leaves, that surface charges negative. If photoemission or ion collection removes more electrons than the environment supplies, the surface can charge positive. If two adjacent surfaces reach different potentials, the spacecraft has differential charging, and the field between them can exceed breakdown thresholds even when the absolute potential is modest. If a buried dielectric or floating conductor stores charge internally, the discharge may happen close to sensitive electronics rather than on a benign exterior surface.1

The orbital regime sets which terms in that balance dominate. In geosynchronous orbit and during geomagnetic storms, a kiloelectron-volt to multi-keV electron population can drive surface potentials to thousands of volts negative, especially in eclipse when photoemission is unavailable to balance the incoming current. In LEO, the ambient plasma is denser and colder, so absolute charging levels are usually lower, but high-voltage solar arrays, polar passes, auroral arcs, and rapid plasma transitions can still drive arc-prone potentials and large parasitic currents.5 In all regimes, a poorly grounded dielectric on the outside of a spacecraft will find a way to store charge that the structure cannot bleed off.

This is why "structure ground" in a spacecraft is not the same as earth ground in a factory. The spacecraft is a finite object moving through plasma, and its structure is only the local reference. A part can be bolted into a grounded assembly and still create a problem if the conductive path is intermittent, if a dielectric skin stores charge, if a nearby conductor is floating, or if the part's resistance shifts in cold vacuum.

NASA's ESD test-practice guidance describes space plasma as ionized gas that can reach high energies, with interaction between plasma and common dielectric spacecraft surfaces depositing negative charge. If the resulting electric field exceeds dielectric breakdown strength, an ESD spark can disrupt digital and analog electronics or damage spacecraft hardware.6 That is the physical bridge from "surface material" to "mission anomaly."

What The Discharge Can Do

The damage is not abstract. NASA's 2023 Space Environmental Effects ESD testing poster lists ESD hazards that include burns, ablation, pitting, cracking, channeling, EMI, electronic component damage, and GPS or communications disruption, with the risk extending to system loss and mission loss.4 NASA/JPL test-practice guidance also notes that ESD energy can reach as much as one joule in some cases, though it is usually in the millijoule range, and that tests should simulate the expected ESD source as closely as possible.6

A single arc event can produce several distinct failure modes at once: a fast voltage transient that propagates into adjacent harnesses and trips logic, an electromagnetic pulse that couples through nominally shielded apertures, plasma ejecta that contaminates optical surfaces, and a sustained low-current arc that erodes solar-cell interconnects until the string is no longer usable. Surface charging tends to damage external hardware: thermal blankets, coatings, solar cells, antenna feeds. Internal charging tends to damage critical microelectronics and electromechanical systems: data buses, sensor front-ends, regulators, and command and data handling. Either way, the failure rarely announces itself as "ESD." It looks like a single-event upset, an unexplained reset, a degrading power channel, or an attitude excursion.

The two images below are from the NASA/NESC spacecraft charging briefing material. The first shows arc damage in laboratory testing of a chromic-acid-anodized thermal-control coating over ISS orbital debris shields. The second shows sustained arc damage on the ESA EURECA satellite solar array.2

Space ESD Is Not Terrestrial ESD

On Earth, static control usually starts with contact and separation: a tray sliding across a package, a technician handling a board, a device entering a carrier, a polymer part rubbing against another polymer part. The terrestrial ESD control stack is built around protected areas, grounding, bonding, ionization, humidity control, low-charging packaging, dissipative surfaces, shielding, and defined material resistance ranges.7

That framework matters. ANSI/ESD-style test methods are useful because they force repeatable language around surface resistance, volume resistance, low charging behavior, electric-field shielding, and discharge shielding. But spacecraft charging is a different physical problem.

In orbit, charge is driven by interactions among spacecraft materials, space plasma, high-energy electrons, sunlight-driven photoemission, secondary electron emission, biased power systems, and floating conductors. There is no building ground. The spacecraft structure becomes the reference. Surfaces can float relative to the plasma. A conductor that looks harmless on the bench can become an internal charge-storage site if it is isolated in flight.1

NASA separates the problem into two major categories: surface charging and internal charging. Surface charging occurs on exterior surfaces exposed to space plasma and sunlight. Internal charging occurs when higher-energy particles penetrate into spacecraft materials, buried dielectrics, or floating conductors and deposit charge inside the vehicle.1 NASA notes that internal charging can be especially severe because a discharge can occur close to a victim pin or wire with little attenuation.

That difference changes the material specification. An ESD-safe tray may need to prevent tribocharging and drain charge in a controlled way inside an ESD protected area. A satellite material may need to do that while also retaining its electrical behavior after cold soak, hot soak, vacuum exposure, total ionizing dose, atomic oxygen erosion, launch vibration, and years of mechanical constraint in a grounded or partially grounded assembly. The terrestrial standard is "did the operator damage the device?" The space standard is "will this part still dissipate charge correctly after five years on orbit?"

NASA Treats Charging As A Design Hazard

NASA-HDBK-4002B is useful because it does not treat material conductivity as a magic shield. It frames charging mitigation around mission environment, geometry, grounding, leakage paths, dielectric use, shielding, testing, and inspection.1

The mitigation hierarchy is consistent across NASA guidance and worth stating plainly, because it shapes every material decision downstream:

• Avoid the failure mode. Eliminate floating conductors, minimize large isolated dielectric surfaces, and design grounding so no metallic element on the spacecraft is left without a bonded path to structure.
• Bond and ground deliberately. Use defined, low-impedance paths to a common structure reference, with verified continuity at every interface. Bonding is not "the part is touching the chassis." It is a measured, documented connection that survives launch, thermal cycling, and assembly tolerances.
• Dissipate, do not insulate. Where a dielectric is unavoidable, make it static-dissipative or electrically leaky so charge can drain fast enough to prevent hazardous buildup, but controlled enough to avoid damaging current transients or unintended circuit paths.
• Shield where dissipation is not enough. Use conductive coatings, conductive enclosures, and adequate shielding mass to keep energetic electrons from reaching buried dielectrics and floating conductors in the first place.
• Test the system, not the coupon. For systems covered by this standard, verification cannot rely solely on analysis; representative testing in the relevant plasma environment is required.

Several points from the handbook matter directly for polymer selection:

• Material electrical properties should be known before use, including resistivity or conductivity, dielectric strength, stored charge, and electrostatic energy.
• Resistivity can change with time in space, temperature, radiation dose, atomic oxygen erosion, radiation-induced conductivity, electric-field-induced conductivity, and contamination.
• Surface contamination over time can change charging behavior, so beginning-of-mission and end-of-mission behavior may differ.
• Exterior spacecraft surfaces should generally be at least partially conductive in the ESD sense and bonded to structure where that is the mitigation path.
• Interior dielectrics should be made static-dissipative or electrically leaky when practical, as long as the leakiness does not interfere with circuit function.
• Carbon-loaded polymers and other particle-filled dielectric composites can be attractive, but common conductivity measurements may overestimate their conductivity, and the desired conduction properties must be retained across the mission thermal and radiation environment.1

NASA-STD-4005A, which covers high-voltage spacecraft power systems operating in LEO plasma, reinforces this system-level view for systems susceptible to arcing or large parasitic plasma-current drains. It requires LEO systems susceptible to arcing or large parasitic plasma-current drains to be tested in a simulated LEO plasma environment under worst-case operational conditions before flight. It also says verification of LEO performance in preventing arcing or large parasitic plasma currents shall never be attempted solely by analysis.5

That is the standard-driven lesson for ESD polymers in space hardware: the material must be specified as part of a discharge-control design, and the discharge-control design must be tested as a system. A flat-plaque resistance value is a screening datapoint, not a mission assurance argument.

Surface Resistance Is Useful, But It Is Only A Snapshot

Surface resistance is a real measurement. ANSI/ESD STM11.11 exists because static-dissipative planar materials need a repeatable method for surface-resistance measurement.8 It is far better than a vague "antistatic" label.

It also helps avoid a common mistake: confusing surface resistance with surface resistivity. STM11.11 measures resistance in ohms on a defined planar sample using specified equipment, conditioning, voltage, and reporting practices. Converting that result to ohms per square is a separate step, and it is not always meaningful for real molded parts, laminates, plated surfaces, coatings, or filled composites. The safer engineering habit is to report the actual method, sample form, voltage, conditioning, electrode geometry, and acceptance range.

The limitation is that the test is still a coupon-level measurement. It does not automatically answer:

• whether a molded part is electrically uniform through ribs, weld lines, gates, bosses, thin walls, and far-flow regions
• whether the conductive path reaches spacecraft structure or leaves a floating conductive island
• whether the part dissipates charge through the surface, through the bulk, or only through a local skin
• whether the resistance remains in range after vacuum, temperature, radiation, AO exposure, and mechanical wear
• whether the filler system changes CTE, shrinkage, modulus, toughness, RF behavior, magnetic signature, or demisability

ANSI/ESD S541 makes a similar point in terrestrial packaging. Resistance is not the only property used to classify ESD protective packaging; low charging, electric-field shielding, and discharge shielding are separate protective properties.9 If resistance alone is not enough for protecting electronics on Earth, it is not enough for spacecraft hardware.

NASA's language is even more demanding. For spacecraft charging, a "static-conductive" material is not defined by one universal range. NASA notes that the useful range depends on charging flux and configuration, and that the material must be properly grounded to mitigate spacecraft charging.1 In other words, "ESD-safe" is not an intrinsic label. It is a behavior of the material inside an electrical, mechanical, and environmental design.

What A Space ESD Material Has To Prove

Specifying a space ESD material means specifying the behaviors that resistance alone does not capture. The table below lists the requirement set we use when evaluating a candidate polymer for satellite hardware, and what each requirement adds beyond a coupon resistance number.

That table is why the material decision belongs early in the design cycle. A team can qualify a flat coupon and still discover later that the actual molded component is electrically nonuniform, contaminating, too brittle, too reflective, too magnetic, or too survivable at reentry. Catching that during qualification is expensive. Catching it after launch is a mission risk.

LEO Adds Atomic Oxygen, Outgassing, And Thermal Cycling

LEO is not just vacuum. Exterior surfaces see plasma, charged particles, UV, thermal cycling, micrometeoroid and debris risk, and atomic oxygen. Each of those mechanisms can move a material's ESD behavior independently of the others, and the combination is what matters for flight.

Atomic oxygen matters because it attacks many polymers directly. Atomic oxygen is often the dominant neutral species over much of LEO, especially in the approximate 200–800 km regime, and it strikes ram-facing spacecraft surfaces at hyperthermal energies on the order of 5 eV. That energy is high enough to break C-H and C-C bonds at exposed surfaces. NASA-HDBK-6024 was created to give spacecraft designers LEO atomic-oxygen durability data for polymers considered for spaceflight, including erosion-yield data from materials exposed for about four years on the exterior of the International Space Station.10 NASA's MISSE work makes the practical consequence clear: in low Earth orbit, atomic oxygen can react with spacecraft surfaces and erode polymers, while radiation can embrittle and crack materials.11

That matters for ESD because the conductive network has to remain stable near the exposed surface. A material that is initially dissipative can drift if AO exposure removes binder, exposes filler, roughens the surface, changes optical properties, or creates a degraded skin. A fresh coupon can be in range while the flight-exposed surface moves somewhere else. For carbon-filled systems specifically, AO can preferentially erode the polymer matrix and leave a fragile, dust-shedding filler-rich layer that no longer behaves like the original composite. The ESD performance of the part as flown is then a function of the surface chemistry the AO leaves behind.

Vacuum outgassing is a separate gate. NASA Goddard describes ASTM E595 testing as a method for determining total mass loss and collected volatile condensable materials in vacuum, with data used to substantiate low-outgassing performance for spaceflight environments.12 For electronics packaging, optics, star trackers, thermal-control surfaces, and contamination-sensitive payloads, low outgassing is not optional compatibility work. It is part of keeping nearby hardware clean enough to function. A common screening target for many spacecraft materials is TML ≤ 1.0% and CVCM ≤ 0.10%, subject to project-specific contamination-control requirements. These requirements constrain every additive in the formulation, including processing aids and dispersion agents used to disperse conductive filler.

Thermal cycling adds the next layer. Polymer composites can shift resistance as the polymer expands and contracts, filler-filler contact changes, residual stress relaxes, and interfaces age. NASA-HDBK-4002B specifically calls out temperature, radiation dose, AO erosion, and contamination as variables that can alter charging response.1 A space ESD material should be screened for resistance stability after the relevant environment, not only before it. In practice, that means measuring resistance before and after vacuum bakeout, before and after thermal vacuum cycling, and before and after AO and UV exposure on representative coupons, then re-measuring on molded parts that include the actual gating, weld lines, and wall transitions of the flight design.

Why Filler Choice Matters

Most conductive thermoplastics start with the same basic move: add conductive filler to an insulating polymer until a conductive network forms. The details decide whether the material is useful for spacecraft hardware.

Carbon black can build conductivity at relatively low cost, but it often requires loadings of 15 to 25 weight percent that change viscosity, toughness, elongation, surface finish, cleanliness, and particle behavior. At those loadings the polymer no longer behaves like the neat resin; mechanical properties, mold flow, and shrinkage all shift, and resistance can swing through orders of magnitude over very small loading changes near the percolation threshold. Carbon fiber can improve stiffness and conductivity, but it can introduce flow-aligned anisotropy, exposed fiber ends, local electrical variation, and conductive particulate risk. Metal fillers can help with conduction or shielding, but they can raise density, alter RF behavior, create magnetic or corrosion concerns depending on alloy, and work against demisability when high-melting materials survive reentry too well.

NASA calls out the composite-material problem directly: particle-filled conductive dielectrics, including carbon-loaded polymers, can be attractive for nonmetallic conductive spacecraft surfaces, but common conductivity measurement techniques may significantly overestimate their conductivity and the material must retain the desired conduction properties across the mission thermal and radiation environment.1

Carbon nanotubes provide a different engineering lever. A major review of CNT polymer composites found that electrical percolation has been studied across more than 30 polymer matrices, and that polymer choice and dispersion method strongly influence percolation behavior.13 That review also notes that reported percolation thresholds for CNT composites span several orders of magnitude depending on aspect ratio, alignment, and the degree to which the nanotubes are individualized rather than left in bundles. That is the central point. The goal is not simply "add CNT." The goal is a stable, dispersed, connected network that reaches the target resistance without overwhelming the base polymer.

That is where discrete CNT materials can help. Lower effective loading, often a fraction of what carbon black requires, leaves more room for the polymer to do its mechanical, thermal, dimensional, and cleanliness jobs. Better dispersion reduces electrical hot spots and part-to-part variation, which matters when ESD compliance has to be demonstrated on every molded geometry. A more stable network supports tunable charge dissipation without forcing the usual tradeoff between "conductive enough" and "still usable as a spacecraft polymer."

Conductive Is Not Always Better

It is tempting to push resistance lower. If 10^9 ohm is good, 10^5 ohm must be better. In spacecraft hardware, that assumption can create new problems.

The ESD Association broadly distinguishes conductive materials below 1 x 10^4 ohm, dissipative materials from 1 x 10^4 ohm to below 1 x 10^11 ohm, and insulative materials at or above 1 x 10^11 ohm.7 Spacecraft charging uses mission-specific language. NASA describes static-conductive materials as partially resistive materials that are neither conductors nor insulators, with the useful range dependent on charging flux and material configuration.1

The key phrase is "properly grounded." A conductive object that floats can still charge, and in some cases it charges faster and discharges harder than a comparable dissipative one would. A very low-resistance path can also route discharge energy into a sensitive circuit if the grounding architecture is wrong. NASA's guidance repeatedly points designers toward bonding, structure reference, leakage paths, avoidance of floating conductors, and control of electric fields, not just low material resistance.

The correct target is controlled dissipation in the actual assembly. Sometimes that means low resistance. Sometimes it means mid-range dissipative behavior. Sometimes it means a leaky dielectric that avoids charge storage without disrupting circuit operation. Sometimes it means a grounded conductive coating. Sometimes it means avoiding a conductive material entirely because the RF, magnetic, optical, or plasma-current consequences are worse than the charging risk.

The material has to be tuned to the failure mode.

Demisability Is Part Of The Materials Conversation

For many LEO components, end-of-life behavior is now part of the materials trade space. NASA's orbital debris standard limits human casualty risk from components that survive reentry, and identifies atmospheric-reentry debris casualty risk as a design and mission-assurance issue.14 ESA describes "Design for Demise" as intentionally designing space-system hardware to burn up or ablate during uncontrolled atmospheric reentry, reducing the risk that surviving fragments can injure people on the ground.15

That creates a real material conflict. A high-temperature, high-stiffness, metal-filled or carbon-fiber-filled part can be attractive during the mission, but less attractive at disposal if it survives reentry too well. A space ESD material may need to balance:

• enough thermal stability for launch, orbit, and component service temperature
• enough electrical conductivity for controlled charge dissipation
• enough mechanical strength and dimensional stability for the hardware function
• low enough density and suitable thermophysical behavior for reentry demise goals

That is not a catalog-number problem. It is a coupled materials-design problem, and it is one of the reasons filler choice has consequences that outlive the mission itself.

Where Elect Nano Materials Fit

Elect Nano's qualified ESD-safe materials are already in use in space-hardware applications, and the product portfolio is built around the broader requirement set that NASA guidance points toward: controlled conductivity, molded-part uniformity, stable polymer performance, low-particle conductive networks, and mission-specific filler packages.

The core technology is discrete carbon nanotubes: nanotubes that are individualized and dispersed, rather than left as the bundled agglomerates that arrive in most commodity CNT masterbatches. That single difference is what enables the performance the data sheets describe. Discrete CNT networks reach percolation at loadings well below those required for carbon black or bundled CNT, which keeps the base polymer in charge of mechanical, thermal, optical, and outgassing behavior. The uniformity of the network reduces the resistance variation that shows up in real molded geometries with weld lines and flow-direction effects. And because the conductive phase is a small fraction of the total composition, it adds less density, alters RF behavior less, and burns up more readily at reentry than metal-filled or heavily fiber-filled alternatives.

That translates into specific products tuned to specific corners of the space-hardware envelope:

LCP LEO DiMiseio™ is the clearest example for LEO hardware. This molding compound consists of a high-flow thermotropic LCP nanocomposite with 30 wt% thin glass fiber, discrete CNT technology, and fillers selected for complete demisability upon atmospheric reentry. It is tuned for 1E+07 ohm surface resistance by ANSI STM11.11, has a 253.5˚C heat deflection temperature at 1.82 MPa, low outgassing, atomic oxygen resistance, and low optical reflectance.16 For satellite components that need a molded, ESD-safe, dimensionally stable LCP platform with LEO exposure and reentry assumptions in the material concept, this is the direct fit.

PPSUper Tough™ ESD fits a different part of the envelope: toughness, ductility, impact resistance, and high-temperature PPSU performance paired with static-control behavior. This material is tuned for 1E+10 ohm surface resistance, 77.1 MPa tensile strength, 23.5% elongation at break, 119.3 J/m notched Izod impact strength, and 207˚C heat deflection temperature.17 The extended temperature data from -90˚C to +170˚C is useful for discussions where impact, ductility, and thermal-mechanical behavior matter as much as the ESD number.

Other Elect Nano ESD-safe materials extend the same discrete CNT platform across COC, MPPO, LCP, PPSU, and TPU systems for applications where the base resin has to be chosen around moisture uptake, toughness, heat resistance, stiffness, flexibility, optical behavior, RF interaction, magnetic signature, or cleanroom handling.18

The common thread is not "conductive plastic." It is controlled charge dissipation in a polymer system that can still satisfy the rest of the space-hardware requirement: low outgassing, AO survival, thermal-cycle stability, dimensional consistency at molded-part scale, low particle generation, and where it matters, demisability at end of life.

A Better Specification For Satellite ESD Materials

Instead of specifying only "surface resistance: 10^6 to 10^9 ohm," satellite teams should define the material around the actual service condition:

• target surface resistance and volume resistance, with test method, voltage, conditioning, electrode geometry, and acceptance range
• charge decay, leakage, and discharge behavior in the intended grounding architecture
• coupon and molded-part resistance mapping across gates, flow direction, weld lines, ribs, bosses, and contact points
• resistance stability after thermal cycling, vacuum exposure, radiation screening, humidity conditioning if relevant, and mechanical wear
• ASTM E595-style outgassing expectations for TML and CVCM where contamination matters
• AO erosion or AO screening plan for exposed LEO surfaces
• UV, radiation, and thermal-aging exposure plan
• CTE, shrinkage, creep, modulus, impact, fracture, and fastener-interface requirements
• particle generation and surface sloughing limits for electronics packaging, optical, sensor, or cleanroom-adjacent hardware
• magnetic signature and RF behavior where the part is near antennas, magnetometers, payload sensors, or high-frequency electronics
• reentry demisability assumptions for LEO hardware where surviving debris risk matters

That specification gives procurement, materials, electrical, reliability, and mission-assurance teams a shared language. It also prevents the common mistake: treating a resistance number as if it proves charge dissipation, durability, cleanliness, mechanical integrity, and disposal behavior.

The Bottom Line

Space ESD is not terrestrial ESD with a stricter data sheet. It is spacecraft charging, internal charging, grounding architecture, plasma interaction, material durability, contamination control, mechanical design, and end-of-life risk folded into one materials decision.

Surface resistance still matters. It should be measured carefully, reported honestly, and tied to the right standard. But for satellite hardware, it is only the first screen. The real question is whether the conductive network is stable, uniform, dispersed at low enough loading to preserve the polymer, and compatible with the rest of the mission environment.

Elect Nano's space-materials work is aimed at that harder problem: conductive thermoplastics built on discrete carbon nanotube technology, tuned to be stable, low-particle, mechanically useful, and compatible with the orbital environment. If you are designing ESD-safe LEO components, satellite electronics packaging, spacecraft fixtures, RF-adjacent housings, demisable molded parts, or custom charge-dissipative hardware, start with the full requirement set: resistance target, geometry, grounding condition, orbit, thermal envelope, AO exposure, outgassing requirement, mechanical loads, magnetic/RF constraints, and end-of-life assumptions.

That is where the material decision becomes real. Not "is it ESD-safe?" but "will it dissipate charge correctly and survive the mission?"

For teams working through that trade space, Elect Nano can help translate the requirement into candidate materials, molded samples, and a qualification plan. Start with the ESD-safe materials portfolio or contact the Elect Nano team with the orbit, part geometry, target resistance range, grounding assumptions, and environmental requirements.