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There is no single best material for a spacesuit, spacecraft or orbital computer. The right choice depends on the job, the orbit, the mission duration and the finished assembly—not just a promising property on a datasheet. A material may perform well in one respect and fail another: a coating that sheds heat can still be vulnerable to damage, and a strong composite can lose its expected mass advantage once the hardware around it is included.
What makes a space material suitable?
Space hardware faces interacting stresses, and the mix varies by mission. In low Earth orbit (LEO), NASA identifies atomic oxygen, ultraviolet (UV) exposure, micrometeoroids and orbital debris, contamination and particle radiation as relevant environmental factors. Their effects can include changes to a surface’s thermal-optical properties, erosion of composites, dimensional changes during thermal cycling and outgassing in vacuum. These are not identical conditions in every orbit or for every spacecraft.
Materials selection is therefore an application-specific engineering trade. NASA’s spacecraft-materials chapter identifies mechanical and thermal properties, radiation and debris protection, optical behavior, contamination, toxicity and flammability for crewed vehicles, fracture control, manufacturability and interfaces as factors to consider. The design must also account for how the actual hardware performs after it is built.
- Mechanical performance: strength, flexibility, abrasion, puncture resistance and fracture behavior.
- Environmental compatibility: response to the mission’s radiation, atomic oxygen, thermal cycles, vacuum and contamination limits.
- Thermal and optical behavior: heat absorbed from sunlight and heat emitted as infrared radiation, alongside the component’s temperature limits.
- Integration: bonding, seals, lubricants, adhesives, surface geometry, mass and neighboring hardware.
- Practicality: toxicity and flammability where crews are involved, manufacturability, repairability and qualification evidence.
In Miria M. Finckenor’s NASA chapter “Materials for Spacecraft,” published August 1, 2018, an ISS science-rack example illustrates why an attractive material property is not enough: projected weight savings from graphite/epoxy disappeared when vibration isolation, Shuttle frequency and experiment-operation requirements were included. A candidate has to work as part of the design, not just in isolation.
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Spacesuits: choose for protection, mobility and heat rejection
A spacesuit is a one-person spacecraft: its materials have to work within integrated systems for pressure, life support, thermal control and mobility. There is no useful way to select an outer fabric on strength alone if it cannot meet the suit’s other requirements. NASA’s “Spacewalk Research and Technology” page, published May 15, 2025 and updated May 14, 2025, describes suit-material research involving fabrics, damage-sensing textiles, puncture resistance, radiation exposure and heat rejection.
Outer fabrics must survive exposure and wear
NASA’s MISSE-7 results summary reports a specific, limited test: six pristine and lunar-dust-abraded Apollo outer-layer suit-fabric samples spent 18 months exposed in the wake environment of the International Space Station (ISS). Space radiation darkened and reddened all six samples, increasing integrated solar absorptance by 7% to 38% across the tested set. In the lunar-dust-abraded Apollo fibers, ultimate tensile strength and elongation to failure fell by a factor of 4, while elastic modulus increased by a factor of 2.
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Those figures describe the tested samples, not a universal degradation rate for all suit fabrics or all missions. They show why exposure history, abrasion and the fabric’s changing thermal-optical and mechanical properties matter alongside its initial specification.
Protective treatments need evidence for the relevant use
NASA’s spacewalk research page also reports that materials treated with shear-thickening fluids in MISSE-9 maintained mechanical-performance characteristics and puncture resistance after extended exposure. The page summary does not give enough quantitative protocol detail to compare that result directly with other materials. It is evidence of a research direction, not a basis for ranking suit materials across missions.
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Cooling is a suit-system problem
Heat rejection depends on the suit’s thermal-control system as well as its textiles. NASA describes the Spacesuit Evaporation Rejection Flight Experiment (SERFE) as testing water evaporation to reject heat from a suit. In conventional sublimation cooling, water is exposed to space, freezes and then turns to vapor while carrying heat away. The appropriate approach depends on the system and mission; a fabric by itself does not provide the cooling solution.
Spacecraft structure and thermal-control surfaces
For spacecraft surfaces, the key thermal trade is between solar absorptivity and infrared emissivity. Solar absorptivity describes how much incoming sunlight a surface absorbs; infrared emissivity describes how effectively it radiates thermal energy. Neither property is automatically “better”: the intended temperature and the component’s role determine the useful combination.
| Surface example | Solar absorptivity | Infrared emissivity | Typical thermal implication |
|---|---|---|---|
| Matte black paint | High | High | Absorbs more sunlight and emits infrared effectively. |
| Matte white paint | Low | High | Absorbs less sunlight while emitting infrared effectively. |
| Second-surface silver FEP tape | Low | High | Used as a radiator coating to limit solar absorption while emitting infrared effectively. |
These examples are described in NASA’s small-spacecraft “Thermal Systems” report. A surface choice also depends on temperature limits, application method, geometry, when it is applied during assembly, durability, handling and bonding. A coating’s optical properties alone do not establish whether it will work on a particular spacecraft.
Multilayer insulation limits radiative heat transfer
Multilayer insulation (MLI) uses multiple thin, low-emissivity layers, usually with a durable outer layer, to limit heat transfer by radiation. Perforations or netting can reduce conduction between layers and let trapped gas vent after the spacecraft reaches orbit. NASA notes that MLI commonly helps keep on-orbit electronics and batteries within their temperature ranges, but compression can sharply reduce its performance. How it is installed matters as much as its nominal construction.
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Orbital electronics: radiation hardness is a mission assurance process
A “radiation-hardened” label alone is not enough to select an electronic part. NASA’s March 3, 2022 overview, “Avionics Radiation-Hardness Assurance for Safe Exploration Beyond Low Earth Orbit,” defines radiation-hardness assurance as work to ensure that electronics and materials meet design specifications after exposure to the natural space radiation environment.
That work includes defining the radiation environment, selecting and testing electrical, electronic, electromechanical and electro-optical (EEEE) parts, planning spacecraft layout, using radiation-tolerant design and setting mission, system and subsystem requirements. It balances risk and design against the particular mission’s environment, application, lifetime and resource constraints.
As a result, a part suitable for one mission may not be suitable for another. The selection has to account for where the spacecraft operates, how long it must function, the surrounding design and the consequences of failure—not branding in isolation.
How to choose and qualify a candidate
- Define the mission environment and duration. Identify the orbit and the relevant exposure conditions, including radiation, atomic oxygen where applicable, UV, thermal cycling, vacuum and debris risk. Do not assume every orbit presents the same combination.
- Specify the part’s job and limits. Set mechanical, thermal, optical and contamination requirements, plus crew-safety requirements for crewed vehicles. Include the interfaces the material must make with surrounding hardware.
- Compare candidates against the whole design. Consider mass, geometry, manufacturing, bonding, handling, repairability and system interactions—not just a single strength, temperature or optical value.
- Plan the evidence and tests. Match qualification and testing to the intended environment and the finished configuration. For electronics, make radiation-hardness assurance part of the mission design rather than a late parts-screening step.
- Check the as-built hardware. Finckenor’s NASA chapter puts the point plainly: “It is important to remember that the actual hardware must be tested to understand the real, ‘as-built’ performance, as it could vary from the design intent.”
NASA-STD-6016C with Change 1 is a NASA standards-record entry covering materials and processes for the design, fabrication and testing of NASA flight components, including vendor-designed and off-the-shelf items. The record lists a change date of November 15, 2023, says the standard is not a NASA mandatory standard and gives September 30, 2026 as its next five-year review date. Since that review date has passed, check the live NASA standards record before relying on its current status or applicability.
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