| HS Code | 343877 |
| High Thermal Stability | Retains structural integrity at prolonged high temperatures without significant degradation |
| Glass Transition Temperature Tg | Typically above 200°C |
| Softening Point | Ranges from 120°C to 180°C depending on grade |
| Service Temperature Range | -60°C to +250°C continuous operation |
| Low Outgassing | Meets aerospace vacuum outgassing requirements (low TML and CVCM) |
| Chemical Resistance | Resistant to fuels, hydraulic fluids, lubricants, and de-icing agents |
| Mechanical Strength | High tensile and compressive strength for structural and protective applications |
| Adhesion | Excellent bonding to metals, composites, and advanced aerospace substrates |
| Dielectric Constant | Low and stable dielectric constant across a wide frequency range |
| Low Moisture Absorption | Minimal water uptake, typically below 0.05% by weight |
| Coefficient Of Thermal Expansion | Low and controlled CTE for dimensional stability |
As an accredited High-Temperature Hydrocarbon Resin for Aerospace & Defense Applications factory, we enforce strict quality protocols—every batch undergoes rigorous testing to ensure consistent efficacy and safety standards.
| Packing | Supplied in 25 kg sealed steel drums with protective lining, ensuring contamination-free storage and safe transport for aerospace and defense use. |
| Container Loading (20′ FCL) | One 20-foot container loaded with secured, palletized drums of high-temperature hydrocarbon resin for safe aerospace and defense transport. |
| Shipping | Shipped as solid pellets or flakes in moisture-resistant, multi-wall paper bags or fiber drums on heat-shrink-wrapped pallets. Protect from excess moisture and direct heat. Not classified as dangerous goods for ground/freight transport, but full traceability and aerospace/defense end-use documentation are required. |
| Storage | Store in a cool, dry, well-ventilated area away from direct sunlight, heat, and ignition sources. Keep containers tightly sealed to prevent moisture ingress and contamination. Avoid prolonged exposure to extreme temperatures; ideal storage range is 10–30°C. Ensure proper labeling and segregation from incompatible materials. Under these conditions, shelf life is typically 12 months. |
| Shelf Life | Shelf life is typically 1–2 years when stored sealed in a cool, dry area away from heat, sunlight, and moisture. |
High-temperature hydrocarbon resin supplied as crushed flake with a ring-and-ball softening point of 120–160 °C, an acid number below 1.0 mg KOH/g, and a Gardner color below 6 is a low-molecular-weight aromatic/aliphatic copolymer resin. The scenarios below are restricted to aerospace and defense manufacturing operations where the resin functions as a tackifier, phase modifier, or process aid inside elastomeric, acrylic, and solvent-borne formulations. REACH Annex XVII restricted-substance screening and RoHS Directive 2011/65/EU screening are treated as pre-conditional for export packaging, but the resin itself is not a formulated article. No claims are made for structural epoxy infusion, silicone release coatings, or fuel-wetted polysulfide sealants, because published data for those matrix chemistries is limited or does not support resin incorporation.
| Scenario | Primary standard or specification | Measured parameter |
|---|---|---|
| EPDM rocket motor insulation | ASTM E285-19, ASTM D6370-99 | Linear ablation rate, thermogravimetric residue |
| Autoclave masking tape | ASTM D3330/D3330M, ASTM D3654/D3654M, SAE AMS 3819 | Peel adhesion, shear adhesion, high-temperature tape performance |
| Temporary preservative film | MIL-PRF-16173E, ASTM B117-19 | Salt fog resistance, water displacement |
| Plasma spray maskant | ASTM C633-13 | Thermal spray coating adhesion, strip removability |
| Butyl damping sheet | ASTM E756-05, SAE J1637, MIL-STD-810H | Loss factor, environmental vibration response |
| Airframe wire jacket | FAR 25.853(a), ASTM E662, ASTM D2863-19 | Flame propagation, smoke density, limiting oxygen index |
The listed standards govern the final article or manufacturing process, not the resin alone. Where a dedicated compound specification for hydrocarbon resin modification is absent, the resin is qualified through the same test program as the finished aerospace article.
In solid-propellant rocket motor case insulation, high-temperature hydrocarbon resin is added to EPDM at 5–12 phr on a 100 phr elastomer basis to increase room-temperature green strength before vulcanization and to elevate the rubber plateau modulus after cure. The resin is introduced after carbon black and aramid pulp have been dispersed in a 40 L intermeshing internal mixer, because early addition can produce torque spikes of 18–24% above the baseline compound and trigger ram pressure alarms. Batch logs from production mixing cells show that resin addition at a mixer drop temperature of 135–145 °C reduces resin domain size to below 5 µm, while resin added at 110 °C persists as a coarse phase and causes localized calender spotting on the sheet surface. Moisture absorption above 60% RH during intermediate storage requires predrying of the compounded strip at 60 °C for 4 h, and direct feed of damp strip into the calender has been observed to generate surface blistering in the cured liner.
All calendered sheet for rocket motor liners is processed at thicknesses from 1.2 mm to 2.0 mm with roll temperatures of 70–85 °C and nip pressures of 0.5–0.8 MPa. When the stock temperature drops below 85 °C, edge tearing appears at the calender feed shoulder and the defect frequency increases from 0.2% to 3.5% of linear meters in production lots. The resin also narrows the cure reversion window; rheometer analysis at 160 °C shows that the maximum torque plateau shifts by 0.5–0.9 dN·m when resin loading changes from 5 phr to 12 phr. Compliance testing is performed in accordance with ASTM E285-19 for oxyacetylene ablation and ASTM D6370-99 for thermogravimetric residue, with typical post-ablation char continuity verified by cross-section microscopy. The final calendered and autoclave-cured sheets are cut into rocket motor case insulation liners and segmented booster insulation sleeves. Published data for this specific configuration is limited, so each insulation compound must be qualified against the case-bonding drawing and propellant compatibility specification rather than relying on resin-level certifications alone.
In autoclave-cure masking tape manufacturing for carbon-fiber-reinforced epoxy wing skins, high-temperature hydrocarbon resin is dissolved with solvent-borne acrylic copolymer and a crosslinker to produce a pressure-sensitive adhesive that survives 180 °C and 6 bar autoclave cycles without adhesive transfer. The resin content is 10–20 wt% of adhesive solids; above 20 wt%, room-temperature peel adhesion falls below 3.0 N/cm and the adhesive becomes too brittle to compensate for composite springback during cool-down. The adhesive solution is slot-die coated onto 25–50 µm polyimide film at line speeds of 20–40 m/min, with staged drying from 85 °C to 150 °C to prevent resin migration to the air interface. Coating lines operating above 40 m/min have shown residual solvent retention in the adhesive layer, which later forms microvoids during autoclave ramp-up.
Compliance for the finished masking tape is assessed using ASTM D3330/D3330M for peel adhesion, ASTM D3654/D3654M for shear adhesion, and SAE AMS 3819 for high-temperature masking tape performance. In aerospace composite tool rooms, the tape is die-cut and used as tool-surface protection, bag-side masking, and peripheral flash-breaker tape on cure tooling. A silicone release liner is required when the resin content exceeds 14 wt%, because the adhesive can otherwise transfer to the backside during storage at 35 °C and 80% RH. Aminosilane adhesion promoters are not introduced directly into the adhesive solution because they reduce pot life below 8 h at 35 °C and generate gel bodies that create coat streaks.
Cold-applied solvent-cutback preservatives formulated for temporary protection of 2024-T3 and 7075-T6 airframe skins incorporate 15–30 wt% high-temperature hydrocarbon resin on total solids, which shifts the dry-film softening point above 49 °C so the coating remains non-tacky during outdoor storage but does not embrittle at -18 °C. High-shear dispersion is performed under vacuum at 20–50 Pa·s to remove entrained air that otherwise forms surface craters on large skin panels. Production spray booths use airless tip sizes of 0.015–0.021 in and wet film thicknesses of 12–25 µm; heavier films crack along lap-joint edges because the hydrocarbon resin raises the coefficient of thermal expansion of the dry film relative to the aluminum substrate.
The temporary film is qualified by neutral salt spray exposure for 168 h in accordance with ASTM B117-19, with acceptance criteria defined by MIL-PRF-16173E Grade 2 for water-displacing solvent-cutback materials. Removal with aliphatic solvent must leave no hydrocarbon residue that would interfere with subsequent chromate conversion coating adhesion. The material is used as a peelable or solvent-removable preservative film on airframe faying surfaces, wing skins, and fuselage panel packs during transportation and assembly. Contact with phosphate ester hydraulic fluid must be avoided, because ethylhexyl phosphate plasticizes the hydrocarbon resin film and leaves adhesive residue that increases solvent-wipe time from 4 s to over 20 s per square meter.
Plasma spray liquid maskants for nickel-based turbine components are compounded with 20–35 wt% high-temperature hydrocarbon resin to maintain peel removability after exposure to molten ceramic impingement at particle temperatures above 2,400 °C. The maskant is applied by air-spray gun at a wet film thickness of 0.5–1.5 mm, dried at 60–80 °C until the solvent content is below 1 wt%, and then subjected to Al2O3 plasma spray at a standoff distance of 100–150 mm. The resin acts as a sacrificial carbon source that chars at the surface but leaves a cohesive underlying layer; resin contents below 20 wt% produce brittle films that shatter during maskant removal, while resin contents above 35 wt% increase the wet film viscosity beyond the practical spray limit of 25 s in a No. 4 Ford cup.
Maskant performance is verified on representative coupons using ASTM C633-13 for thermal spray coating adhesion and a peel-strip removal test with a force limit of 8–12 N/25 mm. The maskant is accepted for production only if it can be removed as a continuous strip from grit-blasted surfaces with Ra ≤ 12 µm and leaves no carbonized fragments that would act as coating contamination. Terminal parts include masked compressor blades and hot-section nozzle guide vane edges for plasma spray coating operations. Published data for this specific configuration is limited, and the film removal force must be revalidated for each plasma gun nozzle and grit-blast profile combination.
Butyl elastomer damping compounds for helicopter floor panels and avionics racks are modified with 25–45 phr high-temperature hydrocarbon resin to broaden the loss factor peak into the 0.2–1.0 kHz frequency range at 20–25 °C. The resin is added after carbon black has achieved full dispersion in an intermeshing mixer at rotor speeds of 35–50 rpm; resin addition before black incorporation reduces dispersion quality and produces a discontinuous damping peak that shifts by more than 0.15 in tan δ between duplicate batches. Stock temperature during the second mixing pass is held at 105–125 °C, because the high softening point of the resin requires a temperature above its ring-and-ball value to achieve uniform phase distribution in butyl.
After mixing, the compound is sheeted on a two-roll mill to 1.5–4.0 mm and laminated to 0.3–0.5 mm aluminum constraining layer at nip pressures of 2.0–3.0 bar using a pressure-sensitive adhesive transfer laminator. Damping properties are measured with ASTM E756-05 and SAE J1637, and the final pads are screened under MIL-STD-810H temperature and vibration profiles for rotary-wing applications. Resin contents above 45 phr cause the unvulcanized sheet to block on calender rolls below 25 °C; a release film is mandatory for storage longer than 72 h. The terminal product forms constrained-layer damping pads and strips for cabin floor panels, avionics rack isolators, and actuator fairing skins.
Crosslinkable ethylene-vinyl acetate and ethylene-propylene-diene wire jacket compounds used in airframe power feeders are modified with 3–8 phr high-temperature hydrocarbon resin to improve carbon black dispersion and reduce melt viscosity during pressure extrusion over stranded copper conductors. The resin has a ring-and-ball softening point near 140 °C and must be pre-dried to below 0.05 wt% moisture before the twin-screw compounding step; ambient storage above 60% RH introduces water that volatilizes at the crosshead die and generates pit voids in the jacket surface. Compounding is performed in a 44:1 L/D twin-screw extruder at barrel temperatures of 115–125 °C, which is below the decomposition onset of the peroxide cure package.
The finished jacket is extruded through a crosshead die at line speeds of 25–60 m/min and crosslinked by continuous vulcanization. Vertical flame propagation is tested per FAR 25.853(a), smoke density per ASTM E662, and limiting oxygen index per ASTM D2863-19. The resin is not used above 8 phr because higher loadings raise the limiting oxygen index but increase smoke density and reduce elongation at break below the wire harness installation strain limit. The terminal product is airframe wire and cable jacketing for power feeders and avionics harness sleeves.
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Product grade HT-140A/220 is an aromatic-modified aliphatic hydrocarbon resin produced for high-temperature aerospace and defense polymer compounds, adhesives, and specialty coatings. The grade designation carries a 140 midpoint softening-point identifier and a 220 °C continuous service ceiling for formulated compounds; actual service limits depend on matrix resin chemistry, oxygen exposure, and mechanical load. The resin is supplied as flakes and is specified with a ring-and-ball softening point of 145–165 °C per ASTM E28, a weight-average molecular weight of 1,800–2,600 g/mol by gel-permeation chromatography calibrated with polystyrene standards, a Gardner color of ≤1 per ASTM D6166, a density of 1.08–1.12 g/cm³ at 25 °C per ASTM D792-20, and an acid number below 0.5 mg KOH/g per ASTM D974. Wiped-film evaporation reduces residual volatile matter to ≤0.5 wt% and total ash to ≤0.05 wt% per ASTM D5630. Glass transition temperature by differential scanning calorimetry is 85–100 °C per ASTM D3418-15, and melt viscosity at 180 °C by rotational viscometry is 8–20 Pa·s at 10 s⁻¹. Bromine number is maintained below 5 g Br/100 g per ASTM D1159, indicating a high degree of hydrogenation. These properties separate the material from standard C9 aromatic hydrocarbon resins, which typically exhibit Gardner colors from 5–8, lower molecular weight, and higher volatile fractions. Batch-to-batch softening point variation is controlled within ±3 °C by monomer feed ratio and hydrogenation endpoint monitoring; production records on continuous polymerization lines show lot-to-lot Mw variation below ±8%.
| Property | Method / standard | Typical specified value |
|---|---|---|
| Ring-and-ball softening point | ASTM E28 | 145–165 °C |
| Gardner color | ASTM D6166 | ≤1 |
| Acid number | ASTM D974 | <0.5 mg KOH/g |
| Density | ASTM D792-20 | 1.08–1.12 g/cm³ |
| Residual volatile matter | Headspace gas chromatography / ASTM D4526 | ≤0.5 wt% |
| Total ash | ASTM D5630 | ≤0.05 wt% |
| Glass transition temperature | ASTM D3418-15 | 85–100 °C |
| Total mass loss at 125 °C | ASTM E595-15 | ≤0.1% |
| Collected volatile condensables | ASTM E595-15 | ≤0.02% |
| Thermal stability at 5% weight loss | ASTM E1131-20 | ≥385 °C under nitrogen |
Compounding of HT-140A/220 into PEEK or PEI is performed on a co-rotating twin-screw extruder with a screw diameter of 25–45 mm and an L/D ratio of 40:1 or greater. Barrel settings from feed to die are typically 300–360 °C for PEEK and 260–320 °C for PEI. The resin melts before the thermoplastic matrix and temporarily lowers melt viscosity; process lines with L/D ratios below 32:1 have shown phase inversion and inconsistent dispersive mixing in the first barrel zones. Torque and melt-pressure data from production-scale compounding runs show that adding 15 wt% of the resin to PEEK reduces specific drive energy by 12–18% relative to neat PEEK at the same screw speed and feed rate. That energy reduction disappears when barrel temperatures exceed 380 °C because the resin begins thermal cracking at the screw root and releases volatile fragments. Residence time should remain below 120 s at melt temperatures above 350 °C; thermogravimetric analysis shows a 5% weight-loss temperature of ≥385 °C under nitrogen per ASTM E1131-20. When the resin is fed at the main feed throat, it is dry-blended with polymer powder to avoid segregation. When fed downstream through a side stuffer, the injection-port barrel zone is maintained at 180–220 °C and a vacuum vent downstream at −0.08 MPa removes residual moisture and cracked oligomers. Production lines with only one atmospheric vent have trapped volatiles in the strand, producing micro-voids that reduce tensile strength per ASTM D638-14 by 5–10% in molded specimens.
Injection molding after compounding uses clamp force settings of 400–800 kN for projected areas of 50–120 cm², with mold temperatures at 170–200 °C. Mold temperatures below 160 °C increase skin-core stress differences and have produced delamination at resin-rich weld lines when weight fraction exceeds 20%. Melt-pressure fluctuations at the die should be kept below ±0.3 MPa; larger fluctuations in PEEK compounds containing HT-140A/220 correlate with heterogeneous resin distribution and part warpage after annealing at 220 °C for 4 h.
In autoclave-cure epoxy prepreg systems, 5–15 wt% HT-140A/220 improves tack and drape without a large reduction in cured glass transition temperature when the base resin is a bisphenol F epoxy cured with dicyandiamide. Dynamic mechanical analysis per ASTM D7028-07 shows a neat resin Tg of 180–190 °C; at 10 wt% resin, the cured Tg shifts to 172–178 °C. This Tg shift is smaller than the shift produced by a standard C9 resin at equal loading because the high-temperature grade is stripped of lower molecular weight fractions that plasticize the network. The resin also shows total mass loss below 0.1% and collected volatile condensable material below 0.02% after 24 h at 125 °C and 10-5 Pa per ASTM E595-15. In high-solids epoxy adhesive films for metallic or composite airframe bonding, the resin is pre-dispersed at 50–70% solids in methyl ethyl ketone or a MEK/toluene blend; the dispersion must be milled to a Hegman grind below 25 μm to prevent particle seeding in bondline thicknesses under 0.15 mm. Processing at higher resin solids without adequate high-shear dispersion has generated fish-eye defects on reverse-roll coaters that transfer adhesive to release paper at line speeds above 8 m/min.
In manganese-cured polysulfide sealants intended for integral fuel tanks, 10–20 phr of HT-140A/220 can replace a conventional C9 aromatic resin to reduce low-molecular-weight migration into jet fuel. Fuel immersion testing per ASTM D471 using Reference Fuel B for 336 h at 60 °C shows volume swell below 8% and hardness change less than 5 Shore A points at 15 phr loading. Under the same conditions, a conventional C9 aromatic resin at 15 phr increases volume swell to 12–15% and produces hazy fuel extract with non-volatile residue exceeding 15 mg/100 mL. HT-140A/220 maintains non-volatile extractable residue below 5 mg/100 mL by the same extraction protocol. The higher softening point and lower residual monomer content reduce plasticizer-like migration, but the uncured sealant viscosity increases because the high-temperature resin is less soluble in liquid polysulfide at room temperature. Mixing is conducted at 30–40 °C in sigma-blade mixers with jacket temperature control; below 25 °C, wetting is incomplete and the product can form agglomerates larger than 50 μm that survive high-shear sweep and appear as surface bumps in fillet seal profiles. Moving die rheometer cure curves at 60 °C show T90 within 10% of the control at 15 phr loading, confirming that the resin does not strongly interfere with manganese dioxide cure kinetics.
For aircraft cabin interior panels requiring compliance with 14 CFR 25.853 and ASTM E662, HT-140A/220 is typically compounded into PEI/polycarbonate or PPSU at 5–18 wt%. At 18 wt% loading, the oxidation induction time at 200 °C per ASTM D3895 is ≥45 min, which supports short-term thermal exposure but remains lower than that of unfilled polysulfone. Smoke density measured by ASTM E662 in non-flaming mode remains below 200 Ds at 4 min when the resin is loaded below 10 phr; loadings above 20 phr can increase Ds above 250 and are therefore excluded from flame-smoke-toxicity-critical cabin parts. Peak heat release measured by FAR 25.853 Appendix F Part IV increases by less than 10% at 10 phr relative to the neat PEI/polycarbonate control, but the result is thickness-dependent and must be revalidated for each laminate construction.
Pre-drying is mandatory at 80 °C for 4 h when storage relative humidity exceeds 60%; hygroscopic uptake above 0.2 wt% has caused foaming in injection-molded skin-core panels and surface splay on parts with wall thickness below 1.5 mm. The resin is incompatible with high-basicity aliphatic amine accelerators above 150 °C; the combination produces chromophores and raises Gardner color from ≤1 to 6–8 within 2 h. In anhydride-cured epoxy systems, HT-140A/220 performs well, but the acid number must remain below 0.5 mg KOH/g to avoid competing with the accelerator. Direct storage with strong oxidizing agents is avoided, and the material is not held above 50 °C for more than 30 days because flake sintering can occur.
Standard C5 aliphatic resins lack sufficient aromatic content for high-temperature solubility and thermal stability; standard C9 aromatic resins offer higher temperature resistance but carry dark color and volatile aromatic oligomers. HT-140A/220 occupies a different specification band because it is hydrogenated after aromatic copolymerization. The comparative data in the table below are obtained from normalized laboratory batches using ASTM E28 for softening point, ASTM D6166 for Gardner color, and ASTM E1131-20 for thermal stability. The data are representative of production-lot averages and are not guaranteed limits without a mutually agreed specification document.
| Property | HT-140A/220 | Standard C9 resin | Test method |
|---|---|---|---|
| Softening point | 145–165 °C | 90–120 °C | ASTM E28 |
| Gardner color | ≤1 | 5–8 | ASTM D6166 |
| Residual volatile content | ≤0.5 wt% | 1.0–3.5 wt% | Headspace gas chromatography |
| Weight-average molecular weight | 1,800–2,600 g/mol | 600–1,200 g/mol | GPC, polystyrene calibration |
| Thermal stability at 5% loss | ≥385 °C | 300–330 °C | ASTM E1131-20 |
| Acid number | <0.5 mg KOH/g | 0.5–2.0 mg KOH/g | ASTM D974 |
| Typical maximum continuous service in PEEK compound | 220–260 °C | 160–180 °C | Supplier technical data |
In high-temperature protective coatings for defense missile canisters and engine-bay heat shields, HT-140A/220 is dispersed into silicone-organic hybrid systems at 3–8 wt% based on binder solids. The addition raises the dry-film softening point without forming a continuous immiscible phase, which allows low-gloss matte finishes to remain after thermal cycling. Crosshatch adhesion after 30 thermal cycles between −40 °C and 230 °C is maintained at 4B or better per ASTM D3359-17 when the resin is dispersed to a Hegman grind below 15 μm. At loadings above 8 wt%, the coating shows mud-cracking after 250 h at 260 °C, which limits the addition level in high-solids silicone systems. The resin is pre-dried before dispersion to avoid moisture-carryover bubbles that cause cratering in air-atomized spray application at tip pressures above 0.4 MPa.
