Composite　structures　have　been　widely　applied　in　aerospace.　Their　dimensional　geometries　and　residual　strength　predictions　in　service　are　critical　to　ensure　structural　integrity　and　safety　for　aerospace　applications.　Composites　are　known　to　show　significant　viscoelasticity.　In　this　research,　we　have　established　a　theoretical　model　and　investigated　the　creep　behaviour　of　a　polymeric　carbon　composite.　A　Weibull　distribution　function　was　fitted　to　establish　the　master　curve　based　on　the　superposition　principles　in　order　to　construct　explore　the　service-life　prediction　model.　The　time-temperature　boundary　of　the　composite　was　created　to　benefit　long-term　creep　predictions　of　the　aerospace　composite.