Insulation for spacecraft components helps to guard against the extreme conditions found in outer space, and to control thermal environments, for reliable operation of the spacecraft over long-durations. For example, because the exterior temperature of the spacecraft can vary by several hundred degrees depending on the spacecraft's exposure to solar radiation, such insulation may be used to thermally isolate the interior of the spacecraft or specific components to minimize thermal cycling. Multi-layer insulation (MLI) is considered the standard means for providing a thermal barrier for spacecraft components, and has been used in space-related applications for more than 50 years. MLI is typically composed of multiple flat layers of metallized Mylar or Kapton film, with a thin netting of an insulating polymer material, such as Dacron or Nomex, placed in between each film layer to minimize contact, and thus reduce thermal conduction between layers. However, the performance of MLI is strongly dependent on the manner in which it is formed and thereafter attached to the spacecraft, because areas where the MLI overlaps to produce folds, or areas having seams or penetrations, may dramatically reduce insulative performance. Because MLI's performance is so dependent on how well the individual flat panels fit together to form a covering that is free from compressive forces, the MLI blanket panels must be designed and sewn together in a custom manner, which is a time-consuming and expensive process. Moreover, MLI's insulative performance is difficult to predict due to its dependence on fit and the negative impact of seams or folds, which introduce unwanted conductive heat paths. Increasing the number of layers is a typical technique to compensate for this unpredictability.