The present disclosure is directed to a method of repairing an aircraft. The method comprises charging a thermal transfer blanket comprising a thermal energy storage media with thermal energy from a heat source. The method further comprises positioning a thermally curable patch on an exterior surface of an aircraft. The thermally curable patch comprises an uncured polymer having a first temperature. The thermal transfer blanket is applied to the thermally curable patch. Thermal energy is transferred between the thermal transfer blanket and the thermally curable patch to increase the first temperature of the uncured polymer to a cure temperature for a sufficient amount of time to cure the polymer.

The present disclosure is directed to a method of repairing an aircraft. The method comprises charging a thermal transfer blanket comprising a thermal energy storage media with thermal energy from a heat source. The method further comprises positioning a thermally curable patch on an exterior surface of an aircraft. The thermally curable patch comprises an uncured polymer having a first temperature. The thermal transfer blanket is applied to the thermally curable patch. Thermal energy is transferred between the thermal transfer blanket and the thermally curable patch to increase the first temperature of the uncured polymer to a cure temperature for a sufficient amount of time to cure the polymer.

A method of thermally treating a material includes applying a thermal transfer blanket to a surface of the material. The thermal transfer blanket comprises a thermal energy storage media having a first temperature, the material having a second temperature that is different than the first temperature. Thermal energy is transferred between the thermal transfer blanket and the material, thereby modifying the temperature of the material.

Methods of embedding an elongate susceptor within a thermoplastic body and systems that perform the methods are disclosed herein. The methods include extending the elongate susceptor such that an extended portion of the elongate susceptor extends between a guide structure and a body-contacting structure. The methods also include heating a segment of the elongate susceptor to produce a heated portion of the elongate susceptor. The methods further include pressing a leading region of the heated portion of the elongate susceptor through a body surface of the thermoplastic body and into the thermoplastic body. The methods also include operatively translating at least one of the guide structure, the body-contacting structure, and an application tool that includes the guide structure and the body-contacting structure along an embedment pathway for the elongate susceptor.

The present disclosure is directed to a method of repairing an aircraft. The method comprises charging a thermal transfer blanket comprising a thermal energy storage media with thermal energy from a heat source. The method further comprises positioning a thermally curable patch on an exterior surface of an aircraft. The thermally curable patch comprises an uncured polymer having a first temperature. The thermal transfer blanket is applied to the thermally curable patch. Thermal energy is transferred between the thermal transfer blanket and the thermally curable patch to increase the first temperature of the uncured polymer to a cure temperature for a sufficient amount of time to cure the polymer.

The present disclosure is directed to a method of repairing an aircraft. The method comprises charging a thermal transfer blanket comprising a thermal energy storage media with thermal energy from a heat source. The method further comprises positioning a thermally curable patch on an exterior surface of an aircraft. The thermally curable patch comprises an uncured polymer having a first temperature. The thermal transfer blanket is applied to the thermally curable patch. Thermal energy is transferred between the thermal transfer blanket and the thermally curable patch to increase the first temperature of the uncured polymer to a cure temperature for a sufficient amount of time to cure the polymer.

A method of repairing a sandwich structure includes: removing a damaged portion of a core and a damaged portion of a first facesheet to form an open volume; filling the open volume with an ultraviolet-curable photomonomer; partially curing the ultraviolet-curable photomonomer to form a plurality of photopolymer waveguides by utilizing ultraviolet light; and arranging a replacement facesheet on the damaged portion of the first facesheet and over the photopolymer waveguides.

A hot stapler includes a body, two heat conducting units, an electrical storage unit, a circuit unit, and a switch button. The body includes a head and a handle. The electrical storage unit is disposed in the handle and has a voltage value less than 6 volts. A first wire and a first resistor of the circuit unit are electrically mounted between one of the two heat conducting units and the electrical storage unit. A second wire and a second resistor of the circuit unit are electrically mounted between the other one of the two heat conducting units and the electrical storage unit. The switch button is disposed on the handle and is switchable between a power-on position and a power-off position.

There is provided a method of forming a patterned anisotropic-comprising composite material, comprising inserting at least a part of a heated probe into a matrix to induce a local phase change around the probe within the matrix, the matrix being a matrix of thermo-reversible material and anisotropic fillers, and moving the heated probe within the matrix to form an alignment pattern of the anisotropic fillers comprised in the matrix. There is also provided a patterned anisotropic-comprising composite material formed from the method.

There is provided a method of forming a patterned anisotropic-comprising composite material, comprising inserting at least a part of a heated probe into a matrix to induce a local phase change around the probe within the matrix, the matrix being a matrix of thermo-reversible material and anisotropic fillers, and moving the heated probe within the matrix to form an alignment pattern of the anisotropic fillers comprised in the matrix. There is also provided a patterned anisotropic-comprising composite material formed from the method.