A load distribution panel assembly for providing a uniform load distribution in a thrust reverser of a gas turbine engine of an aircraft, the load distribution panel assembly comprising: a panel structure comprising at least one circumferential structural panel, the circumferential structural panel comprising: a first end and a second end, the first end configured to be coupled to a fixed structure of the gas turbine engine; a first compliant portion extending away from the first end, the first compliant portion comprising a compliant barrel portion and having a first inner surface and a first outer surface; and a second stiffened portion angled with respect to the first compliant portion and extending radially away from the first compliant portion, and terminating at the second end, the second stiffened portion comprising a stiffened bulb portion and having a second inner surface and a second outer surface, and having a closed stiffened cavity portion integral with a perimeter lip portion comprising a filled core interior filled with a stiffened material comprising one of a honeycomb core and a foam core; wherein the second stiffened portion has a stiffness that is greater than a stiffness of the first compliant portion; such that the load distribution panel assembly is configured to convert one or more fore/aft point loads applied to a point load interface on the second stiffened portion of the load distribution panel assembly by one or more load applying apparatuses, to a hoop tension load and a hoop compression load, and react a load offset between the one or more load applying apparatuses and the load distribution panel assembly, in one or more in-plane loads, to provide the uniform load distribution of the one or more fore/aft point loads, through the load distribution panel assembly, and to the fixed structure. a panel structure comprising at least one circumferential structural panel, the circumferential structural panel comprising: a first end and a second end, the first end configured to be coupled to a fixed structure of the gas turbine engine; a first compliant portion extending away from the first end, the first compliant portion comprising a compliant barrel portion and having a first inner surface and a first outer surface; and a second stiffened portion angled with respect to the first compliant portion and extending radially away from the first compliant portion, and terminating at the second end, the second stiffened portion comprising a stiffened bulb portion and having a second inner surface and a second outer surface, and having a closed stiffened cavity portion integral with a perimeter lip portion comprising a filled core interior filled with a stiffened material comprising one of a honeycomb core and a foam core; a first end and a second end, the first end configured to be coupled to a fixed structure of the gas turbine engine; a first compliant portion extending away from the first end, the first compliant portion comprising a compliant barrel portion and having a first inner surface and a first outer surface; and a second stiffened portion angled with respect to the first compliant portion and extending radially away from the first compliant portion, and terminating at the second end, the second stiffened portion comprising a stiffened bulb portion and having a second inner surface and a second outer surface, and having a closed stiffened cavity portion integral with a perimeter lip portion comprising a filled core interior filled with a stiffened material comprising one of a honeycomb core and a foam core; wherein the second stiffened portion has a stiffness that is greater than a stiffness of the first compliant portion; such that the load distribution panel assembly is configured to convert one or more fore/aft point loads applied to a point load interface on the second stiffened portion of the load distribution panel assembly by one or more load applying apparatuses, to a hoop tension load and a hoop compression load, and react a load offset between the one or more load applying apparatuses and the load distribution panel assembly, in one or more in-plane loads, to provide the uniform load distribution of the one or more fore/aft point loads, through the load distribution panel assembly, and to the fixed structure.