Flexible thermal protection system is developed for thermal protection requirement of hypersonic in-
flatable aerodynamic decelerators, which is focused on thermal protection system for large mass earth entry and future
mars entry, descent and landing systems. A brief historical retrospect is given on the flight experiments which have
been and will be carried out for developing hypersonic inflatable aerodynamic decelerators. Mars entry, descent and
landing systems application required for flexible thermal protection system is depicted. The basic components of flexi-
ble thermal protection system definition are described. The correlative heating tests for flexible thermal protection sys-
tem are introduced in details.