An Armadillo-Like Flexible Thermal Protection System for Inflatable Decelerators: A Novel Paradigm

Abstract

Polymeric ablative materials play a strategic role in the whole aerospace industry: they are used to produce the thermal protection system (TPS), which protects vehicles during the hypersonic flight through a planetary atmosphere. To date, TPSs are typically designed as rigid monolithic heat shields. Inflatable deployable aeroshells (IDAs) offer an alternative to rigid TPSs: IDAs are based on the use of flexible TPSs (FTPSs). State of the art FTPSs can handle heat fluxes up to approximately 20 W cm−2. However, next generation FTPSs for IADs should be able to survive heat fluxes up to 150 W cm−2. To satisfy these stringent requirements, we propose a radically brand‐new paradigm of flexible TPS based on the use of state of the art elastomeric ablatives (EPDM/Aramid) employed to produce the insulation liners for solid rocket motors. This class of ablatives is able to survive heat fluxes in the range of (300–1000) W cm−2. Most important, we envisioned to introduce an “Armadillo‐Like” design in which a series of overlapping sacrificial movable tiles could work as a continuous flexible thermal barrier.

Feasibility of a Morphing Rocket Nozzle for Thrust Vector Control based on Corrugated Composite Laminates

“…For AS2 scenarios, the presence of high temperatures and gas exhaust velocities could be critical for the erosion of ablative material. The specific conditions and requirements of the nozzle concept under study require an experimental assessment and could lead to the development of ad hoc formulated flexible protective layers, such as the one conceived for inflatable thermal shield presented in [60]. Innovative solutions for the nozzle protection could also be developed by using ablative/refractory and insulating layer made of fiber pre-forms.…”

Delamination Detection in Polymeric Ablative Materials Using Pulse-Compression Thermography and Air-Coupled Ultrasound

“…In the case of space vehicles, the PAM is typically a rigid aeroshell system. Silicone has been used as an infiltrant in different materials, including Acusil® I-IV, SLA-561, SLA-220, and Silicone Impregnated Reusable Ceramic Ablators (SIRCAs) [2,8,9]. However, the payload fairing of the rocket can limit the diameter of the structure.…”

“…Preliminary studies on IDAs indicate that these systems tend to require a smaller payload volume and mass fraction than traditional rigid materials. For example, NASA studied an advanced high temperature IDA for an inflatable re-entry vehicle, where the flexible construction contained high temperature fabrics, insulators, and a gas barrier [9]. Silicone has been used as a liner/coating or as a bonding agent in the production of such materials.…”