Rocket Nozzle Thermal Blanket With Water-Cooled Reusable Insulation

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Conventional thermal protection systems for rocket engine nozzles and launch vehicle components are prone to damage from high temperatures and require frequent refurbishment, and existing insulation materials are not durable enough for reusable launches.

Innovation Solution

A flexible thermal protection apparatus with a metal alloy outer fabric layer, ceramic fiber insulation, and water saturation to provide impact resistance, high heat capacity, and efficient heat absorption through vaporization.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If conventional insulating blankets made from silica insulation and quartz fabric are used, then thermal protection is provided, but the insulation is easily damaged by impact during flight and requires frequent replacement

Engineering Contradiction:

Improvedurability of insulationVSAvoidimpact damage

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The patent uses a composite structure combining silica insulation with a fabric reinforcement layer. The fabric layer is woven from high-temperature resistant fibers and stitched to the silica insulation using impact-resistant stitching patterns, creating a composite material that combines the thermal insulation properties of silica with the mechanical strength and impact resistance of the fabric reinforcement.

Inventive Principle:

Principle #40Composite materials

Solution Approach 2:

The patent employs a flexible fabric layer as a protective shell over the silica insulation. This thin film structure is designed to withstand impact forces during flight while maintaining flexibility for conforming to the rocket surface. The fabric layer acts as a protective barrier that prevents direct impact damage to the underlying silica insulation.

Inventive Principle:

Principle #30Flexible shells and thin films

2Temperature

If metal shielding is used to protect engine nozzles from high temperatures, then thermal protection is provided, but the metal changes shape due to thermal expansion

Engineering Contradiction:

Improveheat resistanceVSAvoiddimensional stability

Core Design Contradiction:

TemperatureVSShape

Solution Approach 1:

The patent changes the material parameters by using silica-based insulation materials that have low thermal conductivity and high temperature stability. The silica insulation maintains its structural integrity and dimensional stability at high temperatures, preventing the shape changes that occur with metal shielding. The material properties are specifically selected to resist thermal expansion while providing effective thermal protection.

Inventive Principle:

Principle #35Parameter changes

3Reliability

If single-use insulation is used, then thermal protection is provided for each launch, but the insulation must be replaced after every rocket launch

Engineering Contradiction:

Improvethermal protection effectivenessVSAvoidrefurbishment time

Core Design Contradiction:

ReliabilityVSLoss of time

Solution Approach 1:

The patent designs the insulation system with built-in impact resistance and durability features that prevent damage during flight and landing. The fabric reinforcement and impact-resistant stitching patterns provide beforehand protection against impact forces, allowing the insulation to survive multiple launches without degradation. This eliminates the need for replacement after each launch, reducing refurbishment time and costs.

Inventive Principle:

Principle #11Beforehand cushioning (Prior cushioning)

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

The apparatus effectively reduces heat exposure, maintains structural integrity, and allows for reusable launches with minimal refurbishment, while reducing the risk of deformation and damage.

Implementation Method 1

The apparatus can be saturated with water. This approach can utilize the high heat capacity and high heat of vaporization of water to insulate launch vehicle components when the launch vehicle reenters the atmosphere and lands.

Methodology Applied

Scientific EffectVaporization: Evaporation

Implementation Method 2

This approach can utilize the high heat capacity and high heat of vaporization of water to insulate launch vehicle components

Methodology Applied

Scientific EffectHeat of vaporization: Latent Heat

Implementation Method 3

an insulation layer positioned between two fabric layers... designed to reduce the effects of heat on the components

Methodology Applied

Scientific EffectThermal insulation: Thermal Insulation

Data Source

PatentUS20260071595A1High Temperature Thermal Protection System for Rockets, and Associated Methods

Publication Date: 2026.03.12 BLUE ORIGIN MANUFACTURING LLC

AI summary

A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and/or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and/or cooling effects.