Resorbable Nozzle Cowling for Spacecraft Drag Reduction

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Solution Overview

Problem

Current solutions for reducing aerodynamic drag on spacecraft during non-atmospheric flight phases are either heavy, complex, or pose debris risks, especially when rocket engines are unused, as they require heavy release mechanisms and additional drag during ignition.

Innovation Solution

A lightweight, passive rocket engine nozzle cowling device made of resorbable material that covers the nozzle and is designed to be eliminated by combustion, ensuring safe ignition and elimination without debris risks, using a conical shape to reduce drag and attachable via removable means for easy reuse.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a heavy release device is used to drop the conical rear cover before rocket ignition, then the cover can be removed to allow engine operation, but the device becomes heavy and complex and risks debris damage to engines

Engineering Contradiction:

Improvesafe engine ignitionVSAvoidweight of release device

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The harmful conical rear cover is extracted from the system by designing it to be automatically removed through combustion during rocket ignition, eliminating the need for heavy mechanical release devices and debris containment mechanisms

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The potentially harmful debris from cover removal is converted into a beneficial combustion process that actively clears the cover away, transforming a risk into a reliable removal mechanism that ensures safe engine operation

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

2Ease of operation

If removable active devices are used to mask the nozzle, then the device can be maneuvered and positioned, but the device becomes heavy and requires complex maneuvering mechanisms

Engineering Contradiction:

Improvedevice positioningVSAvoidweight of maneuvering device

Core Design Contradiction:

Ease of operationVSWeight of moving object

Solution Approach 1:

The conical rear cover is designed to position itself automatically through aerodynamic forces and combustion-driven removal, eliminating the need for active maneuvering systems and reducing overall device weight

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

Mechanical maneuvering systems are replaced with a passive combustion-based removal mechanism that automatically positions and eliminates the cover, simplifying the system and reducing weight

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Manufacturing precision

If complex deployment systems are used to deploy the nozzle cover, then the cover can be positioned accurately, but the system creates additional drag during ignition and becomes complex to implement

Engineering Contradiction:

Improvecover deployment accuracyVSAvoidcomplexity of deployment system

Core Design Contradiction:

Manufacturing precisionVSDevice complexity

Solution Approach 1:

The complex deployment system is extracted and replaced with a simple combustion-driven removal mechanism that achieves accurate positioning through the natural combustion process rather than mechanical deployment

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The state of the cover transitions from intact to combusted through temperature and pressure parameter changes during rocket ignition, achieving deployment without complex mechanical systems

Inventive Principle:

Principle #35Parameter changes

4Shape

If fluid injection devices are used to fill the depression at the rear of the vehicle, then the aerodynamic profile is improved, but the fluid must be loaded into the vehicle which reduces payload

Engineering Contradiction:

Improveaerodynamic profileVSAvoidpayload capacity

Core Design Contradiction:

ShapeVSQuantity of substance

Solution Approach 1:

Instead of loading valuable payload fluid, a disposable conical cover is used that is eliminated through combustion, providing aerodynamic benefits during atmospheric flight without consuming payload resources

Inventive Principle:

Principle #27Cheap short-living objects (Disposable)

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 solution effectively reduces aerodynamic drag during atmospheric and non-atmospheric phases while ensuring safe engine ignition and eliminating debris risks, with a lightweight and simple design that maintains aerodynamic efficiency and can be reused.

Implementation Method 1

at least one masking element 5 made of resorbable material 6, that is to say a material which is eliminated by combustion when it is subjected to a flow of heat

Methodology Applied

Scientific EffectCombustion: Combustion

Implementation Method 2

a material which is eliminated by combustion when it is subjected to a flow of heat coming from the jet of an engine

Methodology Applied

Scientific EffectAerodynamic heating: Aerodynamic Heating

Data Source

PatentEP2242691B1Device for reducing aerodynamic drag

Publication Date: 2017.03.01 AIRBUS DEFENCE & SPACE SAS

AI summary

The invention relates to a device for reducing the aerodynamic drag of a vehicle (1) provided with at least one engine (2) including a gas ejection nozzle (3) protruding from the rear of the vehicle fuselage (4) and flaring away from the rear of the vehicle fuselage, characterised in that it comprises at least one member (5) for masking at least a portion of the nozzle, made of a resorptive material (6) that can be eliminated in the nozzle flow once the engine is operating. The invention also relates to a spacecraft including the same.