Ablative Fin Stop Tangs for High Speed Vehicle Launch

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Solution Overview

Problem

Existing aerodynamic surface locking systems for boosted launch vehicles are complex, pose safety hazards due to debris from frangible or pyrotechnically disengaged locks, and fail to reliably disengage at predetermined flight phases, risking uncontrollable flight or carrier aircraft collision.

Innovation Solution

A passive control fin stop system using an ablatively erodible tang housing that constrains control fins during launch and releases them through aerodynamic heating, ensuring safe separation and allowing free motion upon power application.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Stability of the object's composition

If mechanical control locks are used to maintain control surfaces in a neutral position during launch, then control surface stability is improved, but device complexity increases and additional failure modes are introduced

Engineering Contradiction:
Improvecontrol surface stabilityVSAvoidlocking mechanism complexity
Core Design Contradiction:
Stability of the object's compositionVSDevice complexity

Solution Approach 1:

The patent extracts the locking function from complex mechanical mechanisms and implements it through simple ablatively erodible tangs that passively constrain control surfaces. The tangs are basic structural elements without moving parts, activation mechanisms, or complex geometries, eliminating the complexity associated with traditional mechanical locks while maintaining the stabilizing function during launch.

Inventive Principle:
Principle #2Taking out (Extraction)

Solution Approach 2:

The control surface locking tangs are designed as disposable, ablatively erodible components that serve their locking function only during the brief launch phase. They are intentionally designed to be consumed through ablation when exposed to aerodynamic heating, transitioning from a constrained to an unconstrained state without requiring complex activation mechanisms.

Inventive Principle:
Principle #27Cheap short-living objects (Disposable)

2Ease of operation

If frangible locks or pyrotechnically disengaged locks are used to release control surfaces, then control surface disengagement is achieved, but debris is produced which poses safety hazards to the vehicle

Engineering Contradiction:
Improvecontrol surface disengagementVSAvoiddebris hazard
Core Design Contradiction:
Ease of operationVSObject-generated harmful factors

Solution Approach 1:

The patent converts the harmful effect of aerodynamic heating into a beneficial disengagement mechanism. The same aerodynamic heating that occurs during normal flight is utilized to ablatively erode the tangs, causing them to shrink and release the control surfaces. This eliminates the need for frangible locks or pyrotechnics that会产生 debris, as the tangs disintegrate cleanly through controlled ablation.

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

3Stability of the object's composition

If traditional locking mechanisms are used, then control surface constraint is achieved, but reliable disengagement at predetermined flight phases cannot be ensured

Engineering Contradiction:
Improvecontrol surface constraintVSAvoiddisengagement reliability
Core Design Contradiction:
Stability of the object's compositionVSReliability

Solution Approach 1:

The patent utilizes parameter changes in the tang material properties through ablation. The tangs are made from materials with specific ablation characteristics that cause them to shrink and change geometry when exposed to aerodynamic heating at predetermined flight phases. This automatic parameter change ensures reliable disengagement without requiring external activation signals or complex timing mechanisms.

Inventive Principle:
Principle #35Parameter changes

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 system provides a structurally simple, cost-effective means to prevent unwanted control fin motion during launch, ensuring safe separation and reliable disengagement, while being fail-safe and non-obstructive to powered actuation.

Implementation Method 1

The tang is ablatively erodible at a predetermined temperature induced by a flight profile of the vehicle to allow unconstrained motion of the fin

Methodology Applied
Scientific EffectAblation: Ablation

Implementation Method 2

a predetermined temperature induced by a flight profile of the vehicle

Methodology Applied
Scientific EffectAerodynamic heating: Aerodynamic Heating

Data Source

PatentUS9372055B2Passive control fin stops for air launched boosted (two stage) high speed vehicles
Publication Date: 2016.06.21 THE BOEING CO
  • US9372055B2 patent drawing
  • US9372055B2 patent drawing
  • US9372055B2 patent drawing

AI summary

A temporary control fin stop system employs a housing coupled to a vehicle. At least one tang is coupled to the housing and positioned to engage a trailing edge of a fin. The tang is ablatively erodible at a predetermined temperature induced by a flight profile of the vehicle to allow unconstrained motion of the fin.