Electrically Ignitable Propellants for Static Discharge Safety

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Solution Overview

Problem

Conventional electrically controlled propellants face issues such as spark sensitivity to static discharge, inability to sustain combustion at low pressures without continuous electrical power, and lower burn rates at high pressures, limiting their application in space and military uses where precision and efficiency are crucial.

Innovation Solution

Development of a family of electrically ignitable propellants that are resistant to ignition by electrical static discharge, capable of sustained combustion at ambient and elevated pressures without continuous electrical power, and exhibit faster burn rates, using energetic ionic liquid oxidizers and hydrocarbon fuels with specific polymer binders, allowing for ignition and control through electrical power and pressure.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If conventional electrically controlled propellants are used, then ignition control is achieved, but the propellants are sensitive to static discharge sparks causing accidental ignition

Engineering Contradiction:

Improveignition controlVSAvoidstatic discharge sensitivity

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The patent changes the chemical composition parameters of the propellant by incorporating specific oxidizers (ammonium perchlorate, ammonium nitrate), fuels (aluminum powder, iron powder), and binders (hydroxyl-terminated polybutadiene, polyvinylidene fluoride) in optimized ratios. This composition modification raises the ignition temperature threshold and reduces sensitivity to static discharge while maintaining electrical controllability through careful selection of conductive binders and oxidizer particle characteristics.

Inventive Principle:

Principle #35Parameter changes

2Duration of action of moving object

If conventional propellants are used, then combustion can be initiated electrically, but sustained combustion at low pressures requires continuous electrical power

Engineering Contradiction:

Improvecombustion sustainabilityVSAvoidelectrical power consumption

Core Design Contradiction:

Duration of action of moving objectVSUse of energy by moving object

Solution Approach 1:

The patent creates a self-sustaining combustion system where the propellant composition itself provides the necessary oxidizer (ammonium perchlorate, ammonium nitrate) and fuel (aluminum, iron powders) in optimal proportions. Once initiated electrically, the chemical reactions within the composite generate sufficient heat and self-oxidation to maintain combustion without continuous external electrical power, especially at elevated pressures where the reaction rate increases.

Inventive Principle:

Principle #25Self-service

3Productivity

If conventional propellants are used, then basic propulsion function is achieved, but burn rates are lower at high pressures

Engineering Contradiction:

Improveburn rateVSAvoidhigh pressure performance

Core Design Contradiction:

ProductivityVSStress or pressure

Solution Approach 1:

The patent employs a composite propellant formulation combining multiple components with complementary properties: ammonium perchlorate and ammonium nitrate oxidizers provide rapid oxygen release, aluminum and iron fuels offer high energy density and burn rate enhancement, hydroxyl-terminated polybutadiene provides flexible binder matrix with good combustion characteristics, and polyvinylidene fluoride adds electrostatic control capability. This composite structure synergistically increases burn rate at high pressures while maintaining structural integrity.

Inventive Principle:

Principle #40Composite materials

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 new propellants provide improved safety, efficiency, and precision in combustion, enabling applications in space and military systems with enhanced thrust and specific impulse, reducing the need for chemical sensitizers and minimizing toxicity and cost.

Implementation Method 1

capable of ignition or enhanced combustion or detonation by the input of electrical power

Methodology Applied

Scientific EffectCombustion: Combustion

Implementation Method 2

ignition and control through electrical power

Methodology Applied

Scientific EffectJoule heating: Joule Heating

Data Source

PatentUS8888935B2Family of modifiable high performance electrically controlled propellants and explosives

Publication Date: 2014.11.18 DIGITAL SOLID STATE PROPULSION INC

AI summary

A composition capable of producing either solid propellant grains, liquid or gel monopropellants, all of which are electrically ignitable and capable of sustained controllable combustion at ambient pressure. Additional compositions capable of sustained controllable combustion at elevated pressures are described. Applications for the compositions disclosed herein are provided, and include among other applications use in small micro thrusters, large core-burning solid propellant gains, shaped explosives charges for military application, and pumpable liquids and gel monopropellants or explosives for military, commercial mining or gas and oil recovery. In alternative embodiments the above compositions may also incorporate an energetic nitrate polymer, bum rate modifiers, and/or metal fuel(s). The HIPEP formulation makes it possible to ignite and sustain combustion at ambient and vacuum conditions (a) without continuous electrical power and (b) while providing faster bum rates.