Multi-pulse rocket motor
US-2021381468-A1 · Dec 9, 2021 · US
Rocket motor with concentric propellant structures for shock mitigation
US10731604B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10731604-B2 |
| Application number | US-201615221638-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jul 28, 2016 |
| Priority date | Aug 13, 2015 |
| Publication date | Aug 4, 2020 |
| Grant date | Aug 4, 2020 |
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- Title
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Abstract
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A solid rocket motor includes a first solid propellant and a second solid propellant at least partially surrounding the first solid propellant. The second solid propellant is resistant to fragment impact and the first solid propellant has a higher impulse than the second solid propellant.
First claim
Opening claim text (preview).
What is claimed is: 1. A solid rocket motor comprising: a first solid propellant and a second solid propellant at least partially surrounding the first solid propellant, wherein the second solid propellant is resistant to fragment impact and the first solid propellant has a higher impulse than the second solid propellant, wherein the rocket motor has a diameter, and the second solid propellant has a total diametric thickness, as a percentage of the diameter, of 5% to 20%, and the first solid propellant includes nitramine solid oxidizer and the second solid propellant excludes any nitramine solid oxidizer, wherein the first solid propellant has a composition: Constituent Trade Name Function Nominal wt % Flake Aluminum Aluminum Ballistic ≤0.5% Modifier Lead Citrate Lead Citrate Burn Rate 2-5% Modifier Cyclotetramethyl- HMX, <3 Solid energetic/ 45%-65% enetetranitramine micron gas generator Nitrocellulose NC Energetic 0-2% Binder Trimethylolethane TMETN Energetic 10-20% trinitrate Plasticizer Butanetriol BTTN Energetic 10-20% trinitrate Plasticizer R-18 Polyester R-18 Binder 4-6% Polycaprolactone PCL Binder 2-4% Nitrodiphenylamine 2-NDPA Stabilizer 0.5%-1.0% N-Methyl-P-Nitroaniline MNA Stabilizer 0.5%-1.0% Hexamethylene diisocyanate HMDI Curative .5-2.0% and the second solid propellant has a composition: Constituent Trade Name Function Nominal wt % Flake Aluminum Aluminum Ballistic ≤0.5% Modifier Lead Citrate Lead Citrate Burn Rate 2-5% Modifier Nitrotriazolone NTO Solid energetic/ 45%-65% gas generator Nitrocellulose NC Energetic 0-2% Binder Trimethylolethane TMETN Energetic 10-20% trinitrate Plasticizer Butanetriol trinitrate BTTN Energetic 10-20% Plasticizer R-18 Polyester R-18 Binder 4-6% Polycaprolactone PCL Binder 2-4% Nitrodiphenylamine 2-NDPA Stabilizer 0.5%-1.0% N-Methyl-P- MNA Stabilizer 0.5%-1.0% Nitroaniline Hexamethylene HMDI Curative .5-2.0%. diisocyanate 2. The solid rocket motor as recited in claim 1 , further comprising a migration barrier between the first solid propellant and the second solid propellant. 3. The solid rocket motor as recited in claim 2 , wherein the migration barrier includes a polymeric layer or a metallic layer. 4. The solid rocket motor as recited in claim 1 , wherein the second solid propellant is resistant to fragment impact according to MIL-STD-2105D and NATO STANAG 4496. 5. The solid rocket motor as recited in claim 1 , further comprising a motor case in which the first solid propellant and the second solid propellant are disposed, and a nozzle disposed at one end of the motor case. 6. The solid rocket motor as recited in claim 2 , wherein the migration barrier includes a vin
Assignees
Inventors
Classifications
Stabilisers (e.g. thermal stabilisers) (processes C06B21/0091; foam stabilisers C06B23/002) · CPC title
Shape or structure of solid propellant charges · CPC title
made of two or more portions burning at different rates {or having different characteristics} · CPC title
The resin being a polymer bearing energetic groups or containing a soluble organic explosive · CPC title
having contiguous layers or zones · CPC title
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Frequently asked questions
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- What does patent US10731604B2 cover?
- A solid rocket motor includes a first solid propellant and a second solid propellant at least partially surrounding the first solid propellant. The second solid propellant is resistant to fragment impact and the first solid propellant has a higher impulse than the second solid propellant.
- Who is the assignee on this patent?
- Aerojet Rocketdyne Inc
- What technology area does this patent fall under?
- Primary CPC classification F02K9/28. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Aug 04 2020 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).