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Insensitive propellant composition

a propellant composition and insensitive technology, applied in the field of propellant compositions, can solve the problems of insufficient cracks in the binder, and intrinsic disadvantage of sco testing of htpb/ap propellant, and achieve the effect of improving sco properties

Inactive Publication Date: 2012-09-13
AGENCY FOR DEFENSE DEV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0009]The object of the present invention, which has been designed to solve the problems of prior arts, is to provide a novel solid propellant composition which is insensitive to impact and thermal stimulus and is suitably used for a solid rocket propulsion unit, specifically to provide a sold propellant composition which has class 1.3 in LSGT, 15 MPa / ms or less in a friability test and improved SCO properties.

Problems solved by technology

In the HTPB binder, a crosslinking reaction from double-bonds therein is generated which causes increase in brittleness as well as decomposition or vaporization of the components, leading to cracks in the binder.
For these reasons, the HTPB / AP propellant is intrinsically disadvantageous to SCO test.
Such HTPB / AP propellant with insensitive characteristics shows good results in friability test and LSGT properties, however it does not pass the SCO test.
In summary, HTPB / AP propellant shows good results in a bullet impact test, a fragment impact test and fast cook-off test, but its properties tested in SCO are not good enough.

Method used

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example

[0023]Hereinafter, the present invention is further illustrated through the following examples and comparative examples.

[0024]Tests regarding impact and thermal reactions in the examples and comparative examples were carried out by the following methods.

[0025]LSGT

[0026]LSGT refers to a large scale card gap test (LSGT) developed by US Naval ordnance laboratory (NOL), in which the reaction of a propellant to the energy delivered in the form of shock pressure is estimated. The shock pressure to be delivered to the specimen is generated by using detonation of a donor, i.e. an explosive, and adjusted by the gap between cards which are inserted between the explosive and specimen as a buffering material. As for the donor, Pentolite or Tetrile may be used, and as for the card material, wax, polymethylmethacrylate (PMMA), cellulose acetate and the like may be used.

[0027]When the card number is 70 or more (thickness 17.78 mm or more and shock pressure 31.74 Kbar or less), the hazard class is ...

example 1

[0035]A solid propellant composition composed of HTPE 6.5 wt %, N-3200 0.5 wt %, IPDI 0.3 wt %, BuNENA 10.8 wt %, AP 69.75 wt % (AP200 46 wt % and AP6 23.75 wt %), AN 10 wt % (AN150), ZrC 1.0 wt %, Fe2O3 0.25 wt %, TEPANOL 0.15 wt %, NMA 0.5 wt % and 2NDPA 0.25 wt % was prepared.

[0036]The above-mentioned various test results of this composition were shown in Table 1.

[0037]9.85 mm / s of combustion rate at 1,000 psia (20° C.), 0.5334 of pressure index, 7.5 bar of tensile strength, 65% of strain rate, 20.2 bar of elastic modulus, 1.714 g / cc of density and 2 pieces from EIDS SCO test.

example 2

[0038]A solid propellant composition composed of HTPE 6.5 wt %, N-3200 0.5 wt %, IPDI 0.3 wt %, BuNENA 10.8 wt %, AP 69.75 wt % (AP200 46 wt % and AP6 23.75 wt %), AN 10 wt % (AN50), ZrC 1.0 wt %, Fe2O3 0.25 wt % TEPANOL 0.15 wt %, NMA 0.5 wt % and 2NDPA 0.25 wt % was prepared.

[0039]The above-mentioned various test results of this composition were shown in Table 1.

[0040]9.87 mm / s of combustion rate at 1,000 psia (20° C.), 0.5321 of pressure index, 9.7 bar of tensile strength, 59% of strain rate, 24 bar of elastic modulus, 1.715 g / cc of density and 2 pieces from EIDS SCO test.

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Abstract

The present invention relates to a propellant composition which comprises hydroxy-terminated polyether (HTPE), N-butyl-(2-nitratoethyl)nitramine (BuNENA) and ammonium perchlorate (AP) and is insensitive to impact and thermal reactions and thus suitably used for a solid rocket propulsion unit.

Description

CROSS-REFERENCE TO RELATED APPLICATION[0001]This application claims the benefit of Korean Patent Application No. 10-2011-0020788 filed on Mar. 9, 2011, the entire disclosure of which is incorporated herein by reference.FIELD OF THE INVENTION[0002]The present invention relates to a propellant composition which comprises hydroxy-terminated polyether (HTPE), N-butyl-(2-nitratoethyl)nitramine (BuNENA) and ammonium perchlorate (AP) and is insensitive to impact and thermal stimulus and thus suitably is used for a solid rocket propulsion unit.BACKGROUND OF THE INVENTION[0003]Propulsion units, depending on their dimensions, casing types and propellant characteristics, exhibit different reactions to shock or heat applied from outside. It would be ideal if propulsion units do not show any reactions to shock or heat applied from outside, however they show any of reactions such as burning, deflagration, explosion or detonation.[0004]There are techniques for desensitizing a solid rocket propulsi...

Claims

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Application Information

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IPC IPC(8): C06B31/32
CPCC06B29/22C06B45/105C06B33/14C06B27/00C06B31/28
Inventor KIM, CHANG KEEYOO, JI CHANGMIN, BYOUNG SUNPARK, YOUNG CHUL
Owner AGENCY FOR DEFENSE DEV
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