JPS58223683A - Propellent composition - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION This invention relates to propellant compositions, and more particularly to composite propellant compositions with improved pressure index.

Conventionally, the launch@ is a single base from its main component.

Double base, triple base and composite Ru...
It is classified as a propellant charge, and each one is known.

In general, the performance required for propellants is that the explosive power (f) is high, the combustion temperature (T) is low, and the pressure index (n index) is small, as well as physical strength that can withstand use.
These include having sensitivity and stability.

Here, the n index is the value of n expressed by the following formula.

r=BPn (r is the firing rate, P is the combustion pressure, and B is the coefficient) As the composite propellant, ethyl cell mouth)-su,
Energy-free plasticizer (using isodecyl perabonate),
A propellant composition based on triaminoguanidine (TAGN) and cyclotetramethylenetetranitramine (HMX) is disclosed in U.S. Pat. No. 8,782,130.
Also, nitrocellulose (NC), energy-free plasticizer (
(using polyethylene glycol or polypropylene glycol).

Propellant compositions based on TA()N and HMX or cyclotrimethylenetrinitramine (RDX), respectively, are disclosed in US Pat. No. 3,909,828.

However, these compositions have explosive power (f) of about 1o
o o o ~11500 t-Kp・17cm”Ay
is relatively small, and nothing is shown about the n index.

As a propellant with higher explosive power (1) than these compositions, the main components are NC, nitroplasticizer (using trimethylolethane trinitrate, triethylene glycol trinitrate), TAC)N, and RDX or HMX. A propellant composition is disclosed in US Pat. No. 8,732,131.

However, this composition does not support the high explosive power that double base propellants have, i.e. 12,000 t-Ky in f.
Although it has the advantages of both f, km”/Kp and a low combustion temperature like that of triple pace propellants, i.e.
7 cm'') had the disadvantage that the n-index was 1.4 or more.

The n-index required for propellant is the commonly used l
OOO~? 4 FI OOK 9.17 cm" combustion pressure range is preferably 1.0 F or higher, and if it is 1.1 or higher, the combustion pressure will rise abnormally when ignited inside the gun, so it is recommended to set it below the allowable passenger pressure of the gun. design is impossible.

In addition, TAGN is used in all of the above specifications.

There is no description regarding the particle sizes of RDX and HMX.

Therefore, the inventors of the present invention developed a large explosive power (f-ki 12,000
t-Ky-f/♂/9) and low combustion temperature (T-Ky800
As a result of extensive research on composite propellant compositions that maintain n-index values smaller than 1.1 while maintaining the The present invention was completed by using and RDX.

That is, the present invention provides the following advantages: NC1 plasticizer, TAGN and DX
In the propellant composition mainly composed of, the plasticizer consists of nitroglycerin (NG) and an energyless plasticizer,
The propellant composition is characterized in that the weight average particle diameter of TAGN and RDX is 20 μm or less.

Here, the energy-free plasticizer refers to NG and the above-mentioned US patent 1.
It does not mean a plasticizer made of a compound having a nitro group, such as the nitro plasticizer described in the TA7AZTAT specification, but a plasticizer made of a compound that does not have a nitro group in its molecule.

Such plasticizers include, for example, diethyl phthalate (DEP), polyethylene glycol (PEG), polypropylene glycol (PPG).

Examples include diisobutylazibe) (DIBA) and dioctylazibe) (DOA).

When these plasticizers are used, they are used in combination with KaNG, which is used alone or as a mixture of two or more culms. Unless used in combination with NG, the n-index cannot be lowered.

Further, even if the above-mentioned nitro plasticizer is used instead of the combination of N() and an energyless plasticizer, the n-index cannot be lowered.

Further, the weight average particle size of TAGN and RDX used in the present invention must be 20 μm or less, and if the weight average particle size of both or one of them is larger than 20 μm, the n-index cannot be lowered.

What is the proportion of the main components in the propellant composition of the present invention?

NCIJ'-10-20 heavy punch%, NG is 5-15mM
%.

It is preferable that the energy-free plasticizer is fi-10% by weight, and the total amount of TAGN and RDX is 65 to 801% by weight.

If the NC is less than 10% by weight and the combined amount of NG and the energy-free plasticizer is less than 10% by weight, it is unfavorable from the viewpoint of productivity.
If it is less than % b, the gunpowder power decreases, so KIFf is not possible. Furthermore, if the NC content exceeds 20% by weight, the explosive power decreases and the combustion temperature increases, which is undesirable.If the total amount of plasticizer exceeds 81% by weight, the physical strength decreases, which is undesirable. The total amount of is 80%
Exceeding this is not preferable because the n index tends to increase.

The propellant composition of the present invention can be produced, for example, as follows.

First, RDX and TA()N are each processed using a ball mill etc.
The average particle diameter of the mold is adjusted to 20 μm or less. Add the specified amounts of this RDX, TAGN, and NC in a uniform manner, add a specified solvent (for example, a mixed solvent of ethyl acetate and ethanol), and if necessary, dissolve a stabilizer in the solvent, then add a small amount of the solvent. Perform premixing. -Next, a predetermined amount of NG, an energyless plasticizer i agent, and the remaining solvent are added thereto, and main kneading is carried out for 8 to Φ hours. Then, companding is performed. Both kneading and drawing can be carried out using a conventional solvent drawing device. Next, the drawn powder is air-exposed, cut into desired shapes or lengths depending on the use, and dried to obtain propellants.

Example 1 A propellant having the composition shown in Table 1 (Example 1) at tP was produced as follows.

R whose weight average particle diameters are 15 μm and 2 μm, respectively.
DX and TA()N were prepared.

Next, 26% ethanol wet NC (759° nitrogen iig, e% in dry i7) and RDX 150? To'i'AG
Pour N2 (lOf) into ethyl acetate:
Of the mixed solvent 105F of 1:1 ethanol, fifig was added and premixed for 10 minutes. In addition, all 3 stabilizers (ethyl central) (ECL) are added to the mixed solvent in advance.
2 had been dissolved. Next, 50r of NG, DEP151 and the remaining 50r of the mixed solvent were added, and the main addition was carried out for 8 hours. Next, the kneaded drug was loaded into a drawing machine, and a pre-pressure was gently applied to form a drug mass containing no air bubbles, which was then drawn using a 7-hole drug manufacturing die. This drawn charge was exposed to the wind, cut, and dry-recorded to obtain propellant charge.

Using this propellant, a combustion test was conducted using a sealed pump (inner volume: 150 cc) for evaluating ordinary propellants, the combustion pressure and combustion time were measured, and the n-index was determined therefrom. The results are shown in Table 1 from 1000 to aoooQ・f/
It is expressed as an average n index at a combustion pressure of -.

In addition, the explosive power (
f) and combustion temperature (T) were determined, and the results are also shown in Table 1.

Example 2 A propellant having the formulation 1 and composition (Example 2) shown in Table 1 was produced in accordance with Example 1K except that DEP, which is an energyless plasticizer, was replaced with DOA K.

The same combustion tests and calculations as in Example 1 were performed using the obtained propellant. The results are shown in the J%i table.

DEP, which is an energy-free plasticizer, was replaced with py:a (molecular weight 400) and t-lDIBAtC, RDX and f'A.
GN (7) Weight average particle diameter of 8 μm and 12 μm, respectively.
Propellant powders having the formulations shown in Table 1 (Examples 8 and 4) were produced according to Example 1, except that μm, 4 μm, and 211 m were used.

Using the obtained propellants, the same combustion tests and calculations as in Example 1 were conducted for each. The results are shown in Table 1.

Example 11CQ4 A propellant having the formulation shown in Table 1 (Example b) was produced in the same manner as in Example 11CQ4, except that the energy-free plasticizer DEP was replaced with a mixture of DEP and DOA.

Using the obtained propellant, the same combustion test as in Example 1 and 1
I performed f calculation. The results are shown in Table i1.

The symbols in Table 1 are as follows: NC: Nitrocellulose NG = Nitroglycerin Dgp: Diethyl phthalate DOA: Dioctyl adipate PEG:
Polyethylene glycol DIBA: Diisobutyl adipate RDX: Cyclotrimethylenetrinitramine TA()N: )Liaminoguanidine nitrate ECL: Ethyl centralit Comparative example 1 The formulation composition shown in Table 2 (Comparative Example 1) was prepared according to Example 11, except that the agents trimethylolethanetrinitrite (TMETN) and triethylene glycol trikitreinite (TEGTN) were replaced. Propellant was manufactured.

The same combustion tests and calculations as in Example 1 were performed using the obtained propellant. The results are shown in Table 2.

Comparative Examples 2 and 8 Same as Example 1 except that RDX with a weight average particle diameter of 120 μm or 8 μm and TAGN with a weight average particle diameter of 2 μm or 80 μm were used, respectively, and the formulation composition shown in Table 2 (Comparative Example 2 and 8) propellant was manufactured.

Using the obtained propellants, the same combustion tests and calculations as in Example 1 were conducted for each. The results are shown in Table 2.

Comparative Example Example except that the nitroplasticizers TMETN and TEGTN were used instead of the multi-NG and the turnip energy plasticizer DIUP, and RDX with a weight average particle size of 120 μm and TAGN with a weight average particle size of 80 μm were used. A propellant having the composition shown in Table 2 (Comparative Example 4) was manufactured according to IK.

The same combustion tests and calculations as in Example 1 were performed using the obtained propellant. The results are shown in Table 2.

The same symbols as in Table 1 on the middle side of Table 2 indicate the same compounds TMETN
: ) Limethylolethane trinitrate TEG
TN: ) using NG and a non-energy plasticizer as a polyethylene glycol trinitrate plasticizer,
and TAGN and RD with a weight average particle diameter of 20 μm or less
The propellant compositions of the present invention (Examples 1 to 5) using
Large explosive power (fki 12000t-Kp・f7tx”7
The first priority is to maintain a low combustion temperature (8000°K during T) and a small n index of 0.97 to 1.08.
It is clear from the table.

On the other hand, TAGN and R with a weight average particle diameter of 20 μm or less
Even if DX is used, in the case of a propellant composition using a nitroplasticizer (Comparative Example 1), a large explosive power and a low combustion temperature are maintained, but the n-index is clear from Table 2. It is as high as 1.11. This n index is '1' AGN with large grain size.
Even if RDX and RDX are used (comparative example Φ), it cannot be made smaller, and on the contrary, it is as large as 1.51.

In addition, even if NG and a non-energy plasticizer are used as plasticizers, if the weight average particle diameter of TAGN or RDX exceeds 204 m (Comparative Examples 2 and 8), large explosive power and low combustion temperature can be maintained. As is clear from Table 2, the index is thick as Kl, gl゛, and 1.42.

As explained in detail above, the propellant composition of the present invention σ) is n
It has a low pulse rate, high explosive power, and low combustion temperature, making it extremely useful in industry as a firing pear.

Patent applicant: NOF Corporation

Claims (1)

[Scope of Claims] A propellant composition comprising L nitrocellulose, a plasticizer, triaminoguanidine nitrate, and cyclotrimethylene l-IJ nitramine, wherein the plasticizer comprises nitroglycerin and an energyless plasticizer. Become,
A propellant composition characterized in that the triaminoguanidine nitrate and cyclotrimethylene trinitramine have a weight average particle diameter of 1□1 particle of 20 μm or less. λ Nitrocellulose is 10-2omfi:%, nitroglycerin is 5-15%, and energy-free plasticizer is 5%.
~10% by weight, the total amount of triaminoguanidine nitrate and cyclotrimethylene trinitramine is 55~8
The propellant composition according to claim 1, wherein the retention range is 0% by weight. & Heat energy plasticizer is diethyl phthalate. The propellant composition according to claim 1 or 2, which is one or more selected from the group consisting of polyethylene glycol, polypropylene glycol, diisobutyl adipate, and dioctyl adipate.