Middle-boron-content rich fuel propellant with high burning rate pressure exponent

A fuel-rich propellant, boron content technology, applied in offensive equipment, compressed gas generation, explosives, etc., can solve the problems of boron-rich fuel-rich propellant energy performance, burning rate and pressure index difficulties, etc., to improve the gas phase product Concentration, increased gas production, increased heat absorption effect

Active Publication Date: 2018-06-22
NAT UNIV OF DEFENSE TECH
4 Cites 10 Cited by

AI-Extracted Technical Summary

Problems solved by technology

[0009] Although the agglomeration of boron particles can effectively improve the burning rate pressure index of boron-containing fuel-rich propellants, in engineering applications, after the content of agglomerated boron in the formulation of boron...
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Abstract

The invention discloses a middle-boron-content rich fuel propellant with a high burning rate pressure exponent. The middle-boron-content rich fuel propellant is prepared from 20-28 wt% of adhesive system which is composed of an adhesive and plasticizer, 20-28 wt% of oxidizing agent, 10-20 wt% of metal fuel, 5-15 wt% of amorphous boron powder, 10-20 wt% of agglomerated boron, 3-6 wt% of burning rate catalyst, 0.5-1.5 wt% of curing agent and 0.5-6 wt% of modifier, wherein the modifier is selected from one of titanium hydride, fluorene, ammonium nitrate, nanometer ferric oxide, adamantane, anthracene and anthraquinone. By means of the middle-boron-content rich fuel propellant, the burning rate pressure exponent can be increased, and the negative influence on the energy performance of the richfuel propellant is reduced.

Application Domain

ExplosivesPressure gas generation

Technology Topic

ChemistryBurn rate +14

Image

  • Middle-boron-content rich fuel propellant with high burning rate pressure exponent
  • Middle-boron-content rich fuel propellant with high burning rate pressure exponent
  • Middle-boron-content rich fuel propellant with high burning rate pressure exponent

Examples

  • Experimental program(6)

Example Embodiment

[0028] Example 1
[0029] (1) Propellant composition
[0030] The formula composition of the reference formula and the propellant of the present invention is shown in Table 1 below, and the content thereof is calculated by mass percentage.
[0031] Table 1 The composition of the formula of the invention and the reference formula in Example 1
[0032]
[0033] (2) Performance of boron-containing fuel-rich propellant: the burning rate pressure index of the propellant of the reference formula at 0.5-2.0 MPa is 0.35, and the measured calorific value of the oxygen bomb is -23185.9 kJ/kg; the propellant of the present invention is 0.5 The burning rate pressure index under -2.0MPa is 0.44, and the measured calorific value of the oxygen bomb is -23791.4kJ/kg.

Example Embodiment

[0034] Example 2
[0035] (1) Propellant composition
[0036] The formula composition of the reference formula and the propellant of the present invention is shown in Table 2 below, and the content thereof is calculated by mass percentage.
[0037] Table 2 The composition of the formula of the invention and the reference formula in Example 2
[0038]
[0039] (2) Performance of boron-containing fuel-rich propellant: the burning rate pressure index of the propellant of the reference formula at 0.5-2.0 MPa is 0.35, and the measured calorific value of the oxygen bomb is -23185.9 kJ/kg; the propellant of the present invention is 0.5 The burning rate pressure index under -2.0MPa is 0.44, and the measured calorific value of the oxygen bomb is -24086.5kJ/kg.

Example Embodiment

[0040] Example 3
[0041] (1) Propellant composition
[0042] The formula composition of the reference formula and the propellant of the present invention is shown in Table 3 below, and the content thereof is calculated by mass percentage.
[0043] Table 3 The composition of the formula of the invention and the reference formula in Example 3
[0044]
[0045] (2) Performance of boron-containing fuel-rich propellant: the burning rate pressure index of the propellant of the reference formula at 0.5-2.0 MPa is 0.35, and the measured calorific value of the oxygen bomb is -23185.9 kJ/kg; the propellant of the present invention is 0.5 The burning rate pressure index under -2.0MPa is 0.42, and the measured calorific value of the oxygen bomb is -24043.6kJ/kg.

PUM

PropertyMeasurementUnit
Calorific value23185.9kJ/kg
Calorific value23791.4kJ/kg
Calorific value24086.5kJ/kg

Description & Claims & Application Information

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