Charging structure suitable for low-temperature ignition

A low-temperature ignition and charging technology, which is applied to rocket engine devices, jet propulsion devices, gas turbine devices, etc., can solve the problems of low detonation heat value of propellants, slow reaction rate, delayed ignition, etc., to improve ignition reliability and operation Convenience, improve the effect of delayed ignition

Active Publication Date: 2021-05-28
XIAN MODERN CHEM RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

From the perspective of propellants, low-combustion temperature solid gas generators mostly use low-combustion temperature double-base propellants. This type of propellant has a low detonation heat value, and its detonation heat value is le

Method used

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  • Charging structure suitable for low-temperature ignition
  • Charging structure suitable for low-temperature ignition
  • Charging structure suitable for low-temperature ignition

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Embodiment 1

[0049] This embodiment provides a charge structure suitable for low temperature ignition, such as image 3 As shown, it includes a propellant grain 1, and the center of the propellant grain 1 is provided with a central hole 2 through both ends along the axial direction;

[0050] One end of the propellant grain 1 is provided with an inner tapered opening 3 coaxially arranged and connected to the central hole 2;

[0051] The end surface of the other end of the propellant grain 1 is provided with a igniter ring installation groove 4, and a igniter ring 5 is embedded in the igniter ring installation groove 4, and the igniter ring 5 is coaxial with the central hole 2 set up;

[0052] One end face of the igniting drug ring 5 and the groove bottom of the igniting drug ring mounting groove 4 are bonded by a nitrocellulose solution adhesive layer 6;

[0053] A cladding layer 7 is arranged on the side wall of the propellant grain 1 .

[0054] As a preferred solution of this embodimen...

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Abstract

The invention provides a charging structure suitable for low-temperature ignition. The charging structure comprises a propellant grain, and a center hole with the two ends being through is formed in the center of the propellant grain in the axial direction; an inner conical opening which is coaxial with the center hole and communicates with the center hole is formed in one end of the propellant grain; an ignition powder ring mounting groove is formed in the end face of the other end of the propellant grain, an ignition powder ring is mounted in the ignition powder ring mounting groove in an embedded mode, and the ignition powder ring and the center hole are coaxially arranged; the end face of one end of the ignition powder ring and the bottom of the ignition powder ring mounting groove are bonded through a nitrocotton solution bonding layer; and a coating layer is arranged on the side wall of the propellant grain. According to the charging structure, on the premise that the internal ballistic property is met, the charging ignition reliability in the low-temperature environment can be effectively improved; and the phenomena of delayed ignition, ignition failure and the like during charging low-temperature ignition can be effectively improved, and the ignition reliability of charging in the low-temperature environment is greatly improved.

Description

technical field [0001] The invention belongs to the field of solid gas generators, and relates to a charging structure for ignition, in particular to a charging structure suitable for low-temperature ignition. Background technique [0002] Due to the low combustion temperature solid gas generator has the characteristics of low gas temperature, clean gas, and maintenance-free, it is widely used in aerospace, aviation, modern weaponry and other fields, such as turbine start, missile tail rudder attitude control, missile body wing Exhibition, low-temperature gas charging, etc. Reliable ignition of low-combustion temperature solid gas generators in low-temperature environments is a more concerned issue in this field, involving many comprehensive influencing factors. From the perspective of propellants, low-combustion temperature solid gas generators mostly use low-combustion temperature double-base propellants. This type of propellant has a low detonation heat value, and its de...

Claims

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Application Information

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IPC IPC(8): F02K9/95F02C7/264
CPCF02K9/95F02C7/264
Inventor 朱佳佳王中舒慧明杨立波郝碧莹贺海民弥阳丽张军
Owner XIAN MODERN CHEM RES INST
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