Annular combustion increasing structure on charging outer end surface of missile engine
An engine and outer end face technology, applied in rocket engine installations, machines/engines, mechanical equipment, etc., can solve the problems of reduced engine mass ratio, increased engine risk, and reduced performance, increased initial thrust, and eliminated grain stress concentration. With cracks, the effect of avoiding the reduction of the mass ratio
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[0014] The invention will be described in more detail hereinafter with reference to the accompanying drawings showing embodiments of the invention. However, this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
[0015] Such as figure 1 Shown is a schematic diagram of the circumferential combustion-increasing structure on the outer end face of the missile engine charge of the present invention.
[0016] The combustion-increasing structure includes 1: powder column, 2: coating sleeve, and 3: liner. The powder column and the covering sleeve are firmly bonded through the lining layer.
[0017] The powder column 1 adopts hydroxybutylated propellant, and the powder column 1 is in the shape of a solid column charged with powder. The ou...
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