Micro-power solid rocket engine combustion chamber shell bonding structure
A solid rocket and combustion chamber technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of unguaranteed assembly efficiency, high dependence on assembly tooling, and difficulty in meeting the requirements of appearance quality, so as to improve the appearance. Quality performance, guaranteed appearance, and the effect of improving production efficiency
Pending Publication Date: 2021-10-22
内蒙航天动力机械测试所
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Problems solved by technology
If the existing traditional thread and other connection methods are used for assembly like other types of engines, the reliance on assembly tooling is high, the process is complicated, the assembly efficiency cannot be guaranteed, and the appearance quality is difficult to meet the requirements.
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[0019] In order to make the purpose, features and advantages of the technical solution proposed by the present invention more obvious and understandable, the embodiments of the technical solution proposed by the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are only some of the embodiments of the proposed technical solution, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0020] Such as figure 1 Shown is a cross-sectional view of the bonding structure of the combustor shell of the new micro-powered solid rocket motor. It includes two parts, the front section 1 of the combustion chamber casing and the rear section 2 of the nozzle pipe of the combustion chamber casing. The entire combustion chambe...
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The invention relates to a solid rocket engine design and manufacturing technology, in particular to a micro-power solid rocket engine combustion chamber shell bonding structure. The bonding structure comprises a combustion chamber shell front section and a combustion chamber shell spray pipe rear section, wherein a joint of the combustion chamber shell front section 1 and the combustion chamber shell spray pipe rear section 2 is bonded by using glue, and the outer wall of the combustion chamber shell front section 1 and the inner wall of the combustion chamber shell spray pipe rear section 2 are bonded to form a solid rocket engine combustion chamber. According to the bonding structure, the problems of stress concentration, non-uniform strength and the like caused by single part machining due to usage of other connection modes are solved, the dependence on a later final assembly tool is greatly reduced or even eliminated, a technological process is simplified, especially for engines produced in batches, production efficiency is greatly improved, an appearance of a product is effectively prevented from being damaged, and appearance quality performance of the product is improved.
Description
technical field [0001] The invention relates to the design and manufacture technology of a solid rocket motor, in particular to a bonding structure for a shell of a combustion chamber of a micro-power solid rocket motor. Background technique [0002] Due to the particularity of the solid rocket motor, the assembly of the motor is manual work. Due to the limited size of the micro-engine and the consideration of the mass ratio, the combustion chamber shell is generally made of soft and light (relative to steel) aluminum. If traditional threads and other connection methods are used like other types of engines, the efficiency of later assembly will not be guaranteed, and the appearance quality will hardly meet the requirements. Aiming at this problem, the present invention proposes a bonding structure for the combustor casing of a micro-powered solid rocket motor, which divides the combustor casing into two and bonds them during assembly, which can replace the front head and the...
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Login to View More IPC IPC(8): F02K9/34F02K9/32
CPCF02K9/34F02K9/343F02K9/32
Inventor 陈国栋马海波邓斌
Owner 内蒙航天动力机械测试所