Forming method suitable for main force bearing frame body of satellite laser radar frame

A technology of laser radar and forming method, which is applied in applications, household appliances, household components, etc., can solve the problems affecting the imaging accuracy of laser radar, and achieve the effect of weight reduction, high structural precision and maintenance of structural precision

Active Publication Date: 2019-03-08
SHANGHAI COMPOSITES SCI & TECH CO LTD
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  • Application Information

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Problems solved by technology

[0003] Traditional metal materials have inherent characteristics of ther

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  • Forming method suitable for main force bearing frame body of satellite laser radar frame
  • Forming method suitable for main force bearing frame body of satellite laser radar frame
  • Forming method suitable for main force bearing frame body of satellite laser radar frame

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Embodiment Construction

[0048] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0049] The present invention provides a molding method suitable for the main load-bearing frame of the satellite laser radar frame, which includes the following steps: Step S1: laying prepreg on the mold, and reserving flanging to form the overall part of the frame 1 layering ;Step S2: laying prepreg on the heat expansion mold core, vacuumizing and pre-compacting after laying to form the frame cavity part 2 layup; step S3: laying prepreg on the mold and preparing frame reinforcement 3 ; Step S4: Lay the...

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Abstract

The invention provides a forming method suitable for a main force bearing frame body of a satellite laser radar frame. The forming method comprises the following steps: S1, prepreg is laid on a mold,a flange is reserved, and a laid layer of a frame body overall part (1) is formed; S2, prepreg is laid on a thermal expansion mold core, after laying is completed, vacuumizing and pre-compacting are conducted, and a laid layer of a frame body cavity part (2) is formed; S3, prepreg is laid on the mold, and frame body reinforcing ribs (3) are prepared; and S4, the laid layer of the frame body cavitypart (2) is placed at the preset position, the prepared frame body reinforcing ribs (3) are sequentially placed into the main force bearing frame body cavity part (2), and a frame body cavity mechanism is constituted. According to the forming method suitable for the frame body of the satellite laser radar frame, the overall rigidity of a main force bearing frame and structural stability of a product are improved, and meanwhile, the requirement of weight reduction is met.

Description

technical field [0001] The invention relates to a molding method of a composite material structure, in particular to a molding method suitable for a main load-bearing frame of a satellite lidar frame. Background technique [0002] With the continuous progress and development of the aerospace industry, the accuracy requirements of satellites are becoming more and more stringent. At the same time, reducing the weight of satellite structures is one of the main means to improve satellite performance. The reduction of satellite structure weight not only greatly reduces the launch of satellites. cost, and can also provide space for the design of the payload. The satellite lidar frame requires high installation accuracy and structural stability. In order to ensure the imaging requirements, it is suitable for the satellite lidar frame. , the parallelism between benchmarks is better than 0.01mm, and the angle accuracy must be guaranteed to ±0.01. In order to ensure the imaging stab...

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Application Information

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IPC IPC(8): B29C70/34B29C70/44B29C70/54B29L31/30
CPCB29C70/342B29C70/44B29C70/54B29L2031/3097
Inventor 史文锋赵丁丁郭金海詹光亮赵雍章宇界刘扬叶周军翟东坤
Owner SHANGHAI COMPOSITES SCI & TECH CO LTD
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