Composite material thin-wall type telescopic probe rod for satellite and forming method of composite material thin-wall type telescopic probe rod

Abstract

The invention discloses a composite material thin-wall type telescopic feeler lever for satellites and a forming method of the feeler lever, and belongs to the technical field of satellite accessories. (2) preparing a mold; (3) blanking: cutting prepreg sheets at various angles required by laying by using an automatic fabric cutting machine for later use; 4) paving: preparing a prepreg, and paving according to a sequence of 45 degrees, 0 degree and-45 degrees; (5) manufacturing a vacuum bag, namely uniformly wrapping the outermost layer with a layer of isolating membrane without wrinkles on the surface after paving, and tightly attaching the vacuum bag to the product; 6) curing: after a cold pressing test, carrying out final curing in an autoclave; according to the method, the defects that in the prior art, a metal telescopic rod is high in manufacturing cost, large in manufacturing difficulty, complex in operation and large in weight are overcome, and the defects that in the prior art, a metal telescopic rod is high in manufacturing cost, large in manufacturing difficulty, complex in operation and large in weight are overcome.

Description

Technical Field

[0001] The invention relates to the technical field of satellite accessories, and in particular to a method for forming a composite material thin-walled telescopic probe rod for satellites. Background Art

[0002] Composite material thin-walled retractable probe rods are mainly used for satellites to extend and fix cameras in space for shooting and studying environmental changes of ±100℃ in space. The camera is bound to the front of the rod and the tail is fixed on a manual reel. When the probe rod is extended, it must be straightened and immobile without being affected by gravity. When it is retracted, it must be rolled back and extended again for subsequent shooting. It needs to be extended and retracted about 10 times.

[0003] The prior art discloses a probe made of metal material. For the lightweight requirements of aviation equipment, the metal probe greatly increases the weight. Facing the complex environmental factors in space, it is expensive and difficult to manufacture a retractable probe that is corrosion-resistant, heat-resistant and easy to operate. It requires high-precision technical support and a large amount of investment. Metal materials are very rigid and can only be retracted like a fishing rod when retracted, which is more complicated than the retracting operation. Therefore, it is very meaningful to invent a probe that can be straightened when unfolded, can be easily retracted, and can ensure repeated retractability, temperature resistance of ±100℃ and light weight. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides a method for forming a composite thin-walled retractable probe rod for satellites, which solves the shortcomings of the prior art of metal telescopic rods, such as high cost, great difficulty in production, complex operation and heavy weight.

[0005] The objective of the present invention is achieved in this way: a composite material thin-walled telescopic probe for satellites is made of carbon fiber material, including an extended state and a retracted state. In a non-stress state, the telescopic probe is in an extended state. In the extended state, the telescopic probe is a long thin sheet structure and is arc-shaped as a whole; in a stress state, the telescopic rod is in a retracted state and is a curled structure.

[0006] A method for forming a composite material thin-walled retractable probe as claimed in claim 1, comprising the following steps: 1) Material preparation: Take out the carbon fiber / epoxy resin plain prepreg from the cold storage and cool it at room temperature for use; 2) Mold preparation: Degrease, clean and apply multiple coats of release agent to the probe mold before use; 3) Cutting: Use an automatic cloth cutting machine to cut the prepreg sheets at various angles required for the ply for later use; 4) Laying: Prepare prepreg, lay the layers in the order of 45°, 0, -45°, lay 3 layers in total, the length direction of the telescopic probe is 0°, the margin line needs to be covered during laying, the joints are laid in a butt-jointed manner and the joint positions of each layer are staggered; 5) Make vacuum bags: After the prepreg is laid, a layer of wrinkle-free isolation film needs to be evenly wrapped on the outermost layer, and then a layer of thin breathable cloth needs to be wrapped. After completion, put it into the finished whole bag, and then put breathable felt around the mold. The vacuum bag fits tightly to the product; 6) Curing: After passing the cold pressure test, it enters the autoclave for final curing; the curing parameters are set according to the prepreg resin system; 7) Demolding: Demolding the semi-finished joint parts after solidification; 8) Cutting: Cut the composite probe semi-finished product to the specified size according to the cutting line mark; 9) Drilling: Use the drilling tool to locate and drill the mounting holes at both ends of the probe rod.

[0007] Furthermore, the probe rod mold in step 2) is a cylindrical steel mold with a radius of 25 mm.

[0008] Furthermore, the step 2) of applying the release agent multiple times specifically includes: applying the release agent six times, with an interval of 15 minutes between each application of the release agent.

[0009] Furthermore, the prepreg in step 4) is a carbon fiber plain weave prepreg with a single layer thickness of 0.10-0.12 mm.

[0010] Furthermore, the breathable felt in step 5) needs to be overlapped on the breathable cloth outside the product without touching the surface of the product.

[0011] Furthermore, the breathable cloth is a peelable cloth.

[0012] The present invention adopts the above technical scheme, and compared with the prior art, the beneficial effects are as follows: the molding method of the present invention, lays carbon fiber plain weave / epoxy resin prepreg on a cylindrical steel mold, makes a vacuum bag and then enters the autoclave for molding, and after cutting, uses special tooling to open holes to obtain a semicircular probe rod with a radius of 25mm and a length of 2m. The material toughness of the carbon fiber can ensure that the probe rod can remain straight when unfolded and can be rolled back, and it does not affect the use in an ambient temperature of ±100℃. This method is not only low in cost and simple to operate, but also meets the strength requirements while ensuring dimensional accuracy and appearance requirements, and completes the parts with high quality and high efficiency.

[0013] The probe is made of composite materials, does not contain any metal, has a relatively low density, and meets the requirements of lightweight. The joint is formed by prepreg paving and autoclave molding, which reduces the porosity of the composite material, and the quality is controllable and the performance is stable, meeting the acceptance requirements; the raw material is carbon fiber prepreg, which improves its tear resistance and structural strength. The special vacuum bag manufacturing method described in the molding process can effectively ensure the structural size and qualified rate of the product. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0015] Figure 1 This is a schematic diagram of the telescopic probe of the present invention in an extended state.

[0016] Figure 2 It is a schematic diagram of the retracted state of the telescopic probe of the present invention.

[0017] Among them, 100 telescopic probe rods. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] Example 1 like Figure 1-2 The shown is a composite thin-walled telescopic probe for satellites, which is made of carbon fiber material and includes an extended state and a retracted state. In the non-stress state, the telescopic probe 100 is in an extended state. In the extended state, the telescopic probe 100 is a long thin sheet structure and is arc-shaped as a whole; in the stress state, the telescopic rod is in a retracted state and the telescopic probe 100 is a curled structure.

[0020] Example 2 A method for forming a composite material thin-walled retractable probe for satellites, comprising the following steps: 1) Material preparation: Take out the carbon fiber / epoxy resin plain prepreg from the cold storage, cool it at room temperature for more than 6 hours, and set it aside. The cutting and laying of the prepreg is extremely convenient, and different fiber orientations can be achieved, and the resin content is evenly distributed, which effectively guarantees the performance and quality of the product while improving process efficiency.

[0021] 2) Mold preparation: The probe rod mold is a cylindrical steel mold with a radius of 25mm. Before use, it must be degreased, cleaned, and coated with 6 coats of release agent. When applying the release agent, there should be a 15-minute interval between each coat to ensure that the release agent forms a film before applying the next coat. 3) Cutting: According to the results of strength calculation, use an automatic cloth cutting machine to cut the prepreg sheets at various angles required for the ply for later use; 4) Laying: In order to ensure that the probe rod has a semi-arc shape, a thickness of 0.35mm and performance requirements, a single layer of carbon fiber plain prepreg with a thickness of 0.11mm is prepared. The laying angles are laid in the order of 45°, 0, and -45°. The margin line needs to be covered during laying. Because the product is a thin-walled product, the interface is laid in a butt-jointed manner and the positions of each layer of interfaces are staggered. The overlap method will affect the thickness and appearance of the area. 5) Making vacuum bags: After paving, a layer of isolation film needs to be evenly wrapped on the outermost layer. The surface should be wrinkle-free. Laying the isolation film flat can ensure that the surface of the cured product is bright and beautiful, which greatly improves the appearance. Then wrap it with a layer of thin breathable cloth, such as peelable cloth. After completion, put it into the finished bag. Put breathable felt around the mold. The breathable felt should not touch the surface of the product and overlap the peelable cloth outside the product. When arranging the vacuum bag, ensure that there are no vacuum bag wrinkles on the surface of the product and it is tight and solid with the parts. This bag making method effectively ensures that the surface of the product is bright and flat; 6) Curing: After passing the cold pressure test, enter the autoclave for final curing. The curing parameters are set according to the prepreg resin system; 7) Demolding: Demolding the semi-finished joint after solidification; 8) Cutting: Cut the composite probe semi-finished product to the specified size according to the cutting line mark.

[0022] 9) Drilling: Use the drilling tool to locate and drill the mounting holes at both ends of the probe rod; the composite material thin-walled retractable probe rod is now manufactured.

[0023] The present invention provides a method for forming a composite thin-walled retractable probe rod for satellites. Carbon fiber plain weave / epoxy resin prepreg is laid on a cylindrical steel mold, and a vacuum bag is made before entering a hot press for forming. After cutting, a special tool is used to make holes to obtain a semicircular probe rod with a radius of 25 mm and a length of 2 m. The material toughness of the carbon fiber can ensure that the probe rod can remain in a straight state when unfolded, and can be rolled back, and will not affect its use in an ambient temperature of ±100°C. This method is not only low-cost and simple to operate, but also meets the strength requirements while ensuring dimensional accuracy and appearance requirements, and the product is completed with high quality and efficiency. The telescopic probe rod prepared by the present invention is used on satellites, and is mainly used for satellites to control the telescopic movement of cameras in space. It should be noted that the telescopic probe rod of the present invention is in an extended state under normal conditions, such as Figure 1 As shown, when it needs to be retracted, it needs to be rolled back, and the winding direction is as follows Figure 1 As shown, the status is Figure 2 As shown, when it needs to be extended, just release it, and it will automatically unfold and extend due to its material properties.

[0024] The above embodiments are only used to help understand the method and core idea of ​​the present invention. It should be noted that, for those skilled in the art, several improvements and modifications can be made to the present invention without departing from the principles of the present invention, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. A composite material thin-walled telescopic probe for satellite, characterized in that: It is made of carbon fiber material, including extended state and retracted state. In the non-stress state, the telescopic probe is in the extended state. In the extended state, the telescopic probe is a long thin sheet structure and is arc-shaped as a whole; in the stress state, the telescopic rod is in the retracted state and has a curled structure.

2. A method for forming a composite material thin-walled retractable probe as claimed in claim 1, characterized in that: The following steps are involved: 1) Material preparation: Take out the carbon fiber / epoxy resin plain prepreg from the cold storage and cool it at room temperature for use; 2) Mold preparation: Degrease, clean and apply multiple coats of release agent to the probe mold before use; 3) Cutting: Use an automatic cloth cutting machine to cut the prepreg sheets at various angles required for the ply for later use; 4) Laying: Prepare prepreg, lay the layers in the order of 45°, 0, -45°, lay 3 layers in total, the length direction of the telescopic probe is 0°, the margin line needs to be covered during laying, the joints are laid in a butt-jointed manner and the joint positions of each layer are staggered; 5) Make vacuum bags: After the prepreg is laid, a layer of wrinkle-free isolation film needs to be evenly wrapped on the outermost layer, and then a layer of thin breathable cloth needs to be wrapped. After completion, put it into the finished whole bag, and then put breathable felt around the mold. The vacuum bag fits tightly to the product; 6) Curing: After passing the cold pressure test, it enters the autoclave for final curing; the curing parameters are set according to the prepreg resin system; 7) Demolding: Demolding the semi-finished joint parts after solidification; 8) Cutting: Cut the composite probe semi-finished product to the specified size according to the cutting line mark; 9) Drilling: Use the drilling tool to locate and drill the mounting holes at both ends of the probe rod.

3. The method for forming a composite material thin-walled retractable probe rod for satellites according to claim 2, characterized in that: The probe rod mold in step 2) is a cylindrical steel mold with a radius of 25 mm.

4. The method for forming a composite material thin-walled retractable probe rod for satellites according to claim 2, characterized in that: The step 2) of applying the release agent multiple times specifically includes: applying the release agent six times, with an interval of 15 minutes between each application of the release agent.

5. The method for forming a composite material thin-walled retractable probe for satellites according to claim 2, characterized in that: The prepreg in step 4) is a carbon fiber plain weave prepreg with a single layer thickness of 0.10-0.12 mm.

6. The method for forming a composite material thin-walled retractable probe for satellites according to claim 2, characterized in that: The breathable felt described in step 5) needs to be overlapped on the breathable cloth outside the product without touching the surface of the product.

7. A method for forming a composite material thin-walled retractable probe for satellites according to claim 2 or 6, characterized in that: The breathable cloth is a peelable cloth.

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