CN111824460A - Multilayer components of satellite propulsion systems - Google Patents

Abstract

The invention provides a multilayer assembly of a satellite propulsion system, comprising a first material layer and a second material layer which are laid at intervals, wherein: the second material layer is removed at a ground end and a lap end of the multilayer assembly, exposing the first material layer; and the first material layers are in direct contact at the grounding end part and the lap joint end part of the multilayer assembly and/or are connected through the conductive parts, so that a simple grounding structure of the multilayer heat insulation assembly between the first material layers is realized, and the manufacturing and assembling processes of multiple layers are simplified. The multilayer manufacturing and assembling process can be simplified, the problem that the grounding sheet is not easy to rivet due to the shape of the multilayer heat insulation assembly of the long-strip pipeline is solved, the multilayer grounding flow of the pipeline is simplified, and the full and effective grounding of the multilayer heat insulation assembly of the pipeline is ensured, so that the charging and discharging risks of a satellite propulsion system are effectively reduced.

Description

Multilayer components of satellite propulsion systems

technical field

The invention relates to the technical field of aerospace, in particular to a multi-layer assembly of a satellite propulsion system.

Background technique

The propulsion system is the executive body of the satellite attitude and orbit control subsystem, which is used to provide rate damping, maintain the orbit, maintain the attitude, adjust the attitude and change the orbit, etc. It is an extremely important part of the satellite. The propulsion system includes storage tanks, pipelines, pressure sensors, self-locking valves, adding and exhausting valves, and solenoid valves. In order to meet the requirements of on-orbit flight, the temperature of the propulsion system needs to be controlled within a high range, which requires various components. The heater is pasted on top and covered with multi-layer thermal insulation components to improve heating efficiency and reduce the influence of the temperature of other single machines in the cabin.

In order to prevent the accumulation of static electricity and electrostatic discharge in the satellite, protect the satellite from electric shock caused by any electromagnetic pulse effect in the environment, and reduce electromagnetic interference and discharge pollution caused by electromagnetic fields or other forms of inductive coupling, all conductive parts inside and outside the satellite should be Ground as required. The multi-layer thermal insulation component should also be overlapped with the satellite structure according to the specified process. The grounding resistance between the multi-layer grounding reference point and the structural grounding stake should be less than 1.0Ω, and the ground wiring should be as short as possible.

Most of the traditional multi-layer thermal insulation components of storage tanks are designed with multiple pieces. In order to fit the spherical shape, they are usually divided into at least 8 pieces, which is not only complicated in the process, but also very complicated in the assembly and grounding process. Due to its slender shape, the propulsion pipeline needs to be wound along the pipeline with long strips and multiple layers, and faces the problems of multi-layer overlap and difficulty in grounding. At present, the more common treatment methods for the propulsion pipeline are: not covering the multi-layer thermal insulation component, and covering the multi-layer thermal insulation component but grounding or not using the traditional grounding sheet method. The disadvantage of not coating multi-layer thermal insulation components is obvious. The temperature of the pipeline is easily affected by the temperature change of the surrounding single machine, which reduces the stability; if the multi-layer coating is not grounded, although the electrostatic accumulation ability is weak, it is still isolated. The traditional multi-layer grounding structure is to set grounding rivets on the multi-layers, and the double-sided aluminized polyester film in each multi-layer unit is lapped and grounded on both sides through the grounding rivets. The multi-layer thermal insulation components of the pipeline are of the same size, which makes the grounding structure particularly cumbersome, difficult to manufacture and difficult to fix.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a multi-layer assembly of a satellite propulsion system, so as to solve the problems of complex structure and difficult assembly of the existing multi-layer assembly of the satellite propulsion system.

In order to solve the above-mentioned technical problems, the present invention provides a multi-layer assembly of a satellite propulsion system, comprising a first material layer and a second material layer laid at intervals, wherein:

the second layer of material is removed at the ground and lap ends of the multilayer assembly, exposing the first layer of material; and

The first material layer is in direct contact at the grounded end and the bonded end of the multilayer assembly, and/or is connected by a conductive member.

Optionally, in the multi-layer assembly of the satellite propulsion system, the satellite propulsion system includes a spherical tank, wherein:

The first multi-layer module wrapping the tank includes two single-sided serrated module pieces, and two petal-shaped module pieces;

The two unilateral serrated component pieces are butted on the side facing away from the serrations, and are fixed on the spherical tank by silicone rubber. The two petal-shaped component pieces are respectively fixed by silicone rubber to cover the gap between the two unilateral serrated component pieces .

Optionally, in the multi-layer assembly of the satellite propulsion system, the satellite propulsion system further includes a pipeline, wherein:

The second multi-layer component wrapping the pipeline is a long strip of component pieces, which is wound on the pipeline at a certain angle and is wound along the center line of the upper layer in turn. After fixing, the outermost layer is covered with a layer of aluminized surface. Aluminized mylar on one side facing outwards, the ends are secured with aluminized pressure sensitive adhesive.

Optionally, in the multi-layer assembly of the satellite propulsion system, a first ground end portion is further included, and the first ground end portion includes an accordion-shaped aluminum foil, a rivet and a ground solder tab, wherein:

the second material layer is removed at the first ground end, exposing the first material layer;

The number of layers of the organ-shaped aluminum foil is consistent with the number of layers of the first material layer, each layer of the organ-shaped aluminum foil is embedded between each layer of the first material layer, and the ground soldering tab is crimped on the top layer of said accordion foil;

The rivets riveted the ground welding tab, the accordion-shaped aluminum foil and the first material layer into one body.

Optionally, in the multi-layer assembly of the satellite propulsion system, the overlapping end portion includes a first overlapping assembly and a second overlapping assembly, wherein:

the second material layer of the first lap assembly is removed, exposing the first material layer of the first lap assembly;

the second material layer of the second lap assembly is removed, exposing the first material layer of the second lap assembly;

The first material layer of the first lap assembly is in a positive step shape, and is folded along the direction in contact with the second lap assembly;

The first material layer of the second lap assembly is an inverted stepped shape;

Each layer of the first material layer of the first overlapping component is in direct contact with each layer of the first material layer of the second overlapping component in turn, and the two are firmly adhered by polyimide tape .

Optionally, in the multi-layer assembly of the satellite propulsion system, a second ground end portion is also included, wherein:

the second material layer is removed at the second ground end, exposing the first material layer;

The first material layer of the second ground end is stepped and folded along the direction in contact with the conductive surface;

The first material layer of the second ground end is in direct contact with the conductive surface and is fixed with an aluminum-plated pressure-sensitive adhesive.

Optionally, in the multi-layer assembly of the satellite propulsion system, the first grounded end portion is located on all other multi-layered assemblies except the second multi-layered assembly, and the second grounded end portion is located on all the other multi-layered assemblies. on the second multi-layer assembly, the overlapping ends are located on the second multi-layer assembly.

Optionally, in the multi-layer assembly of the satellite propulsion system, the first material layer is a double-sided aluminized polyester film, the second material layer is a nylon mesh, and a layer of the first material layer covers A module unit is formed on a layer of the second material layer, and the innermost layer of the plurality of module units is covered with a polyimide film;

The satellite propulsion system also includes a pressure sensor, a self-locking valve and an add-exhaust valve, and the pressure sensor, the self-lock valve and the add-exhaust valve are wrapped with 15 component units;

The first multi-layer assembly includes 10 module units, and the second multi-layer module includes 3 module units.

In the multi-layer assembly of the satellite propulsion system provided by the present invention, the first material layer is exposed by the second material layer being removed at the grounding end and the overlapping end of the multi-layer assembly, and the first material layer is exposed. The material layers are in direct contact at the grounding end and the overlapping end of the multi-layer assembly, and/or are connected through conductive parts, thereby realizing a simple grounding structure of the multi-layer thermal insulation assembly between the first material layers, simplifying the multi-layer production and assembly process.

The invention relates to a multi-layer component design and grounding scheme of a satellite propulsion system. The satellite propulsion system includes a storage tank, a pipeline, a pressure sensor, a self-locking valve, a discharge valve and a solenoid valve. Covered with multi-layer insulation components.

The invention designs a four-piece storage tank multi-layer heat insulation assembly, which can adapt to the spherical characteristics of the storage tank, closely fit its shape, and simplifies the technological process; the pressure sensor, self-locking valve and other relatively square-shaped components are designed. The multi-layer thermal insulation component is designed; the pipeline long-strip multi-layer thermal insulation component and its overlapping method are designed: when the length of the multi-layer strip is insufficient and needs to be connected, the first material layer is trimmed into a stepped shape in the length direction and Fold along the direction of the contact surface with the continuous multi-layer, and trim the first material layer of the continuous multi-layer into stepped contact with it in turn, so as to ensure that each first material layer of the two multi-layers is in double-sided contact; design The grounding structure of the multi-layer thermal insulation assembly: the first material layer is trimmed into a stepped shape in the length direction and folded in the direction of contact with the conductive surface, and then directly contacted and fixed on the conductive surface, thus ensuring that each layer of the multi-layer The first material layers are both grounded. It can simplify the multi-layer production and assembly process, solve the problem that the multi-layer thermal insulation component of the long pipeline is not easy to rivete the grounding piece due to the shape, simplifies the grounding process of the pipeline multi-layer and ensures that it is fully and effectively grounded, thereby effectively reducing the cost. The charging and discharging risks of the small satellite propulsion system.

Description of drawings

1 is a schematic diagram of a first multi-layer assembly according to an embodiment of the present invention;

2 is a schematic diagram of the installation of the first multi-layer assembly and the tank according to an embodiment of the present invention;

FIG. 3 is a schematic diagram of a first ground terminal according to an embodiment of the present invention;

FIG. 4 is a schematic diagram of a lap joint end according to an embodiment of the present invention;

FIG. 5 is a schematic diagram of a second ground terminal according to an embodiment of the present invention;

FIG. 6 is a schematic diagram of the installation of the second ground terminal according to an embodiment of the present invention;

7 is a schematic diagram of a satellite propulsion system according to an embodiment of the present invention;

Shown in the picture:

100 - the first multi-layer assembly;

110-ground position;

200-tank;

210-Single-sided serrated component piece;

220 - petal-shaped component piece;

300 - the first ground terminal;

310 - double-sided aluminized polyester film;

320-ground plate;

330-ground wire;

340 - hollow rivet;

350-silver plated solder tab;

360 - aluminum foil strip;

400 - lapped end;

410-pipeline multilayer 1;

420-pipeline multilayer 2;

430 - double-sided aluminized polyester film;

500 - the second ground terminal;

510 - double-sided aluminized polyester film;

600 - satellite propulsion system;

610 - solenoid valve;

620-pipeline and solenoid valve connector;

630-propulsion line;

700 - the second ground terminal;

710 - Second multi-layer assembly;

720-Line and solenoid valve connections.

Detailed ways

The multi-layer components of the satellite propulsion system proposed by the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become apparent from the following description and claims. It should be noted that, the accompanying drawings are all in a very simplified form and in inaccurate scales, and are only used to facilitate and clearly assist the purpose of explaining the embodiments of the present invention.

Furthermore, unless stated otherwise, features in different embodiments of the invention may be combined with each other. For example, a certain feature in the second embodiment can be used to replace the corresponding or functionally identical or similar feature in the first embodiment, and the resulting embodiment also falls within the scope of disclosure or description of the present application.

The core idea of the present invention is to provide a multi-layer assembly of a satellite propulsion system, so as to solve the problems of complex structure and difficult assembly of the existing multi-layer assembly of the satellite propulsion system.

In order to realize the above-mentioned idea, the present invention provides a multi-layer assembly of a satellite propulsion system, comprising a first material layer and a second material layer laid at intervals, wherein: the second material layer is at the grounding end and the ground end of the multi-layer assembly. The overlapped ends are removed, exposing the first material layer; and the first material layer is in direct contact at the ground and overlapped ends of the multilayer assembly, and/or connected by a conductive member.

The invention provides a multi-layer component design and grounding scheme for a satellite propulsion system, including a multi-layer thermal insulation component design for components such as tanks, pipelines and pressure sensors, a multi-layer thermal insulation component overlapping structure for pipelines, and pipelines. The multi-layer thermal insulation component grounding structure, etc. The structure can simplify the multi-layer manufacturing, assembling and grounding process, solve the problem that the long-strip pipeline multi-layer thermal insulation assembly is difficult to riveted to the grounding piece due to its shape, simplifies the pipeline multi-layer grounding process and ensures that it is fully and effectively grounded.

As shown in FIG. 2 , in one embodiment of the present invention, the multi-layer thermal insulation components of the tank 200 are of four-piece design, with two pieces in each of the upper and lower hemispheres with similar shapes, and one piece is grass-like (one-sided serrated component piece). 210), and one piece is petal-shaped (petal-shaped component piece 220). When assembling the multi-layer thermal insulation assembly of the storage tank, first assemble two grass-like layers and stick them firmly with silicone rubber, then cover the two petal-like layers on the gaps of the grass-like layers, and dispense glue firmly.

As shown in Figure 4, when the pipeline multi-layer 1 (410) and the pipeline multi-layer 2 (420) are overlapped, the two multi-layer nylon mesh towels (the second material layer) are cut short to expose the double-sided aluminum plating The polyester film 430 (the first material layer), and the double-sided aluminized polyester film 430 are both trimmed into a stepped shape. When the multi-layer 410 and 420 of the pipeline are overlapped, the double-sided aluminized polyester film 430 of one of the multi-layer 410 is folded along the direction of the contact surface, and the folding length is 5mm. The aluminum polyester films 430 are in contact with each other in sequence to ensure that each layer of double-sided aluminized polyester films 430 is in contact with both sides. When the pipeline is multi-layered, use double-sided and single-sided polyimide tape to firmly stick the two multi-layers that are in contact with each other on both sides.

When the propulsion pipeline is wrapped in multiple layers, it should be wound on the propulsion pipeline in a 45° direction, and the center line of the multi-layer strip should be wound in turn. After fixing, a layer of 16μm single-sided aluminized polyester film ( Aluminized side facing out). As shown in FIG. 5 , when the pipeline is multi-layered for grounding, the nylon mesh is cut short to expose the double-sided aluminized polyester film 510 , and the double-sided aluminized polyester film 510 is trimmed into a stepped shape. When propelling multiple layers of pipelines for grounding, the multiple layers on each pipeline have been fully contacted with electricity during splicing, so they only need to be grounded once.

In the multi-layer thermal insulation assembly of the present invention, the double-sided aluminized polyester film and the net towel are laid at intervals of 1:1, the innermost layer is covered with a layer of polyimide film, and the outermost layer is double-sided aluminized Mylar surface. The multi-layer insulation components of the storage tank, pressure sensor, self-locking valve and the add-drain valve are 10 units, the multi-layer insulation components of the solenoid valve are 15 units, and the multi-layer insulation components of the pipeline are 3 units. The multiple layers of the advance line are multi-layer strips cut to a width of 20 mm. Except for the multi-layer pipeline, each other multi-layer thermal insulation component needs to be riveted to the grounding sheet, and the length of the grounding wire is designed according to the principle of the nearest grounding. Except for the multi-layer pipeline, the structure of the riveted grounding piece of other multi-layer thermal insulation components is the same, and the size of the grounding piece is M4.

Figure 1 shows the design of a four-piece multi-layer thermal insulation assembly for a storage tank. The first multi-layer assembly 100 includes two layers for each of the upper and lower hemispheres. When assembling, the multi-layer (2) and the multi-layer (4) are assembled first. The upper and lower hemispheres of the storage tank are fixed with silicone rubber, and then the multi-layer (1) and the multi-layer (2) are tightly covered on the gap between the multi-layer (2) and the multi-layer (4), and are firmly fixed with silicone rubber to form The structure shown in Figure 2. The multi-layer of the pipeline is a multi-layer strip with a width of 20mm. When wrapping, the head end of the strip-shaped multi-layer component is grounded, and it is wound on the propulsion pipeline in the direction of 45°, and the center line of the multi-layer strip is wound in turn and fixed. Finally, coat a layer of 16 μm single-sided aluminized polyester film (aluminized side facing outward), and fix the ends with aluminized pressure-sensitive adhesive. The rest of the components are relatively square, and the multi-layer fabrication and assembly are handled as usual.

FIG. 3 shows the grounding structure of the first grounding end portion 300 of the components other than the propulsion line. Cut the aluminum foil into 360 long strips of aluminum foil with a width of 20mm, fold it into an organ shape, and the number of organ layers is the same as that of the multi-layer component unit. Between the polyester films 310, ensure that they are in contact with each other on both sides, and then use hollow rivets 340 to rivete the silver-plated solder tab 350 and the organ sheet into one body. The hollow rivet 340 is connected to the ground plate 320 through the ground wire 330 . In the case of FIG. 1 , the first ground end 300 is arranged at the ground position 110 .

FIG. 4 is a schematic illustration of a multi-layered lap end 400 of a propulsion line. When the length of the multi-layer (pipeline multi-layer 1410) is insufficient and needs to be connected, cut the nylon mesh short to expose the double-sided aluminized polyester film 430, and trim the double-sided aluminized polyester film 430 into a stepped shape, along the Fold 5mm in the direction of the contact surface of the continuous multi-layer, and at the same time cut the continuous multi-layer (pipeline multi-layer 2 420) nylon mesh towel, and trim the double-sided aluminized polyester film 430 into a stepped shape, according to the structure shown in the figure. Contact them in sequence, and stick them firmly with double-sided and single-sided polyimide tapes, so as to ensure that each layer of the two-layer double-sided aluminized polyester film of the two layers is in double-sided contact.

Fig. 5 is a schematic diagram of a stepped first end of the second ground end portion 500 of the propulsion pipeline. The double-sided aluminized polyester film 510 is trimmed into a stepped shape and folded 5mm in the direction of contact with the conductive surface. Fig. 6 is a satellite propulsion system 600 is a partial schematic diagram of the pipeline, including the solenoid valve 610 and the pipeline and solenoid valve connector 620; FIG. 7 is a schematic diagram of the grounding structure of the second grounding end 700 of the first end of the second multi-layer assembly 710 of the pipeline. With a similar structure, the nylon mesh towel is cut short to expose the double-sided aluminized polyester film 510, and then directly contacted and fixed on the conductive surface of the pipeline and the solenoid valve connector 720 with aluminized pressure-sensitive adhesive, and fixed with silicone rubber. , so as to ensure that each layer of double-sided aluminized polyester film of the multi-layer assembly is grounded on both sides.

To sum up, the above embodiments describe in detail the different configurations of the multi-layer components of the satellite propulsion system. Of course, the present invention includes but is not limited to the configurations listed in the above embodiments, any configuration provided in the above embodiments The content transformed on the basis belongs to the protection scope of the present invention. Those skilled in the art can draw inferences from the contents of the foregoing embodiments.

The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments can be referred to each other. For the system disclosed in the embodiment, since it corresponds to the structure disclosed in the embodiment, the description is relatively simple, and the related part can be referred to the description of the structure part.

The above description is only a description of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention. Any changes and modifications made by those of ordinary skill in the field of the present invention based on the above disclosure all belong to the protection scope of the claims.

Claims (8)

1. A multi-layer assembly of a satellite propulsion system, characterized in that it comprises a first material layer and a second material layer laid at intervals, wherein: the second layer of material is removed at the ground and lap ends of the multilayer assembly, exposing the first layer of material; and The first material layer is in direct contact at the grounded end and the bonded end of the multilayer assembly, and/or is connected by a conductive member. 2. The multi-layer assembly of the satellite propulsion system of claim 1, wherein the satellite propulsion system comprises a spherical tank, wherein: The first multi-layer module wrapping the tank includes two single-sided serrated module pieces, and two petal-shaped module pieces; The two unilateral serrated component pieces are butted on the side facing away from the serrations, and are fixed on the spherical tank by silicone rubber. The two petal-shaped component pieces are respectively fixed by silicone rubber to cover the gap between the two unilateral serrated component pieces . 3. The multi-layer assembly of the satellite propulsion system of claim 1, wherein the satellite propulsion system further comprises a pipeline, wherein: The second multi-layer component wrapping the pipeline is a long strip of component pieces, which is wound on the pipeline at a certain angle and is wound along the center line of the upper layer in turn. After fixing, the outermost layer is covered with a layer of aluminized surface. Aluminized mylar on one side facing outwards, the ends are secured with aluminized pressure sensitive adhesive. 4. The multi-layer assembly of the satellite propulsion system of claim 3, further comprising a first ground end portion, the first ground end portion comprising an accordion-shaped aluminum foil, a rivet, and a ground lug, wherein: the second material layer is removed at the first ground end, exposing the first material layer; The number of layers of the organ-shaped aluminum foil is consistent with the number of layers of the first material layer, each layer of the organ-shaped aluminum foil is embedded between each layer of the first material layer, and the ground soldering tab is crimped on the top layer of said accordion foil; The rivets riveted the ground welding tab, the accordion-shaped aluminum foil and the first material layer into one body. 5. The multi-layer assembly of a satellite propulsion system of claim 4, wherein the lap end portion comprises a first lap assembly and a second lap assembly, wherein: the second material layer of the first lap assembly is removed, exposing the first material layer of the first lap assembly; the second material layer of the second lap assembly is removed, exposing the first material layer of the second lap assembly; The first material layer of the first lap assembly is in a positive step shape, and is folded along the direction in contact with the second lap assembly; The first material layer of the second lap assembly is an inverted stepped shape; Each layer of the first material layer of the first overlapping component is in direct contact with each layer of the first material layer of the second overlapping component in turn, and the two are firmly adhered by polyimide tape . 6. The multi-layer assembly of the satellite propulsion system of claim 5, further comprising a second grounded end portion, wherein: the second material layer is removed at the second ground end, exposing the first material layer; The first material layer of the second ground end is stepped and folded along the direction in contact with the conductive surface; The first material layer of the second ground end is in direct contact with the conductive surface and is fixed with an aluminum-plated pressure-sensitive adhesive. 7. The multi-layer assembly of a satellite propulsion system of claim 6, wherein the first grounded end portion is located on all other multi-layer assemblies except the second multi-layer assembly, the second grounded The ends are on the second multilayer assembly and the overlapping ends are on the second multilayer assembly. 8. The multi-layer assembly of the satellite propulsion system according to claim 3, wherein the first material layer is a double-sided aluminized polyester film, the second material layer is a nylon mesh, and the first material layer is a nylon mesh. A material layer is covered on a second material layer to form a component unit, and the innermost layer of the plurality of component units is covered with a polyimide film; The satellite propulsion system also includes a pressure sensor, a self-locking valve and an add-exhaust valve, and the pressure sensor, the self-lock valve and the add-exhaust valve are wrapped with 15 component units; The first multi-layer assembly includes 10 module units, and the second multi-layer module includes 3 module units.

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