阅读说明：本技术 基于电缆加热器的航天器动力系统推进管路通用热控装置及方法 (General thermal control device and method for propulsion pipeline of spacecraft power system based on cable heater ) 是由 潘维 钟奇 斯东波 苏生 王德伟 何江 于新刚 于 2021-07-16 设计创作，主要内容包括：本发明提供一种基于电缆加热器的航天器动力系统推进管路的通用热控装置,极大降低热控设计和实施难度,节约实施时间,缩短航天器动力系统研制和维护周期。该热控装置包括：绝缘胶带、电缆加热器、绝缘膜和多层隔热组件；绝缘胶带缠绕在推进管路的外壁上,用于推进管路电绝缘；电缆加热器为内部为电阻丝外部为绝缘层的丝状结构；电缆加热器均匀缠绕在电绝缘处理后的推进管路外部,电缆加热器通过引出线与外部电源相连,形成加热回路；绝缘膜缠绕在电缆加热器外部,用于二次绝缘；多层隔热组件缠绕在绝缘膜外部。此外,本发明还提供一种基于电缆加热器的航天器动力系统推进管路的通用热控方法。(The invention provides a general thermal control device of a propulsion pipeline of a spacecraft power system based on a cable heater, which greatly reduces the difficulty of thermal control design and implementation, saves the implementation time and shortens the development and maintenance period of the spacecraft power system. The thermal control device comprises: an insulating tape, a cable heater, an insulating film, and a multilayer heat insulating assembly; the insulating tape is wound on the outer wall of the propelling pipeline and is used for electrically insulating the propelling pipeline; the cable heater is a wire-shaped structure with the inner part being a resistance wire and the outer part being an insulating layer; the cable heater is uniformly wound outside the electrically insulated propulsion pipeline and is connected with an external power supply through a lead-out wire to form a heating loop; the insulating film is wound outside the cable heater and used for secondary insulation; the multilayer insulation assembly is wrapped around the exterior of the insulating film. In addition, the invention also provides a general thermal control method of the propulsion pipeline of the spacecraft power system based on the cable heater.)

1. Spacecraft driving system impulse line thermal control device based on cable heater, its characterized in that includes: an insulating tape, a cable heater, an insulating film, and a multilayer heat insulating assembly;

the insulating adhesive tape is wound on the outer wall of the propelling pipeline and used for electrically insulating the propelling pipeline;

the cable heater is of a wire-shaped structure, the inner part of the resistance wire is an insulation layer, and the outer part of the resistance wire is an insulation layer; the cable heater is uniformly wound outside the electrically insulated propelling pipeline and is connected with an external power supply through a lead-out wire, so that a heating loop is formed;

the insulating film is wound outside the cable heater and used for secondary insulation;

a multi-layer insulation assembly is wrapped around the exterior of the insulating film.

2. The cable heater-based spacecraft power system propulsion line thermal control apparatus of claim 1, wherein: the resistance wire in the cable heater is a single-stranded or double-stranded constantan wire with the diameter of 0.1 mm-0.5 mm.

3. The cable heater-based spacecraft power system propulsion line thermal control apparatus of claim 1, wherein: and the cable heater is fixed by dispensing through silicon rubber at set intervals.

4. The cable heater-based spacecraft power system propulsion line thermal control apparatus of claim 1, wherein: more than two cable heaters are wound on the propelling pipeline, and the more than two cable heaters are connected in series or in parallel in the heating loop.

5. A cable heater based spacecraft power system propulsion line thermal control apparatus as claimed in any one of claims 1 to 4, wherein: when the propulsion pipeline is generally formed by connecting more than two sections of sub pipelines through communicating pipes, the thermal control device is respectively wound on each section of sub pipeline, and then the cable heaters of the thermal control devices on each section of sub pipeline are connected through conducting wires, so that the cable heaters on each section of sub pipeline are added into a heating loop.

6. The cable heater-based spacecraft power system propulsion line thermal control apparatus of claim 5, wherein: when the cable heaters of the thermal control devices on the sub-pipelines at all sections are connected by welding through the conducting wires, the welding conducting wires matched with the diameters of the resistance wires in the cable heaters are adopted.

7. The cable heater-based spacecraft power system propulsion line thermal control apparatus of claim 5, wherein: and the conducting wires for connecting the two cable heaters outside the sub-pipelines are fixed on the sub-pipelines or the communicating pipes at corresponding positions by using silicon rubber.

8. A thermal control method for a propulsion pipeline of a spacecraft power system based on a cable heater is characterized by comprising the following steps: firstly, determining radiation heat exchange quantity and heat conduction heat exchange quantity of a propelling pipeline to the environment through thermal analysis according to the length of the propelling pipeline and the ambient temperature, thereby obtaining power required to be compensated by a cable heater, further determining the resistance value of the cable heater, and further determining the length of the cable heater;

and then winding an insulating tape on the outer wall surface of the propelling pipeline for electric insulation of the propelling pipeline.

Then uniformly winding the designed cable heater on the outer circumference of the insulating tape, and avoiding the thermistor on the propulsion pipeline during winding; then, the cable heater is fixed on the propelling pipeline by dispensing through silicon rubber at set intervals; the cable heater is connected with an external power supply through an outgoing line to form a heating loop;

after the cable heater is installed and fixed, winding a layer of insulating film outside the cable heater for secondary insulation;

after the insulating film is wound, the multilayer heat insulation assembly is wound outside.

9. The cable heater-based spacecraft power system propulsion line thermal control method of claim 8, wherein: when more than two cable heaters are arranged in the heating loop, recording the resistance value of the heating loop when one cable heater is connected into the heating loop; when all the cable heaters of the heating loop are connected, the lead is led out, the total resistance value and the insulation value of the heating loop are measured, and the actually measured resistance value is compared with the designed resistance value, so that the correct connection of the heating loop of the whole propelling pipeline is confirmed.

Technical Field

The invention relates to a thermal control method, in particular to a general thermal control device and method for a propulsion pipeline of a spacecraft power system based on a cable heater, and belongs to the technical field of thermal control of spacecrafts.

Background

The thermal control of the propulsion pipeline of the spacecraft power system generally adopts an electric heating active temperature control mode. The traditional electric heating carrier adopts a polyimide film electric heating belt. In the implementation method, firstly, a polyimide single-sided pressure-sensitive adhesive tape is uniformly wound on the outer wall of a propelling pipeline, then a layer of GD414 or GD414C room-temperature vulcanized silicone rubber is uniformly coated on the outer surface of the adhesive tape, then an electric heating tape is uniformly wound on the pipeline, and finally a layer of silicone rubber is coated outside the wound heating tape for fixing.

The thermal control method for the propulsion pipeline of the power system of the traditional electric heating belt has the following defects:

(1) the design is complicated, the cycle is long: the length of the heating belt and the length of the corresponding pipeline need to meet a certain proportional relation, the length of the heating belt is related to the magnitude of heating power, the magnitude of the heating power is closely related to the space environment condition, the heating belt has a certain width, and under the condition of multiple coupling constraint, the design of the heating belt for propelling the pipeline needs to be iterated repeatedly for many times, so that the consumed time is huge;

(2) the thermal control implementation process is complex and difficult;

(3) the thermal control implementation efficiency is low, the period is long, and the development progress of the spacecraft is seriously influenced;

(4) the disassembly and replacement are not easy, and the disassembled electric heating belt cannot be reused and can only be scrapped, thus having poor economy.

Disclosure of Invention

In view of the above, the invention provides a thermal control device for a propulsion pipeline of a spacecraft power system based on a cable heater, which has high efficiency and convenient assembly and disassembly, and can greatly shorten the design period, reduce the implementation difficulty, improve the implementation efficiency and save the time for developing the thermal control of the spacecraft power system.

The thermal control device for the propulsion pipeline of the spacecraft power system based on the cable heater comprises: an insulating tape, a cable heater, an insulating film, and a multilayer heat insulating assembly;

the insulating adhesive tape is wound on the outer wall of the propelling pipeline and used for electrically insulating the propelling pipeline;

the cable heater is of a wire-shaped structure, the inner part of the resistance wire is an insulation layer, and the outer part of the resistance wire is an insulation layer; the cable heater is uniformly wound outside the electrically insulated propelling pipeline and is connected with an external power supply through a lead-out wire, so that a heating loop is formed;

the insulating film is wound outside the cable heater and used for secondary insulation;

a multi-layer insulation assembly is wrapped around the exterior of the insulating film.

As a preferable mode of the invention, the resistance wire inside the cable heater is a single-stranded or double-stranded constantan wire with the diameter of 0.1 mm-0.5 mm.

In a preferred embodiment of the present invention, the cable heater is fixed by dispensing with silicone rubber at predetermined intervals.

In a preferred embodiment of the present invention, two or more cable heaters are wound around the propulsion line, and the two or more cable heaters are connected in series or in parallel in the heating circuit.

As a preferred mode of the present invention, when the propulsion pipeline is generally formed by connecting more than two sections of sub-pipelines through a communicating pipe, the thermal control device is wound on each section of sub-pipeline, and then the cable heaters of the thermal control devices on each section of sub-pipeline are connected through a conducting wire, so that the cable heaters on each section of sub-pipeline are added into the heating loop.

As a preferred mode of the invention, when the cable heaters of the thermal control devices on each section of sub-pipeline are connected by welding through the conducting wires, the welding conducting wires matched with the diameters of resistance wires in the cable heaters are adopted.

In a preferred embodiment of the present invention, the lead wires for connecting the cable heaters outside the two sub-pipes are fixed to the sub-pipes or the communicating pipe at the corresponding positions with silicone rubber.

In addition, the invention discloses a thermal control method of a propulsion pipeline of a spacecraft power system based on a cable heater, which comprises the following steps:

firstly, determining radiation heat exchange quantity and heat conduction heat exchange quantity of a propelling pipeline to the environment through thermal analysis according to the length of the propelling pipeline and the ambient temperature, thereby obtaining power required to be compensated by a cable heater, further determining the resistance value of the cable heater, and further determining the length of the cable heater;

and then winding an insulating tape on the outer wall surface of the propelling pipeline for electric insulation of the propelling pipeline.

Then uniformly winding the designed cable heater on the outer circumference of the insulating tape, and avoiding the thermistor on the propulsion pipeline during winding; then, the cable heater is fixed on the propelling pipeline by dispensing through silicon rubber at set intervals; the cable heater is connected with an external power supply through an outgoing line to form a heating loop;

after the cable heater is installed and fixed, winding a layer of insulating film outside the cable heater for secondary insulation;

after the insulating film is wound, the multilayer heat insulation assembly is wound outside.

When more than two cable heaters are arranged in the heating loop, recording the resistance value of the heating loop when one cable heater is connected into the heating loop; when all the cable heaters of the heating loop are connected, the lead is led out, the total resistance value and the insulation value of the heating loop are measured, and the actually measured resistance value is compared with the designed resistance value, so that the correct connection of the heating loop of the whole propelling pipeline is confirmed.

Has the advantages that:

(1) the cable heater is filamentous, and is flexible, can well laminate with the pipe wall when twining the pipeline, and after twining on the pipeline, every interval set distance is fixed with some silicon rubber, and not scribble the silicon rubber on cable heater is whole fixed, and it is convenient to implement, need not scribble the silicon rubber repeatedly, and is efficient, easy dismounting has greatly reduced the driving system pipeline and has implemented the degree of difficulty, has improved implementation efficiency, has practiced thrift the time of implementing of the thermal control of more than half spacecraft driving system, guarantees spacecraft driving system development progress.

(2) When the heater is designed, if a traditional electric heating belt is adopted, the power of the heating belt needs to meet a certain condition, and meanwhile, the ratio (gamma) of the length of the heating belt to the length of a corresponding pipeline is generally required to be less than or equal to 1.4 because the heating belt is in a belt shape. The design difficulty of the heating belt is high due to the limitation of the value of gamma, and repeated iteration is needed; the cable heater is filamentous, the value of gamma can reach 5, the application range is wide, the power constraint can be considered in the heater design, multiple iterative design is not needed, the thermal design difficulty of the propulsion pipeline is greatly reduced, and the design period is shortened.

(3) On the propulsion pipeline of the XX-3 power system, a thermal control method based on a cable heater is adopted; the on-orbit flight test proves that the temperature of the liquid pipeline of the propulsion system is between +15.0 and +25.0 ℃, the temperature of the gas pipeline is between-5.0 and +10.0 ℃, and the temperature of the pipeline is good. The thermal control design period of the propulsion pipeline is shortened from 3 months to 1 month, the thermal control implementation period is shortened from 1 month to two weeks, the design and implementation time is greatly saved, and the manpower and maintenance cost is reduced.

Drawings

FIG. 1 is a schematic diagram of an embodiment of a thermal control device based on cable heating according to the present invention;

FIG. 2 is a temperature change curve of the pipeline measuring point on the track after the thermal control device of the present invention is applied to the XX-3 propelling pipeline.

Wherein: 1-a propulsion line; 2-insulating tape; 3-a cable heater; 4-a polyimide film; 5-multilayer insulation assembly.

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

Example 1:

the embodiment provides a general thermal control device of a propulsion pipeline of a spacecraft power system based on a cable heater, which greatly reduces the difficulty of thermal control design and implementation, saves the implementation time and shortens the development and maintenance period of the spacecraft power system.

As shown in fig. 1, the thermal control device includes: an insulating tape 2, a cable heater 3, a polyimide film 4, and a multi-layer thermal insulation assembly 5.

The insulating tape 2 is a polyimide single-sided pressure-sensitive adhesive tape, is tightly wound on the outer wall of the propelling pipeline 1 and is used for electrically insulating the propelling pipeline.

The appearance of the cable heater 3 is the same as that of a common cable, and the conductive material (namely a lead) in the cable heater is a constantan wire, the diameter of the constantan wire is 0.1-0.5 mm, and the constantan wire can be single-stranded or double-stranded; the external insulating layer is a crosslinked ethylene-tetrafluoroethylene copolymer and can adopt a single-layer or double-layer insulating structure. The cable heater 3 is wound outside the insulating adhesive tape 2, and the winding density is required to be uniform, the cable heater is attached to a pipeline and is smooth and does not bulge, and over-tightness and over-looseness are avoided. And (3) dispensing and fixing the cable heater 3 by using GD414 or GD414C room temperature vulcanized silicone rubber (hereinafter referred to as silicone rubber) at set intervals (reference distance is 30-50 mm).

The cable heater 3 wound outside the propulsion line 1 is connected to an external power source through an outgoing line, thereby forming a heating circuit. The leading-out wire of the heating loop is not suspended and is firmly fixed by the silicon rubber.

A non-perforated polyimide film 4 is wound around the outside of the cable heater 3 for secondary insulation.

The multi-layer insulation assembly 5 is wrapped around the polyimide film 4, allowing for overlap between the multi-layer insulation assembly 5.

The propulsion pipeline of the spacecraft power system is generally formed by connecting a plurality of sections of sub-pipelines through communicating pipes (two-way, three-way or four-way); during installation, according to the power requirement of each section of sub-pipeline, the thermal control device is respectively wound on each section of sub-pipeline, and then the cable heaters 3 of the thermal control devices on each section of sub-pipeline are connected through the conducting wires, so that the cable heaters 3 on each section of sub-pipeline are added into the heating loop.

The connecting wires at the communicating pipes need to smoothly cross over without suspending, and are firmly fixed on the pipelines or the communicating pipes at the corresponding positions by using the silicon rubber.

Due to the adoption of the filamentous cable heater, the value of the length ratio gamma of the cable heater to the length of the corresponding propelling pipeline can reach 5, the application range is wide, the power constraint can be considered in the heater design, the repeated iterative design is not needed, the thermal design difficulty of the propelling pipeline is greatly reduced, and the design period is shortened.

Example 2:

in addition to the above embodiment 1, two or more cable heaters 3 are wound around the propulsion line 1, and the two or more cable heaters 3 are connected in series or in parallel in the heating circuit, and the cable heaters 3 do not cross each other.

Example 3:

in this embodiment, the general thermal control method is further described by taking an XX-3 power system propulsion pipeline thermal control method as an example.

The thermal control method adopts the cable heater 3, the multilayer heat insulation assembly 5 and the like to ensure that the rail temperature of the spacecraft propulsion pipeline 1 is in a proper range and is not too low or too high.

When the method is used for thermal control of the propulsion pipeline, firstly, the cable heater 3 is designed, and the type and the length of the cable heater 3 are determined:

the power of the cable heater 3 was obtained by thermal analysis, specifically: according to the length of the propulsion pipeline 1 and the ambient temperature, determining the radiation heat exchange quantity and the heat conduction heat exchange quantity of the propulsion pipeline 1 to the environment through thermal analysis, so as to obtain the power required to be compensated by the cable heater 3, and further obtain the resistance value of the cable heater 3; for the cable heater of the determined model, the resistance value is proportional to the length, so that the length of the cable heater 3 can be determined, thereby quickly completing the design of the cable heater 3. The XX-3 propulsion system is designed by using two types of cable heaters 3, the direct current resistances of the two types of cable heaters are respectively 61.12 omega/m and 15.28 omega/m at 20 ℃, and the two types of cable heaters are both single-layer insulated cable heaters.

A layer of polyimide single-sided pressure-sensitive adhesive tape is wound on the outer wall surface of the propelling pipeline 1 to serve as an insulating tape 2 for electrically insulating the pipeline.

Then the designed cable heater 3 is wound on the outer circumference of the insulating tape 2, and when the cable heater 3 is wound, the following steps are ensured:

(1) for each section of sub-pipeline of the propulsion pipeline 1, the winding cable heater 3 is required to be uniform in winding density, fit to the pipeline, smooth and free from bulging, and care is taken to avoid over-tightness and over-looseness. When the two-way, three-way or four-way connection is pushed through the pushing pipeline 1, the two-way, three-way or four-way connection is smoothly crossed, a crossover line (namely a lead for connecting the two sub-pipeline outer cable heaters 3) cannot be suspended, and the two-way, three-way or four-way connection is firmly fixed on the corresponding position by using silicon rubber. The cable heater 3 is fixed by silicon rubber points at intervals (reference distance 30 mm-50 mm). Before the cable heater 3 is actually attached, the cable heater 3 should be wound on the pipeline in advance to determine the density of the wound cable heater 3.

(2) The winding cable heater 3 avoids the thermistor on the propulsion pipeline 1;

(3) the connecting lead between each section of the cable heater 3 and the outgoing line of the heating loop are not suspended; fixing the silicon rubber on the propulsion pipeline at the corresponding position;

(4) each welding spot needs to be reliably fixed, the welding spot is smooth and free of burrs, and two layers of heat-shrinkable sleeves are sleeved outside the welding spot.

(5) Considering that the number of the cable heaters 3 to be implemented by the propulsion pipeline 1 is large, in order to prevent the cable heaters 3 from being welded in a missing way and being welded in a wrong way, the resistance value of each implemented cable heater 3 is required to be measured and recorded; and recording the resistance value of the heating loop when one cable heater 3 is connected into the heating loop. All the cable heaters 3 of the heating loop are connected, after the lead is led out, the total resistance value and the insulation value of the heating loop are measured by a digital multimeter, the measured resistance value is compared with the designed resistance value, and the correct connection of the heating loop of the whole propulsion pipeline 1 is confirmed.

After all the cable heaters 3 are installed and fixed, a non-perforated 25 mu polyimide film is wound on the outer part of the cable heaters 3 for secondary insulation. After the polyimide film winding is completed, the multilayer heat insulation assembly 5 is wound outside.

The implementation process needs to be noted:

when the cable heater 3 is used, the cable heater 3 cannot be pulled by force due to the small diameter of the cable heater 3, and the cable heater 3 is prevented from being pulled to cause resistance value change and even being pulled apart, so that the cable heater 3 fails.

After the cable heater 3 is wound on the propelling pipeline 1, the cable heater is fixed by point silicon rubber at intervals, and the cable heater is not fixed by completely coating the silicon rubber, so that small play may exist between the relative position of the cable heater 3 and the propelling pipeline 1. Therefore, the dispensing of the cable heater 1 adjacent to the thermistor on the propelling pipeline 1 is ensured to be reliably fixed, and the phenomenon that the temperature control failure of the pipeline is caused by the fact that the distance between the heater and the thermistor is too close due to the movement of the cable heater 3 is prevented.

When a loop is welded between the cable heaters 3, a welding lead matched with the diameter of the lead of the cable heater 3 is selected.

In this example, the XX-3 power system propulsion line is 52 meters in total length, and the number of cable heaters used is as much as 286. Based on the traditional thermal control design method for the propulsion pipeline of the polyimide film electric heating belt, the design period is required to be 3 months, and the thermal control method adopting the scheme only needs 1 month, so that the design period is saved by 67.7%.

XX-3 adopts the propulsion pipeline heat control method based on the cable heater, effectively controls the pipeline temperature in the appropriate range, the liquid pipeline temperature is + 15.0- +25.0 ℃, the gas pipeline temperature is-5.0- +10.0 ℃, as shown in figure 2.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.