CN-122020867-A - Electromagnetic clean spacecraft thermal control equipment and electromagnetic clean design method thereof

CN122020867ACN 122020867 ACN122020867 ACN 122020867ACN-122020867-A

Abstract

The invention provides electromagnetic clean spacecraft thermal control equipment and an electromagnetic clean design method thereof, wherein the method comprises the steps of arranging notch features on the side edges of a double-layer single-loop electric heater to enable the electric heater to be fixed on a curved surface in a fitting mode, adopting a structure that a pair of twisted wires are connected with the other pair of twisted wires in a local area for wires connected between the double-layer single-loop electric heater and rear-end wires of a temperature element so as to prevent the electric heater from generating electromagnetic interference signals when the electric heater is powered on and powered off, arranging a grounding point network on the surface of the multi-layer heat insulation assembly, and carrying out integrated equipotential grounding design on each grounding point in the multi-layer heat insulation assembly after the grounding point is determined. The invention weakens electromagnetic signals generated when the heating loop is electrified and not electrified, eliminates risk hidden trouble, inhibits electromagnetic stray signals, remarkably enhances the equipotential effect of the whole multi-layer heat insulation assembly, and simultaneously carries out electromagnetic cleaning design on the propulsion system so as to further realize the electromagnetic cleaning effect.

Inventors

LIU LIU
ZHANG XIAOFENG
XIA JIAYI
ZHU XIAOFEI
YANG YONG
LI HUAWANG

Assignees

中国科学院微小卫星创新研究院
上海微小卫星工程中心

Dates

Publication Date: 20260512
Application Date: 20260414

Claims (10)

1. The electromagnetic cleaning design method for the spacecraft thermal control equipment is characterized by comprising the following steps of: The electric heater comprises a double-layer single-loop electric heater, an electromagnetic cleaning design facing the electric heater, a pair of twisted wires and another pair of twisted wires, wherein the side edge of the double-layer single-loop electric heater is provided with a notch feature so that the double-layer single-loop electric heater can be fixed on a curved surface in a fitting way; and the electromagnetic cleaning design faces to the multi-layer heat insulation assembly, wherein a grounding point network is arranged on the surface of the multi-layer heat insulation assembly, and after the grounding position is determined, each grounding point in the multi-layer heat insulation assembly is subjected to integrated equipotential grounding design.
2. The method for designing electromagnetic cleaning of a thermal control device for a spacecraft of claim 1, wherein the step of providing a notch feature on a side of the double-layer single-circuit electric heater comprises: The electric heater is arranged to be of a trapezoid structure as a whole, and the upper edge and the lower edge of the trapezoid are arc-shaped; the shape of the opening of the electric heater is defined as an isosceles triangle structure, wherein the bottom side length of the isosceles triangle structure is Side edge length of ; Introducing a shape factor, an average radius factor and a current position radius factor, wherein the shape factor represents the shape characteristics of the size of the electric heater, and wherein: Shape factor In which, in the process, Is the height of the electric heater, The left and right sides of the electric heater are clamped to form an angle; Average radius factor In which, in the process, Is the arc radius of the top edge of the electric heater, Is the arc radius of the bottom edge of the electric heater, The curvature radius of the curved surface where the electric heater is located; radius factor of current position ; Setting a threshold value And , wherein, To characterize the degree of elongation of the electric heater; To characterize the position of the electric heater on the sphere; For the shape characteristics of the current electric heater size, the number and the positions of the designed electric heater openings are as follows: If it is No opening is needed to be formed on the current electric heater; If it is And is also provided with The electric heater is provided with a gap at the middle parts of the bottom edge and the two side edges respectively, and three gaps are formed in total; If it is And is also provided with The electric heater is provided with a gap at the middle parts of the top edge, the bottom edge and the two side edges respectively, and the total is four; Setting the radius factor of the current position of the notch according to the requirement And form factor of electric heater Setting the shape parameters of the opening The method comprises the following steps: The shape parameter of the opening Will form factor And a current location radius factor The coupling is a deformation driving factor used for describing the relation between the edge warping and the opening size; Setting shape reference parameters Size characteristics of the notch 、 The method comprises the following steps of: In the formula, Representation unit The size change of the bottom edge and the side edge of the opening caused by the change of (a), Indicating when Theoretical gap size at that time.
3. The method for designing electromagnetic cleaning of thermal control equipment for spacecraft according to claim 1, wherein the conducting wire connected between the double-layer single-loop electric heaters and the rear conducting wire of the temperature element are both in a structure of connecting one pair of twisted conducting wires with the other pair of twisted conducting wires in a local area, and the method comprises the following steps: Connecting wires with the same current direction in two pairs of twisted wires to be butted in series or in parallel in a local area, then connecting the formed twisted wires with other twisted wires in the local area in the same way as a new twisted wire, and the like, wherein the connection area is smaller than or equal to a set area threshold value, and the connection mode adopts welding or crimping; And a shielding layer is arranged outside the lead, and the shielding layer is grounded with the equipotential of the satellite.
4. The method for designing electromagnetic cleaning of a thermal control device for a spacecraft of claim 1, wherein the step of arranging a grounding point network on the surface of the multi-layer heat insulation assembly and performing integrated equipotential grounding design on each grounding point in the multi-layer heat insulation assembly after determining the grounding position comprises the steps of: Setting a grounding point network on the surface of the multi-layer heat insulation assembly, wherein the distance from any point on the surface of the multi-layer heat insulation assembly to the nearest grounding point is not more than a set threshold GL, and determining the grounding position; After the grounding position is determined, carrying out integrated equipotential grounding design on each grounding point in the multilayer heat insulation assembly; The multi-layer heat insulation assembly is fixed by adopting a pin-card structure, so that the cross section and the inner and outer surfaces of the multi-layer heat insulation assembly are integrally grounded in an equipotential manner.
5. The method for designing electromagnetic cleaning of a thermal control device for a spacecraft of claim 4, wherein a network of grounding points is provided on a surface of the multi-layer thermal insulation assembly, wherein a distance from any point on the surface of the multi-layer thermal insulation assembly to a nearest grounding point is not greater than a set threshold GL, and determining the grounding position comprises: Setting a grounding area background template according to a set threshold GL, wherein the template takes three circular co-points with the radius GL and a circle center as characteristic array backgrounds; Drawing a drawing of the outer boundary of the multilayer heat insulation assembly, and marking the inner boundary of the multilayer heat insulation assembly on the drawing, wherein the distance from the inner boundary of the multilayer heat insulation assembly to the outer boundary is GL, so as to form the drawing of the multilayer heat insulation assembly; covering the multi-layer heat insulation assembly drawing on the grounding area background template, determining a boundary grounding point and an internal grounding point according to the following determination logic, and designing wiring: taking the three circular common points within the outer boundary range of the multi-layer heat insulation assembly as an inner grounding point; taking the center of a circle between the inner boundary of the multilayer heat insulation assembly and the outer boundary of the multilayer heat insulation assembly as a boundary grounding point; taking the internal grounding point and the boundary grounding point as grounding points of the multi-layer heat insulation assembly, and determining to obtain grounding positions; after the grounding position is determined, the grounding points are connected by adopting an internal grounding wire, and an external grounding wire is led out and used for being grounded with the equipotential of the satellite.
6. The method of claim 4, wherein after determining the grounding location, performing an integrated equipotential grounding design for each grounding point in the multi-layer thermal insulation assembly, comprising: removing a spacer layer with a set area on each layer of the position of the grounding point, so that insulating materials do not cover the reflective layers below the grounding point; the conductive secondary surface mirror is adopted as a heat insulation outer layer of the multilayer heat insulation assembly, the outer surface of the conductive secondary surface mirror is an ITO conductive coating, the inner surface of the conductive secondary surface mirror is a metal layer, and the conductive coating of the ITO layer and the metal layer have conductive characteristics; a non-magnetic metal rivet structure is adopted to vertically penetrate through the multi-layer heat insulation assembly and is pressed, so that all the reflecting layers are in conductive contact, and meanwhile, the reflecting layers are in conductive contact with the metal layers on the inner surface of the conductive secondary surface mirror; When the number of layers of the spacing layer and the reflecting layer is respectively larger than the set threshold value n, the nonmagnetic metal foil is arranged in each layer or part of layers of the reflecting layer so that the compaction degree is adjustable, and the nonmagnetic metal foil is in conductive contact with each reflecting layer when the rivet structure is compacted.
7. The method of electromagnetic cleaning design of a thermal control device for a spacecraft of claim 4, wherein the pin-card structure comprises: the card is prepared from a composite conductive material; the pin is prepared from any one of the following materials: when the pin adopts a cementing base form, the pin is prepared from the same material as the card and is stuck by adopting conductive silicon rubber; When the pin adopts a screw connection base form, the pin is prepared from a non-magnetic metal material.
8. The method of electromagnetic cleaning design for a thermal control device of a spacecraft of any of claims 1-7, further comprising the step of: the design pipeline heating belt is composed of polyimide insulating belts and metal wires, wherein the metal wires are routed in a turn-back mode; A polyimide material layer is attached to the surface of the heat conducting film of the gas cylinder, and meanwhile, a grounding point is arranged, and a grounding wire and a satellite equipotential ground are led out; designing a high-temperature heat shield near the main thruster to form an equipotential structure by adopting a carbon fiber-ceramic composite material with conductive characteristics; an aluminum foil heat-proof cloth is arranged between a secondary surface mirror and an inner multilayer unit in the multilayer heat-insulating assembly near the small thruster, and the aluminum foil heat-proof cloth is in conductive contact with the secondary surface mirror and the reflecting layer.
9. An electromagnetic clean spacecraft thermal control device is characterized in that a notch feature is arranged on the side edge of a double-layer single-loop electric heater, a wire connected between the double-layer single-loop electric heater and a rear end wire of a temperature element are both of a structure that a pair of twisted wires are connected with the other pair of twisted wires in a local area, a grounding point network is arranged on the surface of a multi-layer heat insulation assembly, and each grounding point in the multi-layer heat insulation assembly is designed to be in an integrated equipotential grounding mode.
10. The electromagnetically cleaned spacecraft thermal control device of claim 9, further comprising: in a propulsion system: the pipeline heating belt consists of a polyimide insulating belt and a metal wire, and the metal wire adopts a foldback mode for wiring; The polyimide material layer is adhered to the surface of the heat conducting film of the gas cylinder, a grounding point is arranged, and the grounding wire and the satellite are led out to be grounded in an equipotential manner; the high-temperature heat shield near the main thruster adopts a carbon fiber-ceramic composite material with conductive property to form an equipotential structure; an aluminum foil heat-proof cloth is arranged between the secondary surface mirror and the inner multilayer unit in the multilayer heat-insulating assembly near the small thruster, and the aluminum foil heat-proof cloth is in conductive contact with the secondary surface mirror and the reflecting layer.

Description

Electromagnetic clean spacecraft thermal control equipment and electromagnetic clean design method thereof Technical Field The invention relates to the technical field of spacecraft thermal control, in particular to electromagnetic clean spacecraft thermal control equipment and an electromagnetic clean design method thereof. Background The method is oriented to future deep space exploration tasks, particularly application requirements on in-situ detection of space particles, high-precision magnetic field measurement and the like, and the urgent nature of the design of the top layer on the electromagnetic clean environment of the spacecraft is increasingly highlighted. The existing electromagnetic cleaning method for the spacecraft has more theoretical research, and is mainly realized through source inhibition, propagation blocking and system management, namely, the method of adopting low-noise devices, material shielding, filtering and grounding technology in the design and manufacturing stage, implementing equipment time-sharing work in the operation stage and the like. The measures can reduce electromagnetic interference generated by the spacecraft to a lower level, and simultaneously resist external interference, so that the spacecraft can work in a complex space environment. Through investigation of the current situation and references of research at home and abroad, the method is theoretical research aiming at electromagnetic cleaning of a spacecraft, and a specific electromagnetic cleaning-oriented thermal control product is ambiguous in design method, insufficient in design standardization, weak in implementation operability and lack of practical guidance significance. No description or report of similar technology is found at present, and similar data at home and abroad are not collected. Disclosure of Invention Aiming at the defects in the prior art and aiming at a spacecraft with electromagnetic cleaning property requirements, the invention provides electromagnetic cleaning spacecraft thermal control equipment and an electromagnetic cleaning design method thereof. According to one aspect of the invention, there is provided a method for designing electromagnetic cleanliness of thermal control equipment of a spacecraft, comprising: The electric heater comprises a double-layer single-loop electric heater, an electromagnetic cleaning design facing the electric heater, a pair of twisted wires and another pair of twisted wires, wherein the side edge of the double-layer single-loop electric heater is provided with a notch feature so that the double-layer single-loop electric heater can be fixed on a curved surface in a fitting way; and the electromagnetic cleaning design faces to the multi-layer heat insulation assembly, wherein a grounding point network is arranged on the surface of the multi-layer heat insulation assembly, and after the grounding position is determined, each grounding point in the multi-layer heat insulation assembly is subjected to integrated equipotential grounding design. Preferably, the method further comprises an electromagnetic cleaning design for a propulsion system thermal control apparatus, wherein: the design pipeline heating belt is composed of polyimide insulating belts and metal wires, wherein the metal wires are routed in a turn-back mode; A polyimide material layer is attached to the surface of the heat conducting film of the gas cylinder, and meanwhile, a grounding point is arranged, and a grounding wire and a satellite equipotential ground are led out; designing a high-temperature heat shield near the main thruster to form an equipotential structure by adopting a carbon fiber-ceramic composite material with conductive characteristics; an aluminum foil heat-proof cloth is arranged between a secondary surface mirror and an inner multilayer unit in the multilayer heat-insulating assembly near the small thruster, and the aluminum foil heat-proof cloth is in conductive contact with the secondary surface mirror and the reflecting layer. According to a second aspect of the invention, an electromagnetic clean spacecraft thermal control device is provided, wherein a notch feature is arranged on the side edge of a double-layer single-loop electric heater, a wire connected between the double-layer single-loop electric heater and a rear end wire of a temperature element are both in a structure that one pair of twisted wires is connected with the other pair of twisted wires in a local area, a grounding point network is arranged on the surface of a multi-layer heat insulation assembly, and each grounding point in the multi-layer heat insulation assembly is in an integrated equipotential grounding design. Preferably, the above apparatus further comprises: in a propulsion system: the pipeline heating belt consists of a polyimide insulating belt and a metal wire, and the metal wire adopts a foldback mode for wiring; The polyimide material layer is adhered to the surface of the heat con