CN-115878941-B - Satellite fairing safety temperature drop calculation method

CN115878941BCN 115878941 BCN115878941 BCN 115878941BCN-115878941-B

Abstract

The invention discloses a satellite fairing safe temperature drop calculation method which comprises the steps of S1 calculating the area and the volume of a satellite fairing, S2 calculating the heat transfer coefficient of the satellite fairing, S3 calculating the heat dissipation capacity of each structural parameter of a satellite fairing assembly, S4 calculating the heat consumption of the satellite fairing assembly during transportation, S5 calculating the heat capacity of the satellite fairing assembly, S6 calculating the temperature drop of the satellite fairing assembly based on the principle of conservation of heat between the heat dissipated by the satellite fairing assembly and the heat reduced by the satellite fairing assembly, and S7 drawing a change curve of the temperature drop along with time. The invention can accurately calculate the temperature drop condition in the star cover assembly in the transition and tower opening processes, provides accurate and quantitative guarantee basis for air conditioner temperature and humidity adjustment, introduces temperature drop, time and environmental temperature parameters, establishes a functional relationship, provides a reasonable and feasible technical approach for calculating the temperature drop of the fairing, meets the use requirements, and establishes a temperature drop table curve calculation method, thereby being convenient for engineering application.

Inventors

REN CHAOFENG
XUE FUCHENG
XU WEI
ZHANG PING
HAN XIAO
XIANG YOUHUAN
YI SI
LI QIAN
YU LEI
YUE SHOUTI
LI YAOKAI

Assignees

中国人民解放军63729部队

Dates

Publication Date: 20260505
Application Date: 20221226

Claims (4)

1. The satellite fairing safe temperature drop calculation method is characterized by comprising the following steps of: S1, calculating the area and the volume of a satellite fairing according to structural parameters of the satellite fairing; s2, calculating a satellite fairing heat transfer coefficient based on the thermal resistance of the enclosure structure of the satellite fairing; S3, calculating the heat dissipation capacity of each structural parameter of the satellite fairing assembly by adopting an equivalent calculation method based on the satellite fairing heat transfer coefficient, wherein the heat dissipation capacity of the barrel section, the cone section, the end head and the transport vehicle base are calculated respectively by adopting the following formulas in the step S3: wherein K is a heat transfer coefficient, S is an area, and Q is a heat dissipation capacity; S4, calculating heat consumption during transportation of the satellite cover assembly according to the heat dissipation capacity of each structural parameter of the satellite fairing, wherein the step S4 is used for calculating the heat consumption W Cover for vehicle during transportation of the satellite cover assembly and comprises the following steps: W Cover for vehicle =(Q1+ Q2+Q3+Q4)×12.79 Wherein Q1 is the heat dissipation capacity of the cylinder section, Q2 is the heat dissipation capacity of the cone section, Q3 is the heat dissipation capacity of the end head, and Q4 is the heat dissipation capacity of the base of the transport vehicle; S5, calculating the heat capacity of the star cover assembly according to a heat storage medium in the star cover assembly, wherein the step S5 is used for calculating the heat capacity C Star cover of the star cover assembly and comprises the following steps: C Star cover =A1×α1+ A2×α2+ A3×α3 Wherein A1 is the weight percentage of heat preservation foam, A2 is the weight percentage of glass fiber reinforced plastic wall, A3 is the weight percentage of air, alpha 1, alpha 2 and alpha 3 are the specific heat of heat preservation foam, glass fiber reinforced plastic wall and air respectively; S6, respectively calculating the heat dissipated by the star cover assembly and the heat reduced by the star cover assembly, and calculating the temperature drop of the star cover assembly based on the principle of conservation of heat between the heat dissipated by the star cover assembly and the heat reduced by the star cover assembly; s7, calculating the temperature drop of the star cover assembly along with the time change under different outdoor environment temperatures, and drawing a change curve of the temperature drop along with the time.
2. The method for calculating the safe temperature drop of the satellite fairing according to claim 1, wherein the structural parameters of the satellite fairing in the step S1 include a barrel section, a cone section, an end head and a carrier vehicle base, and the material parameters of the satellite fairing include foam and glass fiber reinforced plastic.
3. The method for calculating the safe temperature drop of the satellite fairing according to claim 1, wherein the step S2 specifically includes the following steps: calculating the heat resistance of the fairing enclosure based on the inner surface heat resistance R Inner part , the heat resistance R Wall board of the glass fiber reinforced plastic wall plate, the heat insulation foam heat resistance R Foam and the outer surface heat resistance R Outer part : Adopting heat resistance of fairing enclosure structure Calculating satellite fairing heat transfer coefficient : Wherein, the For the heat transfer coefficient of the transport vehicle, Is the thermal resistance of the transport vehicle.
4. The method for calculating the safe temperature drop of the satellite fairing according to claim 1, wherein the step S6 specifically includes the following steps: Calculating the heat dissipated by the star cover assembly according to the heat consumption during transportation of the star cover assembly : Wherein t is time; based on the heat capacity calculation of the star cover assembly, the heat quantity Q 2 of the star cover assembly is reduced: Wherein G is the mass of the star cover assembly, Is temperature drop; based on the principle of conservation of heat between the heat dissipated by the star cover assembly and the heat reduced by the star cover assembly, the temperature drop of the star cover assembly is calculated ; = 。

Description

Satellite fairing safety temperature drop calculation method Technical Field The invention belongs to the technical field of fairing temperature drop, and particularly relates to a satellite fairing safe temperature drop calculation method. Background The fairing is an important protection device in the satellite transition and emission processes, plays roles of protection, moisture prevention, heat preservation and the like, and is an important barrier for protecting precise electronic equipment on the satellite. The satellite cover assembly formed after the satellite covers is in the process of transferring from a technical factory building to a transmitting station (or in the process of opening a tower), under the condition of no air conditioner guarantee, the temperature in the cover is always kept by depending on the initial temperature and thermal inertia of the satellite, the temperature drop in the cover in the transferring process is closely related with the initial temperature, the structure, the outdoor temperature, the transferring time and other factors of the satellite, and if the temperature drop is overlarge, the adverse effect is brought to the satellite when the temperature drop exceeds the safety index requirement range. At present, when the outdoor environment temperature of the star cover assembly is lower, the star cover assembly is difficult to reach 15 ℃ index requirements, the safety influence on the working condition, dew prevention and the like of on-board products can be possibly generated, and meanwhile, the star cover assembly is also influenced by the outdoor environment temperature when a transfer time window is selected, so that the star cover assembly needs to be pre-regulated in advance in consideration of the factors such as the temperature index requirements, the outdoor environment temperature and the transition time requirements in the star cover assembly, and meanwhile, the pre-regulation capability of a factory air conditioner needs to be considered, the temperature drop condition of the fairing needs to be accurately predicted, and quantitative reference basis is provided for the air conditioner regulation before transition and tower opening. However, the prior art does not aim at a satellite fairing temperature drop calculation scheme, a complicated finite element model is required to be established in a similar heat transfer calculation scheme, and the heat flux density is calculated by setting the heat transfer temperature and the like. The calculation software is commercial software, and has the problems of long calculation time, complex calculation process, low pertinence, high professional requirements, limited application range and the like. Disclosure of Invention The invention aims to overcome the defects in the prior art and provide a satellite fairing safe temperature drop calculation method so as to solve the problem that a satellite fairing temperature drop calculation scheme is lacked in the prior art. In order to achieve the above purpose, the invention adopts the following technical scheme: A satellite fairing safe temperature drop calculation method comprises the following steps: S1, calculating the area and the volume of a satellite fairing according to structural parameters of the satellite fairing; s2, calculating a satellite fairing heat transfer coefficient based on the thermal resistance of the enclosure structure of the satellite fairing; S3, calculating the heat dissipation capacity of each structural parameter of the satellite fairing assembly by adopting an equivalent calculation method based on the satellite fairing heat transfer coefficient; s4, calculating heat consumption during transportation of the satellite fairing assembly according to the heat dissipation capacity of each structural parameter of the satellite fairing; s5, calculating the heat capacity of the star cover assembly according to the heat storage medium in the star cover assembly; S6, respectively calculating the heat dissipated by the star cover assembly and the heat reduced by the star cover assembly, and calculating the temperature drop of the star cover assembly based on the principle of conservation of heat between the heat dissipated by the star cover assembly and the heat reduced by the star cover assembly; s7, calculating the temperature drop of the star cover assembly along with the time change under different outdoor environment temperatures, and drawing a change curve of the temperature drop along with the time. Further, in step S1, the satellite fairing structural parameters include a barrel section, a cone section, an end head, and a carrier vehicle base, and the satellite fairing material parameters include foam and glass fiber reinforced plastic. Further, step S2 specifically includes the following: Based on the internal surface thermal resistance R Inner part , the glass fiber reinforced plastic wall plate thermal resistance R Wall board , the thermal