CN106650242B - A kind of cost evaluation method for cryogenic propellant in-orbit evaporation capacity control for a long time - Google Patents
A kind of cost evaluation method for cryogenic propellant in-orbit evaporation capacity control for a long time Download PDFInfo
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- 239000003380 propellant Substances 0.000 title claims abstract description 113
- 238000001704 evaporation Methods 0.000 title claims abstract description 69
- 230000008020 evaporation Effects 0.000 title claims abstract description 57
- 238000011156 evaluation Methods 0.000 title claims abstract description 29
- 230000007774 longterm Effects 0.000 claims abstract description 40
- 238000000034 method Methods 0.000 claims abstract description 23
- 238000004364 calculation method Methods 0.000 claims description 38
- 239000010410 layer Substances 0.000 claims description 31
- 239000012774 insulation material Substances 0.000 claims description 17
- 238000009413 insulation Methods 0.000 claims description 14
- 239000011810 insulating material Substances 0.000 claims description 11
- 239000007788 liquid Substances 0.000 claims description 11
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 4
- 239000001257 hydrogen Substances 0.000 claims description 3
- 229910052739 hydrogen Inorganic materials 0.000 claims description 3
- 239000011229 interlayer Substances 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 claims description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims 1
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 238000005457 optimization Methods 0.000 abstract description 2
- 238000001816 cooling Methods 0.000 abstract 1
- 238000001514 detection method Methods 0.000 description 3
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 2
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 231100000956 nontoxicity Toxicity 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- G—PHYSICS
- G16—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR SPECIFIC APPLICATION FIELDS
- G16Z—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR SPECIFIC APPLICATION FIELDS, NOT OTHERWISE PROVIDED FOR
- G16Z99/00—Subject matter not provided for in other main groups of this subclass
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Abstract
The present invention relates to a kind of cost evaluation methods for cryogenic propellant in-orbit evaporation capacity control for a long time, this method considers the leaking heat of the long-term in-orbit storage evaporation amount control system each group part of cryogenic propellant comprehensively, and exhaust can utilize cooling capacity, cryogenic propellant in-orbit storage system evaporation capacity and evaporation rate for a long time are obtained first, evaporation capacity control measure bring weight cost is obtained again, and then the smallest optimal design operating condition of weight cost is obtained, for instructing the design of the in-orbit storage system of cryogenic propellant.The system effectivenesies indexs such as the present invention is light using system weight, power is few, realizability establish Engineering Assessment Method as optimization aim, can effectively carry out cryogenic propellant in-orbit evaporation capacity control system analysis for a long time.
Description
Technical Field
The invention relates to a cost evaluation method for long-term on-orbit evaporation capacity control of a low-temperature propellant, and belongs to the field of long-term on-orbit storage and management of the low-temperature propellant.
Background
The low-temperature propellant has high specific impulse, no toxicity, no pollution and relatively low cost, and is widely applied to domestic and foreign carrier rockets and upper-level vehicles. The low-temperature propellant is considered as the most economical and most efficient chemical propellant for entering space and orbit transfer, and is also the first propellant for future human moon detection, Mars detection and deep space detection at longer distance. Although the performance of the low-temperature propellant is high, the low-temperature propellant has a low boiling point, is easy to evaporate due to heating, is difficult to store for a long time, and can significantly influence the performance of the carrier rocket and the execution of tasks due to the loss of the low-temperature propellant. Therefore, the problem of controlling the evaporation capacity of the low-temperature propellant is solved by adopting reasonable and effective measures, and finally lossless storage is realized, so that the method is an important premise for long-time on-track application of the low-temperature propellant and is a problem to be solved urgently.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a cost evaluation method for long-term on-track evaporation capacity control of a low-temperature propellant.
The above purpose of the invention is mainly realized by the following technical scheme:
a cost evaluation method for long-term on-track evaporation capacity control of a low-temperature propellant comprises the following steps:
(1) determining the in-orbit storage of low-temperature propellantHeat leakage quantity Qloss；
(2) According to the net heat leakage QlossObtaining the evaporation capacity of the low-temperature propellant under different working conditions by the evaporation latent heat gamma corresponding to the saturation temperature of the low-temperature propellant and the on-orbit working time tAnd rate of evaporationi represents different working conditions, i is 1, 2, … …, N, wherein N is the number of working conditions;
(3) obtaining the weight increase brought by introducing the refrigerator under different working conditionsWill be in the same working conditionCorresponding amount of evaporationSumming to obtain the weight cost of the system under the working conditionTraversing system weight costs under all operating conditionsFinding system weight costMinimum value of (d);
(4) recording system weight costAnd taking the working condition corresponding to the minimum value as the optimal working condition.
Long term on-track evaporation of low temperature propellant as described aboveIn the cost evaluation method for control, the step (1) determines the in-rail net stored leakage heat Q of the low-temperature propellantlossThe specific method comprises the following steps:
Qloss＝QMLI+Qstruts+Qparastitic+Qpenetrations-Qvapor-Qcryocooler
wherein: qMLIIndicating the heat leakage of the thermal insulation material on the surface of the propellant storage tank; qstrutsIndicating an amount of heat leakage from the propellant tank support structure; qparastiticIndicating the heat leakage of the refrigerator; qpenetrationsIndicating the heat leakage of the storage tank pipeline; qvaporIndicating the available cold energy for exhausting the low-temperature propellant; qcryocoolerIndicating the refrigerating capacity of the refrigerator.
In the cost evaluation method for long-term on-orbit evaporation capacity control of low-temperature propellant, the heat leakage quantity Q of the thermal insulation material on the surface of the propellant storage tankMLIThe calculation formula of (a) is as follows:
wherein, ThotThe temperature of the outer side of the heat insulation layer of the storage tank; t iscoldIs the temperature of the liquid cryogenic propellant inside the tank, NsIs the total number of the layers of the heat-insulating material.
In the above cost evaluation method for long-term on-orbit evaporation capacity control of a cryogenic propellant, the amount of heat leakage Q of the propellant tank support structurestrutsThe calculation formula of (a) is as follows:
q for liquid oxygen propellantsstruts：
Wherein: c1To design a margin factor, C2Is 0.44, MtankThe weight of the low-temperature propellant storage tank; mpropellantIs the weight of the low-temperature propellant;
q for liquid hydrogen propellantsstruts：
Wherein: c'2Is 0.021.
In the cost evaluation method for long-term on-orbit evaporation capacity control of the low-temperature propellant, the heat leakage quantity Q of the pipeline of the storage tankpenetrationsThe calculation formula of (a) is as follows:
wherein: c1Designing a margin factor; t ishotThe temperature of the outer side of the heat insulation layer of the storage tank; t iscoldIs the temperature, V, of the liquid cryogenic propellant inside the tanktankIs the tank volume.
In the cost evaluation method for long-term on-orbit evaporation capacity control of low-temperature propellant, the heat leakage quantity Q of the refrigerating machineparastiticThe calculation formula of (a) is as follows:
wherein,for input of power to the refrigerator, ThotThe temperature of the outer side of the heat insulation layer of the storage tank; t iscoldThe temperature of the liquid low-temperature propellant in the storage tank is adopted; c1For designing the margin factor, C ″)2Is a shading factor.
In the cost evaluation method for long-term on-orbit evaporation capacity control of the low-temperature propellant, the cold quantity Q available for exhausting the low-temperature propellantvaporThe calculation formula of (a) is as follows:
wherein t is the on-track time, cp,TSpecific heat capacity, T, of propellant at exhaust outlet pressurevapor_beginIs the exhaust outlet temperature, Tvapor_lastThe temperature after the cold has been used up can be utilized for the exhaust.
In the above cost evaluation method for long-term on-track evaporation capacity control of the low-temperature propellant, the evaporation capacity of the low-temperature propellant under different working conditions is obtained in the step (2)And rate of evaporationThe specific method comprises the following steps:
in the above cost evaluation method for long-term on-track evaporation rate control of the low-temperature propellant, the introduction of the refrigerator in the step (3) brings about weight increaseIncluding the weight of the refrigerator itselfRadiator weightSolar array weightWeight of electronic equipmentWeight of pipelineAnd cable weight
In the cost evaluation method for long-term on-orbit evaporation capacity control of low-temperature propellant, the self weight of the refrigerating machineThe calculation formula of (a) is as follows:
wherein: t iscIs the cold head temperature of the refrigerator.
In the above cost evaluation method for long-term on-track evaporation rate control of a cryogenic propellant, radiator weightThe calculation formula of (a) is as follows:
solar array weightThe calculation formula of (a) is as follows:
weight of electronic equipmentThe calculation formula of (a) is as follows:
weight of pipelineThe calculation formula of (a) is as follows:
weight of cableThe calculation formula of (a) is as follows:
wherein:inputting power to the refrigerator;the weight of the refrigerator itself.
In the cost evaluation method for long-term on-track evaporation capacity control of the low-temperature propellant, the input power of the refrigerating machineThe calculation formula of (a) is as follows:
in the above cost evaluation method for long-term on-track evaporation rate control of the low-temperature propellant, the step (3) further comprises the weight of the heat insulation material introduced under different working conditionsWill be in the same working condition Corresponding amount of evaporationSumming to obtain the weight cost of the system under the working conditionTraversing system weight costs under all operating conditionsFinding system weight costIs measured.
In the above cost evaluation method for long-term on-track evaporation rate control of a cryogenic propellant, the weight of the heat insulating materialThe calculation formula of (a) is as follows:
wherein: rhomThe average surface density of the multi-layer heat insulation material reflecting screen; t is tmIs the thickness of the reflecting screen; rhosIs the average areal density, t, of the multi-layer insulation spacersIs the spacer thickness;is the interlayer density of the multi-layer heat insulating material, NsThe total number of the layers of the multi-layer heat insulation material is shown, and A is the area of the multi-layer heat insulation material.
Compared with the prior art, the invention has the following beneficial effects:
(1) the method comprises the steps of firstly obtaining the evaporation capacity and the evaporation rate of the low-temperature propellant long-term on-track storage system, then obtaining the weight cost brought by evaporation capacity control measures, and further obtaining the optimal design working condition with the minimum weight cost for guiding the design of the low-temperature propellant on-track storage system.
(2) The invention establishes an engineering evaluation method by taking system efficiency indexes such as light system weight, low power, realizability and the like as optimization targets, and can effectively carry out long-term on-orbit evaporation capacity control system analysis of the low-temperature propellant.
(3) The cost evaluation method for long-term on-orbit evaporation capacity control of the low-temperature propellant traverses all on-orbit time, all refrigeration capacity, all heat insulation material thicknesses, all propellant weights and other working conditions, considers the factors comprehensively, and greatly improves the accuracy and reliability of the evaluation method.
(4) The cost evaluation method for long-term on-orbit evaporation capacity control of the low-temperature propellant has the advantages of high reliability, wide coverage, high precision and the like.
Drawings
FIG. 1 is a flowchart of a cost evaluation method for long-term on-track evaporation rate control of a low-temperature propellant in an embodiment of the invention.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
the cost evaluation method for on-orbit evaporation capacity control comprises the following specific implementation steps:
(I) the low-temperature propellant long-term on-orbit storage evaporation capacity control system net heat leakage QlossThe calculation method comprises the following steps:
calculating the net heat leakage of the system according to the energy balance, and obtaining the formula (1):
Qloss＝QMLI+Qstruts+Qparastitic+Qpenetrations-Qvapor-Qcryocooler (1)
wherein: qMLIIndicating the heat leakage of the thermal insulation material on the surface of the propellant storage tank; qstrutsIndicating an amount of heat leakage from the propellant tank support structure; qparastiticIndicating the heat leakage of the refrigerator; qpenetrationsIndicating the heat leakage of the storage tank pipeline; qvaporIndicating the available cold energy for exhausting the low-temperature propellant; qcryocoolerIndicating the refrigerating capacity of the refrigerator.
Heat leakage quantity Q of heat insulating material on surface of propellant storage boxMLISee formula (2):
wherein, ThotThe temperature of the outer side of the heat insulation layer of the storage tank is expressed by K; t iscoldThe temperature of the liquid low-temperature propellant in the storage tank is K; n is a radical ofsFor a total number of layers of insulating material, e.g. NsThe value is 10-100.
Heat leakage quantity Q of propellant storage box supporting structurestrutsCalculate support insulation structure (PODS) thermal conductivity data developed based on NASA:
q for liquid oxygen propellantsstrutsSee formula (3):
wherein, C1For designing the margin factor, for example, C is 1-1.22Is 0.44, MtankThe weight of the low-temperature propellant storage tank is kg; mpropellantIs the weight of the low-temperature propellant and has unit kg.
Q for liquid hydrogen propellantsstrutsSee formula (4):
wherein, C1For designing a margin factor, for example, the value is 1-1.2, C'2Is 0.021.
Heat leakage Q of storage tank pipelinepenetrationsIs calculated as follows
Wherein C1 is a design margin factor, for example, V is 1-1.1tankIs a storage tank bodyAnd (4) accumulating.
The heat quantity entering the system through the refrigerating machine when the refrigerating machine is not in operation is mainly based on the data of the AIRS refrigerating machine in the space thermal control Handbook, and the heat leakage quantity Q of the refrigerating machineparastiticThe calculation formula of (a) is as follows:
wherein, C1The value of the design margin factor is 1-1.2, C ″)2Is a shading factor (representing the proportion of time the aircraft is in the shade, the refrigerator is not operating in the shaded region),the power is input to the refrigerator.
Cold quantity Q capable of being used for evaporation and exhaust of low-temperature propellantvaporThe calculation formula of (a) is as follows:
wherein,the evaporation capacity of the low-temperature propellant is shown, and t is the on-orbit time, and the value is 1-500; c. Cp,TSpecific heat capacity of the propellant at the exhaust outlet pressure; t isvapor_beginIs the exhaust outlet temperature, Tvapor_lastThe temperature after the cold has been used up can be utilized for the exhaust.
The cold quantity of the cryogenic refrigerator is determined by the refrigerating capacity of the cryogenic refrigerator, and particularly refers to the refrigerating capacity Q of the cryogenic refrigerator corresponding to the storage temperature (saturation temperature) of the propellantcryocoolerAnd the value is 0-80.
(II) and (1) to (9), according to the saturation temperature of the low-temperature propellant, corresponding to the latent heat of evaporation gamma and the on-orbit working time t,obtaining the net heat leakage Q under different working conditionslossLow temperature propellant evaporationAnd rate of evaporationi represents different working conditions, i is 1, 2, … …, N, wherein N is the number of working conditions;
(III) System cost calculation method
To obtain the weight increase brought by introducing the refrigerator under different working conditionsWill be in the same working conditionCorresponding amount of evaporationSumming to obtain the weight cost of the system under the working conditionTraversing system weight costs under all operating conditionsFinding system weight costIs measured.
Weight increase due to introduction of refrigerating machineIncluding the weight of the refrigerator itselfRadiator weightSolar array weightWeight of electronic equipmentWeight of pipelineAnd cable weight
Namely:
the self weight of the refrigerator under different working conditions is given according to the performance of the current low-temperature refrigeratorThe calculation formula of (a) is as follows:
wherein: t iscIs the cold head temperature of the refrigerator.
Radiator weightThe calculation formula of (a) is as follows:
solar array weightThe calculation formula of (a) is as follows:
weight of electronic equipmentThe calculation formula of (a) is as follows:
weight of pipelineThe calculation formula of (a) is as follows:
weight of cableThe calculation formula of (a) is as follows:
wherein:inputting power to the refrigerator;the weight of the refrigerator itself.
Input power of refrigerator in the above formulaThe calculation formula is as follows:
system weight penalty under this conditionIs represented as follows:
in addition, the step also comprises the weight of the heat insulation material introduced under different working conditionsWill be in the same working conditionCorresponding amount of evaporationSumming to obtain the weight cost of the system under the working conditionTraversing system weight costs under all operating conditionsFinding system weight costIs measured.
Namely, it isCan be expressed as follows:
wherein the weight of the heat insulating materialThe calculation formula of (a) is as follows:
wherein: rhomThe average surface density of the multi-layer heat insulation material reflecting screen; t is tmIs the thickness of the reflecting screen; rhosIs the average areal density, t, of the multi-layer insulation spacersIs the spacer thickness;is the interlayer density of the multi-layer heat insulating material, NsThe total number of the layers of the multi-layer heat insulation material is shown, and A is the area of the multi-layer heat insulation material.
The specific values in this embodiment are:taking 15-25 layers/cm, rhom＝0.00881kg/m2；tm＝0.0064mm；ρs＝0.0073kg/m2，ts＝0.13mm；NsTaking 10-100, wherein A is equal to the surface area of the storage tank.
Fig. 1 is a flowchart of a cost evaluation method for long-term on-track evaporation rate control of a low-temperature propellant in an embodiment of the present invention, where the optimal working conditions obtained according to the method in the embodiment of the present invention are: for the liquid oxygen propellant, the on-orbit time is more than 7 days, and compared with the method of only adopting a passive heat insulation measure, the method has obvious technical advantages after an active refrigerating machine is added, and the system cost is minimum.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (14)
1. A cost evaluation method for long-term on-track evaporation capacity control of a low-temperature propellant is characterized by comprising the following steps of: the method comprises the following steps:
(1) determining the net leakage heat Q of the low-temperature propellant in-orbit storageloss；
(2) According to the net heat leakage QlossObtaining the evaporation capacity of the low-temperature propellant under different working conditions by the evaporation latent heat gamma corresponding to the saturation temperature of the low-temperature propellant and the on-orbit working time tAnd rate of evaporationi represents different working conditions, i is 1, 2, … …, N, wherein N is the number of working conditions;
(3) obtaining the weight increase brought by introducing the refrigerator under different working conditionsWill be in the same working conditionCorresponding amount of evaporationSumming to obtain the weight cost of the system under the working conditionTraversing system weight costs under all operating conditionsFinding system weight costMinimum value of (d);
(4) recording system weight costAnd taking the working condition corresponding to the minimum value as the optimal working condition.
2. The cost assessment method for long-term on-track evaporation rate control of a cryogenic propellant according to claim 1, wherein: determining the net leakage heat Q of the low-temperature propellant stored in the rail in the step (1)lossThe specific method comprises the following steps:
Qloss＝QMLI+Qstruts+Qparastitic+Qpenetrations-Qvapor-Qcryocooler
wherein: qMLIIndicating the heat leakage of the thermal insulation material on the surface of the propellant storage tank; qstrutsIndicating an amount of heat leakage from the propellant tank support structure; qparastiticIndicating the heat leakage of the refrigerator; qpenetrationsIndicating the heat leakage of the storage tank pipeline; qvaporIndicating the available cold energy for exhausting the low-temperature propellant; qcryocoolerIndicating the refrigerating capacity of the refrigerator.
3. The cost assessment method for long-term on-track evaporation control of a cryogenic propellant according to claim 2, wherein: heat leakage quantity Q of heat insulating material on surface of propellant storage boxMLIThe calculation formula of (a) is as follows:
wherein, ThotThe temperature of the outer side of the heat insulation layer of the storage tank; t iscoldThe temperature of the liquid low-temperature propellant in the storage tank is adopted;
Nsis the total number of the layers of the heat-insulating material.
4. The cost assessment method for long-term on-track evaporation control of a cryogenic propellant according to claim 2, wherein: heat leakage quantity Q of propellant storage box supporting structurestrutsThe calculation formula of (a) is as follows:
q for liquid oxygen propellantsstruts：
Wherein: c1To design a margin factor, C2Is 0.44, MtankThe weight of the low-temperature propellant storage tank; mpropellantIs the weight of the low-temperature propellant;
for liquid hydrogen pushQ of the injectionstruts：
Wherein: c'2Is 0.021; t ishotThe temperature of the outer side of the heat insulation layer of the storage tank; t iscoldIs the temperature of the liquid cryogenic propellant inside the tank.
5. The cost assessment method for long-term on-track evaporation control of a cryogenic propellant according to claim 2, wherein: heat leakage Q of storage tank pipelinepenetrationsThe calculation formula of (a) is as follows:
wherein: c1Designing a margin factor; t ishotThe temperature of the outer side of the heat insulation layer of the storage tank; t iscoldIs the temperature, V, of the liquid cryogenic propellant inside the tanktankIs the tank volume.
6. The cost assessment method for long-term on-track evaporation control of a cryogenic propellant according to claim 2, wherein: heat leakage quantity Q of refrigeratorparastiticThe calculation formula of (a) is as follows:
wherein,for input of power to the refrigerator, ThotThe temperature of the outer side of the heat insulation layer of the storage tank; t iscoldThe temperature of the liquid low-temperature propellant in the storage tank is adopted; c1To design a margin factor, C2"is a shading factor.
7. The cost assessment method for long-term on-track evaporation control of a cryogenic propellant according to claim 2, wherein: cold quantity Q capable of being utilized by low-temperature propellant exhaustvaporThe calculation formula of (a) is as follows:
wherein t is the on-track time, cp,TSpecific heat capacity, T, of propellant at exhaust outlet pressurevapor_beginIs the exhaust outlet temperature, Tvapor_lastThe temperature after the cold has been used up can be utilized for the exhaust.
8. The cost evaluation method for long-term on-track evaporation capacity control of a low-temperature propellant according to any one of claims 1 to 7, wherein: the evaporation capacity of the low-temperature propellant under different working conditions is obtained in the step (2)And rate of evaporationThe specific method comprises the following steps:
9. the cost evaluation method for long-term on-track evaporation capacity control of a low-temperature propellant according to any one of claims 1 to 7, wherein: the steps areWeight increase due to introduction of the refrigerator in step (3)Including the weight of the refrigerator itselfRadiator weightSolar array weightWeight of electronic equipmentWeight of pipelineAnd cable weight
10. The cost assessment method for long-term on-track evaporation rate control of a cryogenic propellant according to claim 9, wherein: self weight of refrigeratorThe calculation formula of (a) is as follows:
wherein: t iscIs the cold head temperature of the refrigerator; qcryocoolerIndicating the refrigerating capacity of the refrigerator.
11. The cost assessment method for long-term on-track evaporation rate control of a cryogenic propellant according to claim 9, wherein:
radiator weightThe calculation formula of (a) is as follows:
solar array weightThe calculation formula of (a) is as follows:
weight of electronic equipmentThe calculation formula of (a) is as follows:
weight of pipelineThe calculation formula of (a) is as follows:
weight of cableThe calculation formula of (a) is as follows:
wherein:inputting power to the refrigerator;the weight of the refrigerator itself.
12. The cost assessment method for long-term on-track boil-off control of a cryogenic propellant according to claim 11, wherein: input power of the refrigeratorThe calculation formula of (a) is as follows:
wherein: qcryocoolerIndicating the refrigerating capacity of the refrigerating machine; t ishotThe temperature of the outer side of the heat insulation layer of the storage tank; t iscIs the cold head temperature of the refrigerator.
13. The cost assessment method for long-term on-track evaporation rate control of a cryogenic propellant according to claim 1, wherein: the step (3) also comprises the weight of heat insulation materials introduced under different working conditionsWill be in the same working conditionCorresponding amount of evaporationSumming to obtain the weight cost of the system under the working conditionTraversing system weight costs under all operating conditionsFinding system weight costIs measured.
14. The cost assessment method for long-term on-track evaporation control of a cryogenic propellant according to claim 13, wherein: weight of heat insulating materialThe calculation formula of (a) is as follows:
wherein: rhomThe average surface density of the multi-layer heat insulation material reflecting screen; t is tmIs the thickness of the reflecting screen; rhosIs the average areal density, t, of the multi-layer insulation spacersIs the spacer thickness;is the interlayer density of the multi-layer heat insulating material, NsThe total number of the layers of the multi-layer heat insulation material is shown, and A is the area of the multi-layer heat insulation material.
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| Title |
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| 低温推进剂长时间在轨的蒸发量控制关键技术分析;胡伟峰等;《低温工程》;20110615(第181期);第59-66页 |
| 低温推进剂长时间在轨的蒸发量控制技术进展;胡伟峰等;《导弹与航天运载技术》;20091210(第6期);第28-34页 |
| 低温推进剂长期在轨蒸发量控制分析;张少华等;《中国宇航学会深空探测技术专业委员会第九届学术年会论文集》;20121017;第1068-1073页 |
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