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Optimization Selection of Regulated Pressurization System Schemes for Liquid Attitude and Divert Propulsion Systems
Available online at www.sciencedirect.com
ScienceDirect Procedia Engineering 99 (2015) 1247 – 1251
“APISAT2014”, 2014 Asia-Pacific International Symposium on Aerospace Technology, APISAT2014
Optimization Selection of Regulated Pressurization System Schemes for Liquid Attitude and Divert Propulsion Systems Lie LIU, Guozhu LIANG* School of Astronautics, Beihang University, Beijing 100191, China
Abstract The regulated pressurization system is commonly employed to ensure constant propellant tank pressure in order to maintain stable working status of thrusters. A calculation model for the cold gas and warm gas regulated pressurization systems is founded. The model can calculate the parameters of a whole pressurization system and its components. For the given mission requirements of a liquid attitude and divert system, based on the calculation model and genetic algorithm, the optimization selection can be conducted and the best regulated pressurization system scheme can be selected. According to a typical example, the optimization selection process was demonstrated to select the best regulated pressurization system. The results show that the working capacity, envelope volume, working pattern, thermal management, storage performance, technology maturity, especially the propellant tank pressure have great influences on selection of pressurization system schemes. The method of this paper may be used as a reference for practical design of the regulated pressurization system for liquid attitude and divert propulsion systems. © 2015 2014Published The Authors. Published by is Elsevier © by Elsevier Ltd. This an open Ltd. access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of Chinese Society of Aeronautics and Astronautics (CSAA). Peer-review under responsibility of Chinese Society of Aeronautics and Astronautics (CSAA)
Keywords: liquid attitude and divert propulsion system; regulated pressurization system; optimization selection method
1. Introduction The regulated pressurization system plays a significant role in liquid attitude and divert propulsion systems. When the thrusters operate, to ensure the specified pressure of the combustion chamber, the stable and accurate pressure control of propellant tanks is realized by the regulated pressurization system including the cold and warm gas
* Corresponding author. Tel.:+86-10-8233-9944; fax: +86-10-8233-8798. E-mail address: [email protected]
1877-7058 © 2015 Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license
(http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of Chinese Society of Aeronautics and Astronautics (CSAA)
doi:10.1016/j.proeng.2014.12.655
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Lie Liu and Guozhu Liang / Procedia Engineering 99 (2015) 1247 – 1251
systems which have been used widely[1~6]. It becomes important and necessary to select the best pressurization system through optimization for the given specifications. This paper gives an optimization selection method based on establishment of a pressurization system calculation model and an employment of genetic algorithm. 2. Regulated pressurization system schemes The regulated pressurization systems commonly applied in liquid attitude and divert systems can be seen within the dashed box in Figure 1. These systems can be divided into three basic forms which are the cold gas system, the liquid warm gas system with liquid gas generator, and the solid warm gas system with solid gas generator. These systems can pressurize the propellant tanks to feed the thrusters shown below the dot dash line in Figure 1. liquid warm gas regulated pressurization system
cold gas regulated pressurization system 1 ü gas bottle 2 ü fill and drain valve 3 ü pyrovalve 4 ü filter 5 ü pressure control solenoid valve 6 ü pressure transducer 7 ü computer
8
1 2
GAS
9
4
computer 16
6
17
GAS
3
10 11 12
7 computer
solid warm gas regulated pressurization system
5
14
computer
18
8 ü check valve 9 ü pressure control solenoid valve (warm gas)
13
15
10 ü start gas bottle 11 ü pressure amplified tank 12 ü liquid medium 13 ü burst disk valve 14 ü gas generator (liquid) 15 ü liquid flow regulator 16 ü gas generator (solid) 17 ü gas accumulator 18 ü pressure control solenoid valve (warm gas)
propellant tank NTO
MMH
divert thruster
attitude thruster
Figure.1 Possible regulated pressurization systems in liquid attitude and divert systems
The cold gas system usually includes the gas bottle, pressure control solenoid valve, pressure transducer, filter, pipelines and other valves[7-9]. The decomposition product of hydrazine or hydrazine-70 is operated as the pressurization gas in the liquid warm gas system generally, the components used in this pressurization system is start gas bottle, pressure amplified tank, liquid gas generator, liquid flow regulator, pipelines and other valves[4]. The combustion products of solid propellant are worked as the pressurization gas in the solid warm gas system, and the solid gas generator, gas accumulator, pipelines and other valves constitute this pressurization system. For some uses, there are other two modified regulated pressurization systems with the pressure control solenoid valve and start gas bottle (with pryovalve and pressure control solenoid valve) being replaced by the pressure regulator and the start cartridge in the cold gas system and the liquid warm gas system, respectively. 3. The regulated pressurization system calculation model The regulated pressurization system calculation model for calculating performance, mass, structure arrangement, and working capacity of the regulated pressurization systems can be divided into the system design module, mass calculation module, structure arrangement module, and working capacity calculation module. The system design module can calculate the performance and geometrical parameters shown in Table 1 of the system and components. The mass calculation module can calculate the mass of the components and the whole system, but the total pressurization gas mass is obtained from the system design module. The structure arrangement
Lie Liu and Guozhu Liang / Procedia Engineering 99 (2015) 1247 – 1251
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module can calculate the envelope sizes and centroid position of the system according to geometrical parameters and installation position of components. The working capacity calculation module can calculate the gas mass needed to pressurize propellant tanks and the pressurization efficiency of the pressurization systems. The pressurization efficiency is the ratio of the gas mass needed to the total gas mass including the gas remaining in pipelines and storage vessels. Table 1. Calculated parameters of system and components type
system
parameters
performance parameters
geometrical parameters
cold gas system
initial pressurization pressure end pressurization pressure total pressurization gas mass total pressure loss
---
liquid warm gas system
start pressurization pressure mass flow of pressurization gas liquid energy source mass
---
total pressure loss
pipeline valves filter
start pressurization pressure end pressurization pressure solid energy source mass total pressure loss gas velocity, pressure loss mass flow rate, pressure loss pressure loss
gas bottle
maximum working pressure
gas generator(solid/liquid)
working pressure, thermo properties, mass flow rate, pressure loss
pressure amplified tank
gas side pressure, liquid side pressure
liquid flow regulator
operation pressure, pressure loss
gas accumulator
maximum working pressure
solid warm gas system
components
--diameter, length, wall thickness diameter, length diameter, length, wall thickness volume, diameter, length, height, wall thickness volume, diameter, length, wall thickness volume, diameter, length, wall thickness, piston sizes volume, diameter, length volume, diameter, length, height, wall thickness
4. The optimization selection method The optimization selection method for the best regulated pressurization system is shown in Figure 2. Four steps of this method are model establishment, preliminary selection, optimization, and final determination. The model establishment is conducted based on practical experiences. Through the preliminarily selection, the established schemes are checked out with some schemes being eliminated according to performance requirements. Then, for each feasible scheme, the mass of the system should be minimal under the requirements of the envelope sizes and centroid position. Based on the calculation model and the genetic algorithm, the optimal parameters, such as the initial pressurization pressure and geometrical parameters of the components, etc., can be ensured with some schemes being eliminated because of dissatisfaction of constraints. At last, through detail comparison among a few feasible schemes, the best system scheme can be determined based on some special engineering considerations. 5. An example As an example, a regulated pressurization system is required to have fast respond and high control accuracy and be started repeatedly. The system mass should be as light as possible. The propellant tank pressure is from 1.5~6MPa. The envelope sizes of axial and radial direction are not more than 400mm and 700mm. Helium, hydrazine-70, and ammonium nitrate are used as energy sources in cold gas, liquid and solid warm gas systems, respectively. For the first step of model establishment, seventeen system schemes are established in Table 2. For the second step of preliminary selection, considering requirements for fast respond, high control accuracy, and light mass, seven feasible schemes 5, 8, 9, 12, 13, 14, and 17 are remained.
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Lie Liu and Guozhu Liang / Procedia Engineering 99 (2015) 1247 – 1251
For the third step of optimization process, the results of optimal parameters of feasible schemes for a given preferential pressure 2.5MPa of propellant tanks are shown in Table 3. The five feasible schemes 5, 9, 12, 13, and 14 are remained according to the mission requirements. Table 2. Pressurization system schemes for the typical example schemes 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
pressurization system form
possible shapes of gas vessels shell head cylinder ellipsoid cylinder dish cylinder flat sphere cylinder ellipsoid cylinder dish cylinder flat sphere ellipsoid cylinder dish cylinder cylinder flat sphere ----ellipsoid cylinder dish cylinder cylinder flat sphere
gas vessels
pressure control
pressure regulator cold gas system
gas bottle pressure control solenoid valve
liquid warm gas system
start gas bottle
liquid flow regulator
start cartridge solid warm gas system
pressure control solenoid valve
gas accumulator
Table 3. Result of optimal parameters of feasible pressurization system schemes schemes parameters system mass/kg axial size/mm radial size/mm
scheme 5 scheme 8 (cold gas system) 14.938 --313.8 >400.0 600.0 ---
scheme 9 scheme 12 (liquid warm gas system) 13.108 12.717 170.0 225.5 700.0 700.0
scheme 13 12.204 105.3 700.0
scheme 14 scheme 17 (solid warm gas system) 10.969 --241.0 >400.0 461.3 ---
The relationship between the pressure range (1.5~6MPa) of propellant tanks and minimal system mass for feasible schemes is shown in Figure 3. When the pressure of propellant tanks is not more than 3MPa, the differences of the minimal system masses for these feasible system schemes are modest substantially. When the pressure is over 3MPa, the mass differences become greater. If the pressure reaches 5MPa, the minimal mass of cold gas system scheme is almost twice the warm gas system schemes. With a higher pressure, no appropriate parameters for cold gas system can be obtained but the warm gas systems are suitable for the conditions. model establishment
50
regulated pressurization system establishment
45
preliminary selection
scheme 3
Ă
scheme N
scheme 2'
scheme 3'
Ă
scheme M'
optimization process ( performance parameter/ mass parameter/ envelope size)
scheme 1''
scheme 2''
scheme 3''
Ă
scheme P''
x
40
M
performances selection scheme 1'
optimization
scheme 2
P
Minimal system mass/kg
scheme 1
Scheme Scheme Scheme Scheme Scheme
5 9 12 13 14
35 30 25 20 15 10 x
x
x
x
x
x
x
x
x
x
5
final determination
performances/ envelope volume/ working capacity comparison
0 1.5
2
2.5
3
3.5
4
4.5
5
5.5
6
Pressure of propellant tank/MPa
Figure.2 Flowchart of the optimization selection method
Figure 3. Relationship between the pressure of propellant tanks and minimal mass of pressurization systems
The results of working capacity for schemes are shown in Table 4 for the given preferential pressure of propellant tanks. Scheme 14 can be regarded as the best scheme with the moderate gas mass needed to pressurize propellant tanks and the higher pressurization efficiency.
Lie Liu and Guozhu Liang / Procedia Engineering 99 (2015) 1247 – 1251 Table 4. Result of working capacity for feasible pressurization system schemes schemes working capacity gas mass for pressurization /kg the pressurization efficiency
scheme 5 (cold gas system) 1.38 52.3%
scheme 9,12,13 (liquid warm gas system) 2.58 81.7%
scheme 14 (solid warm gas system) 2.19 80.2%
For the last step of final determination, the propellant tank pressure, working capacity, envelope volume, working pattern, thermal management, storage performance, and technology maturity are compared carefully for the feasible schemes, as shown in Table 5. The envelope volume is impacted by the axial and radial size of pressurization system. The working pattern is mainly affected by the interval time between two starts which influences the possible cooling and condensation of pressurization gas. The thermal management is mainly influenced by the temperature of pressurization gas. In liquid and solid warm gas systems, as the temperature of pressurization gas may reach over 700K, thermal control problems exist. The system storage performance is mainly affected by the leakage characteristics of the stored energy sources and the storage time (up to 10 years). Although the liquid and solid warm gas systems are the trend of development, these systems have not been applied widely. Thus, the technology maturity of cold gas system is much better and has been used for decades. The final system scheme can be determined based on above comparisons and some special practical engineering considerations. Table 5. Comparison of feasible pressurization system schemes schemes comparison content minimal system mass (under 3MPa) minimal system mass (over 3MPa) working capacity envelope volume long interval time between two starts short interval time between two starts thermal management storage performance technology maturity
scheme 5 (cold gas system) C* D B C A A A C A
scheme 9 scheme 12 scheme 13 (liquid warm gas system) B B B B B B B B B B B A A A D A A A B B B B B B B B B
scheme 14 (solid warm gas system) A A A B D A B A B
* A—excellent, B—good, C—average, D—poor
6. Conclusions This paper established an optimization selection method for the regulated pressurization system of liquid attitude and divert propulsion systems. The results show that the working capacity, envelope volume, working pattern, thermal management, storage performance, technology maturity, especially the propellant tank pressure have great influences on selection of the regulated pressurization system. The method of this paper may be used as a reference for practical engineering design. References [1] J. F. Qi, An encyclopedia of world missile and space engines, Military Science Publishing House, Beijing, 1999. [2] J. G. Campbell, Divert propulsion system for army LEAP kill vehicle, AIAA Paper 1993–2637, Jun 1993. [3] J. G. Campbell, Miniature propulsion system, AIAA Paper 1992–3252, Jul 1992. [4] J. C. Maybee, D. J. Krismer, A novel design warm gas pressurization system, AIAA paper 1998–4014, Jul 1998. [5] J. J. Ren, Overview of technology development of propulsion system for space attack and defense weapons abroad, Journal of Rocket Propulsion, 38 (2012) 7–11. [6] D. E. Fritz, G. A. Dressler, and N.L. Mayer, Development and flight qualification of the propulsion and reaction control system for ERIS, AIAA Paper 1992–3663, Jul 1992. [7] D. K. Huzel, Modern Engineer for design of liquid-propellant rocket engine, American Institute of Aeronautics and Astronautics, Washington DC, 1992. [8] K. J. Acampora, H. Wichmann, Component development for micropropulsion systems, AIAA Paper 1992–3255, Jul 1992. [9] J. M. Cory, W. F. Farrell, Internally vented bipropellant valves for divert and ACS missile control, AIAA paper 1996–3267, Jul 1996.
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ScienceDirect Procedia Engineering 99 (2015) 1247 – 1251
“APISAT2014”, 2014 Asia-Pacific International Symposium on Aerospace Technology, APISAT2014
Optimization Selection of Regulated Pressurization System Schemes for Liquid Attitude and Divert Propulsion Systems Lie LIU, Guozhu LIANG* School of Astronautics, Beihang University, Beijing 100191, China
Abstract The regulated pressurization system is commonly employed to ensure constant propellant tank pressure in order to maintain stable working status of thrusters. A calculation model for the cold gas and warm gas regulated pressurization systems is founded. The model can calculate the parameters of a whole pressurization system and its components. For the given mission requirements of a liquid attitude and divert system, based on the calculation model and genetic algorithm, the optimization selection can be conducted and the best regulated pressurization system scheme can be selected. According to a typical example, the optimization selection process was demonstrated to select the best regulated pressurization system. The results show that the working capacity, envelope volume, working pattern, thermal management, storage performance, technology maturity, especially the propellant tank pressure have great influences on selection of pressurization system schemes. The method of this paper may be used as a reference for practical design of the regulated pressurization system for liquid attitude and divert propulsion systems. © 2015 2014Published The Authors. Published by is Elsevier © by Elsevier Ltd. This an open Ltd. access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of Chinese Society of Aeronautics and Astronautics (CSAA). Peer-review under responsibility of Chinese Society of Aeronautics and Astronautics (CSAA)
Keywords: liquid attitude and divert propulsion system; regulated pressurization system; optimization selection method
1. Introduction The regulated pressurization system plays a significant role in liquid attitude and divert propulsion systems. When the thrusters operate, to ensure the specified pressure of the combustion chamber, the stable and accurate pressure control of propellant tanks is realized by the regulated pressurization system including the cold and warm gas
* Corresponding author. Tel.:+86-10-8233-9944; fax: +86-10-8233-8798. E-mail address: [email protected]
1877-7058 © 2015 Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license
(http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of Chinese Society of Aeronautics and Astronautics (CSAA)
doi:10.1016/j.proeng.2014.12.655
1248
Lie Liu and Guozhu Liang / Procedia Engineering 99 (2015) 1247 – 1251
systems which have been used widely[1~6]. It becomes important and necessary to select the best pressurization system through optimization for the given specifications. This paper gives an optimization selection method based on establishment of a pressurization system calculation model and an employment of genetic algorithm. 2. Regulated pressurization system schemes The regulated pressurization systems commonly applied in liquid attitude and divert systems can be seen within the dashed box in Figure 1. These systems can be divided into three basic forms which are the cold gas system, the liquid warm gas system with liquid gas generator, and the solid warm gas system with solid gas generator. These systems can pressurize the propellant tanks to feed the thrusters shown below the dot dash line in Figure 1. liquid warm gas regulated pressurization system
cold gas regulated pressurization system 1 ü gas bottle 2 ü fill and drain valve 3 ü pyrovalve 4 ü filter 5 ü pressure control solenoid valve 6 ü pressure transducer 7 ü computer
8
1 2
GAS
9
4
computer 16
6
17
GAS
3
10 11 12
7 computer
solid warm gas regulated pressurization system
5
14
computer
18
8 ü check valve 9 ü pressure control solenoid valve (warm gas)
13
15
10 ü start gas bottle 11 ü pressure amplified tank 12 ü liquid medium 13 ü burst disk valve 14 ü gas generator (liquid) 15 ü liquid flow regulator 16 ü gas generator (solid) 17 ü gas accumulator 18 ü pressure control solenoid valve (warm gas)
propellant tank NTO
MMH
divert thruster
attitude thruster
Figure.1 Possible regulated pressurization systems in liquid attitude and divert systems
The cold gas system usually includes the gas bottle, pressure control solenoid valve, pressure transducer, filter, pipelines and other valves[7-9]. The decomposition product of hydrazine or hydrazine-70 is operated as the pressurization gas in the liquid warm gas system generally, the components used in this pressurization system is start gas bottle, pressure amplified tank, liquid gas generator, liquid flow regulator, pipelines and other valves[4]. The combustion products of solid propellant are worked as the pressurization gas in the solid warm gas system, and the solid gas generator, gas accumulator, pipelines and other valves constitute this pressurization system. For some uses, there are other two modified regulated pressurization systems with the pressure control solenoid valve and start gas bottle (with pryovalve and pressure control solenoid valve) being replaced by the pressure regulator and the start cartridge in the cold gas system and the liquid warm gas system, respectively. 3. The regulated pressurization system calculation model The regulated pressurization system calculation model for calculating performance, mass, structure arrangement, and working capacity of the regulated pressurization systems can be divided into the system design module, mass calculation module, structure arrangement module, and working capacity calculation module. The system design module can calculate the performance and geometrical parameters shown in Table 1 of the system and components. The mass calculation module can calculate the mass of the components and the whole system, but the total pressurization gas mass is obtained from the system design module. The structure arrangement
Lie Liu and Guozhu Liang / Procedia Engineering 99 (2015) 1247 – 1251
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module can calculate the envelope sizes and centroid position of the system according to geometrical parameters and installation position of components. The working capacity calculation module can calculate the gas mass needed to pressurize propellant tanks and the pressurization efficiency of the pressurization systems. The pressurization efficiency is the ratio of the gas mass needed to the total gas mass including the gas remaining in pipelines and storage vessels. Table 1. Calculated parameters of system and components type
system
parameters
performance parameters
geometrical parameters
cold gas system
initial pressurization pressure end pressurization pressure total pressurization gas mass total pressure loss
---
liquid warm gas system
start pressurization pressure mass flow of pressurization gas liquid energy source mass
---
total pressure loss
pipeline valves filter
start pressurization pressure end pressurization pressure solid energy source mass total pressure loss gas velocity, pressure loss mass flow rate, pressure loss pressure loss
gas bottle
maximum working pressure
gas generator(solid/liquid)
working pressure, thermo properties, mass flow rate, pressure loss
pressure amplified tank
gas side pressure, liquid side pressure
liquid flow regulator
operation pressure, pressure loss
gas accumulator
maximum working pressure
solid warm gas system
components
--diameter, length, wall thickness diameter, length diameter, length, wall thickness volume, diameter, length, height, wall thickness volume, diameter, length, wall thickness volume, diameter, length, wall thickness, piston sizes volume, diameter, length volume, diameter, length, height, wall thickness
4. The optimization selection method The optimization selection method for the best regulated pressurization system is shown in Figure 2. Four steps of this method are model establishment, preliminary selection, optimization, and final determination. The model establishment is conducted based on practical experiences. Through the preliminarily selection, the established schemes are checked out with some schemes being eliminated according to performance requirements. Then, for each feasible scheme, the mass of the system should be minimal under the requirements of the envelope sizes and centroid position. Based on the calculation model and the genetic algorithm, the optimal parameters, such as the initial pressurization pressure and geometrical parameters of the components, etc., can be ensured with some schemes being eliminated because of dissatisfaction of constraints. At last, through detail comparison among a few feasible schemes, the best system scheme can be determined based on some special engineering considerations. 5. An example As an example, a regulated pressurization system is required to have fast respond and high control accuracy and be started repeatedly. The system mass should be as light as possible. The propellant tank pressure is from 1.5~6MPa. The envelope sizes of axial and radial direction are not more than 400mm and 700mm. Helium, hydrazine-70, and ammonium nitrate are used as energy sources in cold gas, liquid and solid warm gas systems, respectively. For the first step of model establishment, seventeen system schemes are established in Table 2. For the second step of preliminary selection, considering requirements for fast respond, high control accuracy, and light mass, seven feasible schemes 5, 8, 9, 12, 13, 14, and 17 are remained.
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Lie Liu and Guozhu Liang / Procedia Engineering 99 (2015) 1247 – 1251
For the third step of optimization process, the results of optimal parameters of feasible schemes for a given preferential pressure 2.5MPa of propellant tanks are shown in Table 3. The five feasible schemes 5, 9, 12, 13, and 14 are remained according to the mission requirements. Table 2. Pressurization system schemes for the typical example schemes 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17
pressurization system form
possible shapes of gas vessels shell head cylinder ellipsoid cylinder dish cylinder flat sphere cylinder ellipsoid cylinder dish cylinder flat sphere ellipsoid cylinder dish cylinder cylinder flat sphere ----ellipsoid cylinder dish cylinder cylinder flat sphere
gas vessels
pressure control
pressure regulator cold gas system
gas bottle pressure control solenoid valve
liquid warm gas system
start gas bottle
liquid flow regulator
start cartridge solid warm gas system
pressure control solenoid valve
gas accumulator
Table 3. Result of optimal parameters of feasible pressurization system schemes schemes parameters system mass/kg axial size/mm radial size/mm
scheme 5 scheme 8 (cold gas system) 14.938 --313.8 >400.0 600.0 ---
scheme 9 scheme 12 (liquid warm gas system) 13.108 12.717 170.0 225.5 700.0 700.0
scheme 13 12.204 105.3 700.0
scheme 14 scheme 17 (solid warm gas system) 10.969 --241.0 >400.0 461.3 ---
The relationship between the pressure range (1.5~6MPa) of propellant tanks and minimal system mass for feasible schemes is shown in Figure 3. When the pressure of propellant tanks is not more than 3MPa, the differences of the minimal system masses for these feasible system schemes are modest substantially. When the pressure is over 3MPa, the mass differences become greater. If the pressure reaches 5MPa, the minimal mass of cold gas system scheme is almost twice the warm gas system schemes. With a higher pressure, no appropriate parameters for cold gas system can be obtained but the warm gas systems are suitable for the conditions. model establishment
50
regulated pressurization system establishment
45
preliminary selection
scheme 3
Ă
scheme N
scheme 2'
scheme 3'
Ă
scheme M'
optimization process ( performance parameter/ mass parameter/ envelope size)
scheme 1''
scheme 2''
scheme 3''
Ă
scheme P''
x
40
M
performances selection scheme 1'
optimization
scheme 2
P
Minimal system mass/kg
scheme 1
Scheme Scheme Scheme Scheme Scheme
5 9 12 13 14
35 30 25 20 15 10 x
x
x
x
x
x
x
x
x
x
5
final determination
performances/ envelope volume/ working capacity comparison
0 1.5
2
2.5
3
3.5
4
4.5
5
5.5
6
Pressure of propellant tank/MPa
Figure.2 Flowchart of the optimization selection method
Figure 3. Relationship between the pressure of propellant tanks and minimal mass of pressurization systems
The results of working capacity for schemes are shown in Table 4 for the given preferential pressure of propellant tanks. Scheme 14 can be regarded as the best scheme with the moderate gas mass needed to pressurize propellant tanks and the higher pressurization efficiency.
Lie Liu and Guozhu Liang / Procedia Engineering 99 (2015) 1247 – 1251 Table 4. Result of working capacity for feasible pressurization system schemes schemes working capacity gas mass for pressurization /kg the pressurization efficiency
scheme 5 (cold gas system) 1.38 52.3%
scheme 9,12,13 (liquid warm gas system) 2.58 81.7%
scheme 14 (solid warm gas system) 2.19 80.2%
For the last step of final determination, the propellant tank pressure, working capacity, envelope volume, working pattern, thermal management, storage performance, and technology maturity are compared carefully for the feasible schemes, as shown in Table 5. The envelope volume is impacted by the axial and radial size of pressurization system. The working pattern is mainly affected by the interval time between two starts which influences the possible cooling and condensation of pressurization gas. The thermal management is mainly influenced by the temperature of pressurization gas. In liquid and solid warm gas systems, as the temperature of pressurization gas may reach over 700K, thermal control problems exist. The system storage performance is mainly affected by the leakage characteristics of the stored energy sources and the storage time (up to 10 years). Although the liquid and solid warm gas systems are the trend of development, these systems have not been applied widely. Thus, the technology maturity of cold gas system is much better and has been used for decades. The final system scheme can be determined based on above comparisons and some special practical engineering considerations. Table 5. Comparison of feasible pressurization system schemes schemes comparison content minimal system mass (under 3MPa) minimal system mass (over 3MPa) working capacity envelope volume long interval time between two starts short interval time between two starts thermal management storage performance technology maturity
scheme 5 (cold gas system) C* D B C A A A C A
scheme 9 scheme 12 scheme 13 (liquid warm gas system) B B B B B B B B B B B A A A D A A A B B B B B B B B B
scheme 14 (solid warm gas system) A A A B D A B A B
* A—excellent, B—good, C—average, D—poor
6. Conclusions This paper established an optimization selection method for the regulated pressurization system of liquid attitude and divert propulsion systems. The results show that the working capacity, envelope volume, working pattern, thermal management, storage performance, technology maturity, especially the propellant tank pressure have great influences on selection of the regulated pressurization system. The method of this paper may be used as a reference for practical engineering design. References [1] J. F. Qi, An encyclopedia of world missile and space engines, Military Science Publishing House, Beijing, 1999. [2] J. G. Campbell, Divert propulsion system for army LEAP kill vehicle, AIAA Paper 1993–2637, Jun 1993. [3] J. G. Campbell, Miniature propulsion system, AIAA Paper 1992–3252, Jul 1992. [4] J. C. Maybee, D. J. Krismer, A novel design warm gas pressurization system, AIAA paper 1998–4014, Jul 1998. [5] J. J. Ren, Overview of technology development of propulsion system for space attack and defense weapons abroad, Journal of Rocket Propulsion, 38 (2012) 7–11. [6] D. E. Fritz, G. A. Dressler, and N.L. Mayer, Development and flight qualification of the propulsion and reaction control system for ERIS, AIAA Paper 1992–3663, Jul 1992. [7] D. K. Huzel, Modern Engineer for design of liquid-propellant rocket engine, American Institute of Aeronautics and Astronautics, Washington DC, 1992. [8] K. J. Acampora, H. Wichmann, Component development for micropropulsion systems, AIAA Paper 1992–3255, Jul 1992. [9] J. M. Cory, W. F. Farrell, Internally vented bipropellant valves for divert and ACS missile control, AIAA paper 1996–3267, Jul 1996.
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