Python Wing_param.convert_to_design_variable方法代码示例

本文整理汇总了Python中DLLM.DLLMGeom.wing_param.Wing_param.convert_to_design_variable方法的典型用法代码示例。如果您正苦于以下问题：Python Wing_param.convert_to_design_variable方法的具体用法？Python Wing_param.convert_to_design_variable怎么用？Python Wing_param.convert_to_design_variable使用的例子？那么恭喜您, 这里精选的方法代码示例或许可以为您提供帮助。您也可以进一步了解该方法所在类DLLM.DLLMGeom.wing_param.Wing_param的用法示例。

在下文中一共展示了Wing_param.convert_to_design_variable方法的7个代码示例，这些例子默认根据受欢迎程度排序。您可以为喜欢或者感觉有用的代码点赞，您的评价将有助于系统推荐出更棒的Python代码示例。

示例1: __init_wing_param

# 需要导入模块: from DLLM.DLLMGeom.wing_param import Wing_param [as 别名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import convert_to_design_variable [as 别名]
 def __init_wing_param(self):
     OC=OperatingCondition('cond1')
     OC.set_Mach(0.7)
     OC.set_AoA(3.0)
     OC.set_altitude(5000.)
     OC.set_T0_deg(20.)
     OC.set_P0(101325.)
     OC.set_humidity(0.)
     OC.compute_atmosphere()
     
     wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
     wing_param.build_wing()
     wing_param.set_value('span',34.1)
     wing_param.set_value('sweep',32.)
     wing_param.set_value('break_percent',33.)
     wing_param.set_value('root_chord',6.1)
     wing_param.set_value('break_chord',4.6)
     wing_param.set_value('tip_chord',1.5)
     wing_param.set_value('root_height',1.28)
     wing_param.set_value('break_height',0.97)
     wing_param.set_value('tip_height',0.33)
     wing_param.convert_to_design_variable('span',(10.,50.))
     wing_param.convert_to_design_variable('sweep',(0.,40.))
     wing_param.convert_to_design_variable('break_percent',(20.,40.))
     wing_param.convert_to_design_variable('root_chord',(5.,7.))
     wing_param.convert_to_design_variable('break_chord',(3.,5.))
     wing_param.convert_to_design_variable('tip_chord',(1.,2.))
     wing_param.convert_to_design_variable('root_height',(1.,1.5))
     wing_param.convert_to_design_variable('break_height',(0.8,1.2))
     wing_param.convert_to_design_variable('tip_height',(0.2,0.5))
     wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
     wing_param.build_airfoils_from_ref()
     wing_param.update()
     
     return wing_param

开发者ID:FrancoisGallard，项目名称:DLLM，代码行数:37，代码来源:test_wing_param.py

示例2:

# 需要导入模块: from DLLM.DLLMGeom.wing_param import Wing_param [as 别名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import convert_to_design_variable [as 别名]
OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()

wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',34.1)
wing_param.set_value('sweep',34.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',6.1)
wing_param.set_value('break_chord',4.6)
wing_param.set_value('tip_chord',1.5)
wing_param.set_value('root_height',1.28)
wing_param.set_value('break_height',0.97)
wing_param.set_value('tip_height',0.33)
wing_param.convert_to_design_variable('span',(10.,50.))
wing_param.convert_to_design_variable('sweep',(0.,40.))
wing_param.convert_to_design_variable('break_percent',(20.,40.))
wing_param.convert_to_design_variable('root_chord',(5.,7.))
wing_param.convert_to_design_variable('break_chord',(3.,5.))
wing_param.convert_to_design_variable('tip_chord',(1.,2.))
wing_param.convert_to_design_variable('root_height',(1.,1.5))
wing_param.convert_to_design_variable('break_height',(0.8,1.2))
wing_param.convert_to_design_variable('tip_height',(0.2,0.5))
wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()

print wing_param

x0=wing_param.get_dv_array()

开发者ID:regislebrun，项目名称:DLLM，代码行数:33，代码来源:valid_grad_DLLM_TCl.py

示例3: test_Wing_param_update

# 需要导入模块: from DLLM.DLLMGeom.wing_param import Wing_param [as 别名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import convert_to_design_variable [as 别名]
 def test_Wing_param_update(self):
     OC=self.__init_OC()
     wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
     wing_param.build_wing()
     wing_param.set_value('span',34.1)
     wing_param.set_value('sweep',32.)
     wing_param.set_value('break_percent',33.)
     wing_param.set_value('root_chord',6.1)
     wing_param.set_value('break_chord',4.6)
     wing_param.set_value('tip_chord',1.5)
     wing_param.set_value('root_height',1.28)
     wing_param.set_value('break_height',0.97)
     wing_param.set_value('tip_height',0.33)
     wing_param.convert_to_design_variable('span',(10.,50.))
     wing_param.convert_to_design_variable('sweep',(0.,40.))
     wing_param.convert_to_design_variable('break_percent',(20.,40.))
     wing_param.convert_to_design_variable('root_chord',(5.,7.))
     wing_param.convert_to_design_variable('break_chord',(3.,5.))
     wing_param.convert_to_design_variable('tip_chord',(1.,2.))
     wing_param.convert_to_design_variable('root_height',(1.,1.5))
     wing_param.convert_to_design_variable('break_height',(0.8,1.2))
     wing_param.convert_to_design_variable('tip_height',(0.2,0.5))
     wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
     wing_param.build_airfoils_from_ref()
     try:
         wing_param.update()
         ok=True
     except:
         ok=False
     assert(ok)

开发者ID:FrancoisGallard，项目名称:DLLM，代码行数:32，代码来源:test_wing_param.py

示例4: test_Wing_param_convert

# 需要导入模块: from DLLM.DLLMGeom.wing_param import Wing_param [as 别名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import convert_to_design_variable [as 别名]
 def test_Wing_param_convert(self):
     wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
     wing_param.build_wing()
     wing_param.set_value('span',34.1)
     wing_param.set_value('sweep',32.)
     wing_param.set_value('break_percent',33.)
     wing_param.set_value('root_chord',6.1)
     wing_param.set_value('break_chord',4.6)
     wing_param.set_value('tip_chord',1.5)
     wing_param.set_value('root_height',1.28)
     wing_param.set_value('break_height',0.97)
     wing_param.set_value('tip_height',0.33)
     try:
         wing_param.convert_to_design_variable('span',(10.,50.))
         wing_param.convert_to_design_variable('sweep',(0.,40.))
         wing_param.convert_to_design_variable('break_percent',(20.,40.))
         wing_param.convert_to_design_variable('root_chord',(5.,7.))
         wing_param.convert_to_design_variable('break_chord',(3.,5.))
         wing_param.convert_to_design_variable('tip_chord',(1.,2.))
         wing_param.convert_to_design_variable('root_height',(1.,1.5))
         wing_param.convert_to_design_variable('break_height',(0.8,1.2))
         wing_param.convert_to_design_variable('tip_height',(0.2,0.5))
         ok=True
     except:
         ok=False
     assert(ok)

开发者ID:FrancoisGallard，项目名称:DLLM，代码行数:28，代码来源:test_wing_param.py

示例5: Wing_param

# 需要导入模块: from DLLM.DLLMGeom.wing_param import Wing_param [as 别名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import convert_to_design_variable [as 别名]
OC.set_P0(101325.0)
OC.set_humidity(0.0)
OC.compute_atmosphere()

wing_param = Wing_param("test_param", geom_type="Broken", n_sect=20)
wing_param.build_wing()
wing_param.set_value("span", 34.1)
wing_param.set_value("sweep", 34.0)
wing_param.set_value("break_percent", 33.0)
wing_param.set_value("root_chord", 6.1)
wing_param.set_value("break_chord", 4.6)
wing_param.set_value("tip_chord", 1.5)
wing_param.set_value("root_height", 1.28)
wing_param.set_value("break_height", 0.97)
wing_param.set_value("tip_height", 0.33)
wing_param.convert_to_design_variable("span", (0.0, 50.0))
wing_param.convert_to_design_variable("sweep", (0.0, 40.0))
wing_param.convert_to_design_variable("break_percent", (20.0, 40.0))
wing_param.convert_to_design_variable("root_chord", (5.0, 7.0))
wing_param.convert_to_design_variable("break_chord", (3.0, 5.0))
wing_param.convert_to_design_variable("tip_chord", (1.0, 2.0))
wing_param.convert_to_design_variable("root_height", (1.0, 1.5))
wing_param.convert_to_design_variable("break_height", (0.8, 1.2))
wing_param.convert_to_design_variable("tip_height", (0.2, 0.5))
wing_param.build_linear_airfoil(OC, AoA0=-2.0, Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()

print wing_param

开发者ID:FrancoisGallard，项目名称:DLLM，代码行数:31，代码来源:valid_dpR_dpiAoA.py

示例6: Wing_param

# 需要导入模块: from DLLM.DLLMGeom.wing_param import Wing_param [as 别名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import convert_to_design_variable [as 别名]
OC.set_P0(101325.0)
OC.set_humidity(0.0)
OC.compute_atmosphere()

wing_param = Wing_param("test_param", geom_type="Broken", n_sect=20)
wing_param.build_wing()
wing_param.set_value("span", 34.1)  # 34.1
wing_param.set_value("sweep", 34.0)
wing_param.set_value("break_percent", 23.0)  # 33.
wing_param.set_value("root_chord", 5.4)  # 6.1
wing_param.set_value("break_chord", 4.6)
wing_param.set_value("tip_chord", 1.2)  # 1.5
wing_param.set_value("root_height", 0.98)
wing_param.set_value("break_height", 0.70)
wing_param.set_value("tip_height", 0.18)
wing_param.convert_to_design_variable("span", (10.0, 50.0))
wing_param.convert_to_design_variable("sweep", (0.0, 40.0))
wing_param.convert_to_design_variable("break_percent", (20.0, 40.0))
wing_param.convert_to_design_variable("root_chord", (5.0, 7.0))
wing_param.convert_to_design_variable("break_chord", (3.0, 5.0))
wing_param.convert_to_design_variable("tip_chord", (1.0, 2.0))
wing_param.convert_to_design_variable("root_height", (0.7, 1.0))
wing_param.convert_to_design_variable("break_height", (0.45, 0.8))
wing_param.convert_to_design_variable("tip_height", (0.10, 0.26))
# wing_param.build_linear_airfoil(OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
wing_param.build_meta_airfoil(
    OC, "../MetaModelCleaning.xml", relative_thickness=0.12, camber=0.0, Sref=1.0, Lref=1.0, sweep=0.0, set_as_ref=True
)
wing_param.build_airfoils_from_ref()
wing_param.update()

开发者ID:regislebrun，项目名称:DLLM，代码行数:32，代码来源:test_meta_airfoil.py

示例7: DLLMOpenMDAOComponent

# 需要导入模块: from DLLM.DLLMGeom.wing_param import Wing_param [as 别名]
# 或者: from DLLM.DLLMGeom.wing_param.Wing_param import convert_to_design_variable [as 别名]

#.........这里部分代码省略.........
    def __set_wing_param(self, wing_param_name='test_param'):
        """Method for wing parameters setting : design variables initial values and bounds
        @param wing_param_name : wing parametrization names
        """
        self.__set_wing_param_values(wing_param_name=wing_param_name)

        self.__set_wing_param_bounds()
        self.__wing_param.build_linear_airfoil(self.OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
        self.__wing_param.build_airfoils_from_ref()
        self.__wing_param.update()

        if self.__display_wing_param:
            self.__display_wing_param = False
            print self.__wing_param

    def __set_wing_param_values(self, wing_param_name='test_param'):
        """Method for wing parameters variables setting
        @param wing_param_name : wing parametrization names
        """
        self.__wing_param = Wing_param(wing_param_name,
                                     geom_type='Broken', n_sect=self.N * 2)
        self.__wing_param.build_wing()
        for i in xrange(self.N):
            self.__wing_param.set_value('rtwist%s' % i, 0.)
        for param in Wing_param.DISCRETE_ATTRIBUTES_LIST:
            self.__wing_param.set_value(param, getattr(self, param))

    def __set_wing_param_bounds(self):
        """Method for desing variables bounds settings
        Values are set to inf/-inf in DLLM component and their 'real' bounds
        are defined when optimization problem is set
        """
        for i in xrange(self.N):
            self.__wing_param.convert_to_design_variable(
                'rtwist%s' % i, (-float('inf'), float('inf')))
        for param in Wing_param.DISCRETE_ATTRIBUTES_LIST:
            self.__wing_param.convert_to_design_variable(param, (-float('inf'), float('inf')))
        return

    def __set_OC_values(self):
        """ Set default operating conditions"""
        self.OC.set_Mach(self.Mach)
        self.OC.set_altitude(self.altitude)
        self.OC.set_T0(self.T0)
        self.OC.set_P0(self.P0)
        self.OC.set_humidity(0.)
        self.OC.compute_atmosphere()
    
    def __update_wing_parame_values(self):
        for dv_id in self.__wing_param.get_dv_id_list():
            if dv_id.startswith('rtwist'):
                i_twist = int(dv_id.replace('rtwist', ''))
                self.__wing_param.set_value(dv_id, self.rtwist[i_twist])
            else:
                self.__wing_param.set_value(dv_id,getattr(self,dv_id))
        self.__wing_param.build_linear_airfoil(self.OC, AoA0=-2., Cm0=-0.1, set_as_ref=True)
        self.__set_wing_param_bounds()
        self.__wing_param.build_airfoils_from_ref()
        self.__wing_param.update()
        return

    def execute(self):
        """ Perform a DLLM computation with the """
        self.__update_wing_parame_values()        
        self.__set_OC_values()
        self.__DLLM.set_target_Lift(self.Target_Lift)

开发者ID:FrancoisGallard，项目名称:DLLM，代码行数:70，代码来源:OpenMDAOWrapper.py

注：本文中的DLLM.DLLMGeom.wing_param.Wing_param.convert_to_design_variable方法示例由纯净天空整理自Github/MSDocs等开源代码及文档管理平台，相关代码片段筛选自各路编程大神贡献的开源项目，源码版权归原作者所有，传播和使用请参考对应项目的License；未经允许，请勿转载。