目的:探讨血清基质金属蛋白酶-1(matrix metalloproteinase-1,MMP1)和纽约食管鳞状细胞癌抗原-1(New York esophageal squamous cell carcinoma 1,NY-ESO-1)自身抗体联合检测在食管鳞状细胞癌中的诊断意义。方法:应用酶联免疫吸附实验检...目的:探讨血清基质金属蛋白酶-1(matrix metalloproteinase-1,MMP1)和纽约食管鳞状细胞癌抗原-1(New York esophageal squamous cell carcinoma 1,NY-ESO-1)自身抗体联合检测在食管鳞状细胞癌中的诊断意义。方法:应用酶联免疫吸附实验检测120例食管鳞状细胞癌患者和120例正常对照血清中MMP1和NY-ESO-1自身抗体的表达水平,采用受试者工作特征(receiver operating characteristic,ROC)曲线评价诊断效能。结果:血清MMP1和NY-ESO-1自身抗体在食管鳞状细胞癌患者中的表达均明显高于正常对照[(8.070±5.738)ng/mL vs(4.331±3.137)ng/mL,Z=6.214,P<0.001;0.463±0.571 vs 0.156±0.086,Z=5.210,P<0.001]。ROC曲线显示,当血清MMP1为最佳诊断临界值10.586 ng/mL时,其在诊断食管鳞状细胞癌的曲线下面积(area under the ROC curve,AUC)为0.732(95%CI:0.671~0.787),敏感度为24.2%,特异度为95.0%。NY-ESO-1自身抗体诊断食管鳞状细胞癌AUC为0.695(95%CI:0.632~0.752),敏感度为33.0%,特异度为95.0%。MMP1和NY-ESO-1自身抗体联合检测诊断食管鳞状细胞癌的AUC为0.800(95%CI:0.744~0.849),敏感度为47.5%,特异度为95.0%。结论:血清MMP1和NY-ESO-1自身抗体联合检测可能有助于提高食管鳞状细胞癌的诊断效能。展开更多
The role of the rocket attitude control system is to execute the required maneuvers for guidance and ensure the stability of the rocket's flight attitude. Attitude control technology has always been one of the key...The role of the rocket attitude control system is to execute the required maneuvers for guidance and ensure the stability of the rocket's flight attitude. Attitude control technology has always been one of the key technologies for ensuring the success of rocket flights and has been a core topic in carrier rocket technology research. The Gravity-1 solid carrier rocket is the first solid rocket bundled rocket developed by China, adopting a configuration with four boosters and a core stage bundled together. During the actual flight process, the four booster engines are ignited first, and then, in the event of insufficient control force from the boosters, the core stage engine is ignited to participate in control. To address thrust asynchrony during the descent of the four boosters, an Extended State Observer(ESO) is employed in the control scheme for this flight segment. This involves real-time estimation and compensation of attitude parameters during flight, identification of thrust asynchrony among the boosters, and simultaneous determination of whether the core stage engine is ignited to participate in control.Through six degrees of freedom simulation analysis and Y1 flight test validation, this method has been proven to be correct and feasible.展开更多
文摘目的:探讨血清基质金属蛋白酶-1(matrix metalloproteinase-1,MMP1)和纽约食管鳞状细胞癌抗原-1(New York esophageal squamous cell carcinoma 1,NY-ESO-1)自身抗体联合检测在食管鳞状细胞癌中的诊断意义。方法:应用酶联免疫吸附实验检测120例食管鳞状细胞癌患者和120例正常对照血清中MMP1和NY-ESO-1自身抗体的表达水平,采用受试者工作特征(receiver operating characteristic,ROC)曲线评价诊断效能。结果:血清MMP1和NY-ESO-1自身抗体在食管鳞状细胞癌患者中的表达均明显高于正常对照[(8.070±5.738)ng/mL vs(4.331±3.137)ng/mL,Z=6.214,P<0.001;0.463±0.571 vs 0.156±0.086,Z=5.210,P<0.001]。ROC曲线显示,当血清MMP1为最佳诊断临界值10.586 ng/mL时,其在诊断食管鳞状细胞癌的曲线下面积(area under the ROC curve,AUC)为0.732(95%CI:0.671~0.787),敏感度为24.2%,特异度为95.0%。NY-ESO-1自身抗体诊断食管鳞状细胞癌AUC为0.695(95%CI:0.632~0.752),敏感度为33.0%,特异度为95.0%。MMP1和NY-ESO-1自身抗体联合检测诊断食管鳞状细胞癌的AUC为0.800(95%CI:0.744~0.849),敏感度为47.5%,特异度为95.0%。结论:血清MMP1和NY-ESO-1自身抗体联合检测可能有助于提高食管鳞状细胞癌的诊断效能。
文摘The role of the rocket attitude control system is to execute the required maneuvers for guidance and ensure the stability of the rocket's flight attitude. Attitude control technology has always been one of the key technologies for ensuring the success of rocket flights and has been a core topic in carrier rocket technology research. The Gravity-1 solid carrier rocket is the first solid rocket bundled rocket developed by China, adopting a configuration with four boosters and a core stage bundled together. During the actual flight process, the four booster engines are ignited first, and then, in the event of insufficient control force from the boosters, the core stage engine is ignited to participate in control. To address thrust asynchrony during the descent of the four boosters, an Extended State Observer(ESO) is employed in the control scheme for this flight segment. This involves real-time estimation and compensation of attitude parameters during flight, identification of thrust asynchrony among the boosters, and simultaneous determination of whether the core stage engine is ignited to participate in control.Through six degrees of freedom simulation analysis and Y1 flight test validation, this method has been proven to be correct and feasible.
