会员体验
专利管家(专利管理)
工作空间(专利管理)
风险监控(情报监控)
数据分析(专利分析)
侵权分析(诉讼无效)
联系我们
交流群
官方交流:
QQ群: 891211   
微信请扫码    >>>
现在联系顾问~
热词
    • 1. 发明申请
    • AEROSPACE VEHICLE FAIRING SYSTEMS AND ASSOCIATED METHODS
    • 航空汽车公共汽车系统及相关方法
    • US20080001036A1
    • 2008-01-03
    • US11758210
    • 2007-06-05
    • Nicolaas Voogt
    • Nicolaas Voogt
    • B64C3/50B21D53/92
    • B64C7/00B64C9/16B64C9/22Y02T50/32Y10T29/49622
    • Aerospace vehicle fairing systems and associated methods, including fairings that house flap surface drive mechanisms on aircraft, are disclosed herein. A method in accordance with one embodiment, for example, can include adjusting lift distribution across an airfoil. The airfoil includes a first inboard portion and a second outboard portion. The method can include locating a point of maximum curvature of a first fairing at least approximately forward of a trailing edge of the airfoil proximate to the first inboard portion. The method can also include locating a point of maximum curvature of a second fairing at least approximately aft of a trailing edge of the airfoil proximate to the second outboard portion. The locations of the points of maximum curvature for the first and second fairings are based, at least in part, on a target lift distribution.
    • 航空航天车辆整流罩系统和相关方法,包括在飞行器上容纳翼片表面驱动机构的整流罩。 例如,根据一个实施例的方法可以包括调整跨越翼型的升力分布。 翼型件包括第一内侧部分和第二外侧部分。 该方法可以包括将第一整流罩的最大曲率点定位在翼型件的后缘的至少大致前方靠近第一内侧部分。 该方法还可以包括将第二整流罩的最大曲率点定位在靠近第二外侧部分的翼型件的后缘的至少近似的后方。 第一和第二整流罩的最大曲率点的位置至少部分地基于目标升力分布。
    • 3. 发明授权
    • Method for the removal of mercury from a gas stream
    • 从气流中去除汞的方法
    • US06974564B2
    • 2005-12-13
    • US10149946
    • 2002-01-23
    • Joseph Jan BiermannNicolaas Voogt
    • Joseph Jan BiermannNicolaas Voogt
    • B01D53/02B01D53/64B01J20/04B01J20/10B01J20/12B01J20/16B01J20/20C10G25/00C10G27/02B01J8/00
    • B01J20/041B01D53/02B01D53/64B01J20/043B01J20/12B01J20/16B01J20/3078B01J2220/42B01J2220/4831
    • The present invention relates to a method for the removal of mercury from a gas stream. The method is characterized in that at a temperature above 170° C. the gas stream is contacted with a sorbent that as the active component is comprised of a mixture of substantially silica-alumina compounds and/or calcium compounds. According to a preference, the sorbent is kaolin, that may or may not be in the dehydrated form of meta-kaolin and is optionally obtained by thermal conversion of a material chosen from paper waste or residue from the paper industry. By this method it is possible to remove mercury at temperatures higher than room temperature.The invention also relates to a method for the removal of mercury from a gas stream, wherein the gas stream is contacted with a sorbent at a temperature above 50° C., which sorbent comprises as active substance a mixture of substantially silica-alumina compounds and/or calcium compounds, as well as with an oxidator. The invention also relates to a mercury-comprising sorbent obtained by this method and products manufactured therewith.
    • 本发明涉及一种从气流中除去汞的方法。 该方法的特征在于,在高于170℃的温度下,气流与吸附剂接触,因为活性组分由基本上二氧化硅 - 氧化铝化合物和/或钙化合物的混合物组成。 根据优选,吸附剂是高岭土,其可以是脱水形式的或可以不是偏高岭土形式,并且任选地通过热转化来自造纸工业的废纸或残渣的材料来获得。 通过该方法,可以在高于室温的温度下除去汞。 本发明还涉及从气流中除去汞的方法,其中气流在高于50℃的温度下与吸附剂接触,该吸附剂包含基本上二氧化硅 - 氧化铝化合物和 /或钙化合物,以及氧化剂。 本发明还涉及通过该方法获得的含汞吸附剂和由其制造的产品。
    • 5. 发明授权
    • Aerospace vehicle fairing systems and associated methods
    • 航空航天车辆整流罩系统及相关方法
    • US07721999B2
    • 2010-05-25
    • US11758210
    • 2007-06-05
    • Nicolaas Voogt
    • Nicolaas Voogt
    • B64C3/38
    • B64C7/00B64C9/16B64C9/22Y02T50/32Y10T29/49622
    • Aerospace vehicle fairing systems and associated methods, including fairings that house flap surface drive mechanisms on aircraft, are disclosed herein. A method in accordance with one embodiment, for example, can include adjusting lift distribution across an airfoil. The airfoil includes a first inboard portion and a second outboard portion. The method can include locating a point of maximum curvature of a first fairing at least approximately forward of a trailing edge of the airfoil proximate to the first inboard portion. The method can also include locating a point of maximum curvature of a second fairing at least approximately aft of a trailing edge of the airfoil proximate to the second outboard portion. The locations of the points of maximum curvature for the first and second fairings are based, at least in part, on a target lift distribution.
    • 航空航天车辆整流罩系统和相关方法,包括在飞行器上容纳翼片表面驱动机构的整流罩。 例如,根据一个实施例的方法可以包括调整跨越翼型的升力分布。 翼型件包括第一内侧部分和第二外侧部分。 该方法可以包括将第一整流罩的最大曲率点定位在翼型件的后缘的至少大致前方靠近第一内侧部分。 该方法还可以包括将第二整流罩的最大曲率点定位在靠近第二外侧部分的翼型件的后缘的至少近似的后方。 第一和第二整流罩的最大曲率点的位置至少部分地基于目标升力分布。
    • 6. 发明申请
    • Method for the removal of mercury from a gas stream
    • 从气流中去除汞的方法
    • US20080028932A1
    • 2008-02-07
    • US10470437
    • 2003-07-28
    • Joseph Jan BiermannNicolaas Voogt
    • Joseph Jan BiermannNicolaas Voogt
    • B01D53/64B01D53/02B01J20/04B01J20/12B01J20/16
    • B01J20/041B01D53/02B01D53/64B01J20/043B01J20/12B01J20/16B01J20/3078B01J2220/42B01J2220/4831
    • The present invention relates to a method for the removal of mercury from a gas stream. The method is characterized in that at a temperature above 170° C. the gas stream is contacted with a sorbent that as the active component is comprised of a mixture of substantially silica-alumina compounds and/or calcium compounds. According to a preference, the sorbent is kaolin, that may or may not be in the dehydrated form of meta-kaolin and is optionally obtained by thermal conversion of a material chosen from paper waste or residue from the paper industry. By this method it is possible to remove mercury at temperatures higher than room temperature. The invention also relates to a method for the removal of mercury from a gas stream, wherein the gas stream is contacted with a sorbent at a temperature above 50° C., which sorbent comprises as active substance a mixture of substantially silica-alumina compounds and/or calcium compounds, as well as with an oxidator. The invention also relates to a mercury-comprising sorbent obtained by this method and products manufactured therewith.
    • 本发明涉及一种从气流中除去汞的方法。 该方法的特征在于,在高于170℃的温度下,气流与吸附剂接触,因为活性组分由基本上二氧化硅 - 氧化铝化合物和/或钙化合物的混合物组成。 根据优选,吸附剂是高岭土,其可以是脱水形式的或可以不是偏高岭土形式,并且任选地通过热转化来自造纸工业的废纸或残渣的材料来获得。 通过该方法,可以在高于室温的温度下除去汞。 本发明还涉及从气流中除去汞的方法,其中气流在高于50℃的温度下与吸附剂接触,该吸附剂包含基本上二氧化硅 - 氧化铝化合物和 /或钙化合物,以及氧化剂。 本发明还涉及通过该方法获得的含汞吸附剂和由其制造的产品。
    • 7. 发明申请
    • Aerospace vehicle fairing systems and associated methods
    • 航空航天车辆整流罩系统及相关方法
    • US20060261217A1
    • 2006-11-23
    • US11134019
    • 2005-05-20
    • Nicolaas Voogt
    • Nicolaas Voogt
    • B64C1/38B64C9/16
    • B64C9/16B64C7/00B64C9/22Y02T50/32
    • Aerospace vehicle fairing systems and associated methods, including fairings that house flap surface drive mechanisms on aircraft, are disclosed herein. One aspect of the invention is directed toward a fairing system that includes a fairing mounted to an airfoil. The fairing can have a longitudinal axis and a fairing section extending along the longitudinal axis forward and aft of a trailing edge portion of an airfoil section. In one embodiment of the invention, the fairing section can have a wide portion located aft of the airfoil section with a single spanwise width that is greater than or equal to a spanwise width of any other portion of the fairing section. In another embodiment of the invention the fairing section can have a first side and a second side, each with a point of maximum curvature. At least one point of maximum curvature can be located aft of the airfoil section.
    • 航空航天车辆整流罩系统和相关方法,包括在飞行器上容纳翼片表面驱动机构的整流罩。 本发明的一个方面涉及一种整流罩系统,其包括安装在翼型上的整流罩。 整流罩可以具有纵向轴线和整流罩部分,其沿着纵向轴线延伸到翼型部分的后缘部分的前部和后部。 在本发明的一个实施例中,整流罩部分可以具有位于翼型部分后部的宽部分,其具有大于或等于整流罩部分的任何其它部分的翼展宽度的单个翼展宽度。 在本发明的另一个实施例中,整流罩部分可以具有第一侧面和第二侧面,每个具有最大曲率点。 至少一个最大曲率点可以位于翼型部分的后方。
    • 8. 发明授权
    • Aerospace vehicle fairing systems and associated methods
    • 航空航天车辆整流罩系统及相关方法
    • US07300021B2
    • 2007-11-27
    • US11134019
    • 2005-05-20
    • Nicolaas Voogt
    • Nicolaas Voogt
    • B64C3/38
    • B64C9/16B64C7/00B64C9/22Y02T50/32
    • Aerospace vehicle fairing systems and associated methods, including fairings that house flap surface drive mechanisms on aircraft, are disclosed herein. One aspect of the invention is directed toward a fairing system that includes a fairing mounted to an airfoil. The fairing can have a longitudinal axis and a fairing section extending along the longitudinal axis forward and aft of a trailing edge portion of an airfoil section. In one embodiment of the invention, the fairing section can have a wide portion located aft of the airfoil section with a single spanwise width that is greater than or equal to a spanwise width of any other portion of the fairing section. In another embodiment of the invention the fairing section can have a first side and a second side, each with a point of maximum curvature. At least one point of maximum curvature can be located aft of the airfoil section.
    • 航空航天车辆整流罩系统和相关方法,包括在飞行器上容纳翼片表面驱动机构的整流罩。 本发明的一个方面涉及一种整流罩系统,其包括安装在翼型上的整流罩。 整流罩可以具有纵向轴线和整流罩部分,其沿着纵向轴线延伸到翼型部分的后缘部分的前部和后部。 在本发明的一个实施例中,整流罩部分可以具有位于翼型部分后部的宽部分,其具有大于或等于整流罩部分的任何其它部分的翼展宽度的单个翼展宽度。 在本发明的另一个实施例中,整流罩部分可以具有第一侧面和第二侧面,每个具有最大曲率点。 至少一个最大曲率点可以位于翼型部分的后方。