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    ARTIFICIAL SATELLITE
    3.
    发明申请
    ARTIFICIAL SATELLITE 审中-公开

    公开(公告)号：US20180237168A1

    公开(公告)日：2018-08-23

    申请号：US15750980

    申请日：2016-08-10

    Applicant: AIRBUS DEFENCE AND SPACE SAS

    Inventor： Philippe CAEL ,  Andrew WALKER ,  Fabrice MENA

    IPC: B64G1/10 ,  B64G1/50 ,  B64G1/44 ,  B64G1/22

    CPC classification number: B64G1/1007 ,  B64G1/10 ,  B64G1/226 ,  B64G1/44 ,  B64G1/503 ,  B64G2001/1092

    Abstract: Disclosed is an artificial satellite including one face from the North face and the South face supporting at least one main radiator having an outer face turned towards space and an inner face opposite the outer face. The satellite includes a bearing structure carrying the North face, the South face, the East face and the West face. At least one part of the at least one main radiator protrudes from at least one face from the East face and the West face. The inner face of the at least one protruding part is covered with a high infrared emissivity material. The value of the dimension of the at least one protruding part is between 19% and 50% of the value of the distance between the East and West faces.

    Carbon nanotube coated structure and associated method of fabrication
    4.
    发明授权
    Carbon nanotube coated structure and associated method of fabrication 有权
    碳纳米管涂层结构及其相关制造方法

    公开(公告)号：US09396828B2

    公开(公告)日：2016-07-19

    申请号：US12907273

    申请日：2010-10-19

    Applicant: Andrew R. Streett

    Inventor： Andrew R. Streett

    IPC: B32B9/00 ,  H01B1/04 ,  C01B31/02 ,  C09D5/24 ,  C09D7/12 ,  B64G1/22 ,  B64G1/50 ,  C08K3/04 ,  C08K7/06

    CPC classification number: C09D5/24 ,  B05D1/02 ,  B64G1/226 ,  B64G1/44 ,  B64G1/50 ,  B82Y30/00 ,  C01B32/158 ,  C08K3/04 ,  C08K7/06 ,  C09D7/70 ,  H01B1/04 ,  Y02P20/129 ,  Y10T428/30

    Abstract: A coated structure is provided that has a highly concentrated coating of carbon nanotubes so as to provide integrated thermal emissivity, atomic oxygen (AO) shielding and tailorable conductivity to the underlying surface, such as the surface of an aerospace vehicle, a solar array, an aeronautical vehicle or the like. A method of fabricating a coated structure is also provided in which a surface is coated with a coating having a relative high concentration of carbon nanotubes that is configured to provide integrated thermal emissivity, AO shielding and tailorable conductivity to the surface.

    Abstract translation: 提供了一种具有高度浓缩的碳纳米管涂层的涂层结构，以便为下层表面提供一体的热辐射率，原子氧（AO）屏蔽和可定制的导电性，例如航空航天车辆的表面，太阳能阵列， 航空车辆等。 还提供了一种制造涂覆结构的方法，其中表面涂覆有具有相对高浓度的碳纳米管的涂层，该涂层被配置为提供一体的热辐射率，AO屏蔽和可表面的导电性。

    Method for Computing Self-Contamination Processes of a Spacecraft
    5.
    发明申请
    Method for Computing Self-Contamination Processes of a Spacecraft 审中-公开
    计算航天器自身污染过程的方法

    公开(公告)号：US20150169805A1

    公开(公告)日：2015-06-18

    申请号：US14567204

    申请日：2014-12-11

    Applicant: Airbus DS GmbH

    Inventor： Joerg HEITZER

    IPC: G06F17/50 ,  G06F17/10

    CPC classification number: G06F17/5009 ,  B64G1/226 ,  B64G1/52 ,  B64G9/00 ,  G06F17/10

    Abstract: A method for computing self-contamination processes of a spacecraft involves receiving a first set of input parameters comprising general definitions of the spacecraft, and a second set of input parameters comprising control parameters for the spacecraft orbital data, physics, numeric. A self-contamination process of the spacecraft is calculated based on the received first and second sets of input data by calculating an analytical solution of a basic equation for calculating a deposit of molecules outgassed from surfaces of the spacecraft in a single computation step with the data processing device. The calculated deposit of molecules is then output.

    Abstract translation: 用于计算航天器的自身污染过程的方法涉及接收包括航天器的一般定义的第一组输入参数，以及包括用于航天器轨道数据，物理学，数字的控制参数的第二组输入参数。 基于接收到的第一和第二组输入数据，通过计算在单个计算步骤中计算从空间飞机的表面脱气的分子的沉积的基本方程式的解析解，计算出航天器的自污染过程，其中数据 处理装置。 然后输出计算的分子沉积物。

    Method for designing sunlight-reflection and heat-radiation multilayer film
    6.
    发明授权
    Method for designing sunlight-reflection and heat-radiation multilayer film 失效
    设计阳光反射和热辐射多层膜的方法

    公开(公告)号：US08712736B2

    公开(公告)日：2014-04-29

    申请号：US13264673

    申请日：2010-04-19

    Applicant: Akira Ohnishi ,  Sumitaka Tachikawa

    Inventor： Akira Ohnishi ,  Sumitaka Tachikawa

    IPC: G06F17/50

    CPC classification number: B64G1/58 ,  B64G1/226 ,  B64G1/50 ,  G02B5/282 ,  Y10T428/31681 ,  Y10T428/31721

    Abstract: A design method for a thermal control film advantageously used in cosmic space, especially for a multilayer film, includes: setting at least two candidate materials for forming the multilayer film and the number of layers of the multilayer film; and designing a combination of the candidate material and a layer thickness by using a genetic algorithm stored in a computer-readable medium using an evaluation function, and recording the obtained results on a computer-readable medium. The evaluation function includes: αs=1−Rs, wherein Rs represents a reflectance of solar energy in a wavelength range used for design, within a solar radiation wavelength range; and ∈H: ∈H=1−RIR, wherein RIR represents a reflectance of heat radiation energy in a wavelength range used for design, within a heat radiation wavelength range.

    Abstract translation: 用于宇宙空间，特别是多层膜的热控制膜的设计方法包括：设置用于形成多层膜的至少两种候选材料和多层膜的层数; 以及通过使用存储在使用评估功能的计算机可读介质中的遗传算法来设计候选材料和层厚度的组合，并将获得的结果记录在计算机可读介质上。 评价函数包括：αs= 1-Rs，其中Rs表示在太阳辐射波长范围内用于设计的波长范围内的太阳能的反射率; 和∈H：∈H= 1-RIR，其中RIR表示在热辐射波长范围内用于设计的波长范围内的热辐射能量的反射率。

    Polymeric coating for protecting objects
    9.
    发明授权
    Polymeric coating for protecting objects 有权
    用于保护物体的聚合物涂层

    公开(公告)号：US08053492B2

    公开(公告)日：2011-11-08

    申请号：US12619641

    申请日：2009-11-16

    Applicant: Garrett Poe ,  Brandon Farmer

    Inventor： Garrett Poe ,  Brandon Farmer

    IPC: C08L79/08 ,  C08G69/28

    CPC classification number: C08F283/04 ,  B64G1/226 ,  B64G1/44 ,  B64G1/58 ,  C08F290/065 ,  C08F290/145 ,  C08G73/1039 ,  C08G73/1042 ,  C08G77/455 ,  C09D179/08 ,  C09D183/10

    Abstract: A protective polymeric coating is applied to the surface of various objects which are to be exposed to a harsh environment. The protective polymeric coating covers the exposed surface, where the polymeric coating includes a polyimide polymer. The polyimide polymer in the polymeric coating has a backbone with at least one non-terminal phenyl group. A linkage is connected to the non-terminal phenyl group, where the linkage can be an amide linkage or an ester linkage. An oligomeric silsesquioxane compound is connected to the linkage through an organic substituent, where the oligomeric silsesquioxane is not incorporated into the polymer backbone. The polymeric coating provides protection to the underlying object.

    Abstract translation: 将保护性聚合物涂层施加到要暴露于恶劣环境的各种物体的表面上。 保护性聚合物涂层覆盖暴露的表面，其中聚合物涂层包括聚酰亚胺聚合物。 聚合物涂层中的聚酰亚胺聚合物具有至少一个非末端苯基的主链。 连接与非末端苯基连接，其中连接可以是酰胺键或酯键。 低聚倍半硅氧烷化合物通过有机取代基与键连接，其中低聚倍半硅氧烷未引入聚合物主链。 聚合物涂层为基础物体提供保护。

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