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    SYSTEMS AND METHODS FOR MAKING AND USING A FITTED CAP FOR APPLYING A SHAPED SEALANT SHROUD TO A PORTION OF A FASTENER
    122.
    发明公开
    SYSTEMS AND METHODS FOR MAKING AND USING A FITTED CAP FOR APPLYING A SHAPED SEALANT SHROUD TO A PORTION OF A FASTENER 审中-公开

    公开(公告)号：EP3915882A1

    公开(公告)日：2021-12-01

    申请号：EP21185432.8

    申请日：2018-10-22

    申请人： The Boeing Company

    发明人： PILLAY, Ganesh R.

    IPC分类号： B64D45/02 ,  F16B37/14 ,  B29C33/68 ,  B29C33/38 ,  B29C33/58 ,  B29C51/10 ,  B29C51/26 ,  B29C51/30 ,  B29C51/12 ,  B29C65/40 ,  B29C65/52

    摘要： A system (501) for applying a shaped sealant shroud (590) to a portion (106) of a fastener (100) comprises a fitted cap (300), comprising a wall (305) and positionable over the portion (106) of the fastener (100) such that a uniform gap (302) is formed between the wall (305) and the portion (106) of the fastener (100). The fitted cap (300) further comprises an inlet opening (306) and a vent (309), communicatively coupled with the uniform gap (302). The system (501) also comprises-a cap-manipulation tool (500), comprising a shaft (510) with a longitudinal central axis (518) and a through, circumferentially closed, channel (516), configured to receive sealant (592). The vent (309) purges gas from the uniform gap (302) as the sealant (592) is communicated through the through, circumferentially closed, channel (516) into the uniform gap (302). The fitted cap (300) is rotatable to distribute the sealant (592) in the uniform gap (302) to form the shaped sealant shroud (590) around the portion (106) of the fastener (100).

    CONTROL ASSEMBLY AND AIRCRAFT
    127.
    发明公开
    CONTROL ASSEMBLY AND AIRCRAFT 审中-公开

    公开(公告)号：EP3892547A1

    公开(公告)日：2021-10-13

    申请号：EP18942639.8

    申请日：2018-12-03

    申请人： SZ DJI Technology Co., Ltd.

    发明人： GAO, Shijing ,  DING, Peng ,  WANG, Chaorui

    IPC分类号： B64D45/00 ,  F16F15/04

    摘要： A control assembly (100) and an aircraft (200) include a bearing board (11), a central board (12), a flight control board (13), a shock absorbing mechanism (14), and a communication connection cable (15). The flight control board (13) is mounted on the central board (12). The central board (12) is connected to the bearing board (11) via the shock absorbing mechanism (14). Therefore, the flight control board (13) and the central board (12) form a whole for shock absorption through the shock absorbing mechanism (14).

    FLIGHT CONTROLLER FOR AN AIRCRAFT AND AIRCRAFT
    129.
    发明公开
    FLIGHT CONTROLLER FOR AN AIRCRAFT AND AIRCRAFT 审中-公开

    公开(公告)号：EP3871983A1

    公开(公告)日：2021-09-01

    申请号：EP21151111.8

    申请日：2021-01-12

    申请人： Subaru Corporation

    发明人： TSUBATA, Hiroyuki

    IPC分类号： B64D45/02 ,  B64C13/16

    摘要： An aircraft (1) includes a fuselage (2), a main wing (12), and a flight controller (18). The main wing (12) is attached to the fuselage (2) and configured to generate lift that acts on the aircraft (1). The flight controller (18) includes an electric field direction estimator (50), an attitude calculator (52), and an attitude controller (54). The electric field direction estimator (50) is configured to estimate a direction of an electric field around the aircraft (1). The attitude calculator (52) is configured to calculate a target airframe attitude (72) that reduces a possibility of occurrence of lightning strike on the aircraft (1), on the basis of the direction of the electric field estimated by the electric field direction estimator (50). The attitude controller (54) is configured to control an attitude of an airframe of the aircraft (1) to cause the attitude of the airframe to be the target airframe attitude (72) calculated by the attitude calculator (52).