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    • 34. 发明公开
    • MESSAGE SUPPLY SYSTEM
    • 消息供应系统
    • EP1343257A1
    • 2003-09-10
    • EP01270966.3
    • 2001-12-13
    • IHI Aerospace Co., Ltd.
    • YAMANAKA, Tsutomu
    • H04B7/185
    • H04B7/18502
    • A message supply system in which a sender, a database, a spacecraft, a spacecraft tracking control device and a recipient are interconnected via a communication network, a message of the sender is stored in at least one of the spacecraft navigating while being acquired in position by the tracking control device and the database on the earth, and the message stored in the spacecraft or the database is supplied to the recipient together with details and positional data of the spacecraft at a date designated by the sender. According to the message supply system, it becomes possible to supplying various kinds of messages such as an image and an animation (a memorial message for a birthday or so, a message for praying health recovery, a message for affectionate expression such as a proposal, a message concerning a will or the past course of life) to the recipient including the sender him/herself by designating the date and the number of times, and possible to designate the shape, the flight path, the launching date and the like of the spacecraft charged with the message.
    • 一种消息供应系统,其中发送者,数据库,宇宙飞船,航天器跟踪控制装置和接收者经由通信网络互连,发送者的消息存储在航天器中的至少一个导航中,同时在位置上获取 通过跟踪控制装置和地球上的数据库,并且存储在航天器或数据库中的消息与在发送者指定的日期的航天器的细节和位置数据一起提供给接收者。 根据消息提供系统,可以提供各种消息,例如图像和动画(生日等的纪念消息,祈祷健康恢复的消息,提议等情感表达的消息, 关于遗嘱或过去的生活过程的消息)通过指定日期和次数给包括发送者他/她自己的接收者,并且可能指定该发送者自己的形状,飞行路径,发射日期等 负责信息的航天器。
    • 38. 发明公开
    • DOCKING DEVICE
    • EP3604144A1
    • 2020-02-05
    • EP18775284.5
    • 2018-02-23
    • IHI Aerospace Co., Ltd.
    • ISAYAMA Michio
    • B64G1/64
    • A docking device including: a base ring 2 disposed in a first space vehicle A; a first-side capturing ring 3 for coming into contact with the second space vehicle B; six links 4 that constitute a parallel link mechanism 5 for coupling the base ring 2 to the first-side capturing ring 3; and linear actuators 10, each of which extends and contracts the link 4 by using a motor 13 as a driving source, wherein resistance generation mechanisms, each of which generates a regenerative current in the motor 13 of the linear actuator 10 to produce resistance force when the second space vehicle B comes into contact with the first-side capturing ring 3 and the link 4 receives a compressive load, are provided. Correction of misalignment with the second space vehicle, and attenuation of inertia force that the second space vehicle has can be performed without requiring complicated electrical control, and simplification and cost reduction of an electrical system can be implemented.