WO2011026278A1 - 航行器紧急状态信息系统 - Google Patents

航行器紧急状态信息系统 Download PDF

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Publication number
WO2011026278A1
WO2011026278A1 PCT/CN2009/074634 CN2009074634W WO2011026278A1 WO 2011026278 A1 WO2011026278 A1 WO 2011026278A1 CN 2009074634 W CN2009074634 W CN 2009074634W WO 2011026278 A1 WO2011026278 A1 WO 2011026278A1
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Prior art keywords
module
aircraft
release
floating
emergency state
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PCT/CN2009/074634
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English (en)
French (fr)
Inventor
杨东宁
Original Assignee
Yang Dongning
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Publication of WO2011026278A1 publication Critical patent/WO2011026278A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for

Definitions

  • the present invention relates to a search and rescue aid, and more particularly to an aircraft emergency state information system that can detect and record an external environment for an aircraft in the event of an emergency.
  • the navigation data recorder commonly known as "black box” is an instrument that stores the situation during the navigation of the equipment. Its application range is quite wide. It not only covers aircraft, airships, hot air balloons, etc., but also has been used in ships in recent years. Marine vehicles such as submarines and even land-based vehicles are on the top.
  • black box When the above device is equipped with a black box, the subsequent need to understand the navigation situation, the recording data in the current operation of the aircraft can be recalled and replayed and analyzed by the playback device to obtain the value data.
  • the existing aircraft black box its stored navigation data is mainly for the internal equipment, such as the real-time recording of the driver's dialogue, the record of the state of the equipment during the navigation, etc., but can not detect the external conditions or environment of the aircraft, this is This makes it impossible for future generations to obtain more reference data at the time of the event once the aircraft malfunctions or is an accident.
  • the existing black box has limited ability to call for help. After an accident occurs in a special geographical environment, it is often difficult for search and rescue personnel to find their whereabouts.
  • the object of the present invention is to overcome the above drawbacks, and provide a quick and accurate real-time collection of environmental information of the living body in an emergency state of the aircraft, and simultaneously issue orientation information and a distress signal, so that the searcher can quickly and accurately find and implement the rescue and finally obtain the incident.
  • Vehicle related emergency information system with relevant information.
  • the object of the invention is achieved in that it comprises a connected airlift module, a release missile module and a traction module, wherein
  • the air-lifting floating module is used for the spacecraft to escape from the air body when it is in an emergency state. It provides convenience and data support for search and rescue. It installs an audio-visual information module for real-time detection and recording of external environmental information, and is used for detecting and recording the location.
  • the air-lifting floating module includes a closed bellows unit capable of performing expansion and contraction changes, The bellows is filled with a high-pressure low-density gas that can automatically expand and generate floating lift and is provided with an auxiliary parachute;
  • the audio-visual information module includes video and audio equipment for recording audio and video condition information of the external environment;
  • the power module corresponding to the audio-visual information module, the positioning call module and the illuminating signal module are provided with a power supply unit;
  • the sleek floating module is provided with a illuminating signal module, which comprises an active illuminating unit and an identification graphic color code for providing Significantly bright graphic signals to facilitate rescue search;
  • the ejection module includes a limiting unit and an ejection unit, and the limiting unit is configured to limit volume compression of the airlifting floating module when not released, and the ejection unit is configured to release the airlifting floating module and eject it out of the aircraft;
  • the traction module is used for connecting the aircraft and the airlifting floating module, ensuring that the floating module can not be lost and keeps a certain distance from the aircraft for collecting external environmental data and sending a distress signal;
  • the traction module comprises a traction cable And releasing the damping unit, the traction cable is connected to the aircraft and the liftable floating module, and the release damping unit is used to control the release speed of the traction cable.
  • the invention Compared with a common search and rescue aid, the invention has the beneficial effects of releasing the capsule body of the lift-off floating module pre-filled with low-density high-pressure gas in an emergency state under the control of the release ejection module, and the capsule is internally Under the action of the high-pressure low-density gas, it expands and suspends in the air or water, and maintains the appropriate distance from the aircraft body under the action of the traction module.
  • the audio-visual information module, the positioning call module and the illuminating signal module are set to work. The environmental status information around the system is collected, and the location information call signal is sent out by the positioning call system, and the illuminating signal module provides the light image identification, which greatly facilitates the rapid and effective search and rescue work in the night and daytime.
  • Figure 1 is a system configuration diagram of the present invention
  • FIG. 2 is a schematic structural diagram of a system according to an embodiment of the present invention ⁇ detailed description ⁇
  • the present invention relates to an aircraft emergency state information system, which can be conveniently applied not only to various aircraft such as airplanes, airships, and spacecrafts, but also to marine vessels such as ships and submarines or other various aircraft. on. Including a connected airlift module, a release catapult module, and a traction module, wherein
  • the air-lifting floating module is used for the spacecraft to escape from the air body when it is in an emergency state. It provides convenience and data support for search and rescue. It installs an audio-visual information module for real-time detection and recording of external environmental information, and is used for detecting and recording the location.
  • the calling module records the external environment status information;
  • Traction module used to connect the aircraft and the liftable floating module, to ensure that the floating module can be lifted and kept away from the aircraft for external environmental data collection and distress signal transmission.
  • the slewing floating module further includes an illuminating signal module, which includes an active illuminating unit and an identification graphic color code for providing a significant light pattern.
  • the text signal facilitates rescue search.
  • the audiovisual information module includes video and audio devices for recording audio and video status information of the external environment
  • the liftable floating module includes a closed bellows unit and an auxiliary parachute that can be flexibly changed, and the bellows is filled with a high-pressure low-density gas that can automatically expand and generate floating lift.
  • the release ejection module includes a limiting unit for limiting the volume compression of the liftable floating module when it is not released, and an ejection unit for releasing the ejectable floating module and ejecting it out of the aircraft.
  • the traction module includes a traction cable and a release damping unit, the traction cable is coupled to the aircraft and the liftable floating module, and the release damping unit is configured to control the release speed of the traction cable.
  • the traction cable of the traction module is composed of two synchronous and wound wire ropes, a connecting buckle and a speed limiter. One end of the wire rope is connected to the bellows, and one of the single ropes at the other end passes through the hanging ring of the connecting aircraft body, and is hung. The ring must have sufficient aperture and strength to slide smoothly when the two wire ropes are pulled, so that the corresponding aircraft body part can be lifted after replacing the steel cable in the subsequent rescue.
  • the power module is provided with a power supply unit corresponding to the audio and video information module, the positioning call module and the lighting signal module.
  • the capsule when the capsule is ejected from the body in an emergency state, if it is in the air, it will rapidly expand under the action of pre-filling low-density gas, and float in the air with the help of the auxiliary parachute. If it falls into the water, the bellows can Floating the water surface for a long time, and the traction cable keeps connected with the body, gradually widening the distance from the body under the release damping unit of the traction module, and the video unit of the built-in audio and video recording module will record from near to far. The whole process is performed, and the positioning call module acquires the orientation information of the corresponding position and simultaneously sends a distress signal.
  • one or more sets of emergency information systems of the present invention can be designed and installed.
  • Small aircraft can be installed near the top of the cockpit; large aircraft can be installed with four sets, respectively, on the two wings, near the top of the cockpit, and at the appropriate part of the rear fuselage.
  • the two wire ropes of the traction cable in the traction module of the emergency state information system pass through the main beam hanging ring of the connecting body.
  • the hanging ring must have sufficient aperture and strength to slide smoothly when the two wire ropes are pulled. After that, the body can be lifted.
  • the controller that releases the ejection module should be installed at the most convenient place for the control personnel to control.
  • the electric release button can be used. Otherwise, the mechanical release wrench is used.
  • the interlocking release button and release wrench ensure reliability.
  • the inflation valve at the top of the membrane module of the liftable floating module is filled with high pressure and low density gas (such as hydrogen or helium) according to the design parameters.
  • the pressure is detected by the pressure beside the valve. Table indication.
  • the pilot presses the release button or the mechanical release wrench (the electric release button can be used when the power supply is normal, otherwise the mechanical release wrench is used) to release the floating module of the floating module; if the aircraft explodes instantaneously, the floating module membrane can be lifted off.
  • the box is automatically released due to the stress pull of the release catapult module to control the cable.
  • the ground command system immediately starts the search and rescue after receiving the GPS positioning and the distress signal; there is GPS navigation, the light signal at the top of the bellows, the identification color of the bellows, and the speed is found at night or during the day. If the plane crashes into the sea, replace the winch (vehicle) with a steel rope. By connecting the bellows to the wire rope of the body, the steel cable is quickly replaced from small to large, so that the body can be lifted for auxiliary rescue. In addition, after collecting the product afterwards, through the analysis of the environmental data recorded by the built-in equipment, the whole process outside the aircraft emergency state machine can be understood. In addition, if the device is towed to the original "black box" of the aircraft, the recovery rate of the black box can be further enhanced, and the information in the aircraft body of the emergency state can be obtained.
  • the whole system designs the signal source according to international conventions and supports the receiving equipment.
  • Steel wire replacement winch (car). It is used to quickly replace the steel cable from small to large by connecting the bellows to the body of the steel cord to lift the body.
  • the present invention releases the capsule body of the lift-off floating module pre-charged with low-density high-pressure gas in an emergency state under the control of the release ejection module, and the bellows expands under the action of the internal high-pressure low-density gas.
  • the audiovisual information module, the positioning call module and the illuminating signal module are set to work, and the environmental state information around the system is collected.
  • the location information calling signal is sent out by the positioning call system, and the illuminating signal module provides the light image identification, which greatly facilitates the instant and effective development of the search and rescue work.

Description

航行器紧急状态信息系统
【技术领域】
本发明涉及一种搜救辅助设备， 尤其是指一种可针对航行器当其发生 紧急状况时对外部环境进行检测记录并提供救援协助的航行器紧急状态信 息系统。
【背景技术】
航行数据记录仪， 俗名 "黑匣子" 是一种将设备航行过程中情况储存 下来的仪器， 其应用范围现以相当广， 不仅囊括飞机、 飞艇、 热气球等航 空器， 近些年来也开始使用在船舶、 潜艇等航海器甚至陆地运行的交通工 具等上头。 当上述设备设置了黑匣子后， 后续需要了解航行情况时， 均可 通过重放设备将航行器当时运作过程中的记录数据调出并进行重放、 分析, 从而得出价值数据。 然而现有航行器黑匣子， 其存储的航行状况资料主要 是针对设备内部的， 诸如驾驶员对话实时录音、 航行过程设备状态的记录 等， 却无法对航行器外部情况或环境进行检测记录， 这就使得一旦航行器 发生故障或者事故， 后人无法得到事件当时的更多参考数据。 此外， 现有 黑匣子自主呼救能力有限， 在航行器在特殊地理环境中发生事故后， 搜救 人员往往难以即时找寻其下落。
【发明内容】
本发明的目的在于克服了上述缺陷， 提供一种可在航行器紧急状态下 快速准确实时收集机体周围环境信息， 同时发出方位信息及呼救信号， 以 便搜索人员快速准确寻找实施救援并最终取得事发时相关信息的航行器紧 急状态信息系统。
本发明的目的是这样实现的： 它包括相连的可升空漂浮模块、 释放弹 射模块及牵引模块， 其中
可升空漂浮模块， 用于航天器发生紧急状态时脱离机体， 为搜索救援 提供便利及数据支持， 其内安装用于实时检测并记录外部周围环境信息的 音像信息模块、 用于检测并记录所在地理位置， 并对控制中心发出呼叫求 救信号的定位呼叫模块以及用于满足全系统提供基本用电需求的电源模 块； 一旦可升空漂浮模块脱离机体其即会同时启动其内音像信息模块及定 位呼叫模块记录所处外部环境状态信息； 所述可升空漂浮模块包括可进行 伸缩变化的密闭膜盒单元， 膜盒中充有可使其自动膨胀并产生漂浮升力的 高压低密度气体并设有辅助降落伞； 所述音像信息模块包括视频及音频设 备， 用于记录外部环境的音频、 视频状况信息； 所述电源模块对应音像信 息模块、 定位呼叫模块及发光信号模块一一设置有供电单元； 所述可升空 漂浮模块上设有发光信号模块， 它包括主动发光单元及识别图文色标， 用 于提供显著亮光图文信号， 为救援搜索提供便利；
释放弹射模块， 安装于航行器机体及可升空漂浮模块之间， 电动和手 动或自动控制启动， 用于在必要时将相连的可升空漂浮模块释放弹射至航 行器机体外； 所述释放弹射模块包括限位单元及弹射单元， 限位单元用于 限制可升空漂浮模块在未释放时的体积压缩， 而弹射单元用于释放可升空 漂浮模块并将其弹射出航行器外；
牵引模块， 用于连接航行器及可升空漂浮模块， 确保可升空漂浮模块 不会丟失并与航行器保持一定距离进行外部环境数据的收集及求救信号的 发送； 所述牵引模块包括牵引缆绳及释放阻尼单元， 牵引缆绳与航行器及 可升空漂浮模块相连， 而释放阻尼单元用于控制牵引缆绳的释放速度。
相比于常见的搜救辅助设备， 本发明的有益效果在于通过应用预充低 密度高压气体的升空漂浮模块的膜盒主体， 在释放弹射模块的控制下在紧 急状态时释放， 膜盒在内部高压低密度气体作用下膨胀并悬浮于空气或水 中， 在牵引模块的作用下保持与航行器机体阶段性的适当距离， 同时其设 置的音像信息模块、 定位呼叫模块、 发光信号模块开始工作， 对系统周围 的环境状态信息进行收集， 同时通过定位呼叫系统发出方位信息呼救信号， 而发光信号模块则提供亮光图文标识， 大大方便黑夜和白天的搜索救援工 作快速有效开展。
【附图说明】
下面结合附图详述本发明的具体结构
图 1为本发明的系统构成图
图 2为本发明具体实施例系统构成示意图 【具体实施方式】
如图 1 所示， 本发明涉及一种航行器紧急状态信息系统， 不仅可方便 的应用在飞机、 飞艇、 飞船等各类航空器， 也可应用在船舶、 潜艇等航海 器或其他各种航行器上。 包括相连的可升空漂浮模块、 释放弹射模块及牵 引模块， 其中
可升空漂浮模块， 用于航天器发生紧急状态时脱离机体， 为搜索救援 提供便利及数据支持， 其内安装用于实时检测并记录外部周围环境信息的 音像信息模块、 用于检测并记录所在地理位置， 并对控制中心发出呼叫求 救信号的定位呼叫模块以及用于满足全系统提供基本用电需求的电源模 块； 一旦可升空漂浮模块脱离机体其即会同时启动其内音像信息模块及定 位呼叫模块记录所处外部环境状态信息；
释放弹射模块， 安装于航行器机体及可升空漂浮模块之间， 电动和手 动或自动控制启动， 用于在必要时将相连的可升空漂浮模块释放弹射至航 行器机体外；
牵引模块， 用于连接航行器及可升空漂浮模块， 确保可升空漂浮模块 不会丟失并与航行器保持一定距离进行外部环境数据的收集及求救信号的 发送。
参见图 2为具体实施例的系统构成图， 该具体实施的系统中： 可升空漂浮模块上还设有发光信号模块， 它包括主动发光单元及识别 图文色标， 用于提供显著亮光图文信号， 为救援搜索提供便利。
音像信息模块包括视频及音频设备， 用于记录外部环境的音频、 视频 状况信息；
可升空漂浮模块包括可进行伸缩变化的密闭膜盒单元和辅助降落伞， 膜盒中充有可使其自动膨胀并产生漂浮升力的高压低密度气体。
释放弹射模块包括限位单元及弹射单元， 限位单元用于限制可升空漂 浮模块在未释放时的体积压缩， 而弹射单元用于释放可升空漂浮模块并将 其弹射出航行器外。
牵引模块包括牵引缆绳及释放阻尼单元， 牵引缆绳与航行器及可升空 漂浮模块相连， 而释放阻尼单元用于控制牵引缆绳的释放速度。 所述牵引 模块的牵引缆绳由二条同步并绕的钢丝绳、 连接扣及限速器组成， 钢丝绳 一端连接膜盒， 另一端的其中一根单绳穿过连接航行器机体吊挂环， 吊挂 环务必有足够孔径和强度， 在二条钢丝绳拉动时能顺利滑动， 以便后续救 援时替换钢缆后能吊起对应航行器机体部分。
电源模块对应音像信息模块、 定位呼叫模块及发光信号模块一一设置 有供电单元。
由此当膜盒于紧急状态弹射离开机体后， 若在空中时， 会在其预充低 密度气体的作用下迅速膨胀， 并在辅助降落伞帮助下漂浮于空中， 若是落 入水中， 膜盒能长时间漂浮水面， 并有牵引钢缆与机体保持连接， 在牵引 模块的释放阻尼单元作用下逐渐拉大与机体距离， 同时其内置音像摄录模 块的视频单元的视角从近到远会摄录下全过程， 而定位呼叫模块获取对应 位置的方位信息， 同时发出呼救信号。
合理配置本发明航行器紧急状态信息系统的航行器后， 可在紧急状态 发生时（如事故或迫降）， 不仅可留下原有航行器黑匣子中机身运行内部数 据， 还可得到当时机体环境数据参数， 并对外主动呼叫发出救援。
对于如何合理配置， 此处以飞机应用为例， 加以说明：
1、 首先根据飞机的机型大小， 可设计安装一套或多套本发明紧急状态 信息系统。 小型飞机可安装一套在驾驶舱顶部附近； 而大型飞机则可选择 安装四套， 分别于两机翼、 驾驶舱顶部附近、 后机身适当部位。
2、 紧急状态信息系统的牵引模块中牵引钢缆的两根钢丝绳穿过连接机 体主梁吊挂环， 吊挂环务必有足够孔径和强度， 在二条钢丝绳拉动时能顺 利滑动， 在替换钢缆后能吊起机体。
3、 释放弹射模块的控制器（电动释放按钮和机械释放扳手）应安装在 控制人员操控最方便处， 机体供电正常时可用电动释放按钮， 否则用机械 释放扳手。 联动的释放按钮和释放扳手确保其可靠性。
4、 在飞机上安装固定本产品后， 由可升空漂浮模块膜盒顶部的充气阀 按设计参数充入高压力低密度的气体（如氢气或氦气）， 压力检测由气阀旁 的压力表指示。 保证在释放弹射模块的限位机构释放后， 膜盒能迅速膨胀 到设定体积， 在辅助降落伞的共同作用下， 渐渐离开飞机悬浮在机体外。
当飞机危急状态时， 飞行员按压释放按钮或机械释放扳手 （机体供电 正常时可用电动释放按钮， 否则用机械释放扳手）释放可升空漂浮模块膜 盒； 若飞机瞬间爆炸， 可升空漂浮模块膜盒由于释放弹射模块操控钢缆的 应力拉动也可自动释放。 释放弹射模块将信息仪上盖板弹出机体， 膜盒限 压解除， 其内置音像信息模块、 定位呼叫模块启动； 膜盒迅速膨胀， 在气 流和辅助降落伞作用下， 离开飞机， 在牵引系统作用下， 与机体距离逐渐 增大（膜盒与飞机依然由钢丝绳连接）， 音像摄录系统视角从近到远摄录全 过程。 同时发出呼救信号和航行器方位信息。 地面指挥系统接收到 GPS定 位、 呼救信号后随即启动搜救； 有 GPS 导航， 有膜盒顶部灯光信号， 膜盒 的识别色标， 不管在夜间或白天， 都将速度找到目标。 假如飞机坠入海中， 应用钢绳替换绞盘 （车）。 通过连接膜盒与机体的钢丝绳， 从小到大逐步迅 速替换钢缆， 以便吊起机体， 进行辅助施救。 此外， 事后在收集到本产品 后， 通过对其内置设备记录的环境数据资料分析， 可了解飞机紧急状态机 体外的全过程。 此外， 若将本装置牵引与飞机原先 "黑匣子" 相连， 可进 一步增强黑匣子的回收率， 获取紧急状态飞机机体内的资料。
此外， 考虑到系统配套：
1、 全系统按照国际惯例设计信号源， 配套接收设备。
2、 钢绳替换绞盘 （车）。 用于通过连接膜盒与机体的钢绳， 从小到大 迅速替换钢缆， 以便吊起机体。
综上所述， 本发明通过应用预充低密度高压气体的升空漂浮模块的膜 盒主体， 在释放弹射模块的控制下在紧急状态时释放， 膜盒在内部高压低 密度气体作用下膨胀并悬浮于空气中， 在牵引模块的作用下保持与航行器 机体阶段性的适当距离， 同时其设置的音像信息模块、 定位呼叫模块、 发 光信号模块开始工作， 对系统周围的环境状态信息进行收集， 同时通过定 位呼叫系统发出方位信息呼救信号， 而发光信号模块则提供亮光图文标识， 大大方便搜寻救援工作的即时有效开展。

Claims

杈利要求书
1、 一种航行器紧急状态信息系统， 其特征在于： 它包括相连的可升空 漂浮模块、 释放弹射模块及牵引模块， 其中
可升空漂浮模块， 用于航天器发生紧急状态时脱离机体， 为搜索救援 提供便利及数据支持， 其内安装用于实时检测并记录外部周围环境信息的 音像信息模块、 用于检测并记录所在地理位置， 并对控制中心发出呼叫求 救信号的定位呼叫模块以及用于满足全系统提供基本用电需求的电源模 块； 一旦可升空漂浮模块脱离机体其即会同时启动其内音像信息模块及定 位呼叫模块记录所处外部环境状态信息；
释放弹射模块， 安装于航行器机体及可升空漂浮模块之间， 电动和手 动或自动控制启动， 用于在必要时将相连的可升空漂浮模块释放弹射至航 行器机体外；
牵引模块， 用于连接航行器及可升空漂浮模块， 确保可升空漂浮模块 不会丟失并与航行器保持一定距离进行外部环境数据的收集及求救信号的 发送。
2、 如权利要求 1所述的航行器紧急状态信息系统， 其特征在于： 所述 音像信息模块包括视频及音频设备， 用于记录外部环境的音频、 视频状况 λ- 自
1口 Ά、。
3、 如权利要求 1所述的航行器紧急状态信息系统， 其特征在于： 所述 可升空漂浮模块包括可进行伸缩变化的密闭膜盒单元， 膜盒中充有可使其 自动膨胀并产生漂浮升力的高压低密度气体并设有辅助降落伞。
4、 如权利要求 1所述的航行器紧急状态信息系统， 其特征在于： 所述 牵引模块包括牵引缆绳及释放阻尼单元， 牵引缆绳与航行器及可升空漂浮 模块相连， 而释放阻尼单元用于控制牵引缆绳的释放速度。
5、 如权利要求 1所述的航行器紧急状态信息系统， 其特征在于： 所述 电源模块对应音像信息模块、 定位呼叫模块及发光信号模块一一设置有供 电单元。
6、 如权利要求 1所述的航行器紧急状态信息系统， 其特征在于： 所述 释放弹射模块包括限位单元及弹射单元， 限位单元用于限制可升空漂浮模 块在未释放时的体积压缩， 而弹射单元用于释放可升空漂浮模块并将其弹 射出航行器外。
7、 如权利要求 1所述的航行器紧急状态信息系统， 其特征在于： 所述 可升空漂浮模块上设有发光信号模块， 它包括主动发光单元及识别图文色 标， 用于提供显著亮光图文信号， 为救援搜索提供便利。
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