WO2015161648A1 - 一种基于航空副油箱系统的拉脱式电连接器 - Google Patents

一种基于航空副油箱系统的拉脱式电连接器 Download PDF

Info

Publication number
WO2015161648A1
WO2015161648A1 PCT/CN2014/092135 CN2014092135W WO2015161648A1 WO 2015161648 A1 WO2015161648 A1 WO 2015161648A1 CN 2014092135 W CN2014092135 W CN 2014092135W WO 2015161648 A1 WO2015161648 A1 WO 2015161648A1
Authority
WO
WIPO (PCT)
Prior art keywords
circumferential wall
housing
pull
fuel tank
electrical connector
Prior art date
Application number
PCT/CN2014/092135
Other languages
English (en)
French (fr)
Inventor
叶学俊
常新峰
徐继华
殷志根
李竹法
Original Assignee
泰兴市航联电连接器有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 泰兴市航联电连接器有限公司 filed Critical 泰兴市航联电连接器有限公司
Publication of WO2015161648A1 publication Critical patent/WO2015161648A1/zh

Links

Images

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
    • H01R13/633—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for disengagement only

Definitions

  • the invention relates to an electrical connector, in particular to a pull-off electrical connector based on an aviation auxiliary fuel tank system.
  • the sub-tank fuel system is one of the larger sub-systems in the aircraft, and it plays a vital role in flight distance and combat radius.
  • the traditional auxiliary fuel tank and its auxiliary electrical interface are generally made of stainless steel due to the stress intensity, and the self-weight and radar wave reflecting surface are large.
  • the auxiliary fuel tank is thrown away from most of the electric detonation separation technology, which is very harmful to the electrical interface and is not conducive to flight safety. Therefore, under the premise of meeting the harsh flight environment, new weight loss materials and safe and reliable electrical interface separation technology are urgently needed.
  • a threaded sleeve is disposed in a gap between a connector housing and a locking section of the locking sleeve, and the threaded sleeve is fixed to the connector housing.
  • the inner surface of the inner hole of the threaded sleeve is provided with an internal thread threadedly connected with the adapter connector, and the thread sleeve is provided with a U-shaped groove for dividing the front portion of the thread sleeve into a claw, and the locking portion of the locking sleeve
  • the inner hole wall is in close contact with the outer peripheral surface of the threaded sleeve for keeping the claw of the threaded sleeve in a close state, and the threaded sleeve is screwed with the adapter connector, when the connector needs to be separated from the adapter connector
  • the locking sleeve can be pulled back by the pulling rope, so that the locking sleeve releases the claw of the threaded sleeve, and under the action of the pulling force, the claw will open, so that the threaded sleeve is separated from the fitting connector, thereby making the connector Separated from the adapter connector.
  • the present invention provides a pull-off type electrical connector based on an aviation auxiliary fuel tank system which is simple in structure, stable in connection structure, and non-detachable from the connector portion.
  • a pull-off type electrical connector based on an aviation auxiliary fuel tank system comprising a head casing, a seat shell, a core assembly and a core assembly, wherein the core assembly and the core assembly are interfitted with each other and They are respectively disposed in the head housing and the seat housing, and one end of the head housing is correspondingly inserted with one end of the seat housing, and one end of the head housing is a connecting nut and a ferrule are sequentially sleeved on the outer circumferential wall facing the other end, and the ferrule and the connecting nut are connected by a horizontal hook structure, and a threaded inner sleeve is sleeved in the gap between the connecting nut and the head housing
  • the inner circumferential wall of the threaded inner sleeve is elastically pressed on the outer circumferential wall of the boss on the outer circumferential wall of the head shell by the inner circumferential wall of the connecting nut, and the outer circumferential wall
  • Constraint tightening thread inner sleeve inner circumferential wall inner threaded joint housing outer circumferential wall outer thread or loosening constraint is under the action of the boss as the fulcrum of the screw thread inner sleeve inner circumferential wall inner threaded seat disengages the outer wall of the outer casing outer thread
  • a clamp is arranged on the outer circumferential wall of the head casing in the other end direction of the boss, and the thread inner sleeve is axially restrained by the clamp and the boss; the outer circumferential wall of the other end of the head shell is sleeved with a wave shape
  • the two sides of the coiled ring are respectively abutted between the outer circumferential wall of the other end of the head casing and the connecting thread.
  • the ferrule is symmetrically connected to both ends of the stainless steel pulling rope, and the stainless steel pulling rope is partially sleeved with a plurality of heat shrinkable sleeves, and the heat shrinkable sleeve is provided with a Teflon layer and a hollow tube from the inside to the outside.
  • the other end of the seat shell is sealed and connected with a cable cover shell via an O-ring, and a shield cap and a shielding sleeve are sequentially arranged from the inside to the outside between the needle core assembly and the cable cover shell at the other end of the seat shell.
  • the other end of the head casing is sealed and connected with a cable cover shell via an O-ring, and a shielding cap and a shielding sleeve are sequentially arranged from the inside to the outside of the hole core assembly and the cable cover shell at the other end of the head casing.
  • the outer circumferential wall of the other end of the head casing is sleeved with a ratchet and a circular ratchet.
  • the opposite sides of the ratchet and the circular ratchet are respectively provided with intermeshing teeth, and the ratchet is connected to the head shell via a flat key.
  • the outer circumference of the circular spine is connected to the inner circumferential wall of the connecting nut via a flat key, and the two sides of the corrugated ring are respectively abutted between the side of the circular ratchet and the connecting thread.
  • the head housing, the seat housing, the coupling nut, the threaded inner sleeve, the ferrule, the cable cover housing, the ratchet and the circular spine are all composite structures.
  • the stainless steel pulling rope exerts the force to pull the connecting nut along the connecting direction of the electric connector through the hook structure, and the outer end of the connecting thread loosens the elasticity formed by the threaded inner sleeve with the boss as the fulcrum.
  • the outer end of the lever structure is restrained, and the internal thread of the threaded inner sleeve of the other end of the boss is disengaged from the external thread of the seat shell. Under the traction of the gravity of the auxiliary tank, the seat shell is quickly separated from the head casing, thereby dropping the auxiliary fuel tank.
  • the side teeth are anti-retracting, and the corrugated elastic recovery makes the connecting nut guide the flat key along the circular spine.
  • the nut re-constrains the outer end of the threaded inner sleeve with the boss as a fulcrum to achieve repeated use of the electrical connector.
  • Lightweight composite materials are used for each component of the electrical connector to ensure the strength, while the weight is significantly lower than that of the stainless steel material, the weight is reduced, and the radar wave reflection surface is also reduced, which is beneficial to flight weight reduction and improved stealth performance;
  • a shielding sleeve and a shielding cap are additionally designed inside the cover.
  • the shielding layer is directly crimped between the shielding sleeve and the shielding cap, and the number of shielding sleeves can be freely adjusted according to the thickness of the shielding layer, and the "point" contact is improved to "face” contact. , greatly enhances the electrical continuity of the outer casing and improves the anti-electromagnetic interference performance.
  • the invention adopts the connection of the elastic constraint head shell and the seat shell to realize rapid disengagement of the external auxiliary fuel tank and the main body, cooperates with the elastic reset electrical connector connecting mechanism and adopts composite material weight reduction and anti-electromagnetic interference design, and the overall structure is compact and stable.
  • the pull-off separation is safe and reliable and is suitable for the aviation auxiliary fuel tank fuel system.
  • Figure 1 is a schematic structural view of the present invention
  • Figure 2 is a partial enlarged view of the structure of the undrawn state of the present invention.
  • Fig. 3 is a partially enlarged view showing the structure of the pulled state of the present invention.
  • cable cover housing 1 shielding sleeve 2, shielding layer 3, O-ring 4, housing housing 5, core assembly 6, head housing 7, core assembly 8, boss 9, clamp 10, Threaded inner sleeve 11, connecting nut 12, corrugated ring 13, circular spine 14, ratchet 15, ferrule 16, stainless steel pull cord 17, heat shrink sleeve 18, hollow tube 19.
  • a pull-off type electrical connector based on an aviation auxiliary fuel tank system includes a cable cover housing 1, a shield sleeve 2, a shield layer 3, an O-ring 4, a seat housing 5, a core assembly 6, and a head shell.
  • the core assembly 8 and the core assembly 6 are inserted into each other and disposed in the head housing 7 and the seat housing 5 respectively.
  • One end of the head housing 7 is inserted into one end of the housing shell 5, and one end of the head housing 7 is turned to the other end.
  • a connecting nut 12 and a ferrule 16 are sequentially sleeved on the outer circumferential wall of the direction, and the ferrule 16 and the connecting nut 12 are connected by a horizontal hook structure, and a gap is formed in the gap between the connecting nut 12 and the head housing 7
  • the sleeve 11 has a central portion of the inner circumferential wall of the threaded inner sleeve 11 which is elastically pressed against the outer circumferential wall of the boss 9 on the outer circumferential wall of the head housing by the inner circumferential wall of the coupling nut, and the outer circumferential wall of the threaded inner sleeve is connected by the connecting screw
  • the female inner circumferential wall is radially elastically constrained to constrain the tightening thread inner sleeve inner circumferential wall inner threaded joint housing outer circumferential wall outer thread or loosening constraint is under the leverage of the boss as a fulcrum thread inner sleeve inner circumferential wall inner thread
  • the opposite sides of the ratchet and the circular ratchet are respectively provided with mutual engagement.
  • the tooth port and the ratchet wheel are connected to the head shell via a flat key, and the outer circumference of the circular ratchet is connected with the inner circumferential wall of the connecting nut via a flat key, and the two sides of the wave ring are respectively abutted against the side of the circular ratchet and the connecting thread.
  • Between the two sides of the ferrule 16 is symmetrically connected to the two ends of the stainless steel pulling rope 17, and the stainless steel pulling rope is partially sleeved with a plurality of heat shrinkable sleeves 18, and the heat shrinkable sleeve is provided with a Teflon layer and a hollow from the inside to the outside.
  • the cable cover shell 1 is provided with a shield cap 3 and a shield sleeve 2 from the inside to the outside between the cable cover shell and the electrical connector; the head shell, the seat shell, the connecting nut, the threaded inner sleeve, the hoop, and the cable
  • the cover housing, the ratchet and the circular spine are all composite structures.
  • the inner circumferential wall of the connecting nut elastically constrains the thread inner sleeve, and the inner end of the thread inner sleeve is commonly restrained by the clamp, the boss and the connecting nut to form an elastic lever with the boss as a fulcrum.
  • the internal thread of the threaded inner sleeve is connected with the external thread of the seat shell, and the electrical connector is normally connected.

Landscapes

  • Details Of Connecting Devices For Male And Female Coupling (AREA)

Abstract

一种基于航空副油箱系统的拉脱式电连接器，包括头壳体（7）、座壳体（5）、孔芯组件（6）和针芯组件（8），针芯组件（8）和孔芯组件（6）相互插合且分别设置于头壳体（7）和座壳体（5）内，头壳体（7）一端与座壳体（5）一端对应插接，采用弹性约束头壳体（7）和座壳体（5）的连接实现外挂副油箱和主机的迅速抛离，配合弹性复位电连接器连接机构和采用复合材料减重、抗电磁干扰设计，其整体结构紧凑、稳定，拉脱分离安全可靠，适用于航空副油箱燃油系统。

Description

一种基于航空副油箱系统的拉脱式电连接器 技术领域
本发明涉及一种电连接器，具体说是一种基于航空副油箱系统的拉脱式电连接器。
背景技术
现代航空技术日新月异，轻量化、抗电磁环境、隐形、飞行安全等成为当前航空技术发展的研究方向。副油箱燃油系统是航空器中自重较大的分系统之一，同时又对飞行距离和作战半径起着至关重要的作用。传统的副油箱及其附属电气接口，由于考虑到应力强度，一般都采用不锈钢材料，自重和雷达波反射面较大。另外，副油箱抛离大部分采用电起爆分离技术，这样对电气接口的损伤很大，也不利于飞行安全。因此，在满足恶劣飞行环境的前提下，亟待新的减重材料和安全可靠的电气接口分离技术。
在专利号为201120324140.6公开的一种解锁可靠的拉脱连接器中，在连接器壳体与锁紧套的锁紧用段之间的间隙内设置上螺纹套，螺纹套固定在连接器壳体上，螺纹套的内孔周面上设置有与适配连接器螺纹连接的内螺纹，螺纹套上设置有将螺纹套的前段分割成弹爪的U型槽，锁紧套的锁紧用段的内孔壁与螺纹套的外周面紧贴配合，用于保持螺纹套的弹爪处于收拢状志，螺纹套会与适配连接器螺纹连接，当需要将连接器与适配连接器分离时，可以通过拉绳向后拉锁紧套，使得锁紧套将螺纹套的弹爪释放，在拉力的作用下，弹爪会张开，使得螺纹套与适配连接器分离，进而使得连接器与适配连接器分离。这种形式的连接器虽然实现了电气接口的拉脱分离，但拉脱导致的锁紧套弹爪张开和螺纹套发生位移，无法复位，一次使用，适用范围小。
发明内容
针对上述电连接拉脱结构中的缺点，本发明提供了一种结构简单，连接结构稳定，非脱离连接器部分可重复使用的基于航空副油箱系统的拉脱式电连接器。
本发明采用的技术方案是：一种基于航空副油箱系统的拉脱式电连接器，包括头壳体、座壳体、孔芯组件和针芯组件，针芯组件和孔芯组件相互插合且分别设置于头壳体和座壳体内，头壳体一端与座壳体一端对应插接，所述头壳体一端 向另一端方向的外圆周壁上依次滑动套接有连接螺母和拉箍，拉箍与连接螺母经水平拉钩结构连接，所述连接螺母与头壳体之间的间隙内套接有螺纹内套，螺纹内套内圆周壁中部由连接螺母内圆周壁弹性压合于头壳体外圆周壁上的凸台外圆周壁上，螺纹内套的外圆周壁由连接螺母内圆周壁径向弹性约束呈约束收紧螺纹内套内圆周壁内螺纹连接座壳体外圆周壁外螺纹或松开约束呈在凸台为支点的杠杆作用下螺纹内套内圆周壁内螺纹座脱开壳体外圆周壁外螺纹连接状态，凸台另一端方向的头壳体外圆周壁上的设有卡箍，螺纹内套经卡箍和凸台轴向限位；所述头壳体另一端外圆周壁上套接有波形圈，波形圈的两侧分别抵紧限位于头壳体另一端外圆周壁与连接螺纹之间。
所述拉箍圆周上对称连接不锈钢拉绳两端，不锈钢拉绳上局部套接有多个热缩套管，热缩套管上由内向外依次设有铁氟龙层和空心管。
所述座壳体另一端经O形圈密封连接有电缆罩壳体，座壳体另一端的针芯组件与电缆罩壳体之间由内向外依次设有屏蔽帽和屏蔽套。
所述头壳体另一端经O形圈密封连接有电缆罩壳体，头壳体另一端的孔芯组件与电缆罩壳体之间由内向外依次设有屏蔽帽和屏蔽套。
所述头壳体另一端外圆周壁上套接有棘轮和圆形棘条，棘轮和圆形棘条的相对侧面上分别设有相互啮合的齿口，棘轮经平键连接于头壳体上，圆形棘条的外圆周与连接螺母内圆周壁经平键导向连接，所述波形圈的两侧分别抵紧于圆形棘条侧面与连接螺纹之间。
所述头壳体、座壳体、连接螺母、螺纹内套、拉箍、电缆罩壳体、棘轮和圆形棘条均为复合材料结构。
采用上述技术方案，本发明的优点是：
1、航空副油箱抛落命令下达后，由不锈钢拉绳施力通过拉钩结构拉动连接螺母沿电连接器插合方向后移，连接螺纹外端松开对螺纹内套以凸台为支点形成的弹性杠杆结构的外端的约束，凸台另一端的螺纹内套的内螺纹脱开与座壳体外螺纹的连接，在副油箱重力的牵引下，座壳体迅速与头壳体分离，从而抛落副油箱，自然重力拉脱，安全系数高，大大提高了副油箱系统分离作业的安全系数；在副油箱脱离完成后，卸去不锈钢拉绳作用力，由波形圈抵紧圆形棘条，圆形棘条由棘轮侧面齿合防退，波形圈弹性恢复使连接螺母沿圆形棘条的平键导向连接 螺母重新约束螺纹内套以凸台为支点形成的弹性杠杆结构的外端，以实现电连接器重复使用。
2、电连接器各组件采用轻型复合材料，保证强度的同时，重量较不锈钢材料明显降低，自重减轻，同时也减小了雷达波反射面，有利于飞行减重和提高隐身性能；在特制电缆罩内部追加设计了屏蔽套和屏蔽帽，屏蔽层直接压接在屏蔽套和屏蔽帽之间，并可根据屏蔽层厚度，自由调节屏蔽套数量，且由“点”接触改进为“面”接触，大大增强了外壳的电连续性，提高了抗电磁干扰性能。
本发明采用弹性约束头壳体和座壳体的连接实现外挂副油箱和主机的迅速抛离，配合弹性复位电连接器连接机构和采用复合材料减重、抗电磁干扰设计，其整体结构紧凑、稳定，拉脱分离安全可靠，适用于航空副油箱燃油系统。
附图说明
图1为本发明结构示意图；
图2为本发明未拉脱状态结构局部放大图；
图3为本发明拉脱状态结构局部放大图。
图中：电缆罩壳体1，屏蔽套2，屏蔽层3，O形圈4，座壳体5，孔芯组件6，头壳体7，针芯组件8，凸台9，卡箍10，螺纹内套11，连接螺母12，波形圈13，圆形棘条14，棘轮15，拉箍16，不锈钢拉绳17，热缩套管18，空心管19。
具体实施方式
以下结合附图和实施例对本发明作进一步描述。
图1所示，一种基于航空副油箱系统的拉脱式电连接器包括电缆罩壳体1、屏蔽套2、屏蔽层3、O形圈4、座壳体5、孔芯组件6、头壳体7、针芯组件8、卡箍10、螺纹内套11、连接螺母12、波形圈13、圆形棘条14、棘轮15、拉箍16、不锈钢拉绳17、热缩套管18和空心管19。针芯组件8和孔芯组件6相互插合且分别设置于头壳体7和座壳体5内，头壳体7一端与座壳体5一端对应插接，头壳体7一端向另一端方向的外圆周壁上依次滑动套接有连接螺母12和拉箍16，拉箍16与连接螺母12经水平拉钩结构连接，连接螺母12与头壳体7之间的间隙内套接有螺纹内套11，螺纹内套11内圆周壁中部由连接螺母内圆周壁弹性压合于头壳体外圆周壁上的凸台9外圆周壁上，螺纹内套的外圆周壁由连接螺 母内圆周壁径向弹性约束呈约束收紧螺纹内套内圆周壁内螺纹连接座壳体外圆周壁外螺纹或松开约束呈在凸台为支点的杠杆作用下螺纹内套内圆周壁内螺纹座脱开壳体外圆周壁外螺纹连接状态，凸台另一端方向的头壳体外圆周壁上的设有卡箍10，螺纹内套经卡箍和凸台轴向限位；头壳体7另一端外圆周壁上套接有波形圈13，头壳体7另一端外圆周壁上套接有棘轮15和圆形棘条14，棘轮和圆形棘条的相对侧面上分别设有相互啮合的齿口，棘轮经平键连接于头壳体上，圆形棘条的外圆周与连接螺母内圆周壁经平键导向连接，波形圈的两侧分别抵紧于圆形棘条侧面与连接螺纹之间；拉箍16圆周上对称连接不锈钢拉绳17两端，不锈钢拉绳上局部套接有多个热缩套管18，热缩套管上由内向外依次设有铁氟龙层和空心管19；头壳体7和座壳体5的非连接端经O形圈4密封连接有电缆罩壳体1，电缆罩壳体与电连接器之间由内向外依次设有屏蔽帽3和屏蔽套2；头壳体、座壳体、连接螺母、螺纹内套、拉箍、电缆罩壳体、棘轮和圆形棘条均为复合材料结构。
图2所示，副油箱未拉脱时，连接螺母的内圆周壁弹性约束螺纹内套，螺纹内套内端经卡箍、凸台与连接螺母共同限位，形成以凸台为支点的弹性杠杆结构，螺纹内套的内螺纹与座壳体的外螺纹连接，电连接器正常连接。
图3所示，副油箱拉脱时，连接螺母发生位移脱开对螺纹内套弹性杠杆结构未限位端的弹性约束，螺纹内套的内螺纹弹性张开松开与座壳体外螺纹的连接，电连接器在副油箱自重作用下可自动拉脱。

Claims (8)

  1. 一种基于航空副油箱系统的拉脱式电连接器，包括头壳体、座壳体、孔芯组件和针芯组件，针芯组件和孔芯组件相互插合且分别设置于头壳体和座壳体内，头壳体一端与座壳体一端对应插接，其特征在于：所述头壳体一端向另一端方向的外圆周壁上依次滑动套接有连接螺母和拉箍，拉箍与连接螺母经水平拉钩结构连接，所述连接螺母与头壳体之间的间隙内套接有螺纹内套，螺纹内套内圆周壁中部由连接螺母内圆周壁弹性压合于头壳体外圆周壁上的凸台外圆周壁上，螺纹内套的外圆周壁由连接螺母内圆周壁径向弹性约束呈收紧螺纹内套内圆周壁内螺纹连接座壳体外圆周壁外螺纹或松开约束呈在凸台为支点的杠杆作用下螺纹内套内圆周壁内螺纹座弹性脱开壳体外圆周壁外螺纹连接状态，凸台另一端方向的头壳体外圆周壁上的设有卡箍，螺纹内套经卡箍和凸台轴向限位；所述头壳体另一端外圆周壁上套接有波形圈，波形圈的两侧分别抵紧限位于头壳体另一端外圆周壁与连接螺纹之间。
  2. 根据权利要求1所述的一种基于航空副油箱系统的拉脱式电连接器，其特征是：所述拉箍圆周上对称连接不锈钢拉绳两端，不锈钢拉绳上局部套接有多个热缩套管，热缩套管上由内向外依次设有铁氟龙层和空心管。
  3. 根据权利要求1所述的一种基于航空副油箱系统的拉脱式电连接器，其特征是：所述座壳体另一端经O形圈密封连接有电缆罩壳体，座壳体另一端的针芯组件与电缆罩壳体之间由内向外依次设有屏蔽帽和屏蔽套。
  4. 根据权利要求1所述的一种基于航空副油箱系统的拉脱式电连接器，其特征是：所述头壳体另一端经O形圈密封连接有电缆罩壳体，头壳体另一端的孔芯组件与电缆罩壳体之间由内向外依次设有屏蔽帽和屏蔽套。
  5. 根据权利要求1所述的一种基于航空副油箱系统的拉脱式电连接器，其特征是：所述头壳体另一端外圆周壁上套接有棘轮和圆形棘条，棘轮和圆形棘条的相对侧面上分别设有相互啮合的齿口，棘轮经平键连接于头壳体上，圆形棘条的外圆周与连接螺母内圆周壁经平键导向连接，所述波形圈的两侧分别抵紧于圆形棘条侧面与连接螺纹之间。
  6. 根据权利要求1至5任一所述的一种基于航空副油箱系统的拉脱式电连接器，其特征是：所述头壳体、座壳体、连接螺母、拉箍和螺纹内套均为复 合材料壳体。
  7. 根据权利要求3或4所述的一种基于航空副油箱系统的拉脱式电连接器，其特征是：所述电缆罩壳体为复合材料壳体。
  8. 根据权利要求5所述的一种基于航空副油箱系统的拉脱式电连接器，其特征是：所述棘轮和圆形棘条均为复合材料结构。
PCT/CN2014/092135 2014-04-22 2014-11-25 一种基于航空副油箱系统的拉脱式电连接器 WO2015161648A1 (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201410162287.8A CN103928791B (zh) 2014-04-22 2014-04-22 一种基于航空副油箱系统的拉脱式电连接器
CN201410162287.8 2014-04-22

Publications (1)

Publication Number Publication Date
WO2015161648A1 true WO2015161648A1 (zh) 2015-10-29

Family

ID=51146920

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2014/092135 WO2015161648A1 (zh) 2014-04-22 2014-11-25 一种基于航空副油箱系统的拉脱式电连接器

Country Status (2)

Country Link
CN (1) CN103928791B (zh)
WO (1) WO2015161648A1 (zh)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106953191A (zh) * 2017-04-10 2017-07-14 沈阳兴华航空电器有限责任公司 一种拉脱式电连接器插头
CN107887753A (zh) * 2017-12-26 2018-04-06 国网河北省电力有限公司衡水供电分公司 一种航空接口防潮装置
CN108879569A (zh) * 2018-01-12 2018-11-23 珩星电子（连云港）股份有限公司 一种光电缆组件
CN110021855A (zh) * 2019-06-05 2019-07-16 上海传输线研究所（中国电子科技集团公司第二十三研究所） 一种拉线分离式机械机构
CN114156694A (zh) * 2021-10-29 2022-03-08 北京宇航系统工程研究所 一种提升容错能力的电气系统箭地接口设计方法
CN118472858A (zh) * 2024-07-12 2024-08-09 山东睿创能源电气有限公司 一种高压开关柜穿线装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103928791B (zh) * 2014-04-22 2015-12-23 泰兴市航联电连接器有限公司 一种基于航空副油箱系统的拉脱式电连接器
CN109309318B (zh) * 2017-07-27 2020-12-04 中航光电科技股份有限公司 一种脱落连接器及脱落连接器组件

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201859989U (zh) * 2010-10-27 2011-06-08 中航光电科技股份有限公司 一种拉绳脱落连接器
WO2012058039A1 (en) * 2010-10-27 2012-05-03 Corning Gilbert Inc. Push-on cable connector with a coupler and retention and release mechanism
CN202454807U (zh) * 2011-12-19 2012-09-26 中航光电科技股份有限公司 一种拉绳脱落连接器
CN103928791A (zh) * 2014-04-22 2014-07-16 泰兴市航联电连接器有限公司 一种基于航空副油箱系统的拉脱式电连接器
CN203895690U (zh) * 2014-04-22 2014-10-22 泰兴市航联电连接器有限公司 一种基于航空副油箱系统的拉脱式电连接器

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1153409A (zh) * 1995-08-09 1997-07-02 住友电装株式会社 连接器用锁定装置及其在充电连接器和/或高压电缆连接器中的应用
CN201985372U (zh) * 2010-12-15 2011-09-21 杭州航天电子技术有限公司 一种电连接器拉线分离机构
CN203339403U (zh) * 2013-05-15 2013-12-11 中航光电科技股份有限公司 分离脱落式电连接器组件
CN103515779A (zh) * 2013-09-05 2014-01-15 陕西益华电子有限责任公司 一种推拉锁紧电连接器

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201859989U (zh) * 2010-10-27 2011-06-08 中航光电科技股份有限公司 一种拉绳脱落连接器
WO2012058039A1 (en) * 2010-10-27 2012-05-03 Corning Gilbert Inc. Push-on cable connector with a coupler and retention and release mechanism
CN202454807U (zh) * 2011-12-19 2012-09-26 中航光电科技股份有限公司 一种拉绳脱落连接器
CN103928791A (zh) * 2014-04-22 2014-07-16 泰兴市航联电连接器有限公司 一种基于航空副油箱系统的拉脱式电连接器
CN203895690U (zh) * 2014-04-22 2014-10-22 泰兴市航联电连接器有限公司 一种基于航空副油箱系统的拉脱式电连接器

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106953191A (zh) * 2017-04-10 2017-07-14 沈阳兴华航空电器有限责任公司 一种拉脱式电连接器插头
CN106953191B (zh) * 2017-04-10 2023-03-10 沈阳兴华航空电器有限责任公司 一种拉脱式电连接器插头
CN107887753A (zh) * 2017-12-26 2018-04-06 国网河北省电力有限公司衡水供电分公司 一种航空接口防潮装置
CN108879569A (zh) * 2018-01-12 2018-11-23 珩星电子（连云港）股份有限公司 一种光电缆组件
CN108879569B (zh) * 2018-01-12 2023-09-29 珩星电子（连云港）股份有限公司 一种光电缆组件
CN110021855A (zh) * 2019-06-05 2019-07-16 上海传输线研究所（中国电子科技集团公司第二十三研究所） 一种拉线分离式机械机构
CN114156694A (zh) * 2021-10-29 2022-03-08 北京宇航系统工程研究所 一种提升容错能力的电气系统箭地接口设计方法
CN114156694B (zh) * 2021-10-29 2023-08-01 北京宇航系统工程研究所 一种提升容错能力的电气系统箭地接口设计方法
CN118472858A (zh) * 2024-07-12 2024-08-09 山东睿创能源电气有限公司 一种高压开关柜穿线装置

Also Published As

Publication number Publication date
CN103928791B (zh) 2015-12-23
CN103928791A (zh) 2014-07-16

Similar Documents

Publication Publication Date Title
WO2015161648A1 (zh) 一种基于航空副油箱系统的拉脱式电连接器
EP2316295A3 (en) Quick Release Buckle Assembly
CN204178298U (zh) 一种新型机箱托架锁紧机构
US20140377977A1 (en) Easy-pull male network connector
CN106877090A (zh) 一种受巨力时紧急分离的锁紧连接器
CN107044222B (zh) 一种用于电动汽车电子锁合装置的应急解锁拉绳离合机构
CN203895690U (zh) 一种基于航空副油箱系统的拉脱式电连接器
CN206369020U (zh) 一种自紧式风电用热缩连接胶管
CN105490242B (zh) 二次电缆线芯绝缘套头
CN104977434B (zh) 一种卡扣式接线插头及使用方法
CN204315801U (zh) 电力连接器
CN107839872B (zh) 一种线位移超控杆结构及其方法
CN207157503U (zh) 新型无人机脚架和包括该脚架的无人机
CN107017587B (zh) 一种护线软管接头
CN205790700U (zh) 一种头盔引线用拉脱电连接器
CN108306245A (zh) 一种通过密封接头实现电缆外屏蔽接壳的结构件
CN106394834A (zh) 潜水器用电缆脱开装置
CN204121645U (zh) 一种灭火器充装阀门
CN208885759U (zh) 一种结构内应力自释放紧固件
CN208570998U (zh) 一种充电座可快速更换插孔端子
CN207664313U (zh) 一种防爆航空插头座
CN208970761U (zh) 一种低压电线接头
CN203176191U (zh) 一种自锁转子联轴器
CN205944588U (zh) 一种防水型电连接器插头
CN202260368U (zh) 一种金属电缆防水接头

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 14890358

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 14890358

Country of ref document: EP

Kind code of ref document: A1