WO2013056626A1 - 一种飞机燃油放沉淀工具 - Google Patents
一种飞机燃油放沉淀工具 Download PDFInfo
- Publication number
- WO2013056626A1 WO2013056626A1 PCT/CN2012/082672 CN2012082672W WO2013056626A1 WO 2013056626 A1 WO2013056626 A1 WO 2013056626A1 CN 2012082672 W CN2012082672 W CN 2012082672W WO 2013056626 A1 WO2013056626 A1 WO 2013056626A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- tool
- tool according
- opening
- spring
- aircraft
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/28—Liquid-handling installations specially adapted for fuelling stationary aircraft
Definitions
- This invention relates to an aircraft fuel discharge sedimentation tool and, more particularly, to an apparatus for opening and continuous fuel discharge of an aircraft fuel discharge valve inside a right and left wing rectification drum. Background technique
- the general ground staff will first open the maintenance port cover at the right and left wing rectification drums, enter the rectification drum package, and then manually lift the fuel discharge sedimentation tool and open the fuel discharge sedimentation valve. , for fuel discharge precipitation operation.
- the prior art fuel deposition and deposition tool requires the ground crew to carry out the lifting for a long time, and the lifting operation is very inconvenient considering the narrow space inside the aircraft wing bulge.
- the interior of the aircraft wing bulge is very dark, it is difficult for the ground crew to align the valve opening device of the sedimentation tool with the fuel discharge valve. This will cause the position of the aircraft to deposit the valve and the precipitation tool. The position is staggered, which will damage the sedimentation valve and cause fuel deposits to leak.
- the object of the present invention is to provide an aircraft fuel depositing and precipitating tool which does not require a ground crew to carry out lifting for a long time during operation, and is easy and labor-saving to operate.
- the present invention provides an aircraft fuel discharge sedimentation tool for opening an aircraft fuel discharge valve in an aircraft wing rectifying drum and discharging the sediment in the fuel tank, including:
- bracket body the upper portion of which is used for connecting a holding cup, and the top of the bracket body is provided with an opening Opening the head, the opening head can open the valve core of the aircraft fuel discharge valve, and the lower part is threaded for mounting the support spring and the support plate;
- a support plate mounted on a frame inside the aircraft wing bulge, and connected to the bracket body through an elastic support portion, the elastic support portion including a support spring, the support spring capable of providing an upward support elastic force,
- the supporting elastic force is equal to the downward elastic force of the aircraft fuel discharge valve spool to be opened and the total gravity of the tool above the elastic support portion, and the rigidity of the support spring is equivalent to the spring stiffness of the aircraft fuel discharge valve spool.
- the tool can be fixed inside the aircraft wing rectifying bulge through the support plate, it is not required to be held by the ground crew during the sedimentation process.
- the stiffness of the support spring is equivalent to the spring stiffness of the aircraft fuel discharge valve spool, when there is no sediment in the holding cup, the head is opened.
- the gravity of the holding cup gradually increases, and the supporting spring is gradually pressed down, whereby the entire rod drives its opening head to gradually move downward, and the spool is completely opened to partially open until closed. Adjusting the opening of the spool reduces the flow of discharge, thereby preventing fuel from escaping from the oil cup.
- the opening device includes an opening cutter head, the front portion of the opening cutter head is a screwdriver head, the middle portion is a connecting rod and a circular tail post, and the circular tail post is further provided with a knife holder spring, the tool holder One end of the spring is in contact with the bottom of the connecting rod, and the other end is in contact with the hole at the top of the bracket body.
- the side of the connecting rod is provided with a sliding slot, and the end of the fastening screw screwed on the telescopic rod is pressed on the sliding slot, so that the torque can be transmitted, and the opening cutter head can be defined in the hole at the top of the bracket body. And can adjust the opening height of the cutter head up and down.
- the shape of the screwdriver head of the opening cutter head may correspond to the shape of the aircraft fuel discharge valve spool to be opened, for example, the shape of the cutter head may be a shape of a figure, a hexagon or a cross.
- the holding cup is made of a transparent material in order to enable the operator to more intuitively perceive the sediment capacity of the containing cup.
- the tool has a light source that illuminates the working environment in a dark environment for easy viewing of oil drains.
- the light source is attached to the bracket body below the outside of the holding cup, which is capable of illuminating the contents of the holding cup and opening head portion.
- the light source can be a miniature explosion-proof flashlight that can be coupled to the stent rod by a clamp of insulating material.
- the light source includes a switch, a bulb, and a power source that can be disposed inside the bracket body, and the bracket body is provided with a control switch.
- the material of the holding cup on the bracket body is made of a transparent material.
- the light bulb of the light source may be an LED light
- the cutter head is made of a transparent light guiding material, and the illumination light of the LED light may be directly led to the valve core through the hole in the middle of the rod body to illuminate the valve core.
- the power supply can be a button battery or a 7-cell battery loaded from the bottom of the bracket body.
- the light source can be mounted as a unitary module.
- a grounding wire is connected to the grounding end of the bracket body to prevent sparks caused by static electricity.
- a discharge port may be provided in the tool.
- a discharge port is opened at the bottom of the holding cup, and the discharge port communicates with the oil guiding hose.
- the receiving cup can also discharge the sediment through the oil guiding hose to the iron or other large capacity receiving device outside the wing bulge while receiving the sediment.
- the support spring due to the action of the support spring, when the sedimentation flow rate in the discharge valve is higher than the discharge rate of the containing cup, the support spring is depressed, so that the spool will change from fully open to partially open, and the outflow rate will also decrease.
- the reading discharge port may also be disposed on the rod body.
- at least a portion of the rod body has a hollow shape, and is opened on a side wall of a portion of the rod extending into the holding cup.
- the introduction port is capable of introducing the sediment I in the holding cup into the hollow portion of the rod body, and a discharge port is opened at a portion of the rod body outside the holding cup, and the discharge port is hollow through the oil guiding oil connected thereto, and is hollow The precipitate in the part is discharged.
- the holding cup may further be provided with a rubber eraser, and the reading rubber holder is made of a soft rubber member, and is capable of fitting with the aircraft skin around the aircraft fuel discharge valve.
- a spacer is disposed at a position where the elastic supporting portion is in contact with the supporting plate, and a spring adjusting nut is disposed at a joint of the elastic supporting portion and the bracket body, and the reading adjusting nut can adjust the pressing force of the supporting spring.
- a position adjustment nut is provided on the support plate at a position where the elastic support portion is in contact with the support plate, and the position adjustment nut is capable of adjusting the height of the tool in the vertical direction.
- a waist groove is formed on the support plate, and the elastic support portion is laterally movable in the waist groove to adjust the horizontal position of the rod.
- the tool of the present invention is fixed by the support plate, the hand lifting is no longer required during use, and the operation is labor-saving and simple. Further, since the support spring of the present invention simultaneously functions as a supporting tool and regulates the flow rate of the fuel discharge valve, the problem of sediment leakage is solved. In addition, since the tool can be provided with a light source, it is also convenient for the operator to observe the specific operation of the sediment in the dark aircraft wing bulge.
- Figure 1 is a schematic view of a first embodiment of the present invention
- Figure 2 is a schematic view of a second embodiment of the present invention.
- FIG. 3 is a schematic illustration of a cutter head assembly in accordance with an embodiment of the present invention. detailed description
- the aircraft fuel deposition and deposition tool of the present invention comprises:
- the cup 3 is used for containing the sediment discharged from the fuel injection valve of the aircraft.
- the containing cup is made of a transparent material, and a rubber tray 2 is arranged on the top, and the rubber sheet 2 is made of soft rubber.
- the opening head includes the opening head including a cutter head assembly 11, and the cutter head assembly 11 is composed of an opening cutter head 1, a fastening screw 6, and a holder spring 5, wherein the front portion of the opening cutter head 1 is a screwdriver head 21, the middle part is composed of a connecting rod 12 and a circular tail column 13, the opening cutter head 1 is inserted into the upper end hole of the bracket rod body 4, and the knife tail spring 5 is further sleeved on the circular tail column 13, the tool holder spring 5- The end is in contact with the bottom of the connecting rod 12, and the other end is in contact with the bracket body 4.
- the front part of the opening of the cutter head 1 is a screwdriver head 21, and the middle part is a joint ⁇ 1 12 .
- the side of the connecting rod 12 is provided with a sliding slot 121, and the end of the fastening screw 6 screwed on the bracket rod body 4 is pressed against the chute. 121.
- the front part of the opening cutter head 1 is a screwdriver head 21 which is a Phillips screwdriver head, and is used for opening the fuel discharge valve and the fixed oil release rod on the aircraft.
- the tool holder spring 5 is installed with a certain pre-tightening pressure and is balanced with the jacking force of the aircraft's sedimentation valve spool. The stiffness is also considerably larger than the spring of the aircraft's sedimentation valve spool. The tool holder spring 5 is used to adjust the front portion to the protruding height of the screwdriver head 21 and to have a certain cushioning effect.
- the inside of the holder body 4 has a hollow shape, and on its side wall extending into the portion 42 of the holding cup (3), an introduction port 43 is opened, which is capable of depositing the sediment in the cup 3.
- the material is introduced into the hollow portion of the bracket body 4, and a portion of the bracket body 4 outside the holding cup 3 is provided with a discharge port 44, and the discharge port 44 passes through the oil guiding hose 45 communicating therewith, and the sediment in the hollow portion is arranged. Go to the iron or other large-capacity container on the outside of the wing drum.
- bracket body 4 located outside the holding cup is connected with a vertically upward explosion-proof flashlight 7 through a clamp, and the light source of the explosion-proof flashlight 7 faces upwards, so as to illuminate the entire holding cup 3 and the opening position of the cutter head.
- An upward support elastic force is provided, the support elastic force being equal to the sum of the above partial gravity, and the rigidity of the support spring 9 is equivalent to the spring stiffness of the aircraft fuel discharge valve spool.
- the support spring force of the support spring 9 needs to be adjusted correspondingly for different spool spring forces. As shown in FIG.
- a gasket 16 is disposed at a position where the elastic supporting portion is in contact with the support plate 10
- a spring adjusting nut 8 is disposed at a joint of the elastic supporting portion and the bracket body 4 , and the adjusting nut 8 can adjust the supporting spring.
- the pressing force since the pressing force is equal to the upward supporting elastic force of the supporting spring 9, adjusts the supporting elastic force by adjusting the pressing force.
- the elastic support portion is in contact with the support plate 10 on the support plate 10, and is provided with a position adjusting nut 14, which is capable of adjusting the height of the tool in the vertical direction.
- a waist groove is formed in the support plate 10, and the elastic support portion is laterally movable in the waist groove to adjust the horizontal lateral and longitudinal positions of the bracket body 4.
- the bracket body 4 extends into the receiving cup 3 and the opening bit 1 is made of a transparent material, and an LED light source is disposed in the hollow of the bracket body 4.
- the deposition valve spool and the holding cup (3) can be illuminated by the light guiding action of 51.
- the support rod body 4 has a power supply, and the support rod body 4 is provided with a control switch. The worker can see the liquid in the holding cup and the position of the sedimentation spool in the dark environment through the cup 3.
- a discharge port 50 is opened at the bottom of the containing cup 3, and the discharge port communicates with the oil guiding hose 53, and the sediment in the holding cup 3 is discharged to the wing through the oil guiding hose 53.
- the outer part of the drum is in a rail or large capacity container.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Harvester Elements (AREA)
Abstract
一种飞机燃油放沉淀工具，其用于在飞机机翼整流鼓包内打开飞机燃油放沉淀阀排放燃油箱内的沉淀，飞机燃油放沉淀工具包括：开启装置、照明装置、盛放杯、杆体和支撑板等。由于本发明的工具通过支撑板固定，所以在使用过程中不再需要人手托举，操作省力简便。并且，工具中带有支撑板和支撑弹簧，利用工具盛放杯内液体的重量变化与和支撑弹簧力的平衡，自动调节燃油放沉淀阀流量的功能，从而避免燃油的溢出。
Description
一种飞机燃油放沉淀工具 技术领域
本发明涉及一种飞机燃油放沉淀工具， 更特别地， 涉及一种在左右 机翼整流鼓包内部用于飞机燃油放沉淀阀的开启和可连续燃油放沉淀 的装置。 背景技术
通常，在飞机上设有多个放沉淀阀，分别在机翼下和整流鼓包内部， 地勤维护时需要打开放沉淀阀 , 进行放沉淀油的工作。
对于在飞机机翼整流鼓包内部的放沉淀阀，一般地勤人员会首先打 开左右机翼整流鼓包处的维护口盖， 进入到整流鼓包内部， 然后人手托 举燃油放沉淀工具并打开燃油放沉淀阀 , 以进行燃油放沉淀操作。
由此可见，现有技术的燃油放沉淀工具需要地勤人员长时间进行托 举， 考虑到飞机机翼鼓包内部空间狭小， 这样的托举操作十分不便。 另 夕卜， 由于飞机机翼鼓包内部十分黑暗， 这就使得地勤人员很难就将放沉 淀工具的阀门开启装置对准燃油放沉淀阀，这就会造成飞机放沉淀阀的 位置与沉淀工具在位置上有所错开， 这既会损坏放沉淀阀， 也容易造成 燃油沉淀物泄漏。 发明内容
本发明的目的在于提供一种飞机燃油放沉淀工具，其在操作中不需 要地勤人员长时间托举， 操作简便省力。
为实现上述目的， 本发明提供一种飞机燃油放沉淀工具， 其用于在 飞机机翼整流鼓包内打开飞机燃油放沉淀阀， 并排放燃油箱内的沉淀， 包括：
盛放杯， 其用于盛放飞机燃油放沉淀阀中放出的沉淀物；
支架杆体， 其上部用于连接盛放杯， 所述支架杆体的顶部设置有开
启头部， 该开启头部能够开启飞机燃油的放沉淀阀的阀芯， 下部带有螺 紋用于安装支撑弹簧和支撑板等；
支撑板， 所述支撑板安装在所述飞机机翼鼓包内部的框架上， 并且 其通过弹性支撑部与支架杆体连接， 所述弹性支撑部包括支撑弹簧， 该 支撑弹簧能够提供向上的支撑弹力，所述支撑弹力等于需开启的飞机燃 油放沉淀阀阀芯的向下弹力和所述工具在弹性支撑部以上部分重力的 总和， 支撑弹簧的刚度与飞机燃油放沉淀阀阀芯的弹簧刚度相当。
所述工具由于能够通过支撑板固定在所述飞机机翼整流鼓包内部， 所以在放沉淀过程中无需地勤人员手持。 另外， 由于支撑弹簧的弹力等 部以上部分重力的总和，并且支撑弹簧的刚度与所述飞机燃油放沉淀阀 阀芯的弹簧刚度相当， 所以当盛放杯中没有沉淀物时， 开启头部在支撑 不断流入盛放杯， 盛放杯的重力逐渐增加， 支撑弹簧被逐渐下压， 由此 整个杆体带动其开启头部逐渐向下移动， 而阀芯由完全打开转变为部分 打开直至关闭， 从而调节阀芯的开度降低排放的流量， 从而防止燃油从 盛油杯中溢出。
特别地， 所述开启装置包括开启刀头， 该开启刀头前部为螺丝刀头 部， 中部为连杆和圓形尾柱， 圆形尾柱上还套设有刀架弹簧， 所述刀架 弹簧一端与所述连杆的底部接触， 另一端与所述支架^ Γ体的顶部的孔接 触。连杆的侧部开设有滑槽，旋在伸缩杆上的紧固螺钉端部压在滑槽上， 这样可以在传递力矩的同时，还可以使开启刀头限定在支架杆体顶部的 孔内， 并能上下活动调节开启刀头的伸出高度。
更优选地，所述开启刀头的螺丝刀头部的形状可以与需开启的飞机 燃油放沉淀阀阀芯的形状对应， 例如， 该刀头的形状可以是一字形、 六 角形或十字形。
在本发明的另一个实施例中，为了能使得操作人员更直观地察觉到 所述盛放杯的沉淀物容量， 所述盛放杯由透明材料制成。
优选地， 考虑到飞机机翼整流鼓包中比较黑暗， 所以在所述工具上
还设置有光源。工具带有光源后可以在黑暗的环境中照亮工作环境便于 观测放油情况。
在本发明的一个实施例中， 该光源被连接在支架杆体上， 位于盛放 杯外的下方， 其能够照亮所述盛放杯和开启头部分位置。 特别地， 光源 可以是微型防爆手电筒， 其能够通过绝缘材料的夹具与支架杆体连接。
此外， 在本发明的另一个实施例中， 光源包括开关、 灯泡和电源可 设置在支架杆体内部， 支架杆体上设有控制的开关。 在该实施例中， 支 架杆体上的盛放杯的材料为透明材料制成。 优选地， 该光源的灯泡可以 是 LED灯， 刀头为透明导光材料制成， LED灯的照射光线可直接通过 杆体中间的孔引到阀芯上照亮阀芯。 电源可以为钮扣电池或者 7号电池 从支架杆体底部装入。 光源可作成一体式模块的结构装入。
支架杆体底部接有接地线与地面接地端连接，以防止因静电产生的 火花。
为了进一步简化飞机燃油放沉淀操作，可以在所述工具中设置有排 出口。 在本发明的一个实施例中， 在所述盛放杯的底部开设有排出口， 并且该排出口连通导油软管。 通过这样的设置， 盛放杯在接收沉淀物的 同时，也能通过导油软管将沉淀物排出到机翼鼓包外的铁通或其它大容 量容纳装置中。 另外， 由于支撑弹簧的作用， 当放沉淀阀中沉淀物流出 速率大于盛放杯排出速率时， 该支撑弹簧会被下压， 从而阀芯会从完全 打开转变为部分打开， 流出速率也会降低， 反之， 当沉淀物流出速率小 于排出速率时， 由于盛放杯的盾量变轻， 支撑弹簧又会逐渐复位到原来 位置， 阀芯又从部分打开转变为完全打开。 由此可见，在上述实施例中， 即保证了沉淀物不会从盛放杯中泄漏到外部， 又保证了阀芯放沉淀的速 率， 并且完全不要操作人员手动操作。
在本发明的另一实施例中， 读排出口也可以设置在杆体上， 在该实 施例中， 杆体内的至少一部分为中空形状， 在其伸入盛放杯的部分的侧 壁上开设有引入口，该引入口能够将盛放杯中的沉淀物 I入杆体内的中 空部分， 在杆体位于盛放杯外的部分开设有排出口， 该排出口通过与其 连通的导油软， 将中空部分内的沉淀物排出。
另外， 优选地， 盛放杯上还可以设置有一圏橡皮托， 读橡皮托由软 质橡胶件制成， 能够与所述飞机燃油放沉淀阀周围的飞机蒙皮贴合。
优选地， 在弹性支撑部与支撑板接触处设置有垫片， 在弹性支撑部 与支架杆体连接处设置有弹簧调节螺母 ,读调节螺母能够调节所述支撑 弹簧的压紧力。
优选地，在支撑板上位于所述弹性支撑部与支撑板接触位置设置有 位置调节螺母， 所述位置调节螺母能够调节所述工具在竖直方向的高 度。
优选地， 在所述支撑板上开设有腰形槽， 所述弹性支撑部能在所述 腰形槽中横向移动， 从而调节所述杆体的水平位置。
由于本发明的工具通过支撑板固定，所以在使用过程中不再需要人 手托举， 操作省力简便。 此外， 由于本发明的支撑弹簧同时起到支撑工 具和调节燃油放沉淀阀流量的作用， 所以解决了沉淀物泄漏的问题。 另 夕卜， 由于在该工具可以设置有光源， 也便于操作人员在黑暗的飞机机翼 鼓包中观察放沉淀的具体操作情况。 附图说明
图 1是本发明第一实施例的示意图；
图 2是本发明第二实施例的示意图；
图 3是本发明实施例中刀头组件的示意图。 具体实施方式
如图 1所示， 本发明的飞机燃油放沉淀工具包括：
盛放杯 3， 其用于盛放飞机燃油放沉淀阀中放出的沉淀物， 该盛放 杯由透明材料制成， 并且在顶部设置有橡皮托 2， 谊橡皮托 2由软质的 像胶件制成， 其能与放沉淀阀周围的飞机蒙皮贴合， 即可以防止燃油的 外溢又能够给工具提供支撑；
支架杆体 4, 支架杆体 4前部带有螺纹， 其穿过所述盛放杯 3的底 部，并且用圆螺母固定盛放杯 3 ,所述支架杆体 4的顶部开孔设置有开
启头部。 所述开启头部包括所述开启头部包括刀头组件 11 , 刀头组件 11由开启刀头 1 , 紧固螺钉 6， 刀架弹簧 5组成， 其中开启刀头 1的前 部为螺丝刀头部 21 , 中部为连杆 12和圆形尾柱 13组成，所述开启刀头 1插入支架杆体 4的上端孔内， 在圆形尾柱 13上还套有刀架弹簧 5， 刀 架弹簧 5—端与所述连杆 12的底部接触， 另一端与支架杆体 4接触。 开启刀头 1的前部为螺丝刀头部 21 , 中部为连^ 1 12, 连杆 12的侧部开 设有滑槽 121 ,旋在支架杆体 4上的紧固螺釘 6的端部压在滑槽 121上。 这样可以在传递力矩的同时，还可以使由开启刀头 1限定在支架杆体 4, 并能上下活动调节开启刀头 1的伸出高度。所述开启刀头 1的前部为螺 丝刀头部 21 为十字螺丝刀头， 其用于开启飞机上的燃油放沉淀阀和固 定放油杆的作用。
刀架弹簧 5安装时带一定的预紧压力，且与飞机放沉淀阀阀芯的顶 起力大小平衡。 刚度也与飞机放沉淀阀阀芯的弹簧相当略大。 该刀架弹 簧 5用于调节所述前部为螺丝刀头部 21的伸出高度和有一定的緩冲作 用。
在该实施例中， 支架杆体 4内为中空形状， 在其伸入盛放杯（ 3 ) 的部分 42的侧壁上开设有引入口 43 ,该引入口 43能够将盛放杯 3中的 沉淀物引入支架杆体 4内的中空部分，在支架杆体 4位于盛放杯 3外的 部分开设有排出口 44, 该排出口 44通过与其连通的导油软管 45, 将中 空部分内的沉淀物排到机翼鼓包外部的铁通或其它大容量的容器中。
另外，所述支架杆体 4位于盛放杯外的部分通过夹具连接有一个竖 直向上的防爆手电筒 7, 该防爆手电筒 7的光源朝上， 这样可以照亮整 个盛放杯 3以及刀头开启位置部分 11 ;
支撑板 10, 该支撑板 10架设在所述飞机机翼鼓包内部的框架上， 并且其通过弹性支撑部与所述支架杆体 4连接，所述弹性支撑部包括支 撑弹簧 9， 读支撑弹簧 9能够提供向上的支撑弹力， 所述支撑弹力等于 以上部分重力的总和，所述支撑弹簧 9的刚度与所述飞机燃油放沉淀阀 阀芯的弹簧刚度相当。
针对不同的阀芯弹力需要相应地调整支撑弹簧 9的支撑弹力。如图 1所示， 在弹性支撑部与支撑板 10接触处设置有垫片 16, 在弹性支撑 部与支架杆体 4连接处设置有弹簧调节螺母 8, 该调节螺母 8能够调节 所述支撑弹簧的压紧力， 由于该压紧力等于支撑弹簧 9 的向上支撑弹 力， 所以通过调节压紧力来实现对支撑弹力的调节。
此外，还可以对工具的垂直位置和水平位置进行调节。如图 1所示， 在支撑板 10上位于所述弹性支撑部与支撑板 10接触，设置有位置调节 螺母 14, 所述位置调节螺母 14能够调节所述工具在竖直方向的高度。 另外， 在所述支撑板 10上开设有腰形槽， 所述弹性支撑部能在所述腰 形槽中横向移动， 从而调节所述支架杆体 4的水平横向和纵向位置。
如图 2所示， 在本发明的第二实施例中， 支架杆体 4伸入所述盛放 杯 3和开启刀头 1 是透明材料制构成， 并在支架杆体 4中空内设置有 LED灯光源，可以通过 51的导光作用照亮放沉淀阀阀芯和盛放杯（3 )。 支架杆体 4内带电源， 支架杆体 4上设有控制的开关。 工人在黑暗的环 境里透过盛放杯 3可以看到盛放杯内的液体和放沉淀阀芯位置。
并且， 如图 2所示， 在盛放杯 3的底部开设排出口 50, 该排出口 与导油软管 53连通，盛放杯 3中的沉淀物通过该导油软管 53排出到机 翼鼓包外部的铁通或大容量容器中。
本发明的技术内容及技术特点已揭示如上， 然而可以理解， 在本发 明的创作思想下, 本领域的技术人员可以对上述结构作各种变化和改 进， 但都属于本发明的保护范围。 上述实施例的描述是例示性的而不是 限制性的， 本发明的保护范围由权利要求所确定。
Claims
1. 一种飞机燃油放沉淀工具， 其用于在飞机机翼整流鼓包内打开 飞机燃油放沉淀阀， 并排放燃油箱内的沉淀， 其特征在于,包括：
盛放杯（3) , 其用于盛放飞机燃油放沉淀阀中放出的沉淀物； 支架杆体（4) ， 其上部用于连接盛放杯（3) , 所述支架杆体（4) 的顶部设置有开启头部， i玄开启头部能够开启飞机燃油的放沉淀阀的阀 芯， 下部带有螺紋用于安装支撑弹簧（9)和支撑板（10) ；
支撑板（ 10) ,所述支撑板安装在所述飞机机翼鼓包内部的框架上， 并且其通过弹性支撑部与支架杆体（4)连接， 所述弹性支撑部包括支 撑弹簧（9) , 该支撑弹簧（9)能够提供向上的支撑弹力， 所述支撑弹 力等于需开启的飞机燃油放沉淀阀阀芯的向下弹力和所述工具在弹性 支撑部以上部分重力的总和， 支撑弹簧（9) 的刚度与飞机燃油放沉淀 阀阀芯的弹簧刚度相当。
2. 如权利要求 1所述的工具， 其特征在于， 所述开启头部包括刀 头組件（11) ， 刀头组件（11) 由开启刀头 （1) , 紧固螺钉（6) , 刀 架弹簧（5)组成， 其中开启刀头 （1) 的前部为螺丝刀头部 （21) , 中 部为连杆（12) 和圆形尾柱（13)組成， 所述开启刀头 （1)插入支架 杆体（4) 的上端孔内， 在圆形尾柱（13)上还套有刀架弹簧（5) ， 刀 架弹簧（ 5 )一端与所述连杆 ( 12 )的底部接触， 另一端与支架杆体（ 4 ) 接触。
3. 如权利要求 2所述的工具， 其特征在于， 所述开启刀头 （1) 为 可更换的， 其前部形状与所需开启的飞机燃油放沉淀阀阀芯的形状对 应。
4. 如权利要求 2中所述的工具， 其特征在于， 开启刀头 （1) 的前 部为螺丝刀头部 （21) ， 中部为连杆（12) ， 连杆（12)的侧部开设有 滑槽（121) , 旋在支架杆体（4)上的紧固螺钉（6) 的端部压在滑槽 (121)上。
5. 如权利要求 1中所述的工具， 其特征在于， 所述盛放杯（3) 由 透明材料制成。 并且在所述工具中设置有照明光源， 该光源能照亮所述 盛放杯， 并透过盛放杯照亮放沉淀工具的开启位置部分。
6. 如权利要求 1所述的工具， 其特征在于， 在所述支架杆体（4) 位于盛放杯 ( 3 )外部下方连接有光源， 该光源能够照亮所述盛放杯（ 3 ) 和开启头位置部分。
7. 如权利要求 6所述的工具，其特征在于，所述光源为微型防爆手 电筒 (7) 。
8. 如权利要求 6中所述的工具， 其特征在于， 所述支架杆体（4) 内中空形状， 在其伸入所述盛放杯的部分（42)的侧壁上开设有引入口 (43) , 该引入口能够将所述盛放杯中的沉淀物引入所述杆体内的中空 部分。 在所述杆体位于所述盛放杯外的部分开设有排出口 （44) , 该排 出口 （45)通过与其连通的导油软管 （45) , 将所述中空部分内的沉淀 物 4非出。
9. 如权利要求 1所述的工具 ， 其特征在于， 所述支架杆体（4)上 方的盛放杯（3)是由透明材料制成， 并在支架杆体 (4) 内部设置有光 源和电源， 支架杆体（4)上设有控制的开关 （52) 。
10. 如权利要求 9所述的工具， 其特征在于， 所述光源为 LED灯 (15) 。
11.如权利要求 9中所述工具， 其特征在于， 所述刀头（51 )为透明 导光材料制成。
12. 如权利要求 9中所述的工具， 其特征在于， 在所述盛放杯 (3) 的底部开设有排出口 （50) ， 并且该排出口连通导油软管。
13. 如权利要求 1-12中任一项所述的工具， 其特征在于， 在所述盛 放杯 (3)上设置有一圈橡皮托（2) , 谚橡皮托由软质橡月史件制成， 能 够与所述飞机燃油放沉淀阀周围的飞机蒙皮贴合。
14. 如权利要求 1-13中任一项所述的工具， 其特征在于， 在所述弹 性支撑部与所述支撑板（10)接触处设置有垫片 （16) ， 在弹性支撑部 与所述支架杆体（ 4 )连接处设置有弹簧调节螺母（ 8 ) , i亥调节螺母（ 8 ) 能够调节所述支撑弹簧（9) 的压紧力。
15. 如权利要求 1-14中任一项所述的工具， 其特征在于， 所迷支撑 板上位于所述弹性支撑部与所述支撑板（ 10 )接触位置设置有位置调节 螺母（14) ， 所述位置调节螺母（14)能够调节所述工具在竖直方向的 高度。
16. 如权利要求 1-15中任一项所述的工具， 其特征在于， 所述支撑 板（ 10)上开设有腰形槽，所述弹性支撑部能在所述腰形槽中横向移动， 从而调节所述支架杆体（4) 的水平横向和纵向位置。
17. 如权利要求 1-16 中任一项所述的工具， 其特征在于， 所述工 具中带有接地线 （20) 与地面接地端连接。
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110315900.1 | 2011-10-18 | ||
| CN201110315900.1A CN102431654B (zh) | 2011-10-18 | 2011-10-18 | 一种飞机燃油放沉淀工具 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2013056626A1 true WO2013056626A1 (zh) | 2013-04-25 |
Family
ID=45980088
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/CN2012/082672 WO2013056626A1 (zh) | 2011-10-18 | 2012-10-10 | 一种飞机燃油放沉淀工具 |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN102431654B (zh) |
| WO (1) | WO2013056626A1 (zh) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3498613A1 (fr) * | 2017-12-18 | 2019-06-19 | Airbus Helicopters | Outil et procede de purge d'eau d'un reservoir de carburant |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102431654B (zh) * | 2011-10-18 | 2014-08-06 | 中国商用飞机有限责任公司 | 一种飞机燃油放沉淀工具 |
| CN104943869B (zh) * | 2015-06-23 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | 一种大型飞机下反机翼燃油系统通气箱余油排放系统 |
| CN107380465B (zh) * | 2017-07-13 | 2020-04-28 | 江西洪都航空工业集团有限责任公司 | 折叠式飞机起落架搭地线 |
| CN109110151B (zh) * | 2018-09-12 | 2020-06-19 | 徐州航空航天技术研究院有限公司 | 一种飞机燃油放沉淀工具 |
| CN113859557B (zh) * | 2021-09-24 | 2023-07-21 | 成都飞机工业（集团）有限责任公司 | 一种飞机空中受油管余油排放助力装置及其使用方法 |
| CN118049738B (zh) * | 2024-04-16 | 2024-06-14 | 深圳市天创达科技有限公司 | 一种基于中央空调温度流量调节用的控制系统 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4235264A (en) * | 1978-12-26 | 1980-11-25 | Rau John K | Apparatus and method for facilitating removal of transmission pans |
| US5878799A (en) * | 1997-09-15 | 1999-03-09 | The United States Of America As Represented By The Secretary Of The Navy | Pencil drain fixture for aircraft defueling |
| US20050081949A1 (en) * | 2003-10-21 | 2005-04-21 | Spokane Industries, Inc. | Aircraft defueling apparatus and method |
| CN102145748A (zh) * | 2010-01-28 | 2011-08-10 | 尤洛考普特公司 | 对储箱进行排泄的方法和装置以及储箱和飞行器 |
| CN102431654A (zh) * | 2011-10-18 | 2012-05-02 | 中国商用飞机有限责任公司 | 一种飞机燃油放沉淀工具 |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5546986A (en) * | 1995-02-07 | 1996-08-20 | Clark Technology Systems, Inc. | Leakproof dual action fluid transfer valve |
| US6125882A (en) * | 1998-12-16 | 2000-10-03 | Kong; Carl Cheung Tung | Fluid transfer system |
| US7171990B2 (en) * | 2005-05-10 | 2007-02-06 | Spokane Industries, Inc. | Contoured surface defueling fitting |
-
2011
- 2011-10-18 CN CN201110315900.1A patent/CN102431654B/zh active Active
-
2012
- 2012-10-10 WO PCT/CN2012/082672 patent/WO2013056626A1/zh active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4235264A (en) * | 1978-12-26 | 1980-11-25 | Rau John K | Apparatus and method for facilitating removal of transmission pans |
| US5878799A (en) * | 1997-09-15 | 1999-03-09 | The United States Of America As Represented By The Secretary Of The Navy | Pencil drain fixture for aircraft defueling |
| US20050081949A1 (en) * | 2003-10-21 | 2005-04-21 | Spokane Industries, Inc. | Aircraft defueling apparatus and method |
| CN102145748A (zh) * | 2010-01-28 | 2011-08-10 | 尤洛考普特公司 | 对储箱进行排泄的方法和装置以及储箱和飞行器 |
| CN102431654A (zh) * | 2011-10-18 | 2012-05-02 | 中国商用飞机有限责任公司 | 一种飞机燃油放沉淀工具 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3498613A1 (fr) * | 2017-12-18 | 2019-06-19 | Airbus Helicopters | Outil et procede de purge d'eau d'un reservoir de carburant |
| FR3075177A1 (fr) * | 2017-12-18 | 2019-06-21 | Airbus Helicopters | Outil et procede de purge d'eau d'un reservoir de carburant |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102431654A (zh) | 2012-05-02 |
| CN102431654B (zh) | 2014-08-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2013056626A1 (zh) | 一种飞机燃油放沉淀工具 | |
| US8394162B2 (en) | Dust collector | |
| CN203344029U (zh) | 军械野战抢修箱 | |
| CN208480215U (zh) | 一种高速贴片机的承料装置 | |
| CN104405016A (zh) | 自动冲水装置 | |
| CN204259593U (zh) | 自动喂食器 | |
| CN203878560U (zh) | 基层施工夯实机 | |
| CN205497604U (zh) | 一种可调式多功能开孔器 | |
| CN213302289U (zh) | 一种电能表线路板功能检测用夹持工装 | |
| CN201268429Y (zh) | 净水桶龙头 | |
| CN208268979U (zh) | 一种led应急照明灯 | |
| CN208838023U (zh) | 一种解剖学用专用解剖刀 | |
| KR101498084B1 (ko) | 정수기 | |
| CN215277432U (zh) | 一种化学实验操作台 | |
| CN205636794U (zh) | 具有自带照明功能的市政电缆井 | |
| CN205300385U (zh) | 一种集双截棍、强光手电和催泪瓦斯为一体的警用器械 | |
| CN205915694U (zh) | 一种提升式固定式化妆盒内胆安装机构 | |
| CN217682544U (zh) | 一种机械加工用气动装置 | |
| CN208774309U (zh) | 一种新型的财经用海绵印泥盒 | |
| CN205109937U (zh) | 一种可便捷调节倾倒速度的洒水装置 | |
| CN211087835U (zh) | 一种会计账展示板 | |
| CN217822957U (zh) | 新能源汽车电池拆解装置 | |
| CN203914536U (zh) | 多功能供水器 | |
| CN220967191U (zh) | 一种马桶盖的快速连接结构 | |
| CN205782183U (zh) | 一种双向照明电筒箱 |
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: 12842442 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: 12842442 Country of ref document: EP Kind code of ref document: A1 |