WO2021036388A1 - 一种民用航空器空速管自分离保护套 - Google Patents

一种民用航空器空速管自分离保护套 Download PDF

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Publication number
WO2021036388A1
WO2021036388A1 PCT/CN2020/094253 CN2020094253W WO2021036388A1 WO 2021036388 A1 WO2021036388 A1 WO 2021036388A1 CN 2020094253 W CN2020094253 W CN 2020094253W WO 2021036388 A1 WO2021036388 A1 WO 2021036388A1
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Prior art keywords
slot
tube
outer shell
groove
shell
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English (en)
French (fr)
Inventor
顾辉
韩熹路
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Shandong Taikoo Aircraft Engineering Co Ltd
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Shandong Taikoo Aircraft Engineering Co Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the invention relates to the technical field of aircraft protection devices, in particular to a self-separating protective cover for the airspeed tube of a civil aircraft.
  • the airspeed tube is also called a pitot tube, a total pressure tube, and a total-static pressure tube. It can feel the total pressure (also called the total pressure) and static pressure of the airflow, and transmit the measured pressure data to the air data computer and the flight instrument Device.
  • the airspeed tube needs to be heated, and the heating can prevent the probe from icing, so as to prevent icing from blocking the measuring hole and affecting the detection accuracy.
  • a drainage hole is provided in the airspeed pipe and a drainage joint is provided in the pipeline of the dynamic/static pressure system.
  • Airspeed tube protective sleeve is a ground protection device for airplane airspeed tube. During the parking period of the aircraft, putting a protective sleeve on the airspeed tube can prevent foreign objects from entering the airspeed tube, thereby avoiding the airspeed indication error caused by the entry of foreign objects.
  • the protective cover usually has a bright red ribbon printed with the words "REMOVE BEFORE FLIGHT" to remind the flight crew to take it off before the plane takes off.
  • the airspeed tube sleeves designed to prevent foreign objects from blocking the airspeed tube are often caused by the crew forgetting to remove the airspeed tube sleeves before flying, which is the main cause of the airspeed tube blockage.
  • the present invention provides a civil aircraft airspeed tube self-separating protective cover that can be separated during the take-off process of the airspeed tube protective cover once a worker forgets to remove the airspeed tube protective cover.
  • a self-separating protective cover for the airspeed tube of a civil aircraft comprising:
  • the outer shell is located at the outer end of the PTV tube, and is provided with a groove I with a semicircular cross section along the axial direction, and the inner diameter of the groove I matches the radius of the PTV tube;
  • the inner shell is located at the inner end of the PTV tube.
  • a groove III with a semicircular cross section is provided in the inner shell along the axial direction. The inner diameter of the groove III matches the radius of the PTV tube.
  • a baffle is provided at the front end, and the baffle is perpendicular to the inner shell;
  • the buckles are arranged at the upper and lower ends of the outer shell.
  • the upper and lower ends of the inner shell are correspondingly provided with grooves.
  • the outer shell is buckled into the grooves by the buckles, and the airspeed tube is inserted into the groove I and the groove. III
  • the front end of the pitot tube is in contact with the baffle; and
  • the separation device is arranged on the outer shell and the inner shell.
  • the take-off speed of the aircraft is greater than or equal to 200Km/h
  • the buckle of the outer shell is separated from the slot of the inner shell, and the outer shell and the inner shell are separated from the airspeed tube .
  • the above-mentioned separating device includes a wing plate I respectively arranged on the outer end of the outer shell and a wing plate II arranged on the inner shell.
  • the wing plate I and the wing plate II are arranged obliquely with a high rear end and a low front end.
  • the angle between the wing plate I and the wing plate II relative to the horizontal plane is 20°-30°.
  • the wing plate I and the wing plate II are arranged symmetrically.
  • the buckle includes an upper elastic piece and a lower elastic piece horizontally arranged on the inner end of the outer shell, and the lower elastic piece is located on the upper side. Below the shrapnel, the upper shrapnel is parallel to the lower shrapnel.
  • the head end of the upper shrapnel is provided with a chucking head I protruding upwards, and the head end of the lower shrapnel is protruding downwards with a chucking head II.
  • the slot II at the front end of the slot I is formed by connecting the slot I and the slot II through a connecting channel.
  • the opening height of the slot I is greater than the distance between the card head I and the card head II.
  • the height of the opening is smaller than the distance between the chuck I and the chuck II.
  • the upper and lower ends of the slot II are respectively provided with positioning grooves.
  • the chuck I When the front face of the outer shell is in contact with the rear face of the baffle, the chuck I is clamped in In the positioning slot above the slot II, the card head II is inserted into the positioning slot below the slot II.
  • the take-off speed of the aircraft is greater than or equal to 200Km/h, the card head I and the card head II are separated from the positioning slot, and the shrapnel is applied. And the lower elastic piece slides from the slot II to the slot I through the connecting channel.
  • the rear end of the outer casing is set to bend inward to form a bent part.
  • the bent part and the outer shell are arranged at a right angle.
  • a groove II is provided in the bent part.
  • the groove II in the bending part is buckled to the rear end of the connecting plate.
  • the rear end of the inner casing is provided with an opening groove along the axial direction.
  • the opening height of the opening groove matches the thickness of the front end of the connecting plate.
  • annular snap ring is provided on the inner shell, and the streamer is fixed on the snap ring by a rope.
  • the beneficial effect of the present invention is that when the aircraft landed, the ground crew first buckled the inner shell to the inner end of the airspeed tube through the groove III, and then buckled the outer shell to the outer end of the airspeed tube through the groove I.
  • the body is inserted into the slot through the buckle to realize the fixation with the inner casing, and the outer casing is fixed with the inner casing to realize the protection of the airspeed tube.
  • the separation device will separate the inner shell and the outer shell when the take-off speed is greater than or equal to 200Km/h, and the inner shell and the outer shell will be separated by gravity. Falling to achieve the purpose of automatic disengagement and ensure the normal operation of the airspeed tube.
  • Fig. 1 is a schematic diagram of the three-dimensional structure of the pitot tube
  • Figure 2 is a schematic diagram of the three-dimensional structure of the present invention.
  • Figure 3 is an exploded state diagram of the three-dimensional structure of the present invention.
  • FIG. 4 is a schematic diagram of an enlarged structure of the buckle part of the present invention.
  • FIG. 5 is a schematic diagram of the structure of the card slot of the present invention.
  • a self-separating protective cover for the airspeed tube of a civil aircraft is connected to a flange 1 through a horizontally arranged connecting plate 3.
  • the flange 1 is fixed on the aircraft body and includes an outer shell 4 located on the airspeed tube 2
  • a groove I6 with a semicircular cross section is arranged in the axial direction.
  • the inner diameter of the groove I6 matches the radius of the PTV 2; the inner casing 5 is located at the inner end of the PTV 2.
  • a semicircular groove III13 with a cross-section is provided in the axial direction.
  • the inner diameter of the groove III13 matches the radius of the air velocity tube 2.
  • the front end of the inner shell 4 is provided with a baffle 16 which is connected to the inner
  • the shell 4 is vertical; the buckles 14 are arranged at the upper and lower ends of the outer shell 4, and the upper and lower ends of the inner shell 5 are correspondingly provided with grooves 15, and the outer shell 4 is buckled into the grooves 15 through the buckles 14, empty
  • the velocity tube 2 is inserted into the cylindrical inner hole formed by the groove I6 and the groove III13, the front end surface of the space velocity tube 2 is in contact with the baffle 16; and the separation device is arranged in the outer shell 4 and the inner shell 5, when the take-off speed of the aircraft is greater than or equal to 200Km/h, the buckle 14 of the outer shell 4 is disengaged from the slot 15 of the inner shell 5, and the outer shell 4 and the inner shell 5 are separated from the airspeed tube 2.
  • the ground crew When the plane landed, the ground crew first buckled the inner shell 5 to the inner end of the PTT 2 through the groove III13, and then buckled the outer shell 4 to the outer end of the PTT 2 through the groove I6, and the outer shell 4 passed through
  • the buckle 14 is inserted into the slot 15 to realize the fixation with the inner housing 5, and the outer housing 4 and the inner housing 5 are fixed to realize the protection of the airspeed tube 2.
  • the separating device will separate the inner shell 5 and the outer shell 4 from each other, and the inner shell will be separated by gravity.
  • the body 5 and the outer shell 4 fall down to realize the purpose of automatic disengagement and ensure the normal operation of the airspeed tube 2.
  • the separating device may have the following structure, which includes a wing plate I9 respectively arranged at the outer end of the outer shell 4 and a wing plate II10 arranged on the inner housing 5, and the wing plate I9 and the wing plate II10 are inclined with a high rear end and a low front end.
  • the angle between the wing plate I9 and the wing plate II10 relative to the horizontal plane is 20°-30°, the wing plate I9 and the wing plate II10 are arranged symmetrically, and the buckle 14 includes an upper elastic piece 141 and a lower elastic piece horizontally arranged at the inner end of the outer shell 4 143, the lower elastic piece 143 is located below the upper elastic piece 141, the upper elastic piece 141 and the lower elastic piece 143 are parallel, the head end of the upper elastic piece 141 is provided with a chuck I142 protruding upward, and the head end of the lower elastic piece 143 is protruding downward with a chuck Head II 144, card slot 15 is composed of slot I 151 and slot II 152 at the front end of slot I 151.
  • Slot I 151 and slot II 152 are connected by connecting channel 153.
  • the opening height of slot I 151 is larger than that of card head I 142 and the card head.
  • the distance between II144 and the opening height of slot II152 is smaller than the distance between chuck I142 and chuck II144.
  • the upper and lower ends of slot II152 are respectively provided with positioning grooves 154.
  • the baffle 16 is in contact with the front end of the air velocity tube 2, the inner shell is not separated from the inner shell 3 5 Will not move, and the angle between the wing plate I 9 and the horizontal plane is 20°-30°, which can meet the requirement of the backward force of the wing plate I9 when the speed exceeds 200Km/h, and the chuck I142 and the chuck II144 Disengaged from the positioning groove 154, the space between the upper elastic piece 141 and the lower elastic piece 143 becomes smaller and compressed and deformed, so that it slides into the slot I151 through the connecting channel 153, and the outer shell 4 moves backward relative to the inner shell 5.
  • the opening height of I151 is greater than the distance between the chuck I142 and the chuck II144, so the downward force received by the wing plate I9 deflects the outer shell 4 relative to the inner shell 5, and the chuck I142 and the chuck II144 are removed from the slot.
  • the wing plate II10 of the inner shell 5 receives a downward force under the action of the airflow to deflect it relative to the PTT 2, so that the inner shell 5 separates from the PTT 2. Realize the automatic detachment of the airspeed tube 2 and the protective shell.
  • the rear end of the outer shell 4 is set to be bent inward to form a bent portion 7.
  • the bent portion 7 and the outer shell 4 are arranged at a right angle.
  • the bent portion 7 is provided with a groove II 8.
  • the groove II 8 in the bending portion 7 is buckled to the rear end of the connecting plate 3.
  • the bending part 7 can be buckled at the rear end of the PTV 2 and inserted into the rear end of the connecting plate 3 by using the groove II8, so that the entire protective sleeve is firmly fixed and at the same time can protect the entire PTV 2 The range is increased.
  • the rear end of the inner casing 5 is provided with an opening groove 11 along the axial direction.
  • the opening height of the opening groove 11 matches the thickness of the front end of the connecting plate 3.
  • the opening groove 11 11 is inserted on the front end of the connecting board 3.
  • annular snap ring 12 is provided on the inner shell 5, and the streamer is fixed to the snap ring 12 by a rope.

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Abstract

一种民用航空器空速管自分离保护套，当飞机降落后，地面勤务人员先将内壳体（5）通过凹槽Ⅲ（13）扣在空速管（2）内侧端，之后将外壳体（4）通过凹槽Ⅰ（6）扣在空速管（2）的外侧端，外壳体（4）通过卡扣（14）插装于卡槽（15）中实现与内壳体（5）的固定，外壳体（4）与内壳体（5）固定后实现对空速管（2）的保护。如果飞机起飞时且地面勤务人员没有取下外壳体（4）与内壳体（5），当起飞速度大于等于200Km/h时分离装置会使内壳体（5）与外壳体（4）相互分离，在重力作用下内壳体（5）与外壳体（4）掉落，实现自动脱开的目的，确保空速管（2）的正常工作。

Description

一种民用航空器空速管自分离保护套 技术领域
本发明涉及航空器保护装置技术领域，具体涉及一种民用航空器空速管自分离保护套。
背景技术
空速管也叫皮托管、总压管、总-静压管，能够感受气流的总压(也称全压)和静压，并将测得的压力数据传送给大气数据计算机、飞行仪表的装置。为了防止结冰，空速管需要加温，加温可以对探头进行防冰，从而防止结冰堵塞测量孔，影响探测精度。为了防止动/静压系统积聚水分，在空速管设有排水孔和动/静压系统管路设有排水接头。
空速管堵塞，可能造成极其严重的后果。飞机空速管保护套是飞机空速管的地面保护装置。在飞机停放期，为飞机套上空速管保护套可避免外来物进入空速管中，从而避免因异物进入导致的空速指示错误。保护套一般带有一条鲜艳的红色飘带，印有“起飞前取下”(“REMOVE BEFORE FLIGHT”)字样，以提醒机务人员在飞机起飞前及时取下。然而，为了避免外来物堵塞空速管而设计的空速管套却常因工作人员飞前忘记取下空速管套，成为造成空速管堵塞的主要原因。
目前多数空速管保护套采用木质套管、皮脂套管或棉线套管，存在使用寿命短、不耐高温、容易变形导致保护失效、无法提供自动分离功能、保护不完全，无法覆盖排水孔等等不同的缺点。
发明内容
本发明为了克服以上技术的不足，提供了一种一旦工作人员忘记取下空速管保护套，在飞机起飞过程中空速管保护套可以分离的民用航空器空速管自分离保护套。
本发明克服其技术问题所采用的技术方案是：
一种民用航空器空速管自分离保护套，空速管通过水平设置的连接板与法兰连接，法兰固定于飞机机体上，包括：
外壳体，位于空速管的外侧端，其内部沿轴向设置有横截面为半圆形的凹槽Ⅰ，所述凹槽Ⅰ的内径与空速管的半径相匹配；
内壳体，位于空速管的内侧端，其内部沿轴向设置有横截面为半圆形的凹槽Ⅲ，所述凹槽Ⅲ的内径与空速管的半径相匹配，内壳体的前端设置有挡板，所述挡板与内壳体相垂直；
卡扣，设置于外壳体上下两端，所述内壳体的上下两端对应设置有卡槽，外壳体通过卡扣扣 合于卡槽中，空速管插装于凹槽Ⅰ与凹槽Ⅲ拼装成的圆柱形的内孔中，空速管的前端面与挡板相接触；以及
分离装置，设置于外壳体及内壳体上，当飞机起飞速度大于等于200Km/h时，外壳体的卡扣与内壳体的卡槽脱离，外壳体与内壳体从空速管上分离。
进一步的，上述分离装置包括分别设置于外壳体外侧端的翼板Ⅰ以及设置于内壳体上的翼板Ⅱ，翼板Ⅰ与翼板Ⅱ均呈后端高前端低的形式倾斜设置，翼板Ⅰ与翼板Ⅱ相对于水平面的夹角为20°-30°，翼板Ⅰ与翼板Ⅱ对称设置，所述卡扣包括水平设置于外壳体内侧端的上弹片以及下弹片，下弹片位于上弹片的下方，上弹片与下弹片相平行，上弹片的头端向上凸起设置有卡头Ⅰ，下弹片的头端向下凸起设置有卡头Ⅱ，所述卡槽由插槽Ⅰ以及位于插槽Ⅰ前端的插槽Ⅱ构成，所述插槽Ⅰ与插槽Ⅱ之间通过连接通道连接，插槽Ⅰ的开口高度大于卡头Ⅰ与卡头Ⅱ之间的间距，插槽Ⅱ的开口高度小于卡头Ⅰ与卡头Ⅱ之间的间距，插槽Ⅱ的上下两端分别设置有定位槽，当外壳体的前端面与挡板的后端面相接触时，卡头Ⅰ卡置于插槽Ⅱ上方的定位槽中，卡头Ⅱ卡置于插槽Ⅱ下方的定位槽中，当飞机起飞速度大于等于200Km/h时，卡头Ⅰ与卡头Ⅱ从定位槽中脱离，上弹片与下弹片从插槽Ⅱ中经连接通道滑动至插槽Ⅰ中。
为了提高保护范围，上述外壳体的后端设置向内侧弯曲形成折弯部，折弯部与外壳体呈直角夹角设置，折弯部内设置有凹槽Ⅱ，当外壳体扣合在空速管外侧端时，折弯部内的凹槽Ⅱ扣合于连接板的后侧端。
为了固定牢固，上述内壳体的后端沿轴向设置有开口槽，所述开口槽的开口高度与连接板前端的厚度相匹配，当内壳体扣合在空速管内侧端时，开口槽插装于连接板的前端。
为了方便固定飘带，上述内壳体上设置有圆环形的卡环，飘带通过绳索固定于卡环上。
本发明的有益效果是：当飞机降落后，地面勤务人员先将内壳体通过凹槽Ⅲ扣在空速管内侧端，之后将外壳体通过凹槽Ⅰ扣在空速管的外侧端，外壳体通过卡扣插装于卡槽中实现与内壳体的固定，外壳体与内壳体固定后实现对空速管的保护。如果飞机起飞时且地面勤务人员没有取下外壳体与内壳体，当起飞速度大于等于200Km/h时分离装置会使内壳体与外壳体相互分离，在重力作用下内壳体与外壳体掉落，实现自动脱开的目的，确保空速管的正常工作。
附图说明
图1为空速管的立体结构示意图；
图2为本发明的立体结构示意图；
图3为本发明的立体结构爆炸状态图；
图4为本发明的卡扣部位的放大结构示意图；
图5为本发明的卡槽部位的结构示意图；
图中，1.法兰 2.空速管 3.连接板 4.外壳体 5.内壳体 6.凹槽Ⅰ 7.折弯部 8.凹槽Ⅱ 9.翼板Ⅰ 10.翼板Ⅱ 11.开口槽 12.卡环 13.凹槽Ⅲ 14.卡扣 15.卡槽 16.挡板 141.上弹片 142.卡头Ⅰ 143.下弹片 144.卡头Ⅱ 151.插槽Ⅰ 152.插槽Ⅱ 153.连接通道 154.定位槽。
具体实施方式
下面结合附图1至附图5对本发明做进一步说明。
一种民用航空器空速管自分离保护套，空速管2通过水平设置的连接板3与法兰1连接，法兰1固定于飞机机体上，包括：外壳体4，位于空速管2的外侧端，其内部沿轴向设置有横截面为半圆形的凹槽Ⅰ6，凹槽Ⅰ6的内径与空速管2的半径相匹配；内壳体5，位于空速管2的内侧端，其内部沿轴向设置有横截面为半圆形的凹槽Ⅲ13，凹槽Ⅲ13的内径与空速管2的半径相匹配，内壳体4的前端设置有挡板16，挡板16与内壳体4相垂直；卡扣14，设置于外壳体4上下两端，内壳体5的上下两端对应设置有卡槽15，外壳体4通过卡扣14扣合于卡槽15中，空速管2插装于凹槽Ⅰ6与凹槽Ⅲ13拼装成的圆柱形的内孔中，空速管2的前端面与挡板16相接触；以及分离装置，设置于外壳体4及内壳体5上，当飞机起飞速度大于等于200Km/h时，外壳体4的卡扣14与内壳体5的卡槽15脱离，外壳体4与内壳体5从空速管2上分离。当飞机降落后，地面勤务人员先将内壳体5通过凹槽Ⅲ13扣在空速管2内侧端，之后将外壳体4通过凹槽Ⅰ6扣在空速管2的外侧端，外壳体4通过卡扣14插装于卡槽15中实现与内壳体5的固定，外壳体4与内壳体5固定后实现对空速管2的保护。如果飞机起飞时且地面勤务人员没有取下外壳体4与内壳体5，当起飞速度大于等于200Km/h时分离装置会使内壳体5与外壳体4相互分离，在重力作用下内壳体5与外壳体4掉落，实现自动脱开的目的，确保空速管2的正常工作。
分离装置可以为如下结构，其包括分别设置于外壳体4外侧端的翼板Ⅰ9以及设置于内壳体5上的翼板Ⅱ10，翼板Ⅰ9与翼板Ⅱ10均呈后端高前端低的形式倾斜设置，翼板Ⅰ9与翼板Ⅱ10相对于水平面的夹角为20°-30°，翼板Ⅰ9与翼板Ⅱ10对称设置，卡扣14包括水平设置于外壳体4内侧端的上弹片141以及下弹片143，下弹片143位于上弹片141的下方，上弹片141与下弹片143相平行，上弹片141的头端向上凸起设置有卡头Ⅰ142，下弹片143的头端向下凸起设置有卡头Ⅱ144，卡槽15由插槽Ⅰ151以及位于插 槽Ⅰ151前端的插槽Ⅱ152构成，插槽Ⅰ151与插槽Ⅱ152之间通过连接通道153连接，插槽Ⅰ151的开口高度大于卡头Ⅰ142与卡头Ⅱ144之间的间距，插槽Ⅱ152的开口高度小于卡头Ⅰ142与卡头Ⅱ144之间的间距，插槽Ⅱ152的上下两端分别设置有定位槽154，当外壳体4的前端面与挡板16的后端面相接触时，卡头Ⅰ142卡置于插槽Ⅱ152上方的定位槽154中，卡头Ⅱ144卡置于插槽Ⅱ152下方的定位槽154中，当飞机起飞速度大于等于200Km/h时，卡头Ⅰ142与卡头Ⅱ144从定位槽154中脱离，上弹片141与下弹片143从插槽Ⅱ152中经连接通道153滑动至插槽Ⅰ151中。如果飞机起飞时，地面勤务人员忘记取下空速管的保护套，飞机起飞时，其滑行速度只要达到200Km/h以上时，其气流作用在倾斜设置的翼板Ⅰ9与翼板Ⅱ10上会产生作用力，作用力一方面是向后方的，另一方面是向下方的，由于挡板16的与空速管2的前端接触，在外壳体3与内壳体5没有分离的时候内壳体5不会移动，而翼板Ⅰ9相对于水平面的夹角为20°-30°的设置可以满足速度超过200Km/h以上时，翼板Ⅰ9向后的作用力使，卡头Ⅰ142与卡头Ⅱ144从定位槽154中脱离，上弹片141与下弹片143之间间距变小压缩变形，使其通过连接通道153滑动至插槽Ⅰ151中，外壳体4相对内壳体5向后方移动，由于插槽Ⅰ151的开口高度大于卡头Ⅰ142与卡头Ⅱ144之间的间距，因此翼板Ⅰ9受到的向下的力回使外壳体4相对内壳体5发生偏转，卡头Ⅰ142与卡头Ⅱ144从插槽Ⅰ151中脱离，外壳体4脱离后，内壳体5的翼板Ⅱ10在气流作用下受到向下的力回使其相对空速管2发生偏转，从而内壳体5相对空速管2脱离，实现空速管2与保护壳的自动脱开。
外壳体4的后端设置向内侧弯曲形成折弯部7，折弯部7与外壳体4呈直角夹角设置，折弯部7内设置有凹槽Ⅱ8，当外壳体4扣合在空速管2外侧端时，折弯部7内的凹槽Ⅱ8扣合于连接板3的后侧端。折弯部7可以扣在空速管2的后端，并利用凹槽Ⅱ8插装在连接板3的后端，从而使整个保护套的固定牢固的同时，可以对整个空速管2的保护范围得以增大。
内壳体5的后端沿轴向设置有开口槽11，开口槽11的开口高度与连接板3前端的厚度相匹配，当内壳体5扣合在空速管2内侧端时，开口槽11插装于连接板3的前端。通过设置开口槽11，可以使内壳体5固定时通过开口槽11与连接板3相互固定，从而防止外壳体4和内壳体5相互转动。
优选的，内壳体5上设置有圆环形的卡环12，飘带通过绳索固定于卡环12上。

Claims (5)

  1. 一种民用航空器空速管自分离保护套，空速管(2)通过水平设置的连接板(3)与法兰(1)连接，法兰(1)固定于飞机机体上，其特征在于，包括：
    外壳体(4)，位于空速管(2)的外侧端，其内部沿轴向设置有横截面为半圆形的凹槽Ⅰ(6)，所述凹槽Ⅰ(6)的内径与空速管(2)的半径相匹配；
    内壳体(5)，位于空速管(2)的内侧端，其内部沿轴向设置有横截面为半圆形的凹槽Ⅲ(13)，所述凹槽Ⅲ(13)的内径与空速管(2)的半径相匹配，内壳体(4)的前端设置有挡板(16)，所述挡板(16)与内壳体(4)相垂直；
    卡扣(14)，设置于外壳体(4)上下两端，所述内壳体(5)的上下两端对应设置有卡槽(15)，外壳体(4)通过卡扣(14)扣合于卡槽(15)中，空速管(2)插装于凹槽Ⅰ(6)与凹槽Ⅲ(13)拼装成的圆柱形的内孔中，空速管(2)的前端面与挡板(16)相接触；以及
    分离装置，设置于外壳体(4)及内壳体(5)上，当飞机起飞速度大于等于200Km/h时，外壳体(4)的卡扣(14)与内壳体(5)的卡槽(15)脱离，外壳体(4)与内壳体(5)从空速管(2)上分离。
  2. 根据权利要求1所述的民用航空器空速管自分离保护套，其特征在于：所述分离装置包括分别设置于外壳体(4)外侧端的翼板Ⅰ(9)以及设置于内壳体(5)上的翼板Ⅱ(10)，翼板Ⅰ(9)与翼板Ⅱ(10)均呈后端高前端低的形式倾斜设置，翼板Ⅰ(9)与翼板Ⅱ(10)相对于水平面的夹角为20°-30°，翼板Ⅰ(9)与翼板Ⅱ(10)对称设置，所述卡扣(14)包括水平设置于外壳体(4)内侧端的上弹片(141)以及下弹片(143)，下弹片(143)位于上弹片(141)的下方，上弹片(141)与下弹片(143)相平行，上弹片(141)的头端向上凸起设置有卡头Ⅰ(142)，下弹片(143)的头端向下凸起设置有卡头Ⅱ(144)，所述卡槽(15)由插槽Ⅰ(151)以及位于插槽Ⅰ(151)前端的插槽Ⅱ(152)构成，所述插槽Ⅰ(151)与插槽Ⅱ(152)之间通过连接通道(153)连接，插槽Ⅰ(151)的开口高度大于卡头Ⅰ(142)与卡头Ⅱ(144)之间的间距，插槽Ⅱ(152)的开口高度小于卡头Ⅰ(142)与卡头Ⅱ(144)之间的间距，插槽Ⅱ(152)的上下两端分别设置有定位槽(154)，当外壳体(4)的前端面与挡板(16)的后端面相接触时，卡头Ⅰ(142)卡置于插槽Ⅱ(152)上方的定位槽(154)中，卡头Ⅱ(144)卡置于插槽Ⅱ(152)下方的定位槽(154)中，当飞机起飞速度大于等于200Km/h时，卡头Ⅰ(142)与卡头Ⅱ(144)从定位槽(154)中脱离，上弹片(141)与下弹片(143)从插槽Ⅱ(152)中经连接通道(153)滑动至插槽Ⅰ(151)中。
  3. 根据权利要求1所述的民用航空器空速管自分离保护套，其特征在于：所述外壳体(4)的后端设置向内侧弯曲形成折弯部(7)，折弯部(7)与外壳体(4)呈直角夹角设置，折弯部(7)内设置有凹槽Ⅱ(8)，当外壳体(4)扣合在空速管(2)外侧端时，折弯部(7)内的凹槽Ⅱ(8)扣合于连接板(3)的后侧端。
  4. 根据权利要求1所述的民用航空器空速管自分离保护套，其特征在于：所述内壳体(5)的后端沿轴向设置有开口槽(11)，所述开口槽(11)的开口高度与连接板(3)前端的厚度相匹配，当内壳体(5)扣合在空速管(2)内侧端时，开口槽(11)插装于连接板(3)的前端。
  5. 根据权利要求1所述的民用航空器空速管自分离保护套，其特征在于：所述内壳体(5)上设置有圆环形的卡环(12)，飘带通过绳索固定于卡环(12)上。
PCT/CN2020/094253 2019-08-30 2020-06-04 一种民用航空器空速管自分离保护套 Ceased WO2021036388A1 (zh)

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