CN105988018B - 具有迎角操作下的改进性能的大气数据探针 - Google Patents
具有迎角操作下的改进性能的大气数据探针 Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
- G01F1/05—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects
- G01F1/34—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects by measuring pressure or differential pressure
- G01F1/36—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects by measuring pressure or differential pressure the pressure or differential pressure being created by the use of flow constriction
- G01F1/40—Details of construction of the flow constriction devices
- G01F1/46—Pitot tubes
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- G—PHYSICS
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- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
- G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
- G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
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Abstract
一种大气数据探针具有在前端处带有分接管的皮托管,所述皮托管界定内流径。所述内流径的横截面积减小直至到达喉部。所述内流径具有大致圆柱形的横截面并且也具有被移除材料的截面。其它实施方案具有独特形状。
Description
发明背景
本申请案涉及用于飞机应用中的大气数据探针,其中它的性能在相关飞机的特定工作条件期间改进。
现代飞机变得愈加精密并且需要精确的信息。现代飞机的控制装置需要准确了解空速。作为确定空速的部分,通常将大气数据探针安装在飞机机体上。
大气数据探针吸入空气并且评估空气以确定空速和其它参数(例如,载有探针的飞机的高度、迎角、侧滑角等)。
这些大气数据探针的要求具有挑战性,尤其在用于包括冰晶的环境中。此外,当相关飞机在大迎角下运行时,空气再循环和边界层分离可能在开口内发生或进入大气数据探针。为使大气数据探针提供准确的信息,总压力恢复要求保持不变,且因此空气再循环和边界层分离产生挑战。
大气数据探针通常包括皮托管,其提供用于接收空气的分接管。上述有关再循环和边界层分离的挑战在皮托管分接管附近发生。
发明概要
一种大气数据探针具有在前端处带有分接管的皮托管,所述皮托管界定内流径。所述内流径的横截面积减小直至到达喉部。所述内流径具有大致圆柱形的横截面并且也具有被移除材料的截面。其它实施方案具有独特形状。
可从下图和说明书中最佳了解这些和其它特征。
附图简述
图1A示出安装在飞机上的现有大气数据探针。
图1B示出现有大气数据探针的操作性挑战。
图2A示出第一实施方案。
图2B是第一实施方案的另一个视图。
图2C图示图2A实施方案的操作性好处。
图3A示出第二实施方案。
图3B是透过第二实施方案的横截面图。
图4示出第三实施方案。
图5示出第四实施方案。
具体实施方式
图1A示意示出飞机机体20。大气数据探针22安装至飞机机体 20。大气数据探针22在皮托管21中的前端处具有分接管24。当飞机移动穿过空气时,分接管24对空气W的部分进行取样。分接空气将移动至通道26中的开口28中并且移动至取压分接管30。取压分接管30被示为与控制装置31连通。控制装置31将分接压力转化为飞机机体20的空速。此外,静压分接管32被利用并且连通至控制装置31。孔33提供分接管以将空气连通至静压分接管32。由于大气数据探针22可能用于有冰环境中,所以提供加热元件36。电加热器连接件38连通至控制装置31并且提供电力给加热器元件36。
如图1B中所示,现有大气数据探针22具有从最外端42向内通至喉部40的分接管24。如所示,大气数据探针22处于与飞行路径相比相对较大的角度下。在这种大迎角操作下,进入分接管24的空气可能具有再循环区域44。也存在边界层分离。在这种情况发生时,变得更难以获得可接受的总压力。
图2A示出其中分接管47从外端48向内朝向喉部50延伸的实施方案46。多个放气孔52从外周边表面处的出口54延伸穿过大气数据探针46的主体至内表面57处的进口56。大气数据探针46的内表面57以一定角度从外端48延伸,所述角度在内流径向内移动时减小内流径的横截面积直至内流径到达喉部50。放气孔52具有位于喉部50上游的进口56。
图2B是示出多个放气孔52的视图。可针对特定环境中的具体操作选择放气孔52的数量、大小和位置。
图2C示出大气数据探针46的操作。穿过放气孔52进入的空气离开内流径,消除图1B中图示的再循环和边界层分离。如所示,现在具有均匀的流量。
图3A示出其中分接管62具有前端66的实施方案60,所述前端 66具有凹槽,所述凹槽具有通至圆周扩大开口68中的圆周薄部分64。分接管62的其它区域70没有槽64/68。
如图3B中所示,相对侧上具有槽64/68,其具有中间的大致圆柱形部分70。明显地,槽64/68在喉部72处终止。
槽64/68协助带入空气以减小再循环和边界层分离,类似于图2A 至图2C实施方案。
一般地,图2A至图2C和图3A、图3B实施方案可被认为已移除材料以协助提供额外空气压力。
图2A至图2C和图3A/图3B实施方案可被认为具有皮托管,其在前端处具有分接管且界定内流径。内流径的横截面积减小直至到达喉部。内流径具有大致圆柱形的横截面并且也具有被移除材料(放气孔52或槽64/68)的截面。
图4示出又一个实施方案74。实施方案74可被视为“长鼻”大气数据探针。鼻部76具备相对较小直径d1。直径d1延伸穿过大致笔直或跨距离d2稍呈锥形的长鼻。在扩大区域78处,直径开始增大以提供空间用于接收加热器元件80。扩大区域78在直径d3处。放气孔 82可被并入,正如图2A至图2C实施方案。
在实施方案中,d3/d1与d2的比率之间具有一定关系。d3数量由探针管和加热器元件80的物理特性控制。d1数量由探针需要在其中工作的环境条件控制。
d1与d3的比率确认d2应多长。申请人已发现与三个数量的关系相关的常数。因此,下列关系优选地适用:
(d1/d3)*1.26=d2
这个等式中的常数1.26是针对类似于本申请案的图中所示的探针的标准皮托管探针确定的常数。在所公开实施方案中,三个数量将大致满足这个关系。在此背景下使用的术语“大致”意指1.26的+/1百分之五(5%)。
长鼻76组合小直径开口75以增强大气数据探针74的操作。
图5示出又一个实施方案84。也示出可选的放气孔88。
探针84的外端在它的外圆周的一部分上具有相对平坦的外表面 85和突部,所述突部背离平坦表面向外延伸且接着向内合并,使得突部提供与平坦部分间隔更远的外径部分,且突部的向后部分87和向前部分89亦如此。
此外,具有突部86的大气数据探针84提供宝贵的测试装置。突部86可以多个角度绕大气数据探针的轴旋转。总压力恢复可在每个角度下检查并且与其它角度比较以确定低压点和高压点。
虽然已公开本发明的实施方案,但是本领域一般技术人员应了解特定修改也在本发明的范围内。有鉴于此,本发明的真实范围和内容应通过研判所附权利要求书来确定。
Claims (8)
1.一种大气数据探针,其包括:
皮托管,其具有带前端的分接管,并且界定内流径,所述内流径的横截面积减小直至到达喉部;及
所述内流径具有大致圆形的横截面并且也具有至少一个放气孔或至少一个槽,
其中,所述喉部的下游的空气流移动进入通道并移动至取压分接管,所述取压分接管与控制装置连通,所述控制装置将分接压力转化为相关联的飞机机体的空速。
2.根据权利要求1所述的大气数据探针,其中所述内流径具有至少一个放气孔,所述至少一个放气孔从所述皮托管的外周边延伸以将空气连通至所述内流径中。
3.根据权利要求2所述的大气数据探针,其中所述至少一个放气孔的进口位于所述喉部的上游。
4.根据权利要求3所述的大气数据探针,其中所述内流径具有多个放气孔。
5.根据权利要求1所述的大气数据探针,其中所述内流径具有至少两个槽,其具有在所述至少两个槽之间圆周间隔的所述大致圆形截面。
6.根据权利要求5所述的大气数据探针,其中所述至少一个槽具有邻近所述皮托管的所述前端的相对圆周薄部分和位于所述相对圆周薄部分下游的相对圆周扩大部分。
7.根据权利要求6所述的大气数据探针,其中所述内流径具有多个槽。
8.根据权利要求6所述的大气数据探针,其中所述至少一个槽在所述喉部处终止。
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US14/665,007 US10281303B2 (en) | 2015-03-23 | 2015-03-23 | Air data probe with improved performance at angle of attack operation |
US14/665007 | 2015-03-23 |
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EP3575803B1 (en) | 2022-05-04 |
US20160282158A1 (en) | 2016-09-29 |
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EP3575803A3 (en) | 2020-02-19 |
US10634530B2 (en) | 2020-04-28 |
CA2919509C (en) | 2024-01-09 |
EP3073276A2 (en) | 2016-09-28 |
EP3073276B1 (en) | 2019-06-26 |
CN105988018A (zh) | 2016-10-05 |
CA2919509A1 (en) | 2016-09-23 |
US20180149501A1 (en) | 2018-05-31 |
EP3575803A2 (en) | 2019-12-04 |
BR102016004891B1 (pt) | 2021-06-15 |
BR102016004891A2 (pt) | 2016-10-18 |
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