CN202295290U - 新型进气道隔道结构 - Google Patents

新型进气道隔道结构 Download PDF

Info

Publication number
CN202295290U
CN202295290U CN2011203368712U CN201120336871U CN202295290U CN 202295290 U CN202295290 U CN 202295290U CN 2011203368712 U CN2011203368712 U CN 2011203368712U CN 201120336871 U CN201120336871 U CN 201120336871U CN 202295290 U CN202295290 U CN 202295290U
Authority
CN
China
Prior art keywords
lozenges
distance
road
inlet channel
wedged
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
Application number
CN2011203368712U
Other languages
English (en)
Inventor
卢杰
贾伟峰
尹志龙
戴佳
任志文
杨俊飞
万志明
万俊丹
王春利
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Jiangxi Hongdu Aviation Industry Group Co Ltd
Original Assignee
Jiangxi Hongdu Aviation Industry Group Co Ltd
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 Jiangxi Hongdu Aviation Industry Group Co Ltd filed Critical Jiangxi Hongdu Aviation Industry Group Co Ltd
Priority to CN2011203368712U priority Critical patent/CN202295290U/zh
Application granted granted Critical
Publication of CN202295290U publication Critical patent/CN202295290U/zh
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Abstract

本实用新型涉及新型进气道隔道结构。在机身与发动机的进气道进口间设有隔道，隔道的楔形面由一级楔形面和二级楔形面组成，一级楔形面楔顶角为θ，二级楔形面的楔顶角为θ2，二级楔形面到一级楔形面的距离为L，两极楔形面之间为圆弧过渡连接，圆弧半径为R。以达到消除附加迎风面M的目的。

Description

新型进气道隔道结构
技术领域
    本实用新型涉及航空飞行器结构，属于进气道结构的改进，特别涉及新型进气道隔道结构。
背景技术
对于内置涡喷或涡扇发动机的亚音速飞行器，一般采用S形进气道作为发动机的进气装置。并且进气道进口布置于飞行器后部。为防止进气道进口前机身产生的附面层进入进气道而使进气道性能下降，一般在进气道与机身间设计隔道（如图1所示）。隔道的形状为楔形，为减小阻力并防止气流在隔道顶部堆积，楔顶角θ通常为40°（如图2所示）。对于小型飞行器，进气道长度较短，相应的进气道与机身相贯线到进气道进口的距离也较短，使得隔道的楔形面无法完全伸展，导致在进气道与机身相贯线处产生附加迎风面M，增加了飞行器的阻力。
实用新型内容
本实用新型的目的是要对现有的楔形隔道进行改进，以消除附加迎风面，使飞行器阻力降低。
为实现上述目的，本实用新型采取以下技术方案，新型进气道隔道结构，在机身与发动机的进气道进口间设有隔道，隔道的楔形面由一级楔形面和二级楔形面组成，一级楔形面楔顶角为θ，二级楔形面的楔顶角为θ2，二级楔形面到一级楔形面的距离为L，两极楔形面之间为圆弧过渡连接，圆弧半径为R。所述两个楔形面间的距离L为隔道总长的0.5～0.6倍。所述圆弧半径R为隔道总长的2倍。
本实用新型是将原隔道由一级楔形改进为二级楔形，二级楔形距一级楔形L处开始，二级楔形的楔顶角为θ2，两极楔形之间通过圆弧过渡，圆弧半径为R。L、θ2和R的值可以根据实际情况选取，可以保证二级楔形完全伸展，以达到消除附加迎风面M的目的。
附图说明
图1是隔道4在飞行器上位置的示意图。
图2是现在隔道4的结构示意图。
图3是本实用新型的结构示意图。
图中：1、机身，2、发动机，3、进气道，4、隔道，41、一级楔形面，42、二级楔形面。
具体实施方式
现结合附图和实施例对本实用新型作进一步说明，参见图3，新型进气道隔道结构，在机身1与发动机2的进气道3进口间设有隔道4，其特征是，隔道4的楔形面由一级楔形面41和二级楔形面42组成，一级楔形面41楔顶角为θ，二级楔形面42的楔顶角为θ2，二级楔形面42到一级楔形面41的距离为L，两极楔形面之间为圆弧过渡连接，圆弧半径为R。所述两个楔形面间的距离L为隔道4总长的0.5～0.6倍。所述圆弧半径R为隔道4总长的2倍。
实施例：本实用新型的进气道隔道结构分为两部分，一级楔形面41和二级楔形面42。一级楔形面41与改进前的隔道一致，楔顶角θ=40°。在距一级楔形面41距离L处，一级楔形面41开始向外扩张，形成二级楔形面42，二级楔形面42的楔顶角为θ2，θ2>θ，选取θ2时应使θ2最小并使二级楔形面42完全伸展，原隔道4下产生的附加迎风面M得以消除，可以降低飞行器阻力。一级楔形面41和二级楔形面42进行倒圆R，保证两级楔形面光滑过渡，以进一步减小阻力。
隔道4上的L、θ2和R的值可以根据实际情况选取，其较佳取值范围是：L为隔道4总长的0.5～0.6倍，R为隔道4总长的2倍。

Claims (3)

1. 新型进气道隔道结构，在机身（1）与发动机（2）的进气道（3）进口间设有隔道（4），其特征是，隔道（4）的楔形面由一级楔形面（41）和二级楔形面（42）组成，一级楔形面（41）楔顶角为θ，二级楔形面（42）的楔顶角为θ2，二级楔形面（42）到一级楔形面（41）的距离为L，两极楔形面之间为圆弧过渡连接，圆弧半径为R。
2.根据权利要求1所述的新型进气道隔道结构，其特征是，所述两个楔形面间的距离L为隔道（4）总长的0.5～0.6倍。
3.根据权利要求1所述的新型进气道隔道结构，其特征是，所述圆弧半径R为隔道（4）总长的2倍。
CN2011203368712U 2011-09-09 2011-09-09 新型进气道隔道结构 Expired - Lifetime CN202295290U (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN2011203368712U CN202295290U (zh) 2011-09-09 2011-09-09 新型进气道隔道结构

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN2011203368712U CN202295290U (zh) 2011-09-09 2011-09-09 新型进气道隔道结构

Publications (1)

Publication Number Publication Date
CN202295290U true CN202295290U (zh) 2012-07-04

Family

ID=46364239

Family Applications (1)

Application Number Title Priority Date Filing Date
CN2011203368712U Expired - Lifetime CN202295290U (zh) 2011-09-09 2011-09-09 新型进气道隔道结构

Country Status (1)

Country Link
CN (1) CN202295290U (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102826229A (zh) * 2012-09-11 2012-12-19 江西洪都航空工业集团有限责任公司 一种飞行器进气道隔道

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102826229A (zh) * 2012-09-11 2012-12-19 江西洪都航空工业集团有限责任公司 一种飞行器进气道隔道

Similar Documents

Publication Publication Date Title
CN203283375U (zh) 一种飞行器的机翼布局结构
CN204399465U (zh) 一种无尾飞翼多操纵面无人机
EP2551197A3 (en) Reduced flow field velocity for a propulsor
CN109455309A (zh) 基于圆锥前体激波的前掠内乘波进气道一体化设计方法
CN203740128U (zh) 乘波体飞行器
CN202295290U (zh) 新型进气道隔道结构
CN204368436U (zh) 平开口风斗
CN103029830A (zh) 一种双乘波体对拼吸气式高超飞行器前体及其设计方法
CN103171758A (zh) 一种飞翼型飞机的增升方法
CN203158227U (zh) 一种改进型的飞机
CN204279926U (zh) 一种带有导流作用的围板式多旋翼飞行器起落架
CN106240799A (zh) 一种提高带锯齿后掠翼跨声速横向飞行品质的机翼
CN202491923U (zh) 喷气式降落伞
CN204489195U (zh) 喷气式直升飞机
CN203780795U (zh) 双发单垂尾式飞机后体吹气式整流装置
CN104097763A (zh) 一种异形机翼翼型
CN204403244U (zh) 一种轻量化气室支架
CN203937855U (zh) 一种腹鳍外形
CN103569351B (zh) 具有双后掠角前缘的鸭翼
WO2013189503A3 (en) High altitude maglev vertical-axis wind turbine system (ham-vawt)
CN203172881U (zh) 水下飞机
CN202624638U (zh) 一种飞机通风冷却系统冲压进气罩
CN101885382A (zh) 带侧向力的降落伞
CN201959566U (zh) 用于三通固定翼飞机的机翼
CN202030002U (zh) 机场折板式导流屏

Legal Events

Date Code Title Description
C14 Grant of patent or utility model
GR01 Patent grant
ASS Succession or assignment of patent right

Owner name: JIANGXI HONGDU TECHNOLOGY CO., LTD.

Free format text: FORMER OWNER: HONGDU AVIATION INDUSTRY GROUP CO., TD., JIANGXI PROV.

Effective date: 20140813

C41 Transfer of patent application or patent right or utility model
COR Change of bibliographic data

Free format text: CORRECT: ADDRESS; FROM: 330000 NANCHANG, JIANGXI PROVINCE TO: 330096 NANCHANG, JIANGXI PROVINCE

TR01 Transfer of patent right

Effective date of registration: 20140813

Address after: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park

Patentee after: Jiangxi Hongdu Technology Co., Ltd.

Address before: 330000 Jiangxi city of Nanchang province Qingyunpu new bridge

Patentee before: Hongdu Aviation Industry Group Co., td., Jiangxi Prov.

EE01 Entry into force of recordation of patent licensing contract

Assignee: Jiangxi Hongdu Technology Co., Ltd.

Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov.

Contract record no.: 2014360000165

Denomination of utility model: Novel separating channel structure of air inlet channel

Granted publication date: 20120704

License type: Exclusive License

Record date: 20140709

LICC Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model
EC01 Cancellation of recordation of patent licensing contract

Assignee: Jiangxi Hongdu Technology Co., Ltd.

Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov.

Contract record no.: 2014360000165

Date of cancellation: 20141202

LICC Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model
C41 Transfer of patent application or patent right or utility model
TR01 Transfer of patent right

Effective date of registration: 20151230

Address after: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001

Patentee after: Hongdu Aviation Industry Group Co., td., Jiangxi Prov.

Address before: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park

Patentee before: Jiangxi Hongdu Technology Co., Ltd.

CX01 Expiry of patent term

Granted publication date: 20120704

CX01 Expiry of patent term