WO2017121115A1 - 尾舵式矢量发动机 - Google Patents

尾舵式矢量发动机 Download PDF

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Publication number
WO2017121115A1
WO2017121115A1 PCT/CN2016/095927 CN2016095927W WO2017121115A1 WO 2017121115 A1 WO2017121115 A1 WO 2017121115A1 CN 2016095927 W CN2016095927 W CN 2016095927W WO 2017121115 A1 WO2017121115 A1 WO 2017121115A1
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Prior art keywords
rudder
tail
engine
tail rudder
vector
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PCT/CN2016/095927
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English (en)
French (fr)
Inventor
王佐良
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王佐良
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Priority to CN201680000745.5A priority Critical patent/CN106103961A/zh
Publication of WO2017121115A1 publication Critical patent/WO2017121115A1/zh

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes

Definitions

  • the invention relates to a tail rudder vector engine, which realizes attitude control of an aircraft by adding a tail rudder at the tail end of the core engine of the jet engine, and has the effect of changing the thrust direction similarly to the vector engine. It belongs to the field of aviation engine technology.
  • the attitude control of existing jet aircraft is mainly done by horizontal tails, vertical tails, duck wings or directly by the wings.
  • the new vector engine can adjust the thrust direction by changing the jet direction of the engine tail nozzle to achieve the attitude control of the aircraft, but the technology is difficult to implement.
  • the US scheme uses a rectangular nozzle with a deflector plate in the up and down direction, which can be deflected at a small angle in the up and down direction to change the direction of the jet.
  • the structure is simple, it cannot be turned 360 degrees. It belongs to the binary thrust vector engine; Russia
  • the solution is to articulate the tail spout with the engine to achieve 360 degree steering of the tail spout.
  • the structure is complex, it can provide omnidirectional thrust and belongs to a multi-thrust vector engine.
  • the existing vector engine utilizes the change of the jet direction of the engine tail nozzle, and uses the principle of action and reaction force to change the direction of the engine thrust.
  • the main problem is that the structural design is difficult and the service life is low.
  • the invention is inspired by the action of the animal's tail to control the body posture and steering. It is proposed to add a tail rudder in the form of a "tail" at the end of the jet engine core machine, and change the thrust direction of the engine through the "tail effect".
  • a tail rudder which is extended backward and can be angularly deflected is designed. When the high pressure airflow of the jet engine flows through the rudder, the rudder passes through the rudder.
  • the deflection produces a "tail effect" that changes the direction of the thrust of the engine;
  • the rudder is a cone;
  • the rudder has a rudder fin, the rudder fin is in the same direction as the central axis of the engine, and perpendicular to the central axis
  • the rudder fin has four fins which are evenly distributed at an angle of 90 degrees to the upper, lower, left and right directions;
  • the rudder is composed of two or more rudders which are connected to each other at the beginning and the end.
  • the rudder fin is designed on the rudder, not only using the force and reaction force of the jet stream, but also utilizing the principles of fluid mechanics and The Nuoli principle, which obtains greater deflection force, is more direct and more agile, has a simpler structural design and is less difficult.
  • FIG. 1 is a schematic structural view of one embodiment of the present invention.
  • FIG. 2 is a working principle diagram of one embodiment of the present invention
  • Figure 3 is a schematic structural view of the second embodiment of the present invention.
  • Figure 4 is a working principle diagram of the second embodiment of the present invention.
  • FIG. 5 is a working principle diagram of the third embodiment of the present invention.
  • 1 is a fan
  • 2 is a compressor
  • 3 is an outer duct
  • 4 is an intrinsic track
  • 5 is a combustion chamber
  • 6 is a turbine
  • 7 is an afterburner
  • 8 is a tail rudder
  • 9 is a rudder fin
  • the second embodiment of the present invention shown in Figures 3 and 4 is a preferred embodiment of the present invention. It not only designed the rudder, but also designed the rudder fin on the rudder. It not only utilized the principle of force and reaction, but also utilized the principles of fluid mechanics and Bernoulli to provide a more rapid, agile and efficient deflection of the engine. force.
  • FIG. 1 is a schematic structural view of one embodiment of the present invention
  • FIG. 2 is a working principle diagram of one embodiment of the present invention
  • 1 and 2 are structural views of a turbofan engine.
  • the rudder 8 of the present invention At the end of the central axis of the core machine of the turbofan engine, there is a long cone, which is the rudder 8 of the present invention.
  • Figure 1 shows the normal state of the rudder 8
  • Figure 2 shows It is the working state of the tail rudder.
  • the rudder 2 is deflected in the high-speed wake of the engine. According to fluid mechanics and Bernoulli's principle, we can know that the thrust direction of the engine will also deflect.
  • FIG. 3 is a schematic structural view of the second embodiment of the present invention
  • FIG. 4 is a working principle diagram of the second embodiment of the present invention.
  • Vector engines are mostly used in fighter aircraft, which use a turbojet engine with an afterburner.
  • Figure 3 and Figure 4 show the structural diagram of the rear half of the turbojet engine (the front compressor section is omitted). It can be seen from the figure that the core of the turbojet engine extends axially rearward, and after passing through the afterburner, there is a long cone at the end of it, which is the rudder 8 of the present invention. Shown is the normal state of the rudder 8, and Figure 2 shows the working state of the rudder. As can be seen from Fig. 3 and Fig.
  • a rudder fin 9 is designed on the rudder 8 which is a fin which is in the same direction as the central axis of the engine and which is perpendicular to the central axis.
  • the rudder fins 9 shown in Fig. 3 and Fig. 4 have four fins, which are evenly distributed at an angle of 90 degrees to the top, bottom, left and right directions.
  • the number, shape and size of the fins of the rudder fin 9 depend on factors such as fluid mechanics, material mechanics, and deflection force requirements. According to the fluid mechanics and Bernoulli principle, we know that the addition of the rudder fin 9 will greatly increase the deflection force that the rudder 8 brings to the engine.
  • This deflection force is more direct and stronger than the force and reaction force of the airflow.
  • the reaction is also more agile.
  • its position is located in the central axis of the engine, it has a large design space, which is convenient for installing the deflection mechanism. It is simpler and less difficult to design the mechanical structure on the outer wall of the engine.
  • the invention utilizes the principles of force and reaction force, the principle of fluid mechanics and the principle of Bernoulli, and has scientific theoretical support.
  • the tail rudder designed by the invention is located at the central axis of the engine, has a large design space, is convenient for installing the deflection mechanism, has a simple structure and low technical difficulty, and is favorable for turning the theory into reality.
  • the use of the rudder fins of the present invention according to the principles of fluid mechanics and Bernoulli, we know that in high-speed airflow, the rudder fins will obtain a very large deflection force, which is much stronger than the force and reaction force of the airflow. Larger and more direct, the aircraft can get more rapid, agile and efficient vector thrust.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种尾舵式矢量发动机，它利用作用力与反作用力原理、流体力学原理、伯努利原理，通过在喷气式发动机核心机中心轴的尾端，设计向后延伸、可以进行角度偏转的尾舵，当喷气式发动机的高压气流流过尾舵时，通过尾舵的偏转产生"尾巴效应"，改变发动机的推力方向；在尾舵上的舵鳍在高速气流中可以获得比气流的作用力与反作用力更大、更直接的偏转力，使飞机的姿态调整更加迅猛、敏捷、高效。该尾舵式矢量发动机具有结构简单、技术难度低的特点。

Description

尾舵式矢量发动机 技术领域
本发明涉及一种尾舵式矢量发动机，它通过在喷气式发动机核心机的尾端加装尾舵的方式，实现对飞行器的姿态控制，起到与矢量发动机相类似的可以改变推力方向的效果，属航空发动机技术领域。
背景技术
现有喷气式飞机的姿态控制，主要通过水平尾翼、垂直尾翼、鸭翼或直接由机翼来完成。新的矢量发动机可通过发动机尾喷口的偏转，改变喷气方向来调整推力方向，实现对飞机的姿态控制，但该技术实现难度较大。美国的方案是采用矩形喷口，上下方向各有一个偏转板，可以分别在上下方向进行小角度偏转，以改变喷气方向，虽然结构简单，但无法360度转向，属于二元推力矢量发动机；俄罗斯的方案是将尾喷口与发动机球形铰接，以实现尾喷口的360度转向，虽然结构复杂，但可提供全方向推力，属于多元推力矢量发动机。2016年1月14日，本人向中国国家知识产权局提交了“一种舵式矢量发动机”(申请号：201610029666.9)的专利申请，提出了一种在尾喷口设计水平舵和垂直舵，通过调整舵面角度实现发动机的多元矢量推力的技术解决方案，本发明在这一技术方案的基础上作进一步补充，是“一种舵式矢量发动机”技术方案的延续。
技术问题
现有的矢量发动机是利用改变发动机尾喷口的喷气方向，利用作用与反作用力原理改变发动机推力方向，其存在的主要问题是结构设计难度大、使用寿命低。
技术解决方案
本发明从动物尾巴具有控制身体姿态及转向的作用中获得灵感，提出在喷气式发动机核心机尾端加装一个“尾巴”形式的尾舵，通过“尾巴效应”改变发动机的推力方向。本发明的技术解决方案：在喷气式发动机核心机中心轴的尾端，设计有向后延伸的、可以进行角度偏转的尾舵，当喷气式发动机的高压气流流过尾舵时，通过尾舵的偏转产生“尾巴效应”，改变发动机的推力方向；所述的尾舵为一个圆锥体；所述的尾舵上有舵鳍，舵鳍是与发动机中心轴同方向，且垂直于中心轴的鳍片；所述的舵鳍有4个鳍片，互相成90度角均匀分布于上、下、左、右4个方向；所述的尾舵由首尾相互连接的两个以上尾舵组成。
有益效果
通过在喷气式发动机核心机中心轴的尾端设计可以进行角度偏转的尾舵，在尾舵上设计舵鳍，不仅仅利用了喷气气流的作用力与反作用力，还利用了流体力学原理和伯努利原理，其获得的偏转力更大、更直接、更敏捷，结构设计更简单，难度更低。
附图说明
附图1是本发明实施例之一的结构示意图
附图2是本发明实施例之一的工作原理图
附图3是本发明实施例之二的结构示意图
附图4是本发明实施例之二的工作原理图
附图5是本发明实施例之三的工作原理图
图中，1是风扇、2是压气机、3是外涵道、4是内涵道、5是燃烧室、6是涡轮、7是加力燃烧室、8是尾舵、9是舵鳍
本发明的最佳实施方式
图3、图4所示的本发明实施例之二是本发明的最佳实施方式。它不仅设计了尾舵，还在尾舵上设计了舵鳍，不仅利用了作用力与反作用力原理，还利用了流体力学原理和伯努利原理，为发动机提供更加迅猛、敏捷、高效的偏转力。
本发明的实施方式
对照附图1、2，图1是本发明实施例之一的结构示意图、图2是本发明实施例之一的工作原理图。图1、图2是一个涡扇发动机的结构图。从图中可以看出，在涡扇发动机核心机中心轴的尾端，有一个长长的圆锥体，就是本发明的尾舵8，图1显示的是尾舵8的正常状态，图2显示的是尾舵的工作状态。从图2可以看出，尾舵2在发动机的高速尾流中进行了偏转， 根据流体力学和伯努利原理我们可以知道，发动机的推力方向也将会发生偏转。
对照附图3、4，图3是本发明实施例之二的结构示意图、图4是本发明实施例之二的工作原理图。矢量发动机多用于战斗机，其使用的是具有加力燃烧室的涡喷发动机。图3、图4显示的就是涡喷发动机后半部分的结构图(省略了前面压气机部分)。从图中可以看出，涡喷发动机核心机的中心轴向后一直延伸，穿过加力燃烧室后，在其尾端有一个长长的圆锥体，就是本发明的尾舵8，图1显示的是尾舵8的正常状态，图2显示的是尾舵的工作状态。对照图3、图4还可以看出，在尾舵8上设计有舵鳍9，舵鳍9是与发动机中心轴同方向，且垂直于中心轴的鳍片。图3、图4显示的舵鳍9有4个鳍片，互相成90度角均匀分布于上、下、左、右4个方向。舵鳍9的鳍片数量、形状及大小取决于流体力学、材料力学以及偏转力需求等因素。根据流体力学和伯努利原理我们知道，舵鳍9的加入，将极大地增大尾舵8带给发动机的偏转力，这种偏转力也较气流的作用力与反作用力更加直接，力量更大，反应也更加敏捷。同时，由于其位置位于发动机中心轴，有较大的设计空间，便于安装偏转机构，较在发动机外壁上设计机械结构更简单，难度更低。
当然，如图5所示，我们也可以设计由首尾相互连接的两个以上尾舵组成的更像“尾巴”一样的尾舵，通过可连续偏转的多节尾舵，来扩大“尾巴效应”，获得平衡、流畅的偏转力，虽然这样的设计结构会非常复杂。
工业实用性
本发明利用了作用力与反作用力原理、流体力学原理、伯努利原理，具有科学的理论支撑。本发明设计的尾舵位于发动机中心轴，有较大的设计空间，便于安装偏转机构，结构简单，技术难度较低，有利于将理论转变为现实。尤其是本发明中舵鳍的使用，根据流体力学和伯努利原理我们知道，在高速气流中，舵鳍会获得非常大的偏转力，这种偏转力要远比气流的作用力与反作用力更大、更直接，使飞机可以获得更加迅猛、敏捷、高效的矢量推力。

Claims (5)

  1. 尾舵式矢量发动机，其特征是：所述的喷气式发动机核心机中心轴的尾端，设计有向后延伸的、可以进行角度偏转的尾舵，当喷气式发动机的高压气流流过尾舵时，通过尾舵的偏转产生“尾巴效应”，改变发动机的推力方向。
  2. 根据权利要求1所述的尾舵式矢量发动机，其特征是：所述的尾舵为一个圆锥体。
  3. 根据权利要求1所述的尾舵式矢量发动机，其特征是：所述的尾舵上有舵鳍，舵鳍是与发动机中心轴同方向，且垂直于中心轴的鳍片。
  4. 根据权利要求3所述的尾舵式矢量发动机，其特征是：所述的舵鳍有4个鳍片，互相成90度角均匀分布于上、下、左、右4个方向。
  5. 根据权利要求1所述的尾舵式矢量发动机，其特征是：所述的尾舵由首尾相互连接的两个以上尾舵组成。
PCT/CN2016/095927 2016-01-14 2016-08-18 尾舵式矢量发动机 WO2017121115A1 (zh)

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CN113374596B (zh) * 2021-06-21 2022-05-31 中国航发沈阳发动机研究所 一种高隐身二元喷管结构
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CN114320658A (zh) * 2022-01-19 2022-04-12 河北福莱卡航空科技有限公司 一种应用于小型涡喷发动机的推力矢量喷口及其设计方法
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