WO2017121114A1 - Vector engine having rudders - Google Patents

Vector engine having rudders Download PDF

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Publication number
WO2017121114A1
WO2017121114A1 PCT/CN2016/095926 CN2016095926W WO2017121114A1 WO 2017121114 A1 WO2017121114 A1 WO 2017121114A1 CN 2016095926 W CN2016095926 W CN 2016095926W WO 2017121114 A1 WO2017121114 A1 WO 2017121114A1
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Prior art keywords
rudder
engine
horizontal
vertical
tail
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PCT/CN2016/095926
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French (fr)
Chinese (zh)
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王佐良
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王佐良
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Publication of WO2017121114A1 publication Critical patent/WO2017121114A1/en

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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
    • F02K1/04—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
    • F02K1/002—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
    • F02K1/78—Other construction of jet pipes

Definitions

  • the invention relates to a rudder type vector engine, which realizes attitude control of an aircraft by adding a rudder at a tail nozzle of a jet engine, and has the effect of changing the thrust direction similar to a vector engine, and belongs to an aeroengine.
  • a rudder type vector engine which realizes attitude control of an aircraft by adding a rudder at a tail nozzle of a jet engine, and has the effect of changing the thrust direction similar to a vector engine, and belongs to an aeroengine.
  • 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 present invention proposes a third technical solution that is different from the above two technical solutions in order to obtain an effect similar to the vector engine that can change the thrust direction while reducing the technical difficulty of implementation.
  • 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 technical solution of the invention is to design a horizontal rudder at the tail nozzle of the jet engine, and the high-speed airflow from the tail nozzle flows through the horizontal rudder, and the binary vector thrust of the engine is realized by adjusting the angle of the rudder surface of the horizontal rudder;
  • the rudder arm is connected to the rudder bearing, and the rudder bearing is connected to the engine body.
  • the rudder is rotated to the bearing with the engine shaft as the axis, and the horizontal rudder is driven to rotate with the engine shaft as the axis, and the horizontal rudder is along the axial direction thereof.
  • the upper and lower adjustment of the rudder angle is carried out to realize the multi-vector thrust of the engine; a vertical rudder can also be designed at the tail nozzle, and the vertical rudder and the horizontal rudder are at an angle of 90 degrees.
  • the horizontal rudder is matched.
  • the rudder angle is adjusted to realize the multi-vector thrust of the engine; the horizontal rudder and the vertical rudder can also be connected to the rudder bearing through the rudder arm, and the rudder bearing is rotated by the engine shaft as the axis, and the horizontal rudder and the vertical rudder are driven to the engine shaft.
  • the heart rotates for the shaft to realize the multi-vector thrust of the engine;
  • the horizontal or vertical rudder can also be designed to be two symmetrical parts Composition, respectively, can be rotated without using both sides of the end of the spout, the spout transfer end of the central region of the gas flow to reduce erosion at the time the steering member of the high-temperature air;
  • the present invention also provides the horizontal
  • the rudder or vertical rudder is designed inside the tail nozzle, for example, at the joint between the engine body and the tail nozzle, so that the horizontal rudder or the vertical rudder can be completely covered by the tail nozzle to block the inside of the tail nozzle, thereby improving the stealth design.
  • the stealth of combat aircraft The stealth of combat aircraft.
  • Figure 1 is a perspective view of one embodiment of the present invention
  • Figure 2 is a cross-sectional view showing the state 1 of the second embodiment of the present invention.
  • Figure 3 is a cross-sectional view showing the second state 2 of the embodiment of the present invention.
  • Figure 4 is a perspective view of the third embodiment of the present invention.
  • 1 is the engine body
  • 2 is the tail nozzle
  • 3 is the horizontal rudder
  • 4 is the rudder arm
  • 5 is the rudder tie rod
  • 6 is the rudder bearing
  • 7 is the vertical rudder
  • A-A' is the engine shaft
  • B-B' is the axis of the horizontal rudder's own rotating shaft
  • C-C' is the axis of the vertical rudder's own rotating shaft.
  • the third embodiment of the present invention shown in Fig. 4 is a preferred embodiment of the present invention, and its main feature is that the structure is simple and the reaction is rapid.
  • FIG. 1 there is shown a perspective view of one of the embodiments of the present invention.
  • the jet engine tail nozzle 2 is designed with a horizontal rudder 3, and the high-speed airflow from the engine tail nozzle 2 flows through the horizontal rudder 3, so that when we adjust the rudder angle of the horizontal rudder 3, even if the horizontal rudder 3 is along itself
  • the thrust direction of the engine can be changed in the vertical direction in the axial direction of the engine, thereby realizing the binary vector thrust of the engine.
  • the horizontal rudder 3 adjusts the rudder surface angle up and down along its own axis B-B'.
  • the rudder surface rod 5 is designed for the horizontal rudder 3, and the rudder rod 5 can be driven by the motor to adjust the level.
  • the horizontal rudder 3 is coupled to the rudder bearing 6 via a rudder arm 4, and the rudder bearing 6 is coupled to the engine body 1, and the rudder bearing 6 is rotatable about the engine axis A-A'.
  • the horizontal rudder 3 is driven to rotate on the axis A-A' of the engine, and the horizontal rudder 3 is adjusted up and down along the axial direction B-B' of the horizontal rudder 3 to realize the multi-vector thrust of the engine.
  • Fig. 2 is a cross-sectional view showing a state 1 of the embodiment of the present invention
  • Fig. 3 is a cross-sectional view showing a state 2 of the second embodiment of the present invention.
  • the structure of the second embodiment shown in FIG. 2 and FIG. 3 is basically the same as the structure of the embodiment shown in FIG. 1. The difference is that the horizontal rudder 3 is composed of two symmetrical left and right portions, when not in use. The left and right parts of the horizontal rudder can be rotated to the left and right sides of the tail nozzle 2 respectively, and the center area of the tail nozzle airflow is turned out.
  • the purpose of the design is to reduce the ablation time of the rudder body under high temperature airflow, thereby reducing the rudder to a certain extent.
  • High temperature technology for bulk materials Indicators extending the use time of the rudder, but the problems brought about by the structure will be relatively complex, the structural strength of the material is higher, and the requirements for the control system will also increase.
  • a horizontal rudder 3 can realize the multi-vector thrust of the engine, the rudder bearing 6 installed on the engine will have a higher structure, cost, and technical requirements.
  • the rudder is rotated toward the bearing 6. The speed is also very fast. Since the radius of the rudder to the bearing 6 is relatively large, it is not easy to make a quick turn. For this reason, we can also consider adding a vertical rudder on the basis of the horizontal rudder 3.
  • FIG 4 is a perspective view of a third embodiment of the present invention.
  • the jet engine tail nozzle 2 is based on the horizontal rudder 3, and a vertical rudder 7 is added.
  • the vertical rudder 7 is at an angle of 90 degrees with the horizontal rudder 3.
  • the rudder of the vertical rudder 7 is adjusted.
  • the angle of the plane even if the vertical rudder 7 adjusts the angle of the rudder surface along its own axis C-C', and then adjusts the angle of the rudder surface with the horizontal rudder 3 along its own axis B-B', the same can be achieved.
  • Vector thrust is a perspective view of a third embodiment of the present invention.
  • the jet engine tail nozzle 2 is based on the horizontal rudder 3, and a vertical rudder 7 is added.
  • the vertical rudder 7 is at an angle of 90 degrees with the horizontal rudder 3.
  • the rudder of the vertical rudder 7 is adjusted.
  • the angle of the plane even
  • the horizontal rudder 3 is connected to the rudder bearing 6 through the rudder arm 4, and the engine shaft A-A' is passed through the rudder bearing 6
  • the horizontal rudder 3 and the vertical rudder 7 are rotated by the engine shaft center A-A' to realize the multi-vector thrust of the engine. Since there are two rudders in the horizontal and vertical directions, the rudder bearing 6 only needs to rotate less than 90 degrees, the requirement for the rotational speed is lowered, and the response speed of the thrust change due to the rotation is also improved.
  • the vertical rudder 7 is designed to be composed of two symmetrical upper and lower parts, and can be rotated to the upper and lower sides of the tail spout 2 when not in use, and the airflow center area of the tail spout is turned out. To reduce the ablation time of the rudder body under high temperature airflow.
  • 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 horizontal rudder and the vertical rudder designed by the invention are simple in structure and low in technical difficulty, which is beneficial to turning the theory into reality.
  • the horizontal rudder and the vertical rudder in the present invention obtain a deflection force in a high-speed airflow much more than a change in the jet direction of the tail nozzle, and the deflection force by the force and the reaction force of the airflow is larger and more direct, so that the aircraft can obtain 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

A vector engine having rudders. A horizontal rudder (3) and a vertical rudder (7) processed with a heat-resistant material having a high technical specification are installed at a jet nozzle (2) of a jet engine. By adjusting angles of control surfaces of the horizontal rudder (3) and the vertical rudder (7), the present invention provides the effect of changing a thrust direction of the engine and realizes a multiple-vector thrust of the engine. The horizontal rudder (3) or the vertical rudder (7) are both designed to be composed of two symmetrical parts which, when not in use, can rotate to two sides of the jet nozzle (2) respectively to be outside of a central region of air flows of the jet nozzle (2) so as to reduce a burning time of the rudders under high-temperature air flows. The horizontal rudder (3) or the vertical rudder (7) are designed to be disposed at an inner side of the jet nozzle (2), such that the horizontal rudder (3) or the vertical rudder (7) are fully covered by a tail pipe and shielded inside of the jet nozzle (2), thereby improving the stealth of a fighter aircraft having a stealth design. The vector engine having rudders is characterized by a simple structure and low technical difficulty.

Description

一种舵式矢量发动机Rudder type vector engine 技术领域Technical field
本发明涉及一种舵式矢量发动机，它通过在喷气式发动机的尾喷口加装舵的方式，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。The invention relates to a rudder type vector engine, which realizes attitude control of an aircraft by adding a rudder at a tail nozzle of a jet engine, and has the effect of changing the thrust direction similar to a vector engine, and belongs to an aeroengine. Technical field.
背景技术Background technique
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。本发明拟提出有别于上述两种技术解决方案的第三种技术解决方案，以期获得与矢量发动机相类似的可以改变推力方向的效果，同时降低实现的技术难度。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. Although 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. Although the structure is complex, it can provide omnidirectional thrust and belongs to a multi-thrust vector engine. The present invention proposes a third technical solution that is different from the above two technical solutions in order to obtain an effect similar to the vector engine that can change the thrust direction while reducing the technical difficulty of implementation.
技术问题 technical problem
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。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.
技术解决方案Technical solution
虽然喷气式发动机尾喷口的气流温度极高，但随着耐高温材料技术的发展，使得我们也可以提出直接在喷气式发动机尾喷口加装舵，通过舵面在垂直于发动机中心轴的自身转动轴方向上角度调整，以及舵在发动机中心轴方向上的转动，起到改变发动机推力方向的效果，获得对飞行器更加敏捷、高效的姿态控制，同时降低实现的技术难度。本发明的技术解决方案：在喷气式发动机尾喷口设计一个水平舵，尾喷口喷出的高速气流流过水平舵，通过调整水平舵的舵面角度，实现发动机的二元矢量推力；水平舵通过舵臂连接在舵向轴承上，舵向轴承连接在发动机机身上，通过舵向轴承以发动机轴心为轴的转动，带动水平舵以发动机轴心为轴转动，配合水平舵沿自身轴向进行的舵面角度的上下调整，实现发动机的多元矢量推力；还可以在尾喷口设计一个垂直舵，垂直舵与水平舵成90度夹角，通过调整垂直舵的舵面角度，配合水平舵的舵面角度调整，实现发动机的多元矢量推力；水平舵、垂直舵也可以通过舵臂连接在舵向轴承上，通过舵向轴承以发动机轴心为轴转动，带动水平舵、垂直舵以发动机轴心为轴转动，实现发动机的多元矢量推力；还可以将水平舵或垂直舵设计成由相互对称的两部分组成，不使用时可以分别向尾喷口的两侧旋转，转出尾喷口气流中心区域，以减少舵体在高温气流下的烧蚀时间；本发明还提出了将水平 舵或垂直舵设计在尾喷口内侧，比如设计在发动机机身与尾喷口的连接处，这样，水平舵或垂直舵就可以完全被尾喷管包裹遮挡在尾喷口里面，从而提高采用隐身设计的作战飞机的隐身性。Although the airflow temperature of the jet nozzle is extremely high, with the development of high temperature resistant material technology, we can also propose to add the rudder directly to the jet nozzle of the jet engine, and rotate itself through the rudder surface perpendicular to the central axis of the engine. The angle adjustment in the axial direction and the rotation of the rudder in the direction of the engine central axis play the role of changing the direction of the engine thrust, obtaining a more agile and efficient attitude control of the aircraft, and at the same time reducing the technical difficulty of implementation. The technical solution of the invention is to design a horizontal rudder at the tail nozzle of the jet engine, and the high-speed airflow from the tail nozzle flows through the horizontal rudder, and the binary vector thrust of the engine is realized by adjusting the angle of the rudder surface of the horizontal rudder; The rudder arm is connected to the rudder bearing, and the rudder bearing is connected to the engine body. The rudder is rotated to the bearing with the engine shaft as the axis, and the horizontal rudder is driven to rotate with the engine shaft as the axis, and the horizontal rudder is along the axial direction thereof. The upper and lower adjustment of the rudder angle is carried out to realize the multi-vector thrust of the engine; a vertical rudder can also be designed at the tail nozzle, and the vertical rudder and the horizontal rudder are at an angle of 90 degrees. By adjusting the angle of the rudder surface of the vertical rudder, the horizontal rudder is matched. The rudder angle is adjusted to realize the multi-vector thrust of the engine; the horizontal rudder and the vertical rudder can also be connected to the rudder bearing through the rudder arm, and the rudder bearing is rotated by the engine shaft as the axis, and the horizontal rudder and the vertical rudder are driven to the engine shaft. The heart rotates for the shaft to realize the multi-vector thrust of the engine; the horizontal or vertical rudder can also be designed to be two symmetrical parts Composition, respectively, can be rotated without using both sides of the end of the spout, the spout transfer end of the central region of the gas flow to reduce erosion at the time the steering member of the high-temperature air; The present invention also provides the horizontal The rudder or vertical rudder is designed inside the tail nozzle, for example, at the joint between the engine body and the tail nozzle, so that the horizontal rudder or the vertical rudder can be completely covered by the tail nozzle to block the inside of the tail nozzle, thereby improving the stealth design. The stealth of combat aircraft.
有益效果Beneficial effect
通过在喷气式发动机尾喷口设计水平舵和垂直舵，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。By designing the horizontal rudder and the vertical rudder at the tail nozzle of the jet engine, not only the force and reaction force of the jet stream but also the principle of fluid mechanics and the Bernoulli principle are utilized, which obtains a larger and more direct deflection force. More agile, structural design is simpler and less difficult.
附图说明DRAWINGS
附图1是本发明实施例之一的立体图Figure 1 is a perspective view of one embodiment of the present invention
附图2是本发明实施例之二状态1的剖面图Figure 2 is a cross-sectional view showing the state 1 of the second embodiment of the present invention.
附图3是本发明实施例之二状态2的剖面图Figure 3 is a cross-sectional view showing the second state 2 of the embodiment of the present invention.
附图4是本发明实施例之三的立体图Figure 4 is a perspective view of the third embodiment of the present invention.
图中，1是发动机机身、2是尾喷口、3是水平舵、4是舵臂、5是舵面拉杆、6是舵向轴承、7是垂直舵、A-A'是发动机轴心、B-B'是水平舵自身转动轴轴心、C-C'是垂直舵自身转动轴轴心In the figure, 1 is the engine body, 2 is the tail nozzle, 3 is the horizontal rudder, 4 is the rudder arm, 5 is the rudder tie rod, 6 is the rudder bearing, 7 is the vertical rudder, A-A' is the engine shaft, B-B' is the axis of the horizontal rudder's own rotating shaft, and C-C' is the axis of the vertical rudder's own rotating shaft.
本发明的最佳实施方式BEST MODE FOR CARRYING OUT THE INVENTION
附图4所示的本发明实施例之三是本发明的最佳实施方式，其主要特点是结构简单、反应迅速。 The third embodiment of the present invention shown in Fig. 4 is a preferred embodiment of the present invention, and its main feature is that the structure is simple and the reaction is rapid.
本发明的实施方式Embodiments of the invention
对照附图1，图1本发明实施例之一的立体图。图中，喷气式发动机尾喷口2设计了一个水平舵3，发动机尾喷口2喷出的高速气流流过水平舵3，这样，当我们调整水平舵3的舵面角度，即使水平舵3沿自身的轴向B-B'进行舵面角度的上下调整时，便可以使发动机的推力方向在飞机轴向上产生上下方向上的变化，从而实现发动机的二元矢量推力。Referring to Figure 1, there is shown a perspective view of one of the embodiments of the present invention. In the figure, the jet engine tail nozzle 2 is designed with a horizontal rudder 3, and the high-speed airflow from the engine tail nozzle 2 flows through the horizontal rudder 3, so that when we adjust the rudder angle of the horizontal rudder 3, even if the horizontal rudder 3 is along itself When the axial direction B-B' is adjusted up and down the angle of the steering surface, the thrust direction of the engine can be changed in the vertical direction in the axial direction of the engine, thereby realizing the binary vector thrust of the engine.
实现水平舵3沿自身轴向B-B'进行舵面角度上下调整的技术解决方案很多，图1中为水平舵3设计了舵面拉杆5，通过马达驱动舵面拉杆5，即可调整水平舵3的舵面角度。There are many technical solutions for the horizontal rudder 3 to adjust the rudder surface angle up and down along its own axis B-B'. In Figure 1, the rudder surface rod 5 is designed for the horizontal rudder 3, and the rudder rod 5 can be driven by the motor to adjust the level. The rudder angle of the rudder 3.
从图1可知，我们只需要让水平舵3也可以同时在发动机轴心方向上转动，配合水平舵3的舵面角度调整，就可以实现发动机的多元矢量推力。As can be seen from Fig. 1, we only need to make the horizontal rudder 3 also rotate in the direction of the engine axis, and the rudder surface angle adjustment of the horizontal rudder 3 can realize the multi-vector thrust of the engine.
对照附图1，水平舵3通过舵臂4连接在舵向轴承6上，舵向轴承6连接在发动机机身1上，舵向轴承6可以以发动机轴心A-A'为轴转动，从而带动水平舵3以发动机轴心A-A'为轴转动，配合水平舵3沿自身轴向B-B'进行舵面角度的上下调整，实现发动机的多元矢量推力。Referring to Figure 1, the horizontal rudder 3 is coupled to the rudder bearing 6 via a rudder arm 4, and the rudder bearing 6 is coupled to the engine body 1, and the rudder bearing 6 is rotatable about the engine axis A-A'. The horizontal rudder 3 is driven to rotate on the axis A-A' of the engine, and the horizontal rudder 3 is adjusted up and down along the axial direction B-B' of the horizontal rudder 3 to realize the multi-vector thrust of the engine.
对照附图2、3，图2是本发明实施例之二状态1的剖面图、图3是本发明实施例之二状态2的剖面图。图2、图3所示的实施例之二的结构与图1所示的实施例之一的结构是基本相同的，所不同的是水平舵3由相互对称的左右两部分组成，不使用时水平舵的左右两部分可以分别向尾喷口2的左右两侧旋转，转出尾喷口气流中心区域，这样设计的目的是可以减少舵体在高温气流下的烧蚀时间，从而一定程度地降低舵体材料的耐高温技术 指标，延长舵的使用时间，但带来的问题除了结构会相对复杂、材料结构强度要求更高之外，对控制***的要求也会随之提高。2 and 3, Fig. 2 is a cross-sectional view showing a state 1 of the embodiment of the present invention, and Fig. 3 is a cross-sectional view showing a state 2 of the second embodiment of the present invention. The structure of the second embodiment shown in FIG. 2 and FIG. 3 is basically the same as the structure of the embodiment shown in FIG. 1. The difference is that the horizontal rudder 3 is composed of two symmetrical left and right portions, when not in use. The left and right parts of the horizontal rudder can be rotated to the left and right sides of the tail nozzle 2 respectively, and the center area of the tail nozzle airflow is turned out. The purpose of the design is to reduce the ablation time of the rudder body under high temperature airflow, thereby reducing the rudder to a certain extent. High temperature technology for bulk materials Indicators, extending the use time of the rudder, but the problems brought about by the structure will be relatively complex, the structural strength of the material is higher, and the requirements for the control system will also increase.
虽然一个水平舵3就可以实现发动机的多元矢量推力，但在发动机上安装舵向轴承6除了结构、成本、技术要求都会比较高外，为了获得对战斗机转向的快速响应，舵向轴承6的转动速度也要非常快，由于舵向轴承6的半径比较大，要做到快速转动并不容易，为此，我们还可以考虑在水平舵3的基础上，增加一个垂直舵。Although a horizontal rudder 3 can realize the multi-vector thrust of the engine, the rudder bearing 6 installed on the engine will have a higher structure, cost, and technical requirements. In order to obtain a quick response to the steering of the fighter, the rudder is rotated toward the bearing 6. The speed is also very fast. Since the radius of the rudder to the bearing 6 is relatively large, it is not easy to make a quick turn. For this reason, we can also consider adding a vertical rudder on the basis of the horizontal rudder 3.
对照附图4，图4是本发明实施例之三的立体图。图中，喷气式发动机尾喷口2在水平舵3的基础上，增加了一个垂直舵7，垂直舵7与水平舵3成90度夹角，我们知道，此时，通过调整垂直舵7的舵面角度，即使垂直舵7沿自身轴向C-C'进行舵面角度的左右调整，再配合水平舵3沿自身轴向B-B'进行舵面角度的上下调整，同样可以实现发动机的多元矢量推力。Referring to Figure 4, Figure 4 is a perspective view of a third embodiment of the present invention. In the figure, the jet engine tail nozzle 2 is based on the horizontal rudder 3, and a vertical rudder 7 is added. The vertical rudder 7 is at an angle of 90 degrees with the horizontal rudder 3. We know that at this time, the rudder of the vertical rudder 7 is adjusted. The angle of the plane, even if the vertical rudder 7 adjusts the angle of the rudder surface along its own axis C-C', and then adjusts the angle of the rudder surface with the horizontal rudder 3 along its own axis B-B', the same can be achieved. Vector thrust.
当然，我们同样也还是可以继续延用舵向轴承6的设计，将水平舵3、垂直舵7通过舵臂4连接在舵向轴承6上，通过舵向轴承6以发动机轴心A-A'为轴的转动，带动水平舵3、垂直舵7以发动机轴心A-A'为轴转动，实现发动机的多元矢量推力。由于有水平和垂直方向的两个舵，舵向轴承6只需要进行小于90度的转动即可，对转动速度的要求降低了，转动带来的推力变化的响应速度也提高了。Of course, we can still continue to use the rudder to the design of the bearing 6, the horizontal rudder 3, the vertical rudder 7 is connected to the rudder bearing 6 through the rudder arm 4, and the engine shaft A-A' is passed through the rudder bearing 6 For the rotation of the shaft, the horizontal rudder 3 and the vertical rudder 7 are rotated by the engine shaft center A-A' to realize the multi-vector thrust of the engine. Since there are two rudders in the horizontal and vertical directions, the rudder bearing 6 only needs to rotate less than 90 degrees, the requirement for the rotational speed is lowered, and the response speed of the thrust change due to the rotation is also improved.
同样，我们也可以参照实施例之二的设计，将垂直舵7设计为由相互对称的上下两部分组成，不使用时可以分别向尾喷口2的上下两侧旋转，转出尾喷口气流中心区域，以减少舵体在高温气流下的烧蚀时间。 Similarly, we can also refer to the design of the second embodiment, the vertical rudder 7 is designed to be composed of two symmetrical upper and lower parts, and can be rotated to the upper and lower sides of the tail spout 2 when not in use, and the airflow center area of the tail spout is turned out. To reduce the ablation time of the rudder body under high temperature airflow.
上述各实施例中，虽然附图均显示水平舵或垂直舵位于尾喷口的外侧，但实际上，我们完成可以将水平舵或垂直舵设计在尾喷口的内侧，比如设计在发动机机身1与尾喷口2的连接处，这样，水平舵或垂直舵就可以完全被尾喷管包裹遮挡在尾喷口里面，从而提高采用隐身设计的作战飞机的隐身性，我们需要的，只是技术指标足够高的耐热材料。In the above embodiments, although the drawings show that the horizontal rudder or the vertical rudder is located outside the tail spout, in fact, we can design the horizontal rudder or the vertical rudder on the inner side of the tail spout, for example, in the engine body 1 and The junction of the tail nozzle 2, so that the horizontal rudder or the vertical rudder can be completely covered by the tail nozzle to block the inside of the tail nozzle, thereby improving the stealth of the stealth-designed combat aircraft. What we need is only a sufficiently high technical index. Heat resistant material.
工业实用性Industrial applicability
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。本发明设计的水平舵、垂直舵结构简单，技术难度低，有利于将理论转变为现实。本发明中的水平舵、垂直舵在高速气流中获得的偏转力要远比改变尾喷口的喷气方向，利用气流的作用力与反作用力带来的偏转力更大、更直接，使飞机可以获得更加迅猛、敏捷、高效的矢量推力。 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 horizontal rudder and the vertical rudder designed by the invention are simple in structure and low in technical difficulty, which is beneficial to turning the theory into reality. The horizontal rudder and the vertical rudder in the present invention obtain a deflection force in a high-speed airflow much more than a change in the jet direction of the tail nozzle, and the deflection force by the force and the reaction force of the airflow is larger and more direct, so that the aircraft can obtain More rapid, agile, and efficient vector thrust.

Claims (7)

  1. 一种舵式矢量发动机，其特征是：所述的喷气式发动机尾喷口(2)有水平舵(3)，发动机尾喷口(2)喷出的高速气流流过水平舵(3)，通过调整水平舵(3)的舵面角度，即使水平舵(3)沿自身的轴向(B-B')进行舵面角度的上下调整，实现发动机的二元矢量推力。A rudder type vector engine, characterized in that: the jet engine tail nozzle (2) has a horizontal rudder (3), and the high-speed airflow ejected from the engine tail vent (2) flows through the horizontal rudder (3), and is adjusted The rudder angle of the horizontal rudder (3) enables the binary vector thrust of the engine even if the horizontal rudder (3) adjusts the upper and lower rudder angles along its own axial direction (B-B').
  2. 根据权利要求1所述的一种舵式矢量发动机，其特征是：所述的水平舵(3)通过舵臂(4)连接在舵向轴承(6)上，舵向轴承(6)连接在发动机机身(1)上，舵向轴承(6)以发动机轴心(A-A')为轴转动，带动水平舵(3)以发动机轴心(A-A')为轴转动，配合水平舵(3)沿自身轴向(B-B')进行的舵面角度的上下调整，实现发动机的多元矢量推力。A rudder type vector engine according to claim 1, wherein said horizontal rudder (3) is coupled to the rudder bearing (6) via a rudder arm (4), and the rudder bearing (6) is coupled thereto. On the engine body (1), the rudder bearing (6) rotates with the engine shaft center (A-A') as the axis, and drives the horizontal rudder (3) to rotate with the engine shaft center (A-A') as the axis. The rudder (3) adjusts the angle of the rudder surface along its own axis (B-B') to achieve multi-vector thrust of the engine.
  3. 根据权利要求1所述的一种舵式矢量发动机，其特征是：所述的喷气式发动机尾喷口(2)有垂直舵(7)，垂直舵(7)与水平舵(3)成90度夹角，通过调整垂直舵(7)的舵面角度，即使垂直舵(7)沿自身的轴向(C-C')进行舵面角度的左右调整，配合水平舵(3)沿自身轴向(B-B')进行的舵面角度的上下调整，实现发动机的多元矢量推力。A rudder vector engine according to claim 1, wherein said jet engine tail nozzle (2) has a vertical rudder (7), and the vertical rudder (7) is at 90 degrees to the horizontal rudder (3). Angle, by adjusting the angle of the rudder surface of the vertical rudder (7), even if the vertical rudder (7) adjusts the angle of the rudder surface along its own axis (C-C'), the horizontal rudder (3) is aligned along its own axis. (B-B') The upper and lower adjustment of the rudder angle is carried out to realize the multivariate vector thrust of the engine.
  4. 根据权利要求3所述的一种舵式矢量发动机，其特征是：所述的水平舵(3)、垂直舵(7)通过舵臂(4)连接在舵向轴承(6)上，舵向轴承(6)连接在发动机机身(1)上，舵向轴承(6)以发动机轴心(A-A')为轴转动，带动水平舵(3)、垂直舵(7)以发动机轴心(A-A')为轴转动，实现发动机的多元矢量推力。 A rudder type vector engine according to claim 3, wherein said horizontal rudder (3) and vertical rudder (7) are coupled to the rudder bearing (6) via a rudder arm (4), and the rudder direction The bearing (6) is connected to the engine body (1), and the rudder bearing (6) is rotated about the engine shaft center (A-A'), and the horizontal rudder (3) and the vertical rudder (7) are driven to the engine shaft center. (A-A') is the rotation of the shaft to achieve the multi-vector thrust of the engine.
  5. 根据权利要求2或权利要求3所述的一种舵式矢量发动机，其特征是：所述的水平舵(3)由相互对称的左右两部分组成，不使用时可以分别向尾喷口(2)的左右两侧旋转，转出尾喷口气流中心区域；所述的垂直舵(7)由相互对称的上下两部分组成，不使用时可以分别向尾喷口(2)的上下两侧旋转，转出尾喷口气流中心区域。A rudder type vector engine according to claim 2 or claim 3, wherein said horizontal rudder (3) is composed of two symmetrical left and right portions, and can be respectively tailed to the tail nozzle when not in use (2) Rotate the left and right sides to turn out the center area of the tail nozzle airflow; the vertical rudder (7) consists of two symmetrical upper and lower parts, which can be rotated to the upper and lower sides of the tail spout (2) when not in use. The center area of the tail vent airflow.
  6. 根据权利要求1所述的一种舵式矢量发动机，其特征是：所述的水平舵(3)位于尾喷口2的内侧，即水平舵(3)可完全被尾喷管包裹遮挡在尾喷口2里面。A rudder type vector engine according to claim 1, wherein said horizontal rudder (3) is located inside the tail spout 2, that is, the horizontal rudder (3) can be completely covered by the tail spout to block the tail spout. 2 inside.
  7. 根据权利要求3所述的一种舵式矢量发动机，其特征是：所述的水平舵(3)、垂直舵(7)位于尾喷口2的内侧，即水平舵(3)、垂直舵(7)可完全被尾喷管包裹遮挡在尾喷口2里面。 A rudder type vector engine according to claim 3, wherein said horizontal rudder (3) and vertical rudder (7) are located inside the tail spout 2, that is, a horizontal rudder (3) and a vertical rudder (7). ) can be completely covered by the tail nozzle to block inside the tail nozzle 2.
PCT/CN2016/095926 2016-01-14 2016-08-18 Vector engine having rudders WO2017121114A1 (en)

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