WO2020134005A1 - 具有非对称后体型面的喉道偏移式气动矢量喷管 - Google Patents

具有非对称后体型面的喉道偏移式气动矢量喷管 Download PDF

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Publication number
WO2020134005A1
WO2020134005A1 PCT/CN2019/094322 CN2019094322W WO2020134005A1 WO 2020134005 A1 WO2020134005 A1 WO 2020134005A1 CN 2019094322 W CN2019094322 W CN 2019094322W WO 2020134005 A1 WO2020134005 A1 WO 2020134005A1
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Prior art keywords
nozzle
profile
vector
rear body
angle
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English (en)
French (fr)
Inventor
黄帅
徐惊雷
汪阳生
蒋晶晶
陈匡世
汪丰
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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Priority to AU2019411947A priority Critical patent/AU2019411947B8/en
Publication of WO2020134005A1 publication Critical patent/WO2020134005A1/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
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners

Definitions

  • the present invention is directed to the increase of the throat offset pneumatic vector nozzle and provides a rear body structure with unequal vector angles, mainly by changing the rear body profile near the nozzle outlet, which is a throat offset pneumatic vector nozzle Increase the vector angle, and at the same time, provide the aircraft with unequal heading and bowing vector angles (ie pitch vector angles).
  • thrust vector aero engine to realize thrust vector function is thrust vector nozzle.
  • the traditional mechanical thrust vectoring nozzle has a complicated structure, poor reliability, and troublesome maintenance. Therefore, it is imminent to develop a thrust vector nozzle with simple structure, light weight and good maintainability.
  • the fluid thrust vector nozzle has gradually become the research focus and research hotspot of various countries due to its simple structure and light weight, and will enter engineering applications in the near future.
  • how to impart more functions to the fluid thrust vector nozzle under the premise of changing the nozzle structure as little as possible has become one of the new research directions of the thrust vector nozzle.
  • the throat offset pneumatic vector nozzle is a new type of fluid thrust vector nozzle that has emerged in recent years. Due to its simple structure, light weight and good vector performance, it is more and more popular.
  • the common throat offset pneumatic vector nozzle is a double throat structure, and the most common is that the area of the second throat is slightly larger than the area of the first throat.
  • the throat offset pneumatic vector nozzle can be divided into active active type and adaptive passive type, wherein the source of the active active type generating thrust vector air source is mostly an external compressor, a gas cylinder or from aviation
  • the bleed air in the high-pressure parts of the engine is characterized by a small change in the thrust vector angle with the nozzle pressure drop ratio, but the thrust loss is large for the entire aero-engine;
  • the adaptive passive type is
  • the self-adaptive bypass channel is set to direct the high-pressure airflow at the inlet of the nozzle to the specified position of the nozzle for injection, which generates disturbance and adaptively realizes the thrust vector, which overcomes the shortcomings of the active active type and affects the thrust of the aircraft engine.
  • the common throat offset pneumatic vector nozzles are mostly fixed geometry nozzles, which can only generate a single direction vector angle of about 20° (such as the pitch direction), and are commonly used to control the pitch direction of the aircraft.
  • a single direction vector angle of about 20° such as the pitch direction
  • the short-range takeoff and landing that countries around the world are vigorously developing has higher efficiency, simpler structure, and lower requirements for aircraft flight control systems, which are more sought after by countries around the world.
  • the inner profile and the outer profile (including the rear body) of the nozzle in active service are both binary up-down symmetry or ternary axisymmetric.
  • the asymmetrical binary nozzle configuration has gradually appeared, but there are few asymmetric aeroengine nozzles with thrust vectoring.
  • most of the nozzle configuration with asymmetric profile is the non-uniform expansion section of the deformed Laval nozzle (that is, the convergence-expansion nozzle), and very few have non-uniform convergence section, resulting in non-uniform engine jet flow.
  • the present invention realizes the enlargement of the nozzle thrust vector angle by changing the nozzle rear body profile and using the interaction of the asymmetric nozzle rear body profile with the engine jet, and at the same time, the head-up vector angle and the head-down vector angle (i.e. The pitch vector angle) is not equal.
  • the present invention addresses the shortcomings of the prior art, based on the existing design scheme of the throat offset pneumatic vector nozzle, when the inner profile of the nozzle is unchanged, the profile of the rear body of the nozzle is changed and its profile is asymmetric, The low pressure generated by the engine jet and the effect of the rear body enlarges the vector angle. At the same time, the asymmetry of the posterior body surface produces different low-pressure areas, which in turn produce unequal vector angles, which further improves the performance of the throat offset pneumatic vector nozzle.
  • a throat offset pneumatic vector nozzle with an asymmetric rear body profile includes a nozzle body, and the rear body profile of the nozzle body is arranged asymmetrically.
  • the rear body profile of the nozzle body one side profile is profile a, the other side profile is profile b; profile a, profile b
  • the axis of the tube body is arranged in an asymmetric structure, and the angle ⁇ between the profile a and the horizontal direction is not greater than 90°.
  • the angle ⁇ between the profile b and the horizontal direction is greater than 90°.
  • the angle ⁇ between the profile a and the horizontal direction has a value range of 45° ⁇ 75°.
  • the profile a is located on the lower side of the nozzle body.
  • the asymmetric rear body profile of the nozzle body is based on the existing vector nozzle body with a symmetric rear body profile, by extending the spray on the side of the existing vector nozzle body
  • the outer wall surface profile of the tube, the connection point of the side rear body profile and the outer wall surface profile of the nozzle is moved from point A to point B, and the connection point C of the side rear body profile and the inner wall surface of the nozzle remains unchanged While forming.
  • the nozzle body is on the side of the existing vector nozzle body, the extended nozzle outer wall surface profile is the nozzle extension AB, and the side rear body profile is the inclined surface BC;
  • the angle ⁇ between the inclined surface BC and the horizontal direction is adjustable, and the length of the nozzle extension AB is adjustable.
  • the angle ⁇ between the inclined surface BC and the horizontal direction has a value range of 45° ⁇ 75°; at this time, the nozzle body and the existing vector nozzle body are in the same nozzle When working with the pressure drop ratio, the aerodynamic vector angle of the nozzle body is 2°-5° larger than that of the existing vector nozzle body.
  • the profile of the inclined surface BC adjacent to the inner wall surface of the nozzle is a straight profile, and the profile of the inclined surface BC adjacent to the profile of the outer wall surface of the nozzle is an outwardly protruding curved surface, and a straight type Smooth transition between the surface and the protruding curved surface.
  • the present invention has the following advantages:
  • the invention realizes the improvement of the nozzle thrust performance, especially the mobility, and the simple structure by changing the rear body profile.
  • Figure 1 is a schematic diagram of a throat offset pneumatic vector nozzle with a symmetric rear body profile.
  • FIG. 2 is a schematic diagram of a throat offset pneumatic vector nozzle with an asymmetric rear body profile according to the present invention.
  • FIG 3 is a schematic diagram of a throat offset pneumatic vector nozzle with an asymmetric rear body profile according to the present invention (no reference numerals).
  • nozzle inlet 1 the first convergent section of the first throat 2, the first throat 3, the expansion section of the front of the second throat 4, the front convergent section of the second throat 5, the second throat (nozzle outlet) 6, rear ⁇ 7.
  • Body 7 the first throat, the first throat 3, the expansion section of the front of the second throat 4, the front convergent section of the second throat 5, the second throat (nozzle outlet) 6, rear ⁇ 7.
  • FIG. 5 is a calculation result of thrust coefficient and thrust vector angle of the throat offset pneumatic vector nozzle with an asymmetric rear body profile according to the present invention under a head down state.
  • spatially relative terms such as “above”, “above”, “above”, “above”, etc. can be used here to describe as shown in the figure The spatial relationship between a device or feature shown and other devices or features. It should be understood that spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation of the device described in the figures. For example, if the device in the drawings is turned upside down, a device described as “above another device or configuration” or “above another device or configuration” will then be positioned as “below other device or configuration” or “in Under other devices or structures”. Thus, the exemplary term “above” may include both “above” and “below” orientations. The device can also be positioned in other different ways (rotated 90 degrees or in other orientations).
  • the throat offset pneumatic vector nozzle with an asymmetric rear body profile is based on the same internal profile of the original throat offset pneumatic vector nozzle , Change its symmetrical rear body profile to an asymmetrical rear body profile, in which the angle between one side profile and the horizontal direction is not more than 90°, and the angle of the other side profile changes according to actual needs.
  • the connection between the end of the slope and the outer wall of the nozzle is continuous with the profile of the outer wall of the nozzle.
  • the specific profile is determined by the aircraft.
  • Throat offset pneumatic vector nozzle with asymmetric rear body profile whose core angle is enlarged and unequal is the asymmetry of the rear body profile, the size formed by the interaction between the engine jet and the asymmetric rear body profile
  • the low pressure area with different strengths promotes the engine jet to be closer to the wall surface, thereby realizing the enlargement of the vector angle.
  • the closer the jet is to the outlet wall the greater the intensity of the low-pressure region formed near the wall, and the lower the pressure, the greater the enlargement of the engine outlet jet vector angle.
  • the rear body angle of the fixed geometric rear body nozzle cannot be unlimited, and the vector angle follows the control variable (passive type: adaptive bypass opening, active Type: The secondary flow injected into the vicinity of a throat varies with varying degrees of linearity, and the optimal range is fixed.
  • ⁇ is the aerodynamic vector angle of the existing vector nozzle body.
  • the preferred value range of the angle ⁇ between the rear body profile on one side and the horizontal direction is 45° ⁇ 75°.
  • the nozzle vector performance of the body can be at a better value, and the aerodynamic vector angle of the nozzle body is 2°-5° larger than that of the symmetric rear body.
  • the posterior body of the throat offset pneumatic vector nozzle can be divided into a fixed geometric posterior body and a variable geometric posterior body.
  • a fixed geometry rear body in general, the angle between the rear body on one side and the horizontal direction is an acute angle, and there is no special requirement on the other side. ⁇ is mostly an obtuse angle to reduce drag.
  • the angle between the upper rear body of the nozzle and the horizontal direction that is, ⁇
  • the angle between the lower rear body and the horizontal direction that is, ⁇
  • the geometric angle of the rear body can be adjusted according to the working state of the engine and the nozzle to take into account the thrust vector performance and stealth performance Wait.
  • the preferred value range of the angle ⁇ between the lower rear body profile and the horizontal direction is 45° ⁇ 75°, above
  • the profile of the side rear body needs to be smooth, and the preferred angle is ⁇ >90°.
  • the upper rear body profile can be designed into a smooth curve using a more detailed design method, and the lower rear body profile and the initial profile near the exit (two throats) should be straight lines to avoid flat The problem of large initial vector angle or vector adjustment step caused by airflow wall flow in the flying state and the bowed vector state.
  • Later profiles can be designed as protruding curved surfaces.
  • variable geometry rear body there are many ways to drive the component, including but not limited to hydraulic actuation, guide rail drive, servo drive, etc.
  • the throat offset pneumatic vector nozzle with an asymmetric rear body profile includes a nozzle body, and the rear body profile of the nozzle body is arranged asymmetrically .
  • the profile on the upper side is profile a
  • the profile on the lower side is profile b
  • the angle ⁇ between the profile a and the horizontal direction is not greater than 90 °
  • the angle ⁇ between the profile b and the horizontal direction is greater than 90°
  • the profiles a and b are arranged in an asymmetric structure with respect to the axis of the nozzle body.
  • the range of the angle ⁇ between the profile a and the horizontal direction is 45° ⁇ 75°.
  • the asymmetric rear body profile of the nozzle body is based on the existing vector nozzle body with a symmetric rear body profile (as shown in Figure 1).
  • the figure is the lower nozzle outer wall surface profile, and the connection point of the side rear body profile and the nozzle outer wall surface profile is moved from point A to point B, and the side rear body profile and the nozzle are maintained
  • the connection point C of the wall surface is formed unchanged, as shown in FIG. 2.
  • the nozzle body is on the side of the existing vector nozzle body, the extended nozzle outer wall surface profile is the nozzle extension AB, and the side rear body profile is the inclined surface BC; the inclined surface BC is sandwiched by the horizontal direction
  • the angle ⁇ is adjustable, and the length of the nozzle extension AB is adjustable.
  • the aerodynamic vector angle of the nozzle body is larger than the aerodynamic vector angle of the existing vector nozzle with a symmetrical rear body by 2°-5°.
  • the profile adjacent to the inclined plane BC and the inner wall of the nozzle is a straight profile, while the profile adjacent to the profile line of the outer wall of the nozzle is a protruding curved surface, and the smooth transition between the straight profile and the protruding curved surface .
  • the calculation is made for a typical configuration of passive throat offset pneumatic vector nozzles, in which the angle of the upper posterior body is 90° and the angle of the other posterior body changes.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Nozzles (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

一种具有非对称后体型面的喉道偏移式气动矢量喷管，包括喷管本体，喷管本体的后体型面设置为非对称结构。在一般情况下，喷管出口外上下后体型面不对称，通过流出喷管出口的主流与非对称喷管后体相互作用产生的低压区，促进主流进一步贴近喷管后体壁面，实现了喷管矢量角的增加。同时，非对称的喷管后体壁面与喷管主流产生了强度不等、范围不同的相互作用，使得喷管俯仰矢量角不等。通过非对称的喷管后体型面设计，喉道偏移式气动矢量喷管的矢量角实现进一步增大，且俯仰矢量角不等大，并提高了喷管的红外隐身性能，满足了飞行器实际需求。

Description

具有非对称后体型面的喉道偏移式气动矢量喷管 技术领域
本发明针对喉道偏移式气动矢量喷管的增大并提供不等矢量角的后体结构，主要是通过改变喷管出口的附近的后体型面，为喉道偏移式气动矢量喷管增大矢量角，同时，为飞行器提供不等的抬头和低头矢量角(即俯仰矢量角)。
背景技术
随着科学技术的发展和实际需求的提高，未来飞行器将越来越多地使用推力矢量航空发动机。推力矢量航空发动机实现推力矢量功能的核心是推力矢量喷管。传统机械式推力矢量喷管结构复杂，可靠性差，维护麻烦。因此开发一种结构简单、重量轻、维护性好的推力矢量喷管迫在眉睫。
当下，流体推力矢量喷管逐渐以其结构简单、重量轻的特点成为各国的研究重点和研究热点，并将在不远的未来进入工程应用。同时，如何在尽可能少改变喷管结构的前提下为流体推力矢量喷管赋予更多的功能成为推力矢量喷管新的领域研究方向之一。
而喉道偏移式气动矢量喷管是近年来兴起的一种新型流体推力矢量喷管，凭借结构简单，重量轻、矢量性能好等的特点，受到越来越多的青睐。常见的喉道偏移式气动矢量喷管为双喉道结构，以二喉道面积略微比一喉道面积大最为常见。一般可以将喉道偏移式气动矢量喷管分为主动有源型和自适应无源型，其中主动有源型产生推力矢量气源的来源多为外置的压缩器、气瓶或者从航空发动机高压部件(多为压气机)中引气，其特点时推力矢量角随喷管工作落压比变化小，但对整台航空发动机来说推力损失较大；而自适应无源型则是设置自适应旁路通道将喷管入口位置的高压气流引至喷管的指定位置注入，自适应产生扰动并最终实现推力矢量，其克服了主动有源型的缺点，对航空发动机整机推力影响较小，矢量角也较为稳定。
常见的喉道偏移式气动矢量喷管多为固定几何喷管，仅仅能产生约20°左右的单一方向矢量角(如俯仰方向)，常见用于飞行器俯仰方向的控制。但从用途需求来说，世界各国目前大力发展的短距起降具有效率更高、结构更为简单、对于飞行器飞行控制系统的要求较低，更加受到世界各国的追捧。
一般来说，现役喷管内型面及外型面(含后体)均为二元上下对称或三元轴对称。但在未来，随着对于飞行器红外隐身要求的提高，型面不对称的二元喷管构型逐渐出现，但具有推力矢量功能的非对称航空发动机喷管少之又少。同时，型面不对称的喷管构型大多数是变形的拉瓦尔喷管(即收敛-扩张喷管)的扩张段非均匀，极少数也有收敛段非均匀，造成发动机喷流的非均匀。而本发明通过改变喷管后体型面，利用非对称的喷管后体型面与发动机喷流的相互作用，实现了对于喷管推力矢量角的放大，同时，抬头矢量角和低头矢量角(即俯仰矢量角)并不相等。
发明内容
本发明针对现有技术的不足，基于喉道偏移式气动矢量喷管现有的设计方案，在 喷管内型面不变的情况下，改变喷管后体型面并使其型面不对称，通过发动机喷流和后体作用产生的低压，放大矢量角。同时，后体型面的不对称产生了不同的低压区，进而产生了不相等的矢量角，实现了对于喉道偏移式气动矢量喷管性能的进一步提升。
为实现以上技术目的，本发明将采取以下的技术方案：
一种具有非对称后体型面的喉道偏移式气动矢量喷管，包括喷管本体，所述喷管本体的后体型面呈非对称设置。
作为本发明的一个优选实施例，所述喷管本体的后体型面，其中的一侧型面为型面a，另一侧型面则为型面b；型面a、型面b关于喷管本体的轴线呈非对称结构设置，且型面a与水平方向的夹角α不大于90°。
作为本发明的一个优选实施例，型面b与水平方向的夹角β大于90°。
作为本发明的一个优选实施例，型面a与水平方向的夹角α的取值范围为45°≤α≤75°。
作为本发明的一个优选实施例，型面a位于喷管本体的下侧。
作为本发明的一个优选实施例，所述喷管本体的非对称后体型面，以具有对称后体型面的既有矢量喷管本体为基础，通过延长该既有矢量喷管本体一侧的喷管外壁面型线，将该侧后体型面与喷管外壁面型线的连接位点从点A后移至点B，并保持该侧后体型面与喷管内壁面的连接位点C不变而形成。
作为本发明的一个优选实施例，所述的喷管本体在既有矢量喷管本体一侧，所延长的喷管外壁面型线为喷管延长段AB，该侧后体型面为斜面BC；所述斜面BC与水平方向的夹角α可调，所述喷管延长段AB的长度可调。
作为本发明的一个优选实施例，所述喷管本体的斜面BC与水平方向的夹角α选取准则为：γ+8≤α≤γ+12；其中：既有矢量喷管本体的斜面AC与水平方向的夹角α’＝90°，γ为该既有矢量喷管本体的气动矢量角。
作为本发明的一个优选实施例，斜面BC与水平方向的夹角α的取值范围为45°≤α≤75°；此时，所述喷管本体与既有矢量喷管本体处于相同喷管工作落压比时，所述喷管本体的气动矢量角较既有矢量喷管本体的气动矢量角大2°-5°。作为本发明的一个优选实施例，斜面BC与喷管内壁面相邻的型面为平直型面，而斜面BC与喷管外壁面型线相邻的型面为外突曲面，且平直型面与外突曲面之间光滑过渡。
本发明与现有技术相比，具有以下优点：
(1)相比传统的喉道偏移式气动矢量喷管，本发明通过改变后体型面，实现了喷管推力性能特别是机动性的提高，结构简单；
(2)通过对于喉道偏移式气动矢量喷管后体的改变，其原理可以应用在几乎全部喉道偏移式气动矢量喷管的改型以及其他类型具有相似几何形状的矢量喷管中，用途广泛；
(3)通过非对称后体设计，为飞行器赋予了更好的隐身特别是红外隐身性能。
附图说明
图1是既有对称后体型面的喉道偏移式气动矢量喷管示意图。
图2是本发明所述具有非对称后体型面的喉道偏移式气动矢量喷管示意图。
图3是本发明所述具有非对称后体型面的喉道偏移式气动矢量喷管示意图(无附图标记)。
其中：喷管进口1、一喉道前部收敛段2、一喉道3、二喉道前部扩张段4、二喉道前部收敛段5、二喉道(喷管出口)6，后体7。
图4是本发明所述具有非对称后体型面的喉道偏移式气动矢量喷管，在抬头状态下推力系数和推力矢量角计算结果；
图5是本发明所述具有非对称后体型面的喉道偏移式气动矢量喷管，在低头状态下推力系数和推力矢量角计算结果。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。以下对至少一个示例性实施例的描述实际上仅仅是说明性的，决不作为对本发明及其应用或使用的任何限制。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。除非另外具体说明，否则在这些实施例中阐述的部件和步骤的相对布置、表达式和数值不限制本发明的范围。同时，应当明白，为了便于描述，附图中所示出的各个部分的尺寸并不是按照实际的比例关系绘制的。对于相关领域普通技术人员已知的技术、方法和设备可能不作详细讨论，但在适当情况下，所述技术、方法和设备应当被视为授权说明书的一部分。在这里示出和讨论的所有示例中，任何具体值应被解释为仅仅是示例性的，而不是作为限制。因此，示例性实施例的其它示例可以具有不同的值。
为了便于描述，在这里可以使用空间相对术语，如“在……之上”、“在……上方”、“在……上表面”、“上面的”等，用来描述如在图中所示的一个器件或特征与其他器件或特征的空间位置关系。应当理解的是，空间相对术语旨在包含除了器件在图中所描述的方位之外的在使用或操作中的不同方位。例如，如果附图中的器件被倒置，则描述为“在其他器件或构造上方”或“在其他器件或构造之上”的器件之后将被定位为“在其他器件或构造下方”或“在其他器件或构造之下”。因而，示例性术语“在……上方”可以包括“在……上方”和“在……下方”两种方位。该器件也可以其他不同方式定位(旋转90度或处于其他方位)。
如图2、图3所示，本发明所述的具有非对称后体型面的喉道偏移式气动矢量喷管，在原有的喉道偏移式气动矢量喷管内型面不变的基础上，将其对称的后体型面改变为非对称的后体型面，其中，一侧型面与水平方向的夹角不大于90°，另外一侧的型面角度结合实际需求来改变。一般来说，斜面尾端与喷管外壁面连线与喷管外壁面型线过渡连续，具体型面由飞行器决定。
具有非对称后体型面的喉道偏移式气动矢量喷管，其矢量角放大且不等的核心是后体型面的不对称，通过发动机射流与不对称后体型面之间相互作用形成的大小、强度均不同的低压区，促进发动机射流进一步贴近壁面，从而实现矢量角的放大。一般来说，射流与出口壁面越接近，在壁面附近形成的低压区强度也大，压力也越低，对于发动机出口射流矢量角的放大也就越大。但考虑到矢量喷管固有的矢量角大小，对于固定几何后体喷管的后体角度不能无限制，且考虑到矢量角随控制变量(无源型：自适应旁路的开度，有源型：一 喉道附近注入的次流流量)变化而变化的线性程度，最优范围是固定的。为了兼具平飞、抬头矢量和低头矢量三个工作状态的不同要求，所述喷管本体的斜面BC与水平方向的夹角α选取准则为：γ+8≤α≤γ+12；其中：既有矢量喷管本体(具有对称后体的喷管构型)的斜面AC与水平方向的夹角α’＝β＝90°，γ为该既有矢量喷管本体的气动矢量角。对于典型的喉道偏移式气动矢量喷管构型来说，一侧后体型面与水平方向的夹角α的较优取值范围为45°≤α≤75°，此时，非对称后体的喷管矢量性能能处于较优值，所述喷管本体的气动矢量角较对称后体的气动矢量角大2°-5°。
进一步地，喉道偏移式气动矢量喷管的后体可以分为固定几何后体和可变几何后体。对于固定几何后体来说，一般情况下，一侧后体与水平方向夹角为锐角，另外一侧没有特殊要求，β多为钝角，以减少阻力。综合考虑飞行器隐身、机动性等需求，一般来说喷管上侧后体与水平方向夹角(即β)为钝角，下侧后体与水平方向夹角(即α)为锐角。对于可变几何后体来说，通过设置作动筒、铰链等简单的机械结构，使得其后体的几何角度可以随着发动机和喷管的工作状态进行调节，以兼顾推力矢量性能、隐身性能等。
进一步地，为了兼具平飞、抬头矢量和低头矢量三个工作状态的不同要求，以下侧后体型面与水平方向的夹角α的较优取值范围为45°≤α≤75°，上侧后体型面要求光滑即可，优选的角度为α＞90°。
进一步地，上侧后体型面可以使用更详细的设计方法将后体型面设计成光滑曲线，而下侧后体型面与出口(二喉道)附近的初始型面以直线为宜，以避免平飞状态和低头矢量状态下由于气流附壁流动等造成的初始矢量角较大或矢量调节阶跃的问题。之后的型面可以设计成外突曲面。
本发明实现俯仰方向控制的原理、注气位置、注气角度等与常规喉道偏移式气动矢量喷管一致，在此不再赘述。同时，本发明适用范围同时满足主动有源型和自适应无源型的喉道偏移式气动矢量喷管。
对于可变几何后体的构型来说，驱动部件的方式很多，包括但不限于液压做动、导轨驱动、伺服装置驱动等。
以下将结合附图详细地说明本发明的技术方案。
如图2-图3所示，本实施例所述的具有非对称后体型面的喉道偏移式气动矢量喷管，包括喷管本体，所述喷管本体的后体型面呈非对称设置。具体地，所述喷管本体的后体型面中，处于上侧的型面为型面a，处于下侧的型面则为型面b；型面a与水平方向的夹角α不大于90°，型面b与水平方向的夹角β大于90°，因此，型面a、型面b关于喷管本体的轴线呈非对称结构设置。
型面a与水平方向的夹角α的取值范围为45°≤α≤75°。
设计时，所述喷管本体的非对称后体型面，以具有对称后体型面的既有矢量喷管本体(如图1所示)为基础，通过延长该既有矢量喷管本体一侧，附图中为下侧的喷管外壁面型线，将该侧后体型面与喷管外壁面型线的连接位点从点A后移至点B，并保持该侧后体型面与喷管内壁面的连接位点C不变而形成，具体如图2所示。所述的喷管本体在既有矢量喷管本体一侧，所延长的喷管外壁面型线为喷管延长段AB，该侧后体型面为斜面BC；所述斜面BC与水平方向的夹角α可调，所述喷管延长段AB的长度可调。为了兼具平飞、抬头矢量和低头矢量三个工作状态的不同要求，所述喷管本体的斜面BC与水平方向的夹角α选取准则为： γ+8≤α≤γ+12；其中：既有矢量喷管本体(具有对称后体的喷管构型)的斜面AC与水平方向的夹角α’＝β＝90°，γ为该既有矢量喷管本体的气动矢量角；综合喷管的不同工作条件，调节要求等限制，一般来说，斜面BC与水平方向的夹角α的取值范围为45°≤α≤75°时，能够取得宽范围内较优的矢量性能，此时，所述喷管本体的气动矢量角较具有对称后体的既有矢量喷管的气动矢量角大2°-5°。斜面BC与喷管内壁面相邻的型面为平直型面，而斜面BC与喷管外壁面型线相邻的型面为外突曲面，且平直型面与外突曲面之间光滑过渡。
针对典型构型的无源型喉道偏移式气动矢量喷管进行计算，其中上侧后体角度为90°，另一侧后体角度变化。其抬头状态下推力系数和推力矢量角计算结果如图4所示：当α≥45°，在NPR≥6时，推力系数基本没有差别；但是在NPR≤4时，推力系数变化趋势不同，总的来说，对于α≥90°的构型推力系数基本没有差别；α＜90°的构型在NPR≤2时推力系数较α＝90°的构型来说更低，随后都出现推力系数随NPR增加而增加的情况，都在NPR＝3处达到推力系数最大，随后逐渐降低。
其低头状态下，推力系数和推力矢量角计算结果如图5所示：当α≤90°的构型都不同程度会出现射流在下侧型面上贴壁膨胀的现象，此时矢量角、推力系数会受到下侧型面角度的影响；特别在NPR＝1.5和4≤NPR≤10时，45°的构型矢量角最大。因此，45°为较好的型面角度。

Claims (10)

  1. 一种具有非对称后体型面的喉道偏移式气动矢量喷管，包括喷管本体，其特征在于，所述喷管本体的后体型面呈非对称设置。
  2. 根据权利要求1所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，所述喷管本体的后体型面，其中的一侧型面为型面a，另一侧型面则为型面b；型面a、型面b关于喷管本体的轴线呈非对称结构设置，且型面a与水平方向的夹角α不大于90°。
  3. 根据权利要求2所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，型面b与水平方向的夹角β大于90°。
  4. 根据权利要求3所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，型面a与水平方向的夹角α的取值范围为45°≤α≤75°。
  5. 根据权利要求3所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，型面a位于喷管本体的下侧。
  6. 根据权利要求1所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，所述喷管本体的非对称后体型面，以具有对称后体型面的既有矢量喷管本体为基础，通过延长该既有矢量喷管本体一侧的喷管外壁面型线，将该侧后体型面与喷管外壁面型线的连接位点从点A后移至点B，并保持该侧后体型面与喷管内壁面的连接位点C不变而形成。
  7. 根据权利要求6所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，所述的喷管本体在既有矢量喷管本体一侧，所延长的喷管外壁面型线为喷管延长段AB，该侧后体型面为斜面BC；所述斜面BC与水平方向的夹角α可调，所述喷管延长段AB的长度可调。
  8. 根据权利要求6所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，所述喷管本体的斜面BC与水平方向的夹角α选取准则为：γ+8≤α≤γ+12；其中：既有矢量喷管本体的斜面AC与水平方向的夹角α’＝90°，γ为该既有矢量喷管本体的气动矢量角。
  9. 根据权利要求6所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，斜面BC与水平方向的夹角α的取值范围为45°≤α≤75°；此时，所述喷管本体与既有矢量喷管本体处于相同喷管工作落压比时，所述喷管本体的气动矢量角较既有矢量喷管本体的气动矢量角大2°-5°。
  10. 根据权利要求6所述的具有非对称后体型面的喉道偏移式气动矢量喷管，其特征在于，斜面BC与喷管内壁面相邻的型面为平直型面，而斜面BC与喷管外壁面型线相邻的型面为外突曲面，且平直型面与外突曲面之间光滑过渡。
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113418937A (zh) * 2021-06-08 2021-09-21 西北工业大学 一种可更换后体的航空发动机超紧凑低散射载体
CN114087087A (zh) * 2021-10-29 2022-02-25 南京航空航天大学 一种多原理多模态气动矢量喷管及控制方法
CN114676507A (zh) * 2022-04-15 2022-06-28 中国航发沈阳发动机研究所 一种喷管出口面积控制规律设计方法
CN114781055A (zh) * 2022-04-08 2022-07-22 南京航空航天大学 一种针对单发倒v布局矢量推进系统的分叉过渡段设计方法
CN115539243A (zh) * 2022-09-17 2022-12-30 西北工业大学 一种s弯喷管后甲板调节机构及保持喷流水平的调节方法
CN117249452A (zh) * 2023-10-10 2023-12-19 中国人民解放军国防科技大学 一种抑制非均匀流动分离的超声速燃烧室及超燃冲压发动机

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109723570B (zh) * 2018-12-24 2021-11-09 南京航空航天大学 具有非对称后体型面的喉道偏移式气动矢量喷管
CN110657043B (zh) * 2019-09-09 2022-02-08 南京航空航天大学 一种机械扰动式喉道偏移式气动矢量喷管
CN112177794B (zh) * 2020-08-21 2022-01-04 南京航空航天大学 一种喉道偏移式气动矢量喷管及其设计方法
CN113915027B (zh) * 2021-12-07 2022-04-01 中国航发沈阳发动机研究所 一种带偏航功能的圆转方二元矢量喷管

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5335489A (en) * 1993-07-09 1994-08-09 United Technologies Corporation Gas turbine vectoring exhaust nozzle
US5511376A (en) * 1993-08-31 1996-04-30 United Technologies Corporation Axisymmetric vectoring nozzle
CN203335272U (zh) * 2013-07-05 2013-12-11 中国航空工业集团公司沈阳发动机设计研究所 一种滑梁连杆式二元收扩矢量喷管扩张段控制机构
CN104033279A (zh) * 2014-06-06 2014-09-10 中国航空工业集团公司沈阳发动机设计研究所 一种新型二元矢量喷管
CN106593696A (zh) * 2016-12-21 2017-04-26 南京航空航天大学 能够改善后体流场的对称及非对称排气系统及其方法
CN108104974A (zh) * 2017-12-14 2018-06-01 中国航发沈阳发动机研究所 一种二元矢量喷管结构及具有其的飞机
CN109723570A (zh) * 2018-12-24 2019-05-07 南京航空航天大学 具有非对称后体型面的喉道偏移式气动矢量喷管

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0723075B1 (en) * 1991-05-16 2001-11-21 General Electric Company Thermal shield for axisymmetric vectoring nozzle
US20060150612A1 (en) * 2005-01-12 2006-07-13 Honeywell International Inc. Thrust vector control
WO2012173546A1 (en) * 2011-06-17 2012-12-20 Saab Ab Variable jet engine outlet with a mainly circle sector-formed cross section
US9732700B2 (en) * 2013-10-24 2017-08-15 The Boeing Company Methods and apparatus for passive thrust vectoring and plume deflection
CN104847529B (zh) * 2015-03-27 2016-08-17 南京航空航天大学 基于新型气动矢量喷管的三自由度矢量推力系统
CN105134407B (zh) * 2015-08-20 2017-08-01 南京航空航天大学 具有垂直起降功能的喉道偏移式气动矢量喷管及控制方法
CN108087145A (zh) * 2017-12-14 2018-05-29 中国航发沈阳发动机研究所 一种单膨胀二元矢量喷管结构及飞机
CN108561242B (zh) * 2018-03-22 2020-04-07 南京航空航天大学 一种基于平移运动的短距起降型喉道偏移式气动矢量喷管
CN108590884B (zh) * 2018-03-22 2020-01-17 南京航空航天大学 一种基于导流板的垂直起降型喉道偏移式气动矢量喷管

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5335489A (en) * 1993-07-09 1994-08-09 United Technologies Corporation Gas turbine vectoring exhaust nozzle
US5511376A (en) * 1993-08-31 1996-04-30 United Technologies Corporation Axisymmetric vectoring nozzle
CN203335272U (zh) * 2013-07-05 2013-12-11 中国航空工业集团公司沈阳发动机设计研究所 一种滑梁连杆式二元收扩矢量喷管扩张段控制机构
CN104033279A (zh) * 2014-06-06 2014-09-10 中国航空工业集团公司沈阳发动机设计研究所 一种新型二元矢量喷管
CN106593696A (zh) * 2016-12-21 2017-04-26 南京航空航天大学 能够改善后体流场的对称及非对称排气系统及其方法
CN108104974A (zh) * 2017-12-14 2018-06-01 中国航发沈阳发动机研究所 一种二元矢量喷管结构及具有其的飞机
CN109723570A (zh) * 2018-12-24 2019-05-07 南京航空航天大学 具有非对称后体型面的喉道偏移式气动矢量喷管

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113418937A (zh) * 2021-06-08 2021-09-21 西北工业大学 一种可更换后体的航空发动机超紧凑低散射载体
CN114087087A (zh) * 2021-10-29 2022-02-25 南京航空航天大学 一种多原理多模态气动矢量喷管及控制方法
CN114781055A (zh) * 2022-04-08 2022-07-22 南京航空航天大学 一种针对单发倒v布局矢量推进系统的分叉过渡段设计方法
CN114676507A (zh) * 2022-04-15 2022-06-28 中国航发沈阳发动机研究所 一种喷管出口面积控制规律设计方法
CN115539243A (zh) * 2022-09-17 2022-12-30 西北工业大学 一种s弯喷管后甲板调节机构及保持喷流水平的调节方法
CN117249452A (zh) * 2023-10-10 2023-12-19 中国人民解放军国防科技大学 一种抑制非均匀流动分离的超声速燃烧室及超燃冲压发动机

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