WO2019179101A1 - Vertical take-off and landing type throat-shifting aerodynamic vectoring nozzle based on deflector - Google Patents
Vertical take-off and landing type throat-shifting aerodynamic vectoring nozzle based on deflector Download PDFInfo
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- WO2019179101A1 WO2019179101A1 PCT/CN2018/112397 CN2018112397W WO2019179101A1 WO 2019179101 A1 WO2019179101 A1 WO 2019179101A1 CN 2018112397 W CN2018112397 W CN 2018112397W WO 2019179101 A1 WO2019179101 A1 WO 2019179101A1
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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
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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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/11—Varying effective area of jet pipe or nozzle by means of pivoted eyelids
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- the invention relates to a vertical take-off type throat offset type pneumatic vector nozzle based on a deflector, belonging to the technical field of thrust vector and vertical takeoff and landing aviation engine nozzle.
- thrust vector aeroengines With the development of science and technology and the improvement of actual demand, future aircraft will increasingly use thrust vector aeroengines.
- the core of the thrust vector aero engine to achieve the thrust vector function is the thrust vector nozzle.
- the traditional mechanical thrust vector nozzle has a complicated structure, poor reliability and troublesome maintenance. Therefore, it is urgent to develop a thrust vector nozzle with simple structure, light weight and good maintenance.
- the fluid thrust vector nozzle has gradually become a research focus and research hotspot in various countries with its simple structure and light weight, and will enter engineering applications in the near future.
- how to give more functions to the fluid thrust vector nozzle under the premise of changing the nozzle structure as little as possible becomes 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 which has been developed in recent years. It is favored by more and more because of its simple structure, light weight and good vector performance.
- the common throat offset pneumatic vector nozzle is a double throat structure, and the second throat area is slightly larger than the area of a throat.
- the throat offset pneumatic vector nozzle can be divided into an active active type and an adaptive passive type, wherein the active active type generating thrust vector air source is mostly an external compressor, a gas cylinder or an aviation source.
- the bleed air in the high-pressure parts of the engine (mostly the compressor) is characterized by a small change in the thrust vector angle with the nozzle drop ratio, but the thrust loss is greater for the entire aeroengine;
- the adaptive passive type is
- the adaptive bypass channel is set to introduce the high-pressure airflow at the nozzle inlet position to the specified position of the nozzle, adaptively generate disturbance and finally realize the thrust vector, which overcomes the shortcomings of the active active type and affects the thrust of the aeroengine. Smaller, vector angles are also more stable.
- the common throat offset pneumatic vector nozzle can only produce a single direction vector angle of about 20°, which is commonly used for the control of the pitch direction of the aircraft. But for a vertical takeoff and landing aircraft, a vector angle of around 20° is not enough. Therefore, it is necessary to use the throat offset pneumatic vector nozzle to achieve vertical takeoff and landing, and the original structure should be properly improved.
- the invention utilizes the profile features of the throat-displacement pneumatic vector nozzle and the front expansion section (cavity) of the second throat, and specially designs the deflector to skillfully combine the thrust vector technology and the vertical take-off and landing technology. It has an efficient and reliable vertical take-off and landing capability and broadens its application under the premise that the thrust vector performance is not affected.
- the present invention provides a vertical take-off type throat offset type pneumatic vector nozzle based on a deflector, which has a specially designed "knife" shaped deflector structure.
- the deflection achieves an efficient and reliable vertical take-off and landing function, which greatly expands its application range.
- a vertical take-off type throat offset type pneumatic vector nozzle based on a deflector comprising a nozzle inlet connected in sequence in a flat flight mode, a straight section at the front of a throat, and a convergent section at the front of a throat , a throat, a front section of the second throat, a converging section of the front of the second throat, and a second throat;
- the fixing portion of the second throat front expansion converging section ie, the combination of the second throat front expansion section and the second throat front convergence section
- the fixing portion of the second throat front expansion converging section is disposed at a lower portion of the throat lower wall surface and a "knife” shaped deflector that rotates around the rotating shaft on the rear side of the fixing portion, and the head of the "knife” shaped deflector in the flat flying mode is closely closed to the inner wall surface of the fixed portion, and the "knives” shaped deflector
- the inner surface and the upper side wall surface form a flow passage of the front portion of the second throat;
- the "knife-knife"-shaped guide vane When switching from the flat flight mode to the vertical take-off and landing mode, the "knife-knife"-shaped guide vane rotates around the rotating shaft to the upper wall surface of the converging head of the tangential point of the second throat, and is guided by a "chopper” shaped guide vane.
- the rotation of the rotating shaft not exceeding 90° realizes the downward flow of the airflow flowing horizontally through a throat without being less than 90°, thereby switching the flat flight mode to the vertical take-off mode.
- the outer profile of the "knife” shaped baffle includes five segments of AB, BC, CD, DE, and AE that are sequentially connected, and the AB and AE segments constitute the tip of the "knife” shaped baffle.
- the CD and DE segments form the tail profile of the "chopper" shaped deflector;
- the AE section adopts the inner profile line of the lower wall surface of the convergent section of the front part of the second throat in the flat flight mode.
- the position corresponding to the upper wall surface of the nozzle is symmetrical, and the AB, BC and CD sections constitute the vertical takeoff and landing mode.
- Part of the nozzle circulation passage; the AB section (especially near the point A) is related to the airtightness of the nozzle in the flat flight state, without considering the factors such as sharp point thermal ablation and sharp point strength,
- the angle between AB and AE at point A is preferably an acute angle. The smaller the angle is, the better the aerodynamic performance is.
- the AB segment is generally straight, and the AB segment is fixed and fixed in the flight mode.
- the inner wall surface of the portion is fitted; the CD segment and the trailing edge profile of the fixed portion form a discharge port for the nozzle airflow in the vertical take-off and landing mode.
- the CD segment is straight, and the CD in the vertical take-off mode is The angle between the segment and the horizontal backward vector direction is 90°-100°; the BC segment is a smooth transition curve connecting the AB segment and the CD segment.
- the design of the DE segment must meet the following two conditions: (1) In the pipe flat flight mode, the nozzle outlet airflow does not occur in the DE section, and the initial, unfavorable and obvious low head vector is generated.
- the airflow of the side circulation channel on the "knife” shaped deflector flows through
- the Coanda flow occurs on the DE section. Therefore, the final result of the DE segment is obtained according to the optimized design.
- the initial angle between the point E side of the DE segment and the horizontal direction is greater than 45°, and the point D of the DE segment is a continuous smooth convex curve.
- the Coanda effect surface is constructed.
- the position of the rotating shaft of the "knife" shaped guide vane is important for the exit direction of the airflow in the vertical take-off and landing mode, and the position of the rotating shaft also indirectly affects the flow of air under a vertical throat mode and mode switching after flowing through a throat.
- the flow area that is, it is possible to influence the position of the nozzle throat (the minimum position of the flow area).
- the rotating shaft is located downstream of the second throat in the level flight mode, and the height of the throat is Hth1, and the horizontal distance x between the rotating shaft and the second throat is preferably 15% ⁇ Hth1 ⁇ x ⁇ 55% ⁇ Hth1; in the vertical direction, the axis of rotation is below the cusp of the lower side of the nozzle of the nozzle in the flight mode, ie, the point E, and the vertical distance y of the axis of the lower side of the second throat is taken
- the value range is 25% x Hth1 ⁇ y ⁇ 60% x Hth1.
- the rotation angle of the "knife” shaped deflector is also affected.
- the rotation from the flat flying mode to the vertical lifting mode the rotation of the "knife” shaped deflector
- the angle ⁇ satisfies 45° ⁇ ⁇ ⁇ 90°, and 55° ⁇ ⁇ ⁇ 70° is a preferred range.
- the cusp head of the "knife" shaped deflector in the vertical take-off and landing mode touches the upper wall of the convergent converging section of the front of the second throat.
- the position of the second throat is 25%-35% of the cavity length (the length of the cavity, that is, the length of the convergence section of the front of the second throat in the flat flight mode), that is, the contact is located in the convergence section of the front of the second throat. Near the turning point.
- the nozzle throat (the minimum flow area) is always at the throat during the vertical take-off mode and modal switching process of the nozzle.
- the sum of the minimum areas of the flow passages on the upper and lower sides of the "knife" shaped deflector during the modal switching is always greater than the area of the throat, so as to minimize the sum of the minimum areas of the upper and lower flow passages during the switching process. Maintaining a throat area of 1.05-1.2 times is optimal, thereby achieving stable nozzle flow.
- the amount of gas injection near the cusp of the lower side of the throat should be adjusted with the degree of rotation, and finally the uniform changes of key parameters such as thrust and lift during the modal switching of the nozzle are realized.
- the gas injection volume should be at a maximum during the 5-15% phase of the phalanx mode to the vertical takeoff and landing mode switching rotation and 85%-95% of the vertical hoisting mode to the leveling mode switching rotation process. status.
- the present invention provides a baffle-based vertical take-off and descending throat offset pneumatic vector nozzle, which has the following advantages over the prior art:
- the invention makes the nozzle have an efficient and reliable vertical take-off and landing capability under the premise that the thrust vector performance is not affected, and broadens its application occasion;
- the rotation angle of the "knife" shaped baffle of the present invention is 55 ° ⁇ ⁇ ⁇ 70 °, and the rotation angle and the rotation range are smaller than the configuration with a larger rotation angle, so the rotation process Short switching time;
- FIG. 1 is a schematic structural view of a vertical take-off type throat offset type pneumatic vector nozzle based on a deflector according to the present invention
- FIG. 2 is a schematic structural view of a "knife" shaped deflector in the present invention
- the figure includes: 1, nozzle inlet, 2, straight section of the front of the throat, 3, a convergent section of the front of the throat, 4, a throat, 5, 2 front section of the throat, 6, " Chopper-shaped guide vane, 7, two throat front convergence section, 8, shaft, 9, two throat.
- a vertical-elevation-type throat-shifting pneumatic vector nozzle based on a baffle includes a nozzle inlet 1, a throat front, and the like in a flat flight mode. , a throat convergence section 3, a throat 4, a second throat front expansion section 5, a second throat front convergence section 7, and a second throat 9;
- a lower portion of the converging section of the front portion of the second throat is disposed with a fixing portion that is in contact with the lower wall surface of the throat 4 and a "knife” shaped deflector 6 that is rotatable about the rotating shaft 8 on the rear side of the fixing portion.
- the head of the "knife” shaped baffle 6 is closely closed to the inner wall surface of the fixed portion, and the inner surface of the "knife” shaped baffle 6 and the upper wall of the convergent converging section of the front portion of the second throat are a flow passage that forms a second throat;
- the "knife” shaped baffle 6 When switching from the level flight mode to the vertical take-off mode, the "knife” shaped baffle 6 rotates clockwise around the rotating shaft 8 to the upper surface of the cusp head and the convergent converging section of the front of the second throat, through the "knife” shape.
- the deflector 6 does not rotate more than 90°, and the downward flow of the airflow flowing horizontally through the throat 4 is not less than 90°, thereby achieving the switching of the flat flight mode to the vertical take-off mode.
- the "knife" shaped baffle 6 is placed substantially horizontally.
- the throat offset pneumatic vector nozzle has only one nozzle outlet, that is, the second throat 9.
- the inner flow passage of the nozzle is a typical double-throat configuration of the throat offset type pneumatic vector nozzle, and the vector angle is realized by gas injection in a sensitive portion (mostly near a throat) in the flow field in the nozzle. It can be generated from external compressors, cylinders or high-pressure components from aeronautical engines (mostly compressors), or it can be introduced from the nozzle inlet through a specially designed bypass passage, how to make the throat through gas injection.
- the vector of the offset-type pneumatic vector nozzle has been matured and will not be described here.
- the "knife-knife"-shaped baffle 6 rotates clockwise around the rotating shaft until the cusp head of the "knife” shaped baffle contacts the upper wall surface of the nozzle and completely closes the upper flow path of the nozzle.
- the airflow passage of the nozzle changes from the original horizontal direction to the airflow flowing through the throat, and can only be ejected from the lower outlet of the nozzle under the blocking action of the deflector, generating a thrust directly above or above.
- the vector that is, the preferred range of the thrust vector angle ⁇ in the vertical take-off and landing mode is 90° ⁇ ⁇ ⁇ 110°.
- the determination of the outer profile of the baffle can be determined by the five lines AB, BC, CD, DE and AE.
- the curve AE selects the inner profile line of the lower wall surface of the convergent section of the second front part of the throat in the level flight mode, and is generally symmetrical with the corresponding position on the upper wall surface of the nozzle.
- Lines AB, BC, and CD are part of the nozzle flow path in the vertical take-off and landing mode.
- Line AB (especially near point A) is related to the problem of air tightness under the condition that the nozzle is flying flat. Without considering the factors such as cusp thermal ablation and cusp strength, AB and AE are clamped near point A.
- the angle should be an acute angle, and the sharper the better, and the line AB can be a straight line; if considering the above factors, it should be properly rounded, the specific rounding size and position are determined by the actual engineering requirements and material properties.
- the line CD and the channel on the trailing edge profile of the non-rotating part of the lower wall of the nozzle determine the direction in which the nozzle airflow is ejected in the vertical take-off and landing mode, which will obviously affect the vector angle in this mode.
- the line CD can be a straight line.
- the angle between the line CD and the horizontally backward vector direction is preferably about 90°-100°, and about 95° is optimal.
- the curve BC is a smooth transition curve of the connecting lines AB and CD.
- the design of the line DE needs to meet the following two conditions at the same time: (1) The nozzle outlet airflow does not flow along the nozzle in the non-vector state of the nozzle, resulting in an initial, unfavorable head vector, that is, near the point E of the line DE. Coanda flow; (2) "Chopper” shaped baffle in the process of flat flight to vertical takeoff or vertical to vertical flight mode switching 40% -60%, from the upper side of the nozzle flow channel flow When the upper side expansion converging section is ejected obliquely downward, it can flow on the part of the line DE (especially the side of the AE curve close to the point E). Therefore, the final optimal design result of the line DE is obtained according to the optimization. Generally, the initial angle between the point E of the line DE and the horizontal direction of the line DE is greater than 45°, and the point D of the line DE is a continuous smooth convex curve.
- the Coanda Effect surface is constructed.
- the position of the rotating shaft is important for the exit direction of the airflow in the vertical take-off and landing mode, and the position of the rotating shaft also indirectly affects the airflow through the vertical take-off and landing mode and modal switching.
- the flow area behind a throat may have an effect on the position of the nozzle throat.
- the preferred position of the rotating shaft is as follows: in the horizontal direction, the rotating shaft is in the flat flight mode, and the downstream of the second throat of the nozzle is suitable, and the range from the rotation axis to the second throat is preferably 15% ⁇ Hth1 ⁇ x ⁇ 55% ⁇ Hth1; in the vertical direction, the rotation axis is below the cusp below the lower throat of the nozzle in the flight mode, and the distance between the rotation axis and the lower cusp of the second throat is better. % ⁇ Hth1 ⁇ y ⁇ 60% ⁇ Hth1.
- the angle of rotation of the "knife” shaped deflector is also affected.
- the head of the "knife” shaped deflector touches the upper wall of the convergent converging section of the front of the nozzle.
- the rotation angle ⁇ satisfies 45° ⁇ ⁇ ⁇ 90°, and 55° ⁇ ⁇ ⁇ 70° is a preferred range.
- the position touched by the head of the "knife" shaped baffle is 25% to 35% after the convergence of the front part of the second throat.
- the position, that is, the contact is near the turning point of the expansion convergence section.
- the nozzle throat is always at a throat during the vertical take-off mode and modal switching, that is, the modal switching process.
- the sum of the minimum areas of the upper and lower flow passages of the middle nozzle is always greater than the area of the throat so that the sum of the minimum areas of the upper and lower flow passages during the switching process is maintained as much as 1.05-1.2 times the throat area. It is optimal to achieve stable nozzle flow.
- the airflow flows through a throat and then turns downward (or obliquely downward).
- the side wall of the flow passage adjacent to the outlet is preferably parallel or slightly tapered, and the axis angle will obviously affect
- the direction of the airflow ejected from the nozzle is such that the angle between the axis and the horizontally rearward vector direction is preferably about 90°-100°, and about 95° is optimal.
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Claims (6)
- 一种基于导流板的垂直起降型喉道偏移式气动矢量喷管,其特征在于,包括平飞模态下依次连通的喷管进口(1)、一喉道前部等直段(2)、一喉道前部收敛段(3)、一喉道(4)、二喉道前部扩张段(5)、二喉道前部收敛段(7)、二喉道(9);A vertical take-off type throat offset type pneumatic vector nozzle based on a baffle, characterized in that it comprises a nozzle inlet (1) and a straight section at the front of a throat which are sequentially connected in a level flight mode ( 2) a convergent section of the front of the throat (3), a throat (4), a front section of the second throat (5), a converging section of the front of the second throat (7), and a second throat (9);其中,所述二喉道前部扩张收敛段的下壁面处设置有与一喉道(4)下壁面相接的固定部以及固定部后侧可绕转轴(8)转动的“菜刀”形导流片(6),平飞模态下“菜刀”形导流片(6)的头部与固定部的内壁面贴紧封闭,“菜刀”形导流片(6)的内表面与二喉道前部扩张收敛段的上壁面之间形成二喉道前部的流通通道;Wherein, the lower wall surface of the expansion section of the front portion of the second throat is provided with a fixing portion that is in contact with the lower wall surface of the throat (4), and a "knife" guide that can rotate around the rotating shaft (8) on the rear side of the fixing portion. The flow piece (6), the head of the "knife" shaped deflector (6) in the flat flight mode is closely closed to the inner wall surface of the fixed portion, and the inner surface of the "knife" shaped deflector (6) and the second throat a flow passageway at the front of the second throat is formed between the upper wall surfaces of the convergence section of the front of the road;由平飞模态切换至垂直起降模态时“菜刀”形导流片(6)绕转轴(8)顺时针转动至其尖点头部触及二喉道前部扩张收敛段的上壁面,通过“菜刀”形导流片(6)绕转轴(8)不超过90°的转动,实现水平流过一喉道(4)的气流不小于90°的向下转向,进而实现平飞模态至垂直起降模态的切换。When switching from the level flight mode to the vertical take-off mode, the "knife" shaped baffle (6) rotates clockwise around the axis of rotation (8) until the tip of the head touches the upper wall of the converging section of the front of the second throat. The "knife" shaped deflector (6) rotates around the rotating shaft (8) no more than 90°, so that the airflow flowing horizontally through a throat (4) is not less than 90°, and the flat flying mode is realized. Switching between vertical takeoff and landing modes.
- 根据权利要求1所述的一种基于导流板的垂直起降型喉道偏移式气动矢量喷管,其特征在于,所述“菜刀”形导流片(6)的外部型线包括依次衔接的AB、BC、CD、DE、AE五段,且AB、AE段构成“菜刀”形导流片(6)的头部型线,CD、DE段构成“菜刀”形导流片(6)的尾部型线;A deflector-based vertical take-off and descending throat offset pneumatic vector nozzle according to claim 1, wherein the outer profile of the "chopper" shaped deflector (6) comprises The five sections of AB, BC, CD, DE, and AE are connected, and the AB and AE sections form the head line of the "knife" shaped deflector (6), and the CD and DE sections constitute the "knife" shaped deflector (6). Tail line;其中,AE段选用平飞模态下二喉道前部扩张收敛段下壁面的内型线,AB段与AE段在点A处的夹角小于90°,且AB段为直线;CD段与固定部的后缘型面之间构成垂直起降模态下喷管气流的喷出口,CD段为直线,垂直起降模态下CD段与水平向后的矢量方向的夹角为90°-100°;BC段为连接AB段与CD段的光滑过渡曲线,DE段的设计需同时满足以下两个条件:(1)喷管平飞模态下喷管出口气流在DE段不会附壁流动;(2)“菜刀”形导流板在模态切换过程中,“菜刀”形导流板上侧流通通道的气流流经上侧扩张收敛段斜向下喷出的时候会在DE段上发生附壁流动;平飞状态下DE段的点E一侧与水平方向的初始夹角大于45°,DE段的点D一侧为由连续光滑外凸曲线构成的科恩达效应曲面。Among them, the AE segment adopts the inner profile line of the lower wall surface of the convergence section of the front part of the second throat in the flat flight mode, and the angle between the AB segment and the AE segment at the point A is less than 90°, and the AB segment is a straight line; the CD segment and The trailing edge profiles of the fixed portion form a discharge port for the nozzle airflow in the vertical take-off and landing mode, the CD segment is a straight line, and the angle between the CD segment in the vertical take-off and landing mode and the horizontally backward vector direction is 90°- 100°; the BC section is a smooth transition curve connecting the AB section and the CD section. The DE section is designed to meet the following two conditions: (1) The nozzle outlet airflow in the nozzle flight mode is not attached to the DE section. (2) "Chopper" shaped baffle in the modal switching process, the airflow of the side circulation channel on the "knife" shaped deflector flowes through the upper side of the expansion and convergence section obliquely downwards in the DE segment The wall flow occurs on the upper side; the initial angle between the point E side of the DE segment and the horizontal direction is greater than 45° in the level flight state, and the point D side of the DE segment is the Coanda effect surface formed by the continuous smooth convex curve.
- 根据权利要求1所述的一种基于导流板的垂直起降型喉道偏移式气动矢量喷管,其特征在于,水平方向上,转轴(8)位于平飞模态下二喉道(9)的下游,记一喉道(4)的高度为Hth1,则转轴(8)与二喉道(9)的水平距离x的取值范围为15%×Hth1≤x≤55%×Hth1;竖直方向上,转轴(8)位于平飞模态下二喉道下侧尖点以下,转轴(8)与二喉道下侧尖点的竖直距离y的取值范围为25%×Hth1≤y≤60%×Hth1。A baffle-based vertical take-off and descending type throat offset type pneumatic vector nozzle according to claim 1, wherein in the horizontal direction, the rotating shaft (8) is located in the flat throat mode (the second throat) ( Downstream of 9), the height of the throat (4) is Hth1, and the horizontal distance x of the shaft (8) and the second throat (9) is 15% × Hth1 ≤ x ≤ 55% × Hth1; In the vertical direction, the rotating shaft (8) is located below the cusp below the lower throat of the second throat, and the vertical distance y of the rotating shaft (8) and the lower cusp of the second throat is 25%×Hth1 ≤ y ≤ 60% × Hth1.
- 根据权利要求1所述的一种基于导流板的垂直起降型喉道偏移式气动矢量喷管,其特征在于,自平飞模态切换至垂直起降模态,“菜刀”形导流片(6)的转动角度θ满足45°≤θ≤90°,且垂直起降模态下“菜刀”形导流片(6)的尖点头部触及二喉道前部扩张收敛段上壁面距离二喉道(9)25%-35%凹腔长度的位置。A baffle-based vertical take-off and descending type throat offset type pneumatic vector nozzle according to claim 1, wherein the self-leveling mode is switched to the vertical take-off and landing mode, and the "chopper" guide The rotation angle θ of the flow sheet (6) satisfies 45° ≤ θ ≤ 90°, and the cusp head of the “Chopper” shaped deflector (6) in the vertical take-off and landing mode touches the upper wall of the expansion section of the front of the second throat. Distance from the second throat (9) 25%-35% cavity length.
- 根据权利要求1所述的一种基于导流板的垂直起降型喉道偏移式气动矢量喷管,其特征在于,所述模态切换过程中“菜刀”形导流片(6)的上下两侧流动通道的最小面积之和始终大于一喉道(4)面积,且二者之和为1.05-1.2倍的一喉道(4)面积。A baffle-based vertical take-off and descending type throat offset type pneumatic vector nozzle according to claim 1, wherein said "knife" shaped deflector (6) during said modal switching The sum of the minimum areas of the flow passages on the upper and lower sides is always larger than the area of one throat (4), and the sum of the two is 1.05-1.2 times the area of a throat (4).
- 根据权利要求1所述的一种基于导流板的垂直起降型喉道偏移式气动矢量喷管,其特征在于,在平飞模态切换至垂直起降模态的0-30%阶段和垂直起降模态切换至平飞模态的70%-100%阶段,在一喉道下侧尖点处向主气流注入次流来进行流动控制。A baffle-based vertical take-off and descending throat offset pneumatic air nozzle according to claim 1, wherein the flat flight mode is switched to a 0-30% phase of the vertical takeoff and landing mode And the vertical take-off and landing mode is switched to the 70%-100% phase of the level flight mode, and a secondary flow is injected into the main airflow at a lower tip of the throat to perform flow control.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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CN201810240317.0 | 2018-03-22 | ||
CN201810240317.0A CN108590884B (en) | 2018-03-22 | 2018-03-22 | Vertical take-off and landing type throat offset pneumatic vectoring nozzle based on guide plate |
Publications (1)
Publication Number | Publication Date |
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WO2019179101A1 true WO2019179101A1 (en) | 2019-09-26 |
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CN108590884B (en) * | 2018-03-22 | 2020-01-17 | 南京航空航天大学 | Vertical take-off and landing type throat offset pneumatic vectoring nozzle based on guide plate |
CN109723570B (en) * | 2018-12-24 | 2021-11-09 | 南京航空航天大学 | Throat offset pneumatic thrust vectoring nozzle with asymmetric aft-body profile |
CN109723571B (en) * | 2018-12-27 | 2021-02-26 | 南京航空航天大学 | Throat offset type pneumatic thrust vectoring nozzle with trapezoidal section and aircraft equipped with same |
CN112177794B (en) * | 2020-08-21 | 2022-01-04 | 南京航空航天大学 | Throat offset type pneumatic vectoring nozzle and design method thereof |
CN112228242B (en) * | 2020-09-17 | 2021-12-14 | 南京航空航天大学 | Mechanical-pneumatic combined thrust vectoring nozzle with short-distance/vertical take-off and landing functions |
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US3792587A (en) * | 1972-07-17 | 1974-02-19 | Gen Electric | Exhaust vectoring means |
US20030183723A1 (en) * | 2002-04-01 | 2003-10-02 | Lockheed Martin Corporation | Propulsion system for a vertical and short takeoff and landing aircraft |
CN103939235A (en) * | 2014-04-25 | 2014-07-23 | 西北工业大学 | Rotary thrust vectoring nozzle for short-distance vertical take-off and landing engine |
CN104863749A (en) * | 2015-03-27 | 2015-08-26 | 南京航空航天大学 | Bypass passive dual-throat vector spray pipe with reverse pushing function |
CN105134407A (en) * | 2015-08-20 | 2015-12-09 | 南京航空航天大学 | Throat offset type pneumatic thrust vectoring nozzle with vertical lifting function and control method |
CN108590884A (en) * | 2018-03-22 | 2018-09-28 | 南京航空航天大学 | A kind of VTOL type venturi offset fluidic vectoring nozzle based on deflector |
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- 2018-03-22 CN CN201810240317.0A patent/CN108590884B/en active Active
- 2018-10-29 WO PCT/CN2018/112397 patent/WO2019179101A1/en active Application Filing
Patent Citations (6)
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US3792587A (en) * | 1972-07-17 | 1974-02-19 | Gen Electric | Exhaust vectoring means |
US20030183723A1 (en) * | 2002-04-01 | 2003-10-02 | Lockheed Martin Corporation | Propulsion system for a vertical and short takeoff and landing aircraft |
CN103939235A (en) * | 2014-04-25 | 2014-07-23 | 西北工业大学 | Rotary thrust vectoring nozzle for short-distance vertical take-off and landing engine |
CN104863749A (en) * | 2015-03-27 | 2015-08-26 | 南京航空航天大学 | Bypass passive dual-throat vector spray pipe with reverse pushing function |
CN105134407A (en) * | 2015-08-20 | 2015-12-09 | 南京航空航天大学 | Throat offset type pneumatic thrust vectoring nozzle with vertical lifting function and control method |
CN108590884A (en) * | 2018-03-22 | 2018-09-28 | 南京航空航天大学 | A kind of VTOL type venturi offset fluidic vectoring nozzle based on deflector |
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CN108590884A (en) | 2018-09-28 |
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