CN105865742A - Wind tunnel test aero-engine thrust vector jet pipe steering system - Google Patents
Wind tunnel test aero-engine thrust vector jet pipe steering system Download PDFInfo
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- CN105865742A CN105865742A CN201610210207.0A CN201610210207A CN105865742A CN 105865742 A CN105865742 A CN 105865742A CN 201610210207 A CN201610210207 A CN 201610210207A CN 105865742 A CN105865742 A CN 105865742A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
Abstract
The invention discloses a wind tunnel test aero-engine thrust vector jet pipe steering system. The system comprises a jet pipe steering system, a master control computer and an aero-engine simulator, wherein the jet pipe steering system comprises a controller, a motor, a transmission mechanism, a steering mechanism and a contraction and expansion nozzle; the controller and the master control computer communicate with each other, and the output end of the controller is connected with the control port of the motor; and the motor drives the steering mechanism to move through the transmission mechanism, the steering mechanism drives the contraction and expansion nozzle to deflect, and thus omnidirectional controllable deflection of an airplane model engine exhaust nozzle is realized. The system brought forward by the system can satisfy the need for a wind tunnel test related to correlated thrust vector technologies, automatically adjusts the deflection of a vector jet pipe and is high in test efficiency.
Description
Technical field
The invention belongs to wind tunnel experiment device technique field, particularly relate to a kind of wind tunnel test boat and send out Thrust-vectoring Nozzle steering.
Background technology
With F22, T50 etc. four the new fighter that represents of Dai Jiwei there is good post stall maneuver ability and STOL ability, and to possess these abilities, current most efficient method uses Thrust Vectoring Technology exactly.Thrust Vectoring Technology refers to change engine exhaust direction by the deflection of control aircraft engine jet pipe in real time, so that aircraft obtains extra operating torque, its prominent feature is that operating torque is relevant with the yawing moment of jet pipe, is not affected by the attitude of aircraft own.Utilize this feature, can aircraft make low speed, big angle of attack maneuvering flight and utilize thrust vectoring to provide during a few near failure of control surface additional manipulation moment to control the maneuvering flight of aircraft.Use Thrust Vectoring Technology to be possible not only to make air maneuver be greatly improved, but also be conducive to reducing the liftoff and touchdown speed of aircraft, shorten the ground run distance of aircraft, make aircraft be provided with unprecedented STOL capability.It addition, utilize thrust vectoring, aircraft control surface can be substantially reduced, so that the Stealth Fighter of aircraft is improved.It can be said that the application of aircraft thrust vectoring technology can give fighter plane super maneuverability, STOL and low detectivity, it is greatly enhanced operation validity and the survival ability of fighter plane.
Sending out the thrust vectoring impact on aircraft handling to obtain boat, meet the Flight Control Law design requirement of aircraft, domestic and international Ge great research institution has carried out substantial amounts of ground experiment and wind tunnel test.At present, wind tunnel test remains the resource of the unique feasible of mass data needed for providing research and development comprehensively and verifying aerocraft system, and the relevant ground flying test of thrust vectoring to be carried out and wind-tunnel technique research, a kind of effective method is exactly to develop the vector spray of wind tunnel test aircraft engine, and carry out wind tunnel test and ground flying test based on this, thus obtain related data.
Relevant wind-tunnel boat sends out the research of Thrust Vectoring Technology at present, is all to carry out based on the jet pipe of fixed deflection angle, still can not automatically control the deflection of vector spray, and test efficiency is low, and cannot carry out the wind tunnel model free flight test that boat thrust vectoring is relevant.
Summary of the invention
In order to solve the problems referred to above, the present invention proposes a kind of wind tunnel test boat and sends out Thrust-vectoring Nozzle steering, it is possible to meets the wind tunnel test needs that relevant Thrust Vectoring Technology is relevant, is automatically adjusted the deflection of vector spray, is effectively increased test efficiency.
For reaching above-mentioned purpose, the technical solution used in the present invention is: a kind of wind tunnel test boat sends out Thrust-vectoring Nozzle steering, including jet pipe steering, main control computer and aero-engine simulator, described jet pipe steering includes that controller, motor, transmission mechanism, steering mechanism and receipts expand spout；
Described controller is in communication with each other with described main control computer, and the output of described controller connects the control port of described motor；Described motor drives steering mechanism to move by transmission mechanism, steering mechanism drive to receive and expand spout deflection, it is achieved the controlled deflection of omnidirectional of model aircraft nozzle；
Described steering mechanism includes fixing end, yaw angle mechanism and angle of pitch mechanism, described fixing end, yaw angle mechanism and angle of pitch mechanism are sequentially connected in series, the rotary shaft of described yaw angle mechanism and angle of pitch mechanism is mutually perpendicular to, and yaw angle and pitch movement will not interfere；
The fixing end of described steering mechanism connects firmly with the outlet of described aero-engine simulator, and the port of export of described steering mechanism connects firmly with receiving expansion spout, and the pressure-air making aero-engine simulator send is sprayed from receiving expansion spout by steering mechanism.
Further, described jet pipe steering is arranged on inside model aircraft, is connected with outside main control computer by controlling cable.This design is used to make the compact conformation of system, appearance and size little, the installation restrictive condition of wide size in meeting model aircraft；In process of the test, this system does not contacts with model aircraft housing and does not highlight model surface, it is to avoid its impact measuring model aerodynamic loading during test, meets the requirement to mechanism's appearance and size of low-speed wind tunnel test and model aircraft.
Further, described steering mechanism uses the cannulated structure of controlled deflection, aero-engine simulator the pressure-air sent sprays by receiving expansion spout according to given deflection angle behind the inner passage of steering mechanism.By the controller controllable adjustment to steering mechanism's corner so that the receipts expansion spout direction flowing through steering mechanism's internal high pressure air is controlled, it is achieved thereby that omnidirectional's deflection simulation in aero-engine simulator exhaust airstream direction.
Further, yaw angle mechanism and the angle of pitch mechanism of described steering mechanism all uses RHRPR mechanism.Wherein R be revolute pair, H be screw pair, P be the code name of moving sets.
Further, described motor includes yaw angle motor and angle of pitch motor.
Further, described yaw angle mechanism includes yaw angle planetary reducer, yaw angle ball-screw, yaw angle nut, yaw angle pin, yaw angle mechanism shift fork and yaw angle mechanism body；
Described yaw angle motor connects described yaw angle planetary reducer, yaw angle ball-screw is driven to rotate by yaw angle planetary reducer, described yaw angle ball-screw rotation forces yaw angle nut axially moves along yaw angle ball-screw, described yaw angle nut connects firmly and drives yaw angle pin axially to move along yaw angle ball-screw with described yaw angle pin, described yaw angle pin promotes described yaw angle mechanism shift fork, yaw angle mechanism body uses sphere-pin pair structure to be connected with fixing end, described sphere-pin pair pin is arranged in sphere-pin pair structure, yaw angle mechanism shift fork makes yaw angle mechanism body rotate around sphere-pin pair pin yaw angle, this yaw angle rotates to drive angle of pitch mechanism and receive expansion spout and does yaw angle motion.
Further, described yaw angle mechanism is hollow structure, and the cooperation face at described yaw angle rotation is sphere, and uses extrusion pressing type sealing means at rotation.Spherical structure ensures that the revolute pair motor function of hollow structure requires and the sealing of contact surface；This sealing means compact conformation, kinetic frictional resistances are little, both can guarantee that the sealing between moving component, can ensure that again motion dexterity.
Further, described angle of pitch mechanism includes angle of pitch planetary reducer, angle of pitch ball-screw, angle of pitch nut, angle of pitch pin, angle of pitch mechanism shift fork and angle of pitch mechanism body；
Described angle of pitch motor connects described angle of pitch planetary reducer, described angle of pitch planetary reducer drives described angle of pitch ball-screw to rotate, described angle of pitch ball-screw rotation forces angle of pitch nut axially moves along angle of pitch ball-screw, angle of pitch nut drives the angle of pitch pin connected firmly with it axially to move along angle of pitch ball-screw again, and angle of pitch pin promotes angle of pitch mechanism shift fork；Angle of pitch mechanism body uses sphere-pin pair structure to be connected with yaw angle mechanism, the sphere-pin pair pin of sphere-pin pair structure is arranged on junction, angle of pitch mechanism shift fork makes angle of pitch mechanism body rotate around the sphere-pin pair pin angle of pitch, and this angle of pitch rotates and the receipts connected firmly with angle of pitch mechanism body expansion spout can be driven to do pitch movement.
Further, described angle of pitch mechanism is hollow structure, and the cooperation face at described angle of pitch rotation is sphere, and uses extrusion pressing type sealing means at rotation.Spherical structure ensures that the revolute pair motor function of hollow structure requires and the sealing of contact surface；This sealing means compact conformation, kinetic frictional resistances are little, both can guarantee that the sealing between moving component, can ensure that again motion dexterity.
A kind of wind tunnel test boat proposed by the invention sends out Thrust-vectoring Nozzle steering, the beneficial effect of employing the technical program:
By the controllable adjustment of steering mechanism so that the direction flowing through steering mechanism's internal high pressure air is controlled, it is achieved thereby that boat sends a manuscript to the compositor omnidirectional's deflection simulation in entraining air stream direction.
Steering mechanism both can guarantee that pressure-air was passed through in its inside and channel wall will not be revealed, and the omnidirectional that the bending that can pass through again channel wall drives receipts expansion spout rotation to realize aero-engine simulator vector spray deflects.
Steering mechanism is made up of yaw angle mechanism and angle of pitch mechanisms in series, and the rotary shaft of yaw angle mechanism and angle of pitch mechanism is mutually perpendicular to, and makes yaw angle and pitch movement to interfere.
Native system only by controlling cable and external connection, can meet the requirement to mechanism's appearance and size of low-speed wind tunnel test and model aircraft；Described jet pipe steering is arranged on inside model aircraft, during wind tunnel test, it does not touches with model housing and does not highlight model surface, and system architecture is compact, appearance and size is little, it is to avoid its impact measuring model aerodynamic loading during test.
Accompanying drawing explanation
Fig. 1 is the structure diagram of a kind of wind tunnel test boat Thrust-vectoring Nozzle steering of the present invention；
Fig. 2 is yaw angle or the principle schematic of angle of pitch mechanism in the embodiment of the present invention；
Fig. 3 is the structural representation of yaw angle mechanism in the embodiment of the present invention；
Fig. 4 is the structural representation of angle of pitch mechanism in the embodiment of the present invention；
Wherein, 1 is main control computer, and 2 is controller, and 3 is motor, and 4 is transmission mechanism, and 5 is steering mechanism, and 6 is to receive to expand spout, and 7 is fixing end, and 8 is yaw angle mechanism, and 9 is angle of pitch mechanism；
81 is yaw angle motor, and 82 is yaw angle planetary reducer, and 83 is yaw angle ball-screw, and 84 is yaw angle nut, and 85 is yaw angle pin, and 86 is yaw angle mechanism shift fork, and 87 is yaw angle mechanism body, and 88 is sphere-pin pair pin, and 89 is O RunddichtringO；
91 is angle of pitch motor, and 92 is angle of pitch planetary reducer, and 93 is angle of pitch ball-screw, and 94 is angle of pitch nut, and 95 is angle of pitch pin, and 96 is angle of pitch mechanism shift fork, and 97 is angle of pitch mechanism body, and 98 is sphere-pin pair pin, and 99 is O RunddichtringO.
Detailed description of the invention
In order to make the object, technical solutions and advantages of the present invention clearer, the present invention is further elaborated below in conjunction with the accompanying drawings.
In embodiment one, shown in Figure 1, the present invention proposes a kind of wind tunnel test boat and sends out Thrust-vectoring Nozzle steering, including jet pipe steering, main control computer 1 and aero-engine simulator, described jet pipe steering includes controller 2, motor 3, transmission mechanism 4, steering mechanism 5 and receives expansion spout 6；
Described controller 2 is in communication with each other with described main control computer 1, and the output of described controller 2 connects the control port of described motor 3；Described motor 3 drives steering mechanism 5 to move by transmission mechanism 4, steering mechanism 5 drive receipts to expand spout 6 and deflect, it is achieved the controlled deflection of omnidirectional of model aircraft nozzle；
Described steering mechanism 5 includes fixing end 7, yaw angle mechanism 8 and angle of pitch mechanism 9, described fixing end 7, yaw angle mechanism 8 and angle of pitch mechanism 9 are sequentially connected in series, the rotary shaft of described yaw angle mechanism 8 and angle of pitch mechanism 9 is mutually perpendicular to, and makes yaw angle and pitch movement to interfere；
The fixing end 7 of described steering mechanism 5 connects firmly with the outlet of described aero-engine simulator, and the port of export of described steering mechanism 5 connects firmly with receiving expansion spout 6, makes pressure-air pass through steering mechanism 5 and sprays from receiving expansion spout 6.
Wherein, described jet pipe steering is arranged on inside model aircraft, is connected with the main control computer 1 being placed in outside model aircraft by controlling cable.This design is used to make the compact conformation of system, appearance and size little, the installation restrictive condition of wide size in meeting model aircraft；In process of the test, this system does not contacts with model aircraft housing and does not highlight model surface, it is to avoid its impact measuring model aerodynamic loading during test, meets the requirement to mechanism's appearance and size of low-speed wind tunnel test and model aircraft.
Wherein, described steering mechanism 5 uses the cannulated structure of controlled deflection, aero-engine simulator the pressure-air sent sprays by receiving expansion spout 6 according to given deflection angle behind the inner passage of steering mechanism 5.By the controller 2 controllable adjustment to steering mechanism 5 corner so that the receipts expansion spout direction flowing through steering mechanism 5 internal high pressure air is controlled, it is achieved thereby that omnidirectional's deflection simulation in aero-engine simulator exhaust airstream direction.
In embodiment two, on the basis of embodiment one, the yaw angle mechanism 8 of described steering mechanism 5 and angle of pitch mechanism 9 all use RHRPR mechanism.Wherein R, H, P are respectively the code name of revolute pair, screw pair, moving sets.
Described motor 3 includes yaw angle motor 81 and angle of pitch motor 91.
As it is shown on figure 3, described yaw angle mechanism 8 includes yaw angle planetary reducer 82, yaw angle ball-screw 83, yaw angle nut 84, yaw angle pin 85, yaw angle mechanism shift fork 86 and yaw angle mechanism body 87；
nullAs shown in Figure 2，Described yaw angle motor 81 connects described yaw angle planetary reducer 82，Yaw angle ball-screw 83 is driven to rotate by yaw angle planetary reducer 82，Described yaw angle ball-screw 83 rotation forces yaw angle nut 84 moves axially along yaw angle ball-screw 83，Described yaw angle nut 84 connects firmly and drives yaw angle pin 85 to move axially along yaw angle ball-screw 83 with described yaw angle pin 85，Described yaw angle pin 85 promotes described yaw angle mechanism shift fork 86，Yaw angle mechanism body 87 is connected with fixing end 7 employing sphere-pin pair structure，Described sphere-pin pair pin 88 is arranged in sphere-pin pair structure，Yaw angle mechanism shift fork 86 makes yaw angle mechanism body 87 rotate around sphere-pin pair pin 88 yaw angle，This yaw angle rotates to drive angle of pitch mechanism 9 and receive expansion spout 6 and does yaw angle motion.
Wherein, described yaw angle mechanism 8 is hollow structure, and the cooperation face at described yaw angle rotation is sphere, and uses extrusion pressing type sealing means at rotation, can use O RunddichtringO 89.Spherical structure ensures that the revolute pair motor function of hollow structure requires and the sealing of contact surface；This sealing means compact conformation, kinetic frictional resistances are little, both can guarantee that the sealing between moving component, can ensure that again motion dexterity.
In embodiment three, on the basis of embodiment one, the yaw angle mechanism 8 of described steering mechanism 5 and angle of pitch mechanism 9 all use RHRPR mechanism.Wherein R, H, P are respectively the code name of revolute pair, screw pair, moving sets.
Described motor 3 includes yaw angle motor 81 and angle of pitch motor 91.
As shown in Figure 4, described angle of pitch mechanism 9 includes angle of pitch planetary reducer 92, angle of pitch ball-screw 93, angle of pitch nut 94, angle of pitch pin 95, angle of pitch mechanism shift fork 96 and angle of pitch mechanism body 97；
As shown in Figure 2, described angle of pitch motor 91 connects described angle of pitch planetary reducer 92, described angle of pitch planetary reducer 92 drives described angle of pitch ball-screw 93 to rotate, described angle of pitch ball-screw 93 rotation forces angle of pitch nut 94 moves axially along angle of pitch ball-screw 93, angle of pitch nut 94 drives the angle of pitch pin 95 connected firmly with it to move axially along angle of pitch ball-screw 93 again, and angle of pitch pin 95 promotes angle of pitch mechanism shift fork 96；Angle of pitch mechanism body 97 uses sphere-pin pair structure to be connected with yaw angle mechanism 8, the sphere-pin pair pin 98 of sphere-pin pair structure is arranged on junction, angle of pitch mechanism shift fork 96 makes angle of pitch mechanism body 97 rotate around sphere-pin pair pin 98 angle of pitch, and this angle of pitch rotates and the receipts connected firmly with angle of pitch mechanism body 97 expansion spout 6 can be driven to do pitch movement.
Wherein, described angle of pitch mechanism 9 is hollow structure, and the cooperation face at described angle of pitch rotation is sphere, and uses extrusion pressing type sealing means at rotation, can use O RunddichtringO 99.Spherical structure ensures that the revolute pair motor function of hollow structure requires and the sealing of contact surface；This sealing means compact conformation, kinetic frictional resistances are little, both can guarantee that the sealing between moving component, can ensure that again motion dexterity.
In order to be better understood from the present invention, below to the description that the operation principle work of the present invention is the most complete:
Before wind tunnel test, being fixedly mounted on inside model aircraft by described jet pipe steering, the fixing end 7 of system connects firmly reliably with the outlet of aero-engine simulator, it is desirable in process of the test, it will not touch with model aircraft housing and not highlight model surface；
During wind tunnel test, steering mechanism 5 inner passage is entered from the pressure-air of aero-engine simulator ejection, by steering mechanism 5, yaw angle and the angle of pitch of model aircraft afterbody vector receipts expansion jet pipe 6 are adjusted, the direction passing through steering mechanism 5 internal high pressure air changes as required, finally expanded spout 6 by receipts to discharge, it is achieved thereby that aero-engine drives omnidirectional's deflection simulation in model aircraft exhaust airstream direction；Exhaust airstream direction can realize arbitrarily angled combination in the range of the angle of pitch-10 °～+10 °, yaw angle-10 °～+10 °.
The general principle of the present invention and principal character and advantages of the present invention have more than been shown and described.Skilled person will appreciate that of the industry; the present invention is not restricted to the described embodiments; the principle that the present invention is simply described described in above-described embodiment and specification; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements both fall within scope of the claimed invention.The claimed scope of this reality invention is defined by appending claims and equivalent thereof.
Claims (9)
1. a wind tunnel test boat sends out Thrust-vectoring Nozzle steering, including jet pipe steering, main control computer (1) and aero-engine simulator, it is characterized in that, described jet pipe steering includes controller (2), motor (3), transmission mechanism (4), steering mechanism (5) and receives expansion spout (6)；
Described controller (2) is in communication with each other with described main control computer (1), and the output of described controller (2) connects the control port of described motor (3)；Described motor (3) drives steering mechanism (5) to move by transmission mechanism (4), steering mechanism (5) drive to receive and expand spout (6) deflection；
Described steering mechanism (5) includes fixing end (7), yaw angle mechanism (8) and angle of pitch mechanism (9), described fixing end (7), yaw angle mechanism (8) and angle of pitch mechanism (9) are sequentially connected in series, and the rotary shaft of described yaw angle mechanism (8) and angle of pitch mechanism (9) is mutually perpendicular to；
The fixing end (7) of described steering mechanism (5) connects firmly with the outlet of described aero-engine simulator, the port of export of described steering mechanism (5) connects firmly with receiving expansion spout (6), and the pressure-air making aero-engine simulator send is sprayed from receiving expansion spout (6) by steering mechanism (5).
A kind of wind tunnel test boat the most according to claim 1 sends out Thrust-vectoring Nozzle steering, it is characterised in that described jet pipe steering is arranged on inside model aircraft, is connected with the main control computer (1) being placed in outside model aircraft by controlling cable.
A kind of wind tunnel test boat the most according to claim 1 sends out Thrust-vectoring Nozzle steering, it is characterized in that, described steering mechanism (5) uses the cannulated structure of controlled deflection, aero-engine simulator the pressure-air sent sprays by receiving expansion spout (6) according to given deflection angle behind the inner passage of steering mechanism (5).
A kind of wind tunnel test boat the most according to claim 1 sends out Thrust-vectoring Nozzle steering, it is characterised in that the yaw angle mechanism (8) of described steering mechanism (5) and angle of pitch mechanism (9) all use RHRPR mechanism.
A kind of wind tunnel test boat the most according to claim 4 sends out Thrust-vectoring Nozzle steering, it is characterised in that described motor (3) includes yaw angle motor (81) and angle of pitch motor (91).
A kind of wind tunnel test boat the most according to claim 5 sends out Thrust-vectoring Nozzle steering, it is characterized in that, described yaw angle mechanism (8) includes yaw angle planetary reducer (82), yaw angle ball-screw (83), yaw angle nut (84), yaw angle pin (85), yaw angle mechanism shift fork (86) and yaw angle mechanism body (87)；
Described yaw angle motor (81) connects described yaw angle planetary reducer (82), yaw angle ball-screw (83) is driven to rotate by yaw angle planetary reducer (82), described yaw angle ball-screw (83) rotation forces yaw angle nut (84) moves axially along yaw angle ball-screw (83), described yaw angle nut (84) connects firmly and drives yaw angle pin (85) to move axially along yaw angle ball-screw (83) with described yaw angle pin (85), and described yaw angle pin (85) promotes described yaw angle mechanism shift fork (86)；Yaw angle mechanism body (87) uses sphere-pin pair structure to be connected with fixing end (7), described sphere-pin pair pin (88) is arranged in sphere-pin pair structure, described yaw angle mechanism shift fork (86) makes yaw angle mechanism body (87) rotate around sphere-pin pair pin (88) yaw angle, and this yaw angle rotates to drive angle of pitch mechanism (9) and receive expansion spout (6) and does yaw angle motion.
A kind of wind tunnel test boat the most according to claim 6 sends out Thrust-vectoring Nozzle steering, it is characterised in that described yaw angle mechanism (8) is hollow structure, and the cooperation face at described yaw angle rotation is sphere, and uses extrusion pressing type sealing means at rotation.
A kind of wind tunnel test boat the most according to claim 5 sends out Thrust-vectoring Nozzle steering, it is characterized in that, described angle of pitch mechanism (9) includes angle of pitch planetary reducer (92), angle of pitch ball-screw (93), angle of pitch nut (94), angle of pitch pin (95), angle of pitch mechanism shift fork (96) and angle of pitch mechanism body (97)；
Described angle of pitch motor (91) connects described angle of pitch planetary reducer (92), described angle of pitch planetary reducer (92) drives described angle of pitch ball-screw (93) to rotate, described angle of pitch ball-screw (93) rotation forces angle of pitch nut (94) moves axially along angle of pitch ball-screw (93), angle of pitch nut (94) drives the angle of pitch pin (95) connected firmly with it to move axially along angle of pitch ball-screw (93) again, and angle of pitch pin (95) promotes angle of pitch mechanism shift fork (96)；Angle of pitch mechanism body (97) uses sphere-pin pair structure to be connected with yaw angle mechanism (8), the sphere-pin pair pin (98) of sphere-pin pair structure is arranged on junction, angle of pitch mechanism shift fork (96) makes angle of pitch mechanism body (97) rotate around sphere-pin pair pin (98) angle of pitch, and this angle of pitch rotates and the receipts connected firmly with angle of pitch mechanism body (97) expansion spout (6) can be driven to do pitch movement.
A kind of wind tunnel test boat the most according to claim 8 sends out Thrust-vectoring Nozzle steering, it is characterised in that described angle of pitch mechanism (9) is hollow structure, and the cooperation face at described angle of pitch rotation is sphere, and uses extrusion pressing type sealing means at rotation.
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| CN201610210207.0A CN105865742B (en) | 2016-04-07 | 2016-04-07 | A kind of wind tunnel test boat hair Thrust-vectoring Nozzle steering |
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| CN201610210207.0A CN105865742B (en) | 2016-04-07 | 2016-04-07 | A kind of wind tunnel test boat hair Thrust-vectoring Nozzle steering |
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| CN105865742B CN105865742B (en) | 2017-05-31 |
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| CN106679923A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司沈阳空气动力研究所 | Pressure decoupling apparatus for high-speed jet-flow impact force-measuring model |
| CN107941450A (en) * | 2017-09-20 | 2018-04-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of spout angle eddy generator for suppressing the low frequency pulsation of opening jet stream wind-tunnel |
| CN115653780A (en) * | 2022-12-13 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | Fluid thrust vectoring nozzle suitable for tailless overall arrangement |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106679923A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司沈阳空气动力研究所 | Pressure decoupling apparatus for high-speed jet-flow impact force-measuring model |
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| CN107941450A (en) * | 2017-09-20 | 2018-04-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of spout angle eddy generator for suppressing the low frequency pulsation of opening jet stream wind-tunnel |
| CN107941450B (en) * | 2017-09-20 | 2023-11-03 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet angle vortex generator for inhibiting low-frequency pressure pulsation of open jet wind tunnel |
| CN115653780A (en) * | 2022-12-13 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | Fluid thrust vectoring nozzle suitable for tailless overall arrangement |
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|---|---|
| CN105865742B (en) | 2017-05-31 |
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