CN204008060U - Aircraft engine model wind tunnel test becomes attack angle mechanism - Google Patents
Aircraft engine model wind tunnel test becomes attack angle mechanism Download PDFInfo
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- CN204008060U CN204008060U CN201420286814.1U CN201420286814U CN204008060U CN 204008060 U CN204008060 U CN 204008060U CN 201420286814 U CN201420286814 U CN 201420286814U CN 204008060 U CN204008060 U CN 204008060U
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Abstract
A kind of aircraft engine model wind tunnel test becomes attack angle mechanism, its frame right side is fixed with oil motor, and the rotating shaft of oil motor is connected with gear one, gear one and gear two engagements, gear two is fixed on transmission shaft with gear three, and transmission shaft is fixed in frame by bearing one, bearing two; The forward and backward side of frame is connected with mobile side plate with right arc-shaped guide rail pair by left arc-shaped guide rail pair respectively; Mobile side plate is fixedly connected with worktable, the right-hand member upper surface fixed sectors gear of mobile side plate, gear three and sector gear engagement; Self-locking mechanism is housed in frame, and four angles are provided with travel mechanism; The center of circle of left arc-shaped guide rail pair, right arc-shaped guide rail pair and sector gear with one heart and be arranged on the horizontal line of engine mockup air intake duct port surface.This kind becomes attack angle mechanism can make the angle of attack of engine mockup change dynamically, makes the result of aircraft engine model wind tunnel test more accurately, reliably.
Description
Technical field
The utility model relates to a kind of aircraft engine model wind tunnel test and becomes attack angle mechanism.
Background technology
Aero-jet engine, no matter be vortex-spraying type, turbofan or ram-type, its front portion all configures air intake duct, and rear portion configuration jet pipe.Air intake duct is the vitals of engine, its function is that the kinetic energy of the air-flow that comes head-on is converted to potential energy, speed of incoming flow is reduced to the speed that firing chamber Flame Propagation speed adapts, improves air-flow pressure and temperature, for engine provides required air mass flow.Engine mockup is carried out to wind tunnel test, being about to engine mockup is placed on the attack angle mechanism of wind-tunnel, angle by attack angle mechanism changes, change the angle of engine mockup (air intake duct), to study the impact of its different air-flow angles of attack on inlet characteristic (total pressure recovery coefficient, coefficient of flow, resistance coefficient and outlet distortion index etc.), thereby for the design of aircraft engine and manufacture, safeguard experimental basis is provided.
Compare with conventional wind tunnel test, the wind tunnel test of engine mockup has special requirement, and environment temperature is 1000 degrees Celsius, and vacuum tightness is 1000pa, the Mach number of air-flow (ratio of the speed of certain point and the velocity of sound of this point in flow field) is higher, generally more than 2; Under this environment, shock load is large, and the attack angle mechanism of wind-tunnel not only will have good Rigidity and strength, also will have good anti-seismic performance, more than its maximum angle of attack requires 10 degree.
The attack angle mechanism of existing wind-tunnel is mainly by the bottom plus-minus cushion block at platform, to carry out the angle of attack variation of the engine mockup on implementation platform, can only carry out the wind tunnel test of the static setting angle of attack, and can not become the dynamic wind tunnel test of the angle of attack.Also the attack angle mechanism that has the dynamic wind tunnel test of the variable angle of attack, its formation is, the bottom surface, middle part of platform and the column upper end of frame are hinged, the rear end of platform and the oil cylinder bar in frame are hinged, the flexible platform that makes by oil cylinder rotates along the jointed shaft of column upper end, thereby the angle of attack of the engine mockup on platform is changed.Because it is to be also engine mockup middle part around platform hinge rotation changes the angle of attack, can make the center of air intake duct port surface of motor head away from the center of wind-tunnel puff prot, and away from the air flow field lack of homogeneity at the center of wind-tunnel puff prot, thereby inconsistent with the uniform situation of air flow field of aircraft engine inlets port surface in practical flight process, and have a strong impact on reliability and the accuracy of test.
Prior art is compared, and the beneficial effects of the utility model are:
Adopt simple gears transmission and arc guide rail auxiliary driving, not only make the angle of attack of engine mockup change dynamically, and during engine mockup angle of attack variation, engine mockup rotates around the middle horizontal line of engine mockup air intake duct port surface all the time, make engine mockup air intake duct port surface center all the time with the center superposition of wind-tunnel puff prot, the even flow field of the air intake duct port surface of engine mockup, simulated more really the air inlet operating mode of engine, made the result of aircraft engine model wind tunnel test more accurately, reliably.The utility model is used gear drive simultaneously, makes whole mechanism carry load ability strong, and long service life is simple in structure.
Further, the concrete formation of self-locking mechanism of the present utility model is: the bottom of back up pad is fixed on the end of frame, fixedly mounts horizontal hydraulic cylinder in back up pad, and the lever of hydraulic cylinder is fixedly connected with the vertical edge of triangular plate through back up pad; The base of triangular plate is placed in frame, and its hypotenuse is stepped; Frame is provided with gib block at the position of both sides, triangular plate base.
Like this, when worktable and engine mockup thereof turn to after specified angle, control Hydraulic Cylinder triangular plate and to worktable center, do transverse movement along gib block, until the ladder of triangular plate hypotenuse and the front/rear end of worktable and bottom surface contacts, be close to, realize the self-locking of worktable.Make engine mockup when carrying out wind tunnel test, bear Air Flow engine mockup is produced in the situation of shock load, engine mockup can keep transfixion, thereby makes the reliable operation of engine mockup wind tunnel test, improves its stability and reliability.And need to become the angle of attack time, control Hydraulic Cylinder triangular plate along gib block to doing transverse movement away from worktable center, until the ladder of triangular plate hypotenuse leaves front/rear end and the bottom surface of worktable, realize the release of worktable, worktable can be subject to the driving of oil motor and carry out angle of attack conversion.
Further, the concrete formation of travel mechanism of the present utility model is: the top of wheel mounting cylinder is fixed on the bottom surface in the bight of frame, and the top of wheel mounting cylinder is connected with bolt thread, and the connecting rod on steamboat inserts in the cylinder chamber, bottom of wheel mounting cylinder.
Like this, in the time need to adjusting attack angle mechanism at the indoor horizontal level of wind-tunnel, by turning the bolt of travel mechanism, bolt is moved downward along wheel mounting cylinder, thereby connecting rod and steamboat are moved downward along wheel mounting cylinder, make four steamboat contact wind-tunnel bottom surfaces, wind-tunnel bottom surface is left in the lifting of frame bottom surface.Promote frame, the i.e. horizontal level of the whole mechanism of capable of regulating.After the horizontal position adjustment of mechanism is good, turn the bolt of travel mechanism, bolt is moved upward along wheel mounting cylinder, connecting rod and steamboat move upward along wheel mounting cylinder, make four steamboats leave wind-tunnel bottom surface, the contact wind-tunnel bottom surface that declines, frame bottom surface.Guaranteed the level of whole attack angle mechanism, be placed in wind-tunnel bottom surface stably, reliable operation while guaranteeing engine mockup wind tunnel test.
Below in conjunction with the drawings and specific embodiments, the utility model is described in further detail.
Utility model content
The purpose of this utility model is to provide a kind of aircraft engine model wind tunnel test and becomes attack angle mechanism, this kind becomes attack angle mechanism can make the angle of attack of engine mockup change dynamically, and during engine mockup angle of attack variation, the center of the air intake duct port surface of engine mockup all the time with the center superposition of wind-tunnel puff prot, the even flow field of the air intake duct port surface of engine mockup, makes the result of aircraft engine model wind tunnel test more accurately, reliably.
The utility model solves the technical scheme that its technical matters adopts: a kind of aircraft engine model wind tunnel test becomes attack angle mechanism, it is characterized in that:
Frame right side is fixed with oil motor, and the rotating shaft of oil motor is connected with gear one, gear one and gear two engagements, and gear two is fixed on transmission shaft with gear three, and transmission shaft is fixed in frame by bearing one, bearing two;
The forward and backward side of frame is connected with mobile side plate with right arc-shaped guide rail pair by left arc-shaped guide rail pair respectively; Mobile side plate is fixedly connected with worktable, the right-hand member upper surface fixed sectors gear of mobile side plate, gear three and sector gear engagement; The left and right end of frame is respectively equipped with self-locking mechanism; Four angles of frame are provided with travel mechanism.
The center of circle of described left arc-shaped guide rail pair, right arc-shaped guide rail pair and sector gear with one heart and be arranged on the horizontal line of engine mockup air intake duct port surface on frame left end top, worktable.
The course of work of the present utility model and principle: oil motor rotates by gear one driven gear two, gear two drives the gear three on same transmission shaft to rotate, the sector gear of three drives of gear and its engagement rotates, and sector gear drives mobile side plate and worktable along left arc-shaped guide rail pair and right arc guide rail secondary motion.Due to the center of circle of left arc-shaped guide rail pair, right arc-shaped guide rail pair and sector gear with one heart and be arranged on the horizontal line of engine mockup air intake duct port surface on frame left end top, worktable.Thereby make engine mockup on worktable and worktable thereof when rotating (the change angle of attack), the middle horizontal line around engine mockup air intake duct port surface rotates all the time.
Accompanying drawing explanation
Fig. 1 is the perspective view of the utility model embodiment.
Fig. 2 is the main TV structure schematic diagram of the utility model embodiment.
Fig. 3 is the plan structure schematic diagram of Fig. 2.
Fig. 4 is the left TV structure schematic diagram of Fig. 2.
Fig. 5 is the right TV structure schematic diagram of Fig. 2.
Specific implementation method
Embodiment
Fig. 1,2,3,4 and 5 illustrates, a kind of specific implementation of the present utility model is, a kind of aircraft engine model wind tunnel test becomes attack angle mechanism, frame 1 right side is fixed with oil motor 9, the rotating shaft of oil motor 9 is connected with gear one 10a, gear one 10a and gear two 10b engagements, gear two 10b and gear 37 are fixed on transmission shaft 11, and transmission shaft 11 is fixed in frame 1 by bearing 1, bearing 2 12;
The forward and backward side of frame 1 is connected with mobile side plate 3 with right arc-shaped guide rail pair 5 by left arc-shaped guide rail pair 2 respectively; Mobile side plate 3 is fixedly connected with worktable 4, the right-hand member upper surface fixed sectors gear 6 of mobile side plate 3, gear 37 and sector gear 6 engagements; The left and right end of frame 1 is respectively equipped with self-locking mechanism; Four angles of frame 1 are provided with travel mechanism 17.
The center of circle of described left arc-shaped guide rail pair 2, right arc-shaped guide rail pair 5 and sector gear 6 with one heart and be arranged on the horizontal line of engine mockup air intake duct port surface on frame 1 left end top, worktable 4.
The concrete formation of the self-locking mechanism that this is routine is: the bottom of back up pad 15 is fixed on the end of frame 1, fixedly mounts horizontal hydraulic cylinder 13 in back up pad 15, and the lever of hydraulic cylinder 13 is fixedly connected with the vertical edge of triangular plate 14 through back up pad 15; The base of triangular plate 14 is placed in frame, and its hypotenuse is stepped; Frame 1 is provided with gib block 16 at the position of triangular plate 14 both sides, base.
The concrete formation of this routine travel mechanism 17 is: the top of wheel mounting cylinder 17b is fixed on the bottom surface in the bight of frame 1, and the top of wheel mounting cylinder 17b is threaded with bolt 17a, and the connecting rod 17d on steamboat 17c inserts in the cylinder chamber, bottom of wheel mounting cylinder 17b.
Claims (3)
1. aircraft engine model wind tunnel test becomes an attack angle mechanism, it is characterized in that:
Frame (1) right side is fixed with oil motor (9), the rotating shaft of oil motor (9) is connected with gear one (10a), gear one (10a) and gear two (10b) engagement, gear two (10b) is fixed on transmission shaft (11) above with gear three (7), and transmission shaft (11) is fixed in frame (1) by bearing one (8), bearing two (12);
The forward and backward side of frame (1) is connected with mobile side plate (3) with right arc-shaped guide rail pair (5) by left arc-shaped guide rail pair (2) respectively; Mobile side plate (3) is fixedly connected with worktable (4), the right-hand member upper surface fixed sectors gear (6) of mobile side plate (3), gear three (7) and sector gear (6) engagement; The left and right end of frame (1) is respectively equipped with self-locking mechanism; Four angles of frame (1) are provided with travel mechanism;
The center of circle of described left arc-shaped guide rail pair (2), right arc-shaped guide rail pair (5) and sector gear (6) with one heart and be arranged on the horizontal line of the upper engine mockup air intake duct port surface of worktable (4) of frame (1) left end top.
2. a kind of aircraft engine model wind tunnel test according to claim 1 becomes attack angle mechanism, it is characterized in that, the concrete formation of described self-locking mechanism is: the bottom of back up pad (15) is fixed on the end of frame (1), the horizontal hydraulic cylinder (13) of the upper fixed installation of back up pad (15), the lever of hydraulic cylinder (13) is fixedly connected with the vertical edge of triangular plate (14) through back up pad (15); The base of triangular plate (14) is placed in frame, and its hypotenuse is stepped; Frame (1) is provided with gib block (16) at the position of triangular plate (14) both sides, base.
3. a kind of aircraft engine model wind tunnel test according to claim 1 becomes attack angle mechanism, it is characterized in that, the concrete formation of described travel mechanism is: the top of wheel mounting cylinder (17b) is fixed on the bottom surface in the bight of frame (1), the top of wheel mounting cylinder (17b) is threaded with bolt (17a), and the connecting rod (17d) on steamboat (17c) inserts in the cylinder chamber, bottom of wheel mounting cylinder (17b).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420286814.1U CN204008060U (en) | 2014-05-30 | 2014-05-30 | Aircraft engine model wind tunnel test becomes attack angle mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420286814.1U CN204008060U (en) | 2014-05-30 | 2014-05-30 | Aircraft engine model wind tunnel test becomes attack angle mechanism |
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| CN204008060U true CN204008060U (en) | 2014-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420286814.1U Withdrawn - After Issue CN204008060U (en) | 2014-05-30 | 2014-05-30 | Aircraft engine model wind tunnel test becomes attack angle mechanism |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104019959A (en) * | 2014-05-30 | 2014-09-03 | 西南交通大学 | Variable attack angel apparatus for wind tunnel test of aircraft engine model |
| CN105806585A (en) * | 2016-05-11 | 2016-07-27 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel large attack angle pitching dynamic stalling test device |
| CN107843435A (en) * | 2017-11-24 | 2018-03-27 | 北京动力机械研究所 | Engine variable sector inlet pressure distortion analog board |
| CN107976315A (en) * | 2017-11-17 | 2018-05-01 | 西安航天动力测控技术研究所 | A kind of angle of attack yaw angle servo control mechanism for Ducted rocket free jet test |
| CN108760221A (en) * | 2018-05-31 | 2018-11-06 | 北京空天技术研究所 | Wind tunnel test guiding device |
| CN118010292A (en) * | 2024-04-09 | 2024-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Sub-transonic progressive direct connection wind tunnel test model supporting device and design method |
| CN118010296A (en) * | 2024-04-09 | 2024-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Support system for supersonic concurrent direct connection wind tunnel test and design method |
-
2014
- 2014-05-30 CN CN201420286814.1U patent/CN204008060U/en not_active Withdrawn - After Issue
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104019959A (en) * | 2014-05-30 | 2014-09-03 | 西南交通大学 | Variable attack angel apparatus for wind tunnel test of aircraft engine model |
| CN104019959B (en) * | 2014-05-30 | 2016-08-17 | 西南交通大学 | A kind of aircraft engine model wind tunnel test attack angle changing device |
| CN105806585A (en) * | 2016-05-11 | 2016-07-27 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel large attack angle pitching dynamic stalling test device |
| CN107976315A (en) * | 2017-11-17 | 2018-05-01 | 西安航天动力测控技术研究所 | A kind of angle of attack yaw angle servo control mechanism for Ducted rocket free jet test |
| CN107976315B (en) * | 2017-11-17 | 2019-05-31 | 西安航天动力测控技术研究所 | A kind of angle of attack yaw angle servo mechanism for Ducted rocket free jet test |
| CN107843435A (en) * | 2017-11-24 | 2018-03-27 | 北京动力机械研究所 | Engine variable sector inlet pressure distortion analog board |
| CN108760221A (en) * | 2018-05-31 | 2018-11-06 | 北京空天技术研究所 | Wind tunnel test guiding device |
| CN108760221B (en) * | 2018-05-31 | 2020-05-19 | 北京空天技术研究所 | Wind tunnel test guiding device |
| CN118010292A (en) * | 2024-04-09 | 2024-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Sub-transonic progressive direct connection wind tunnel test model supporting device and design method |
| CN118010296A (en) * | 2024-04-09 | 2024-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Support system for supersonic concurrent direct connection wind tunnel test and design method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141210 Effective date of abandoning: 20160817 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |