CN111999031A - Sudden change ground effect ground simulation device based on rotary test bed - Google Patents
Sudden change ground effect ground simulation device based on rotary test bed Download PDFInfo
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- CN111999031A CN111999031A CN202010951524.4A CN202010951524A CN111999031A CN 111999031 A CN111999031 A CN 111999031A CN 202010951524 A CN202010951524 A CN 202010951524A CN 111999031 A CN111999031 A CN 111999031A
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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
- G01M9/08—Aerodynamic models
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Abstract
The invention provides a sudden change ground effect ground simulation device based on a rotary test bed, which comprises a rotary arm unit, a driving unit, a supporting frame and an arc-shaped plate surface, wherein the supporting frame is fixedly arranged on a test ground, the rotary arm unit is in a cross-shaped symmetrical structure and is connected with the driving unit, the driving unit is fixedly connected with the supporting frame, a test model is arranged at the outer end of a rotary arm at one side of the rotary arm unit, the driving unit drives the rotary arm unit to rotate around the self axis, the rotary arm unit drives an aircraft to rotate around the self axis in a large radius, the arc-shaped plate surface is vertically and fixedly connected with the test ground, the distance between the arc-shaped plate surface and the axis of the rotary arm unit is larger than the length of the rotary arm at one side of the arc-shaped plate surface, the. The device can simulate the influence of sudden change ground effect on the aerodynamic characteristics of the aircraft in the take-off and landing process, reduce the test flight risk and shorten the development period of a new aircraft.
Description
Technical Field
The invention belongs to the field of aircraft tests, and relates to a sudden change ground effect ground simulation device based on a rotary test bed.
Background
The ground effect causes the aerodynamic force and flow field structure of the aircraft such as lift force, resistance, pitching moment and the like to be changed violently, and the aircraft presents strong nonlinear characteristics. Because the airplane is generally positioned at the edge of a stall attack angle or a stall speed in the taking-off and landing process, if the nonlinear aerodynamic force change in the taking-off and landing process cannot be accurately measured, the flight control system may send out a counter-effect instruction, so that the airplane may enter the stall speed or the stall attack angle, a flight accident is caused, and the taking-off and landing safety of the airplane is influenced. The sudden ground effect refers to the influence of the ground effect on the dynamic aerodynamic characteristics of the airplane under the condition that the ground suddenly appears or disappears in the process of taking off and landing of the airplane. The sudden change ground effect is mainly generated in the processes of landing and leaving of carrier-based aircraft of an aircraft carrier. Compared with the conventional take-off and landing process on the ground, the take-off and landing process of the carrier-based aircraft carrier is more difficult and has higher safety risk. A test facility for accurately simulating the influence of the sudden change ground effect on the aerodynamic characteristics of the carrier-based aircraft is urgently needed.
Disclosure of Invention
In order to solve the defects, the invention aims to provide a sudden change ground effect ground simulation device based on a rotary test bed, which can be used for carrying out a research test on influence of a sudden change ground effect on aerodynamic characteristics of an aircraft in the taking-off and landing processes on the ground.
The technical scheme of the invention is as follows: the utility model provides a sudden change ground effect ground analogue means based on rotation test platform, includes swinging boom unit, drive unit, braced frame and arc face, braced frame fixed mounting is experimental subaerial, the swinging boom unit be cross symmetrical structure, the swinging boom unit is connected with drive unit, drive unit and braced frame fixed connection, the test model is installed to one side swinging boom outer end of swinging boom unit, drive unit drive swinging boom unit is rotatory around its self axle center, the swinging boom unit drives the aircraft and is the major radius rotation around its self axle center, the arc face is with the perpendicular fixed connection in experimental ground, the arc face is greater than the length of its one side swinging boom with the distance in swinging boom unit axle center, the centre of a circle of arc face and the axle center coincidence of swinging boom unit, the arc face is used for simulating the ground that the aircraft.
The invention also has the following technical characteristics:
1. the rotary arm unit comprises two sets of rotary support arms, two inhaul cables, a switching support rod, a pull rod, a connecting plate, a rotary joint, a balance weight arm, a balance weight block and a rotary shaft, wherein the two opposite ends of the rotary joint are fixedly connected with one ends of the two sets of rotary support arms respectively, the upper end of the rotary joint is fixedly connected with the bottom end of the pull rod through the connecting plate, the lower end of the rotary joint is fixedly connected with the rotary shaft, one end of each inhaul cable is fixedly connected with the upper end of the pull rod, the other end of each inhaul cable is fixedly connected with the other end of one set of rotary support arm, the other end of one set of rotary support arm is fixedly connected with the balance weight block through the balance weight.
2. The drive unit include the rotation axis seat, the bearing group, the sliding ring, the tail-hood, vice bevel gear, main bevel gear, the transmission shaft mount pad, the transmission shaft, universal joint and motor, the transmission shaft mount pad links firmly with the rotation axis seat, the transmission shaft is located the transmission shaft mount pad, the rotation axis passes through the bearing group to be installed in the rotation axis seat, the tail-hood links firmly with the rotation axis seat end, the sliding ring is installed to the afterbody of rotation axis, the rotation axis links firmly with vice bevel gear, vice bevel gear and main bevel gear meshing, main bevel gear links firmly with the one end of transmission shaft, the motor passes through the universal joint and is connected with the other one end of.
3. The supporting frame is fixedly connected with the rotating shaft seat, and the rotating shaft seat is perpendicular to the test ground.
The invention has the following advantages and beneficial effects: the device can simulate the influence of the sudden change ground effect on the aerodynamic characteristics of the aircraft in the take-off and landing process, so that the research and test on the influence of the sudden change ground effect on the aerodynamic characteristics of the aircraft in the take-off and landing process can be carried out on the ground, the response parameters of the aircraft in the sudden change ground effect motion process are measured, the motion rule of the aircraft is mastered, necessary technical support is provided for the safe flight of the aircraft, the test flight risk is reduced, and the new aircraft development period is shortened.
Drawings
FIG. 1 is a front view of the apparatus of the present invention;
FIG. 2 is a side view of the apparatus of the present invention;
FIG. 3 is a top view of the apparatus of the present invention;
FIG. 4 is a two-dimensional view of a rotary arm assembly of the present invention;
FIG. 5 is a two-dimensional view of a drive unit of the present invention;
FIG. 6 is a two-dimensional view of the support frame assembly of the present invention;
FIG. 7 is a two-dimensional view of the arcuate flooring assembly of the present invention;
Detailed Description
The invention is further illustrated by way of example in the accompanying drawings of the specification:
example 1
As shown in fig. 1-7, a sudden change ground effect ground simulation device based on a rotary test bed comprises a rotating arm unit, a driving unit, a supporting frame and an arc-shaped plate surface, wherein the supporting frame is fixedly arranged on a test ground, the swinging boom unit be cross symmetrical structure, the swinging boom unit is connected with drive unit, drive unit and braced frame fixed connection, the test model is installed to one side swinging boom outer end of swinging boom unit, drive unit drive swinging boom unit is rotatory around its self axle center, the swinging boom unit drives the aircraft and is the large radius rotation around its self axle center, arc face and the perpendicular fixed connection in test ground, the distance in arc face and swinging boom unit axle center is greater than the length of its one side swinging boom, the centre of a circle of arc face and the axle center coincidence of swinging boom unit, the arc face is used for simulating the ground that the aircraft got into the business turn over.
As shown in fig. 4, the rotating arm unit includes two sets of rotating arms 4, two pulling cables 5, a switching supporting rod 10, a supporting rod 11, a pulling rod 6, a connecting plate 7, a rotating joint 8, a counterweight arm 3, a counterweight block 2 and a rotating shaft 12, wherein two opposite ends of the rotating joint 8 are fixedly connected with one ends of the two sets of rotating arms 4 respectively, the upper end of the rotating joint 8 is fixedly connected with the bottom end of the pulling rod 6 through the connecting plate 7, the lower end of the rotating joint 8 is fixedly connected with the rotating shaft 12, because the span of the rotating arms is large, in order to prevent the rotating arms from bending downwards in the rotating process, one end of each pulling cable 5 is fixedly connected with the upper end of the pulling rod 6, the other end is fixedly connected with the other end of a set of rotating arms, and the bending downwards. In order to ensure the static balance of the rotating arm in the rotating process, the other end of one set of rotating support arm is fixedly connected with a balancing weight 2 through a balance weight arm 3 and a locking nut 1, the other end of the other set of rotating support arm is fixedly connected with a switching support rod 10, the switching support rod 10 is fixedly connected with a support rod 11 through a conical surface, and the support rod 11 is fixedly connected with a test model.
As shown in fig. 5, the driving unit includes a rotating shaft seat 13, a bearing set 14, a slip ring 16, a tail cover 17, a secondary bevel gear 15, a primary bevel gear 18, a transmission shaft mounting seat 19, a transmission shaft 20, a universal joint 21, a motor 22, wherein the transmission shaft mounting seat 19 is fixedly connected with the rotating shaft seat 13, the transmission shaft 20 is located in the transmission shaft 19 mounting seat, the rotating shaft 12 is mounted in the rotating shaft 13 through the bearing set 14, the tail cover 17 is fixedly connected with the tail end of the rotating shaft seat 13, the slip ring 16 is mounted at the tail of the rotating shaft 12 for measuring the rotation parameter of the mechanism, the rotating shaft 12 is fixedly connected with the secondary bevel gear 15, the secondary bevel gear 15 is engaged with the primary bevel gear 18, the primary bevel gear 18 is fixedly connected with one end of the transmission shaft 20, and the motor 22. The motor 22 drives the transmission shaft 20 to rotate through the universal joint 21, and drives the rotating shaft 12 to rotate through the reversing of the main bevel gear and the auxiliary bevel gear.
As shown in fig. 6, the supporting frame is fixedly connected with the rotating shaft seat, and the rotating shaft seat is perpendicular to the test ground. The rotary shaft seat 13 is fixed by clamping the left clamping seat 26 and the right clamping seat 27 of the supporting frame through clamping grooves, the backing plate 25 is used for adjusting the distance between the left clamping seat 26 and the frame body 23, the left clamping seat 26 and the right clamping seat 27 are fixedly connected with the frame body 23 through the tension bolt 24, and the motor mounting seat 28 is fixedly connected with the frame body 23 and used for fixedly mounting the driving motor 22.
As shown in fig. 7, the arc-shaped plate 29 is used for simulating the ground where the test model enters, the center of the arc-shaped plate 29 coincides with the rotation center of the rotary arm 4, and in order to ensure that the arc-shaped plate 29 is vertically placed in the test process, one section of the long support 30, the middle support 31 and the short support 32 is fixedly connected with the arc-shaped plate 29, and the other end of the long support and the short support are fixed with the bottom frame 34 through screws 33.
Claims (4)
1. The utility model provides a sudden change ground effect ground analogue means based on rotation test platform, includes swinging boom unit, drive unit, braced frame and arc face, braced frame fixed mounting is experimental subaerial, a serial communication port, the swinging boom unit be cross symmetrical structure, the swinging boom unit is connected with drive unit, drive unit and braced frame fixed connection, the test model is installed to one side swinging boom outer end of swinging boom unit, drive unit drive swinging boom unit is rotatory around its self axle center, the swinging boom unit drives the aircraft and is the major radius rotation around its self axle center, arc face and the perpendicular fixed connection in experimental ground, the arc face is greater than the length of its one side swinging boom with the distance in swinging boom unit axle center, the centre of a circle of arc face and the coincidence of the axle center of swinging boom unit, the arc face is used for simulating the ground that the.
2. The sudden ground effect ground simulation device based on the rotary test bed as claimed in claim 1, wherein: the rotary arm unit comprises two sets of rotary support arms, two inhaul cables, a switching support rod, a pull rod, a connecting plate, a rotary joint, a balance weight arm, a balance weight block and a rotary shaft, wherein the two opposite ends of the rotary joint are fixedly connected with one ends of the two sets of rotary support arms respectively, the upper end of the rotary joint is fixedly connected with the bottom end of the pull rod through the connecting plate, the lower end of the rotary joint is fixedly connected with the rotary shaft, one end of each inhaul cable is fixedly connected with the upper end of the pull rod, the other end of each inhaul cable is fixedly connected with the other end of one set of rotary support arm, the other end of one set of rotary support arm is fixedly connected with the balance weight block through the balance weight.
3. The sudden ground effect ground simulation device based on the rotary test bed as claimed in claim 2, wherein: the drive unit include the rotation axis seat, the bearing group, the sliding ring, the tail-hood, vice bevel gear, main bevel gear, the transmission shaft mount pad, the transmission shaft, universal joint and motor, the transmission shaft mount pad links firmly with the rotation axis seat, the transmission shaft is located the transmission shaft mount pad, the rotation axis passes through the bearing group to be installed in the rotation axis seat, the tail-hood links firmly with the rotation axis seat end, the sliding ring is installed to the afterbody of rotation axis, the rotation axis links firmly with vice bevel gear, vice bevel gear and main bevel gear meshing, main bevel gear links firmly with the one end of transmission shaft, the motor passes through the universal joint and is connected with the other one end of.
4. The sudden ground effect ground simulation device based on the rotary test bed as claimed in claim 3, wherein: the supporting frame is fixedly connected with the rotating shaft seat, and the rotating shaft seat is perpendicular to the test ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010951524.4A CN111999031A (en) | 2020-09-11 | 2020-09-11 | Sudden change ground effect ground simulation device based on rotary test bed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010951524.4A CN111999031A (en) | 2020-09-11 | 2020-09-11 | Sudden change ground effect ground simulation device based on rotary test bed |
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| CN111999031A true CN111999031A (en) | 2020-11-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010951524.4A Pending CN111999031A (en) | 2020-09-11 | 2020-09-11 | Sudden change ground effect ground simulation device based on rotary test bed |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102589840A (en) * | 2012-01-12 | 2012-07-18 | 清华大学 | Vertical or short-distance takeoff and landing aircraft ground effect test system |
| CN103287587A (en) * | 2013-06-17 | 2013-09-11 | 西北工业大学 | Ground-based simulation flight test platform of plane capable vertical take-off and landing |
| CN103903490A (en) * | 2012-12-28 | 2014-07-02 | 西安远景动力模拟技术有限公司 | Apparatus for simulating aircraft ground effect |
| KR101549526B1 (en) * | 2014-03-12 | 2015-09-03 | 국방과학연구소 | Ground effect test apparatus built-in surface collision protection function |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN108275287A (en) * | 2018-02-05 | 2018-07-13 | 南京航空航天大学 | Multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device and method |
| CN110398341A (en) * | 2019-06-28 | 2019-11-01 | 中国航天空气动力技术研究院 | Centrifugal gravity compensation device and method are launched in a kind of separation |
| CN111289208A (en) * | 2020-03-06 | 2020-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Model tail boom device suitable for fighter plane wind tunnel test |
-
2020
- 2020-09-11 CN CN202010951524.4A patent/CN111999031A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102589840A (en) * | 2012-01-12 | 2012-07-18 | 清华大学 | Vertical or short-distance takeoff and landing aircraft ground effect test system |
| CN103903490A (en) * | 2012-12-28 | 2014-07-02 | 西安远景动力模拟技术有限公司 | Apparatus for simulating aircraft ground effect |
| CN103287587A (en) * | 2013-06-17 | 2013-09-11 | 西北工业大学 | Ground-based simulation flight test platform of plane capable vertical take-off and landing |
| KR101549526B1 (en) * | 2014-03-12 | 2015-09-03 | 국방과학연구소 | Ground effect test apparatus built-in surface collision protection function |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN108275287A (en) * | 2018-02-05 | 2018-07-13 | 南京航空航天大学 | Multi-rotor aerocraft aerodynamic interference and ground effect integrated experiment device and method |
| CN110398341A (en) * | 2019-06-28 | 2019-11-01 | 中国航天空气动力技术研究院 | Centrifugal gravity compensation device and method are launched in a kind of separation |
| CN111289208A (en) * | 2020-03-06 | 2020-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Model tail boom device suitable for fighter plane wind tunnel test |
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Application publication date: 20201127 |