CN108033036B - Full-motion horizontal tail flutter model rotating gap simulation device - Google Patents
Full-motion horizontal tail flutter model rotating gap simulation device Download PDFInfo
- Publication number
- CN108033036B CN108033036B CN201711230964.5A CN201711230964A CN108033036B CN 108033036 B CN108033036 B CN 108033036B CN 201711230964 A CN201711230964 A CN 201711230964A CN 108033036 B CN108033036 B CN 108033036B
- Authority
- CN
- China
- Prior art keywords
- clamping block
- rotating shaft
- horizontal tail
- flutter model
- spring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a full-dynamic horizontal tail flutter model rotation gap simulation device, and belongs to the field of airplane horizontal tail flutter tests. One end of the rotating shaft is connected with the horizontal tail flutter model, the other end of the rotating shaft is connected with the test base, and the rotating shaft rotates around the horizontal tail flutter model; one end of the spring base is sleeved on the rotating shaft through a bearing, and the other end of the spring base is connected with the free end of the operating spring; the first clamping block and the second clamping block are respectively arranged on the rotating shaft, and an adjustable installation gap is formed between the first clamping block and the second clamping block; a boss is arranged at one end of the spring base close to the rotating shaft along the axial direction of the rotating shaft, and the boss is arranged in an installation gap between the first clamping block and the second clamping block; the rotation of the horizontal tail flutter model enables the rotating shaft to drive the first clamping block and the second clamping block to move, and when the first clamping block and the second clamping block collide with the boss, the spring base is driven to overcome the elastic force of the operating spring to swing in a reciprocating mode. The invention can change the size of the rotation clearance of the full-dynamic horizontal tail flutter model and verify the influence of different rotation clearance sizes on the horizontal tail flutter characteristic.
Description
Technical Field
The invention belongs to the technical field of airplane horizontal tail flutter tests, and particularly relates to a full-dynamic horizontal tail flutter model rotation gap simulation device.
Background
In the flutter test flight process of a certain full-dynamic horizontal tail aircraft, the condition that a rotating gap exists at the horizontal tail often occurs, the flight characteristics of the aircraft are influenced to a certain degree, and the flutter test in the aspect is not performed at present in China, so that the design of the flutter model rotating gap simulation device in the aspect is not performed.
Disclosure of Invention
The purpose of the invention is as follows: in order to solve the problems, the invention provides a full-dynamic horizontal tail flutter model rotating gap simulation device, which adopts the technical scheme that a rotating shaft, an operating spring and braking fixture blocks are combined, and the size of the rotating gap of the full-dynamic horizontal tail flutter model can be changed by adjusting the positions of two braking fixture blocks, so that the effect of simulating different rotating gaps in the flutter model test is achieved.
The technical scheme of the invention is as follows: a full-motion horizontal tail flutter model rotation gap simulation device comprises a horizontal tail flutter model, a rotating shaft, a first clamping block, a second clamping block, a spring base and an operating spring;
one end of the rotating shaft is connected with the horizontal tail flutter model, the other end of the rotating shaft is connected with the test base, and the rotating shaft rotates around the horizontal tail flutter model;
one end of the spring base is sleeved on the rotating shaft through a bearing, and the other end of the spring base is connected with a free end of an operating spring, one end of the operating spring is fixed on the test base;
the first clamping block and the second clamping block are respectively arranged on the rotating shaft, and an adjustable installation gap is formed between the first clamping block and the second clamping block;
a boss is arranged at one end, close to the rotating shaft, of the spring base along the axial direction of the rotating shaft, and the boss is installed in an installation gap between the first fixture block and the second fixture block;
the rotation of the horizontal tail flutter model enables the rotating shaft to drive the first clamping block and the second clamping block to move, and when the first clamping block and the second clamping block collide with the boss, the spring base is driven to overcome the elastic force of the operating spring to swing in a reciprocating mode.
Preferably, the first fixture block and the second fixture block are both arc-shaped;
the first clamping block and the second clamping block are adjustably mounted on the side wall of the rotating shaft through bolts.
Preferably, the first clamping block is fixed on the side wall of the rotating shaft through a bolt, and the second clamping block is adjustably mounted on the first clamping block.
Preferably, the second fixture block is provided with a plurality of screw mounting holes at equal intervals, and the first fixture block is provided with mounting holes matched with the second fixture block;
and adjusting the clearance between the first clamping block and the second clamping block relative to the boss by adjusting the second clamping block to be matched with the screw mounting hole.
Preferably, one end of the spring base, which is close to the operating spring, is provided with an insertion hole, and the insertion hole is matched with the free end of the operating spring;
the free end of the operating spring is inserted into the jack.
The technical scheme of the invention has the beneficial technical effects that: according to the full-dynamic horizontal tail flutter model rotation gap simulation device, the size of the rotation gap of the full-dynamic horizontal tail flutter model can be changed by adjusting the positions of the two fixture blocks, so that the effect of simulating different rotation gap sizes in a flutter model test is achieved, and the influence of different rotation gap sizes on the horizontal tail flutter characteristic can be verified.
Drawings
FIG. 1 is a schematic diagram of the structural components and installation of a preferred embodiment of the full dynamic horizontal tail flutter model rotating gap simulator of the present invention;
FIG. 2 is a schematic view illustrating the connection between the spring base and the latch and the operation spring of the embodiment shown in FIG. 1;
the device comprises a horizontal tail flutter model 1, a rotating shaft 2, a first clamping block 3, a second clamping block 4, a spring base 5, an operating spring 6, a boss 7 and an insertion hole 8.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
As shown in fig. 1 to 2, a full-dynamic horizontal tail flutter model rotating gap simulation device includes: the device comprises a horizontal tail flutter model 1, a rotating shaft 2, a first fixture block 3, a second fixture block 4, a spring base 5 and an operating spring 6;
one end of a rotating shaft 2 is connected with the horizontal tail flutter model 1, the other end of the rotating shaft is connected with a test base, and the rotating shaft 2 rotates around the horizontal tail flutter model 1;
the spring base 5 is provided with an annular installation part, the annular installation part extends outwards and is provided with a spring installation part, a bearing is arranged in the annular installation part, the annular installation part at one end of the spring base 5 is sleeved on the rotating shaft 2 through the bearing, and the spring installation part at the other end of the spring base is connected with the free end of an operating spring 6 of which one end is fixed on the test base;
the first fixture block 3 and the second fixture block 4 are respectively annularly arranged on the rotating shaft 2, and an installation gap with an adjustable function is formed between the first fixture block 3 and the second fixture block 4;
a boss 7 extends from one end of the spring base 5 close to the rotating shaft 2 along the axial direction of the rotating shaft 2, and the boss 7 is installed in an installation gap formed between the first fixture block 3 and the second fixture block 4;
the rotation of the horizontal tail flutter model 1 enables the rotating shaft 2 to drive the first fixture block 3 and the second fixture block 4 to move along with the rotating shaft 2, and after the first fixture block 3 and the second fixture block 4 collide with the boss 7, the spring base 5 is driven to overcome the elastic force of the operating spring 6 to swing in a reciprocating mode.
In this embodiment, both first fixture block 3 and second fixture block 4 are the arc, and both one ends are protruding formation screens portion respectively, and screens portion can form effectual limit to keep off the effect to boss 7, and first fixture block 3 and second fixture block 4 pass through bolt adjustable installation on the lateral wall of pivot 2 to install the both sides at boss 7.
In this embodiment, first fixture block 3 passes through the bolt fastening on the lateral wall of pivot 2, and second fixture block 4 is adjustable to be installed on first fixture block 3, can reduce the trompil quantity of 2 lateral walls of pivot, keeps 2 good integrality of pivot, improves 2 structural strength of pivot.
It can be understood that: a plurality of screw mounting holes are formed in one end, far away from the clamping part, of the second clamping block 4 at equal intervals along the extending bending direction of the body, and the first clamping block 3 is provided with mounting holes matched with the second clamping block;
the gap between the first fixture block 3 and the second fixture block 4 relative to the boss 7 is adjusted by selecting the second fixture block 4 to be matched with the first fixture block 3 and the screw mounting hole;
after the adjustment is finished, the second fixture block 4 is fixed on the first fixture block 3 through screws, and the third fixture block 3 is fixed on the rotating shaft 2 through the mounting hole formed in the clamping portion of the third fixture block, so that the first fixture block 3 and the second fixture block 4 can rotate together with the rotating shaft 2.
According to the invention, the size of the rotating gap is adjusted through the relative position of the first fixture block 3 and the second fixture block 4 in the rotating direction, so that the change of the size of the gap is realized, and the test requirement is met.
In this embodiment, one end of the spring base 5 close to the operation spring 6 is provided with an insertion hole 8, the insertion hole 8 is matched with the free end of the operation spring 6, and the free end of the operation spring 6 is inserted into the insertion hole 8 and can move along with the spring base 5.
The specific operation is as follows: when the horizontal tail flutter model 1 rotates, the rotating shaft 2, the first fixture block 3 and the second fixture block 4 are driven to rotate together, and when the first fixture block 3 or the second fixture block 4 does not touch the boss of the spring base 5, the horizontal tail flutter model 1 rotates freely with zero rigidity;
after the first fixture block 3 and the second fixture block 4 touch the boss 7 of the spring base 5, the spring base 5 and the control spring 6 are driven to move together, and the rotation motion of the horizontal tail flutter model 1 is influenced by the rigidity of the control spring 6.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (4)
1. A full-motion horizontal tail flutter model rotation gap simulation device is characterized by comprising a horizontal tail flutter model (1), a rotating shaft (2), a first clamping block (3), a second clamping block (4), a spring base (5) and an operating spring (6);
one end of the rotating shaft (2) is connected with the horizontal tail flutter model (1), the other end of the rotating shaft is connected with the test base, and the rotating shaft (2) rotates around the horizontal tail flutter model (1);
one end of a spring base (5) is sleeved on the rotating shaft (2) through a bearing, the other end of the spring base is connected with a free end of an operating spring (6) of which one end is fixed on the test base, wherein one end, close to the operating spring (6), of the spring base (5) is provided with a jack (8), the jack is matched with the free end of the operating spring (6), and the free end of the operating spring (6) is inserted into the jack (8);
the first clamping block (3) and the second clamping block (4) are respectively arranged on the rotating shaft (2), and an adjustable installation gap is formed between the first clamping block (3) and the second clamping block (4);
a boss (7) is arranged at one end, close to the rotating shaft (2), of the spring base (5) along the axial direction of the rotating shaft (2), and the boss (7) is installed in an installation gap between the first fixture block (3) and the second fixture block (4);
the horizontal tail flutter model (1) rotates to enable the rotating shaft (2) to drive the first clamping block (3) and the second clamping block (4) to move, and when the first clamping block (3) and the second clamping block (4) collide with the boss (7), the spring base (5) is driven to overcome the elastic force of the control spring (6) to swing in a reciprocating mode.
2. The full kinetic horizontal tail flutter model rotation gap simulator according to claim 1, wherein: the first clamping block (3) and the second clamping block (4) are arc-shaped;
the first clamping block (3) and the second clamping block (4) are adjustably mounted on the side wall of the rotating shaft (2) through bolts.
3. The full kinetic horizontal tail flutter model rotation gap simulator according to claim 1, wherein: the first clamping block (3) is fixed on the side wall of the rotating shaft (2) through a bolt, and the second clamping block (4) is adjustably installed on the first clamping block (3).
4. The full kinetic flattail flutter model rotation gap simulator of claim 3, wherein: the second fixture block (4) is provided with a plurality of screw mounting holes at equal intervals, and the first fixture block (3) is provided with mounting holes matched with the second fixture block;
and adjusting the clearance between the first clamping block (3) and the second clamping block (4) relative to the bosses (7) by adjusting the second clamping block (4) to be matched with the screw mounting hole of the first clamping block (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711230964.5A CN108033036B (en) | 2017-11-29 | 2017-11-29 | Full-motion horizontal tail flutter model rotating gap simulation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711230964.5A CN108033036B (en) | 2017-11-29 | 2017-11-29 | Full-motion horizontal tail flutter model rotating gap simulation device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108033036A CN108033036A (en) | 2018-05-15 |
| CN108033036B true CN108033036B (en) | 2021-03-12 |
Family
ID=62094585
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711230964.5A Active CN108033036B (en) | 2017-11-29 | 2017-11-29 | Full-motion horizontal tail flutter model rotating gap simulation device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108033036B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910078B (en) * | 2018-06-25 | 2021-09-10 | 中国商用飞机有限责任公司 | Control gap and rigidity simulation device for flutter model |
| CN111310315B (en) * | 2020-01-21 | 2022-09-09 | 哈尔滨工程大学 | Design method for improving aeroelastic stability of beam structure based on ultra-high-speed aircraft |
| CN112213070B (en) * | 2020-09-21 | 2023-03-14 | 中国航空工业集团公司沈阳飞机设计研究所 | External object hangs clearance analogue means under flutter wind tunnel test wing |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102495241A (en) * | 2011-12-16 | 2012-06-13 | 哈尔滨工业大学 | Simulation device of transmission clearance of servo system |
| CN103639434A (en) * | 2013-11-25 | 2014-03-19 | 重庆市璧山爱华有限责任公司 | Controllable swing-motor reciprocating drive device |
| CN104070545A (en) * | 2014-06-26 | 2014-10-01 | 浙江金达电机电器有限公司 | Rotary reciprocating type swing mechanism |
| CN105571816A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Combined flutter model with adjustable gap |
| CN105606361A (en) * | 2016-01-28 | 2016-05-25 | 上海交通大学 | Adjustable gap experiment platform |
| CN106017851A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Movable surface operation gap simulating device |
| CN206504696U (en) * | 2017-02-16 | 2017-09-19 | 天津电气科学研究院有限公司 | A kind of transmission clearance of servo system simulating test device |
-
2017
- 2017-11-29 CN CN201711230964.5A patent/CN108033036B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102495241A (en) * | 2011-12-16 | 2012-06-13 | 哈尔滨工业大学 | Simulation device of transmission clearance of servo system |
| CN103639434A (en) * | 2013-11-25 | 2014-03-19 | 重庆市璧山爱华有限责任公司 | Controllable swing-motor reciprocating drive device |
| CN104070545A (en) * | 2014-06-26 | 2014-10-01 | 浙江金达电机电器有限公司 | Rotary reciprocating type swing mechanism |
| CN105571816A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Combined flutter model with adjustable gap |
| CN105606361A (en) * | 2016-01-28 | 2016-05-25 | 上海交通大学 | Adjustable gap experiment platform |
| CN106017851A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Movable surface operation gap simulating device |
| CN206504696U (en) * | 2017-02-16 | 2017-09-19 | 天津电气科学研究院有限公司 | A kind of transmission clearance of servo system simulating test device |
Non-Patent Citations (1)
| Title |
|---|
| 《具有间隙非线性的全动舵系统的颤振分析》;张恩阳等;《兵器装备工程学报》;20160125;第37卷(第1期);136-141 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108033036A (en) | 2018-05-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108033036B (en) | Full-motion horizontal tail flutter model rotating gap simulation device | |
| CN103363644B (en) | Indoor unit air outlet device for air conditioner | |
| CN204346448U (en) | A kind of gyroscope vibration proof mechanism | |
| CN203388597U (en) | Screw cap structure and air-conditioner indoor unit applying same | |
| CN202707823U (en) | Shaft end supporting device and air duct type air conditioner with same | |
| CN105332584B (en) | A kind of multi-functional cabinet door hinge | |
| CN203967377U (en) | A kind of Quick Connect Kit | |
| CN204533167U (en) | A kind of electromechanical actuator upper journal | |
| CN203837215U (en) | Automobile air-conditioner vent damper mechanism with thumb wheel not liable to loose | |
| CN208754084U (en) | A kind of brushless motor magnetic rotor structure | |
| CN104682616A (en) | Mounting structure capable of adapting to mounting errors | |
| CN209030032U (en) | Buffer washer, motor host computer and broken wall machine | |
| CN201405704Y (en) | Ventilation window component | |
| CN102927662A (en) | Knob seat, cover plate, adjusting device and air conditioner | |
| CN211172858U (en) | Soft or hard package mounting structure of installation angle quick adjustment | |
| CN204013003U (en) | High-performance threephase asynchronous | |
| CN203940545U (en) | Outdoor machine of air-conditioner mounting bracket | |
| CN106989110A (en) | Various dimensions are adapted to shaft coupling | |
| CN209068051U (en) | A kind of platform-limited mechanism and holder and explosion-proof PTZ camera with it | |
| CN204717870U (en) | On-hook in a kind of air-conditioning unit room | |
| CN204048941U (en) | A kind of video presenter with rotatable light compensating lamp | |
| CN203231516U (en) | Wall-hanging plate mechanism and floor type air conditioner | |
| CN103363774B (en) | Shelf of refrigerator door assembly and comprise its refrigerator | |
| JP6074856B2 (en) | lighting equipment | |
| CN201872104U (en) | Stop for mounting automobile door |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |