CN108267285B - Three-section folding wing dynamic characteristic experimental device using steering engine - Google Patents
Three-section folding wing dynamic characteristic experimental device using steering engine Download PDFInfo
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- CN108267285B CN108267285B CN201810363819.2A CN201810363819A CN108267285B CN 108267285 B CN108267285 B CN 108267285B CN 201810363819 A CN201810363819 A CN 201810363819A CN 108267285 B CN108267285 B CN 108267285B
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 19
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 19
- 238000002474 experimental method Methods 0.000 claims abstract description 14
- 238000000034 method Methods 0.000 claims abstract description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 34
- 239000004917 carbon fiber Substances 0.000 claims description 34
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 34
- 238000005452 bending Methods 0.000 claims description 23
- 230000005284 excitation Effects 0.000 claims description 7
- 239000010935 stainless steel Substances 0.000 claims description 7
- 229910001220 stainless steel Inorganic materials 0.000 claims description 7
- 239000003822 epoxy resin Substances 0.000 claims description 6
- 239000003292 glue Substances 0.000 claims description 6
- 229920000647 polyepoxide Polymers 0.000 claims description 6
- 238000012360 testing method Methods 0.000 claims description 6
- 230000003068 static effect Effects 0.000 claims description 3
- 230000003247 decreasing effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
-
- 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
Abstract
The invention discloses a three-section folding wing dynamic characteristic experiment device using a steering engine, and belongs to the technical field of aircraft experiments. The experimental device comprises a fixed base, a folding wing inner section wing, a folding wing middle section wing and a folding wing outer section wing, and is used for simulating the structure of the folding wing. The fixed base is in threaded connection with supporting aluminum profiles and corner connectors in the inner section wings of the folding wings through bolts, the inner section steering engines of the inner section wings of the folding wings are in threaded connection with the steering engine arms of the middle section wings of the folding wings through bolts, and the steering engine arms of the middle section wings of the folding wings) and the outer section steering engines of the outer section wings of the folding wings are in threaded connection through bolts to form a folding wing model device. The parallel relation of the inner section wing and the outer section wing in the motion process is kept through the closed-loop control system, and meanwhile, the operation is simple and convenient, the occupied space is greatly reduced, the overall quality and the processing difficulty of the mechanism are reduced, and the cost is reduced.
Description
Technical Field
The invention relates to an aviation aircraft experimental device, in particular to an experimental device for researching the dynamic characteristics of a folding wing, which can particularly simulate the vibration characteristics of the folding wing of a morphing aircraft in the unfolding process and belongs to the technical field of aircraft experiments.
Background
As one of the new concept of the changeable aircraft, the folding wing aircraft can actively change the wing area through the extension and the folding of the wings, thereby always keeping the optimal flight state, furthest expanding the flight envelope curve, being capable of executing different tasks and meeting the requirements of different flight environments. When the folding wing aircraft flies at different folding angles, the folding wing aircraft has different vibration characteristics at different angles due to aerodynamic and structural changes caused by changes of wing configurations. Therefore, the experimental model is designed to study the vibration characteristics of the folding wing aircraft at different folding angles, and has very important value for guiding the structural design and safe flight of the folding wing aircraft.
Aiming at the design of an aircraft, the airfoil of the aircraft is designed by adopting variable cross-section size, and the current experimental model is designed by adopting fixed cross-section, so that the reliability of experimental research is influenced to a certain extent. The experimental model can be used for analyzing the dynamic vibration characteristics of the variable-section folding wing.
Disclosure of Invention
The invention discloses a three-section folding wing dynamic characteristic experiment device using a steering engine as a power element, which reduces the floor area of the current experiment model and can analyze the dynamic vibration characteristic of a variable-section folding wing.
The invention discloses a three-section folding wing dynamic characteristic experiment device using a steering engine, which comprises a fixed base (1), a folding wing inner section wing (2), a folding wing middle section wing (3) and a folding wing outer section wing (4), and is used for simulating the structure of a folding wing. The fixed base (1) is in threaded connection with a supporting aluminum profile (7) and an angle code (9) in the inner section wing (2) of the folding wing through bolts, an inner section steering engine (10) of the inner section wing (2) of the folding wing is in threaded connection with a rudder horn (20) of the middle section wing (3) of the folding wing through bolts, the rudder horn (20) of the middle section wing (3) of the folding wing is in threaded connection with an outer section steering engine (22) of the outer section wing (4) of the folding wing through bolts, and a folding wing model device is formed.
The fixed base (1) is connected to the excitation platform through bolts, and the inner section wing (2) of the folding wing is arranged on one side of the fixed base (1); the fixed base (1) is directly connected with the folding wing model device, the fixed base (1) is composed of a plurality of aluminum profiles (5), and the aluminum profiles (5) are connected through angle codes (6).
Folding wing inner segment wing (2) comprise support aluminium alloy (7), inner segment carbon fiber covering (8), angle sign indicating number (9), inner segment steering wheel (10), inner segment floor (11) and stainless steel fixed plate (12) of bending, and wherein, support aluminium alloy (7) and be used for guaranteeing intensity, improve the whole device rigidity. The inner section carbon fiber skin (8) is directly connected to the supporting aluminum section (7) through epoxy resin glue in a bonding mode, and the inner section bending rib plate (11) and the stainless steel fixing plate (12) are in threaded connection to the supporting aluminum section (7) through bolts. And a vibration test sensor is directly arranged on the upper surface of the inner section carbon fiber skin (8). The corner brace (9) is used for connecting the two supporting aluminum profiles (7), and the supporting aluminum profiles (7) are connected with the corner brace (9) through bolts, wherein the bolts are omitted. The inner-section steering engine (10) provides power for lifting the middle section wing (3) of the folding wing, and the inner-section steering engine (10) is connected with the stainless steel fixing plate (12) through bolts. The inner section bending rib plate (11) is used for improving the local strength of the outer side of the inner section wing (2) of the folding wing, so that the outer side and the inner side of the inner section wing (2) of the folding wing form a whole.
The middle wing (3) of the folding wing consists of an outer hexagon screw (13), a nut (14), a fisheye bearing (15), a screw rod (16), a middle-section inner side bending rib plate (17), a middle-section outer side bending rib plate (18), a middle-section rib plate (19), a steering engine arm (20) and a middle-section carbon fiber skin (21). The rudder horn (20) is used for transmitting power provided by the inner section steering engine (10) and the outer section steering engine (24), and the rudder horn (20) is in threaded connection with the middle section rib plate (19) through a bolt to drive the folding wing middle section wing (3) to move. The outer hexagon screw (13), the nut (14), the fisheye bearing (15) and the screw (16) are in threaded connection through thread lines of the outer hexagon screw, the nut (14), the fisheye bearing (15) and the screw (16) to form a structure, the structure provides the strength of the middle section wing (3) of the folding wing, and the support effect is achieved. The middle section inner side bending rib plate (17) and the middle section outer side bending rib plate (18) are directly connected to the middle section carbon fiber skin (21) through epoxy resin glue in a bonding mode and used for improving the local strength of the middle section wing (3) of the folding wing, the screw rod (16) and the middle section carbon fiber skin (21) form a whole, and the outer side fisheye bearing (15) and the middle section carbon fiber skin (21) form a whole.
The outer section wing (4) of the folding wing consists of an outer section steering engine (22), an outer section carbon fiber ribbed plate (23), an outer section carbon fiber skin (24) and an outer section bending ribbed plate (25). The outer section steering engine (22) is in threaded connection with the steering engine arm (20) through bolts to provide power for the movement of the outer section wing (4) of the folding wing, and meanwhile, the servo motor is driven through pwm to enable the outer section wing (4) of the folding wing and the inner section wing (2) of the folding wing to be always parallel. The outer section carbon fiber rib plate (23) and the outer section bending rib plate (25) play a supporting role. The outer section carbon fiber skin (24) is connected to the outer section carbon fiber rib plate (23) and the outer section bending rib plate (25) through epoxy resin glue.
The inner section carbon fiber skin (8) and the middle section carbon fiber skin (21) and the outer section carbon fiber skin (24) are used for simulating the skin of the wing in an experiment.
The invention can carry out the following work contents in practical use:
s1: the inner section steering engine (10) and the outer section steering engine (22) are controlled by the single chip microcomputer PWM to always keep a constant angle in an experiment, meanwhile, the upper surfaces of the inner section wing (2) and the outer section wing (4) of the folding wing can always keep parallel, the structural state of a figure 1, a figure 2, a figure 3, a figure 4 and a figure 5 in a figure 1, a figure 3 and a figure 4 in the attached drawing of the specification can be referred to, and the working states when the included angles between the inner section wing (2) and the middle section wing (3) of the folding wing are respectively 0 degree, 30 degrees, 60 degrees, 90 degrees and 120 degrees are used for simulating the static parameters of the folding wing.
S2: the inner section steering engine (10) and the outer section steering engine (22) are controlled by the single chip microcomputer PWM to keep a specific speed to perform circular motion in an experiment, so that an included angle between the inner section wing (2) and the middle section wing (3) of the folding wing can be gradually increased from 0 degree to 120 degrees and then gradually decreased from 120 degrees to 0 degree, and meanwhile, the inner section wing (2) of the folding wing and the upper surface of the outer section wing (4) of the folding wing are ensured to be parallel to simulate dynamic parameters of the folding wing in the wing unfolding and folding processes.
For the experimental device of the folding wing, the parallel relation of the inner section wing and the outer section wing in the motion process can be kept through the closed-loop control system, and meanwhile, the operation is simple and convenient, the occupied space is greatly reduced, the overall quality and the processing difficulty of the mechanism are reduced, and the cost is reduced. The modal test of the folding wing and the dynamic vibration characteristic test of the folding wing can be carried out.
The invention is further described below with reference to the accompanying drawings.
Drawings
FIG. 1 is a schematic diagram of the overall assembly of a folding wing experimental setup.
Fig. 2 is a schematic view of a fixed base of the folding wing experimental device.
Fig. 3 is an assembly schematic of the internal frame of the inner section wing of the folding wing experimental apparatus.
Fig. 4 is an assembly schematic of the internal frame of the midspan wing of the folding wing experimental apparatus.
Fig. 5 is an assembly schematic of the internal frame of the outer section wing of the folding wing experimental apparatus.
Fig. 6 is a schematic diagram of the middle wing and the inner wing outer wing of the folding wing experimental device being kept horizontal.
Fig. 7 is a schematic diagram of a middle wing and an inner wing outer wing of the folding wing experimental device, which are maintained at 30 degrees.
Fig. 8 is a schematic diagram of a middle wing and an inner wing outer wing of the folding wing experimental device maintaining 60 degrees.
Fig. 9 is a schematic view of a middle wing and an inner wing outer wing of the folding wing experimental device maintaining 90 degrees.
Fig. 10 is a schematic view of a middle wing and an inner wing outer wing of the folded wing experimental device maintained at 120 degrees.
In the figure: 1. the folding wing comprises a fixed base, 2, an inner section wing of the folding wing, 3, a middle section wing of the folding wing, 4, an outer section wing of the folding wing, 5, an aluminum section of the fixed base, 6, an angle code, 7, a supporting aluminum section, 8, an inner section carbon fiber skin, 9, a folding wing angle code, 10, an inner section steering engine, 11, an inner section bending rib plate, 12, a stainless steel fixed plate, 13, an outer hexagon screw, 14, a nut, 15, a fisheye bearing, 16, a screw, 17, a middle section inner side bending rib plate, 18, a middle section outer side bending rib plate, 19, a middle section rib plate, 20, a steering engine arm, 21, a middle section carbon fiber skin, 22, an outer section steering engine, 23, an outer section carbon fiber rib plate, 24, an outer section carbon fiber skin, 25.
Detailed Description
The experimental model disclosed by the invention comprises a fixed base (figure 2), a folding wing inner section wing (figure 3), a folding wing middle section wing (figure 4) and a folding wing outer section wing (figure 5) and is used for simulating the structure of the folding wing.
When a dynamic vibration characteristic test experiment is carried out, a fixed base (figure 2) is installed on an excitation table through bolts, and a folding wing inner section wing (figure 3), a folding wing middle section wing (figure 4) and a folding wing outer section wing (figure 5) are installed at specified positions as shown in figure 1, so that the whole device is fixed on the base, and the boundary condition of a cantilever is simulated. The inner section steering engine (10) and the outer section steering engine (22) perform circular motion at different speeds through pwm control, and simultaneously the outer section wing (shown in figure 5) and the inner section wing (shown in figure 3) of the folding wing are always kept parallel in motion so as to simulate the state of the folding wing in actual work. In the process of movement of the device, initial excitation is applied through the excitation table, forced vibration occurs in the device, and experimental values are measured through the sensor.
The fixed base (1) has a length of 700 mm, a width of 550 mm and a height of 260 mm.
When a modal test experiment is carried out, the angle of the steering engine is kept at a set angle through pwm control, and the wings are kept in a static state at the set angle. The preset angles are 0 ° (fig. 6), 30 ° (fig. 7), 60 ° (fig. 8), 90 ° (fig. 9), 120 ° (fig. 10). The whole folding wing experimental device is fixed on an excitation table, a vibration exciter is used for giving simple harmonic force excitation, the device is forced to vibrate, and an experimental value is measured through a sensor.
Finally, it should be noted that the above embodiments are only used for illustrating the present invention and do not limit the technical solutions described in the present invention; therefore, although the present invention has been described in detail, it should be understood by those skilled in the art that various changes and modifications may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (4)
1. The utility model provides an use three-section folding wing dynamics characteristic experimental apparatus of steering wheel which characterized in that: the experimental device comprises a fixed base (1), a folding wing inner section wing (2), a folding wing middle section wing (3) and a folding wing outer section wing (4), and is used for simulating the structure of the folding wing; the fixed base (1) is in threaded connection with a supporting aluminum profile (7) and an angle code (9) in the inner section wing (2) of the folding wing through bolts, an inner section steering engine (10) of the inner section wing (2) of the folding wing is in threaded connection with a steering engine arm (20) of the middle section wing (3) of the folding wing through bolts, and the steering engine arm (20) of the middle section wing (3) of the folding wing is in threaded connection with an outer section steering engine (22) of the outer section wing (4) of the folding wing through bolts to form a folding wing model device;
the inner section wing (2) of the folding wing consists of a supporting aluminum profile (7), an inner section carbon fiber skin (8), an angle bracket (9), an inner section steering engine (10), an inner section bending rib plate (11) and a stainless steel fixing plate (12), wherein the supporting aluminum profile (7) is used for ensuring the strength and improving the rigidity of the whole device; the inner section carbon fiber skin (8) is directly connected to the supporting aluminum section (7) through epoxy resin glue in a bonding mode, and the inner section bending rib plate (11) and the stainless steel fixing plate (12) are in threaded connection to the supporting aluminum section (7) through bolts; a vibration test sensor is directly arranged on the upper surface of the inner section carbon fiber skin (8); the corner brace (9) is used for connecting the two supporting aluminum profiles (7), and the supporting aluminum profiles (7) are connected with the corner brace (9) through bolts; the inner-section steering engine (10) provides power for lifting the middle-section wing (3) of the folding wing, and the inner-section steering engine (10) is connected with the stainless steel fixing plate (12) through bolts; the inner section bending rib plate (11) is used for improving the local strength of the outer side of the inner section wing (2) of the folding wing, so that the outer side and the inner side of the inner section wing (2) of the folding wing form a whole;
the fixed base (1) is connected to the excitation platform through bolts, and the inner section wing (2) of the folding wing is arranged on one side of the fixed base (1); the fixed base (1) is directly connected with the folding wing model device, the fixed base (1) is composed of a plurality of aluminum profiles (5), and the aluminum profiles (5) are connected through corner connectors (6);
the outer section wing (4) of the folding wing consists of an outer section steering engine (22), an outer section carbon fiber ribbed plate (23), an outer section carbon fiber skin (24) and an outer section bending ribbed plate (25); the outer section steering engine (22) is in threaded connection with the steering engine arm (20) through a bolt, power is provided for the movement of the outer section wing (4) of the folding wing, and meanwhile the servo motor is driven through pwm to enable the outer section wing (4) of the folding wing and the inner section wing (2) of the folding wing to be always parallel; the outer section carbon fiber rib plate (23) and the outer section bending rib plate (25) play a supporting role; the outer section carbon fiber skin (24) is connected to the outer section carbon fiber rib plate (23) and the outer section bending rib plate (25) through epoxy resin glue.
2. The experimental device for the dynamic characteristics of the three-section folding wing using the steering engine as claimed in claim 1, wherein: the middle section wing (3) of the folding wing consists of an outer hexagon screw (13), a nut (14), a fisheye bearing (15), a screw rod (16), a middle section inner side bending rib plate (17), a middle section outer side bending rib plate (18), a middle section rib plate (19), a steering engine arm (20) and a middle section carbon fiber skin (21); the rudder horn (20) is used for transmitting power provided by the inner section steering engine (10) and the outer section steering engine (24), and the rudder horn (20) is in threaded connection with the middle section rib plate (19) through a bolt to drive the folding wing middle section wing (3) to move; the outer hexagon screw (13), the nut (14), the fisheye bearing (15) and the screw (16) are in threaded connection through thread lines of the outer hexagon screw, so that a structure is formed, the structure provides the strength of the middle section wing (3) of the folding wing, and the support effect is achieved; the middle section inner side bending rib plate (17) and the middle section outer side bending rib plate (18) are directly connected to the middle section carbon fiber skin (21) through epoxy resin glue in a bonding mode and used for improving the local strength of the middle section wing (3) of the folding wing, the screw rod (16) and the middle section carbon fiber skin (21) form a whole, and the outer side fisheye bearing (15) and the middle section carbon fiber skin (21) form a whole.
3. The experimental device for the dynamic characteristics of the three-section folding wing using the steering engine as claimed in claim 2, wherein: the inner section carbon fiber skin (8), the middle section carbon fiber skin (21) and the outer section carbon fiber skin (24) are used for simulating the skin of the wing in an experiment.
4. The experimental device for the dynamic characteristics of the three-section folding wing using the steering engine as claimed in claim 1, wherein: the implementation of the device is as follows,
s1: the inner section steering engine (10) and the outer section steering engine (22) are controlled by the single chip microcomputer PWM to always keep a constant angle in an experiment, meanwhile, the upper surfaces of the inner section wing (2) and the outer section wing (4) of the folding wing can always keep parallel, and the included angles between the inner section wing (2) and the middle section wing (3) of the folding wing are respectively in working states of 0 degree, 30 degrees, 60 degrees, 90 degrees and 120 degrees so as to simulate the static parameters of the folding wing;
s2: the inner section steering engine (10) and the outer section steering engine (22) are controlled by the single chip microcomputer PWM to keep a specific speed to perform circular motion in an experiment, so that an included angle between the inner section wing (2) and the middle section wing (3) of the folding wing can be gradually increased from 0 degree to 120 degrees and then gradually decreased from 120 degrees to 0 degree, and meanwhile, the inner section wing (2) of the folding wing and the upper surface of the outer section wing (4) of the folding wing are ensured to be parallel to simulate dynamic parameters of the folding wing in the wing unfolding and folding processes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810363819.2A CN108267285B (en) | 2018-04-22 | 2018-04-22 | Three-section folding wing dynamic characteristic experimental device using steering engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810363819.2A CN108267285B (en) | 2018-04-22 | 2018-04-22 | Three-section folding wing dynamic characteristic experimental device using steering engine |
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| Publication Number | Publication Date |
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| CN108267285A CN108267285A (en) | 2018-07-10 |
| CN108267285B true CN108267285B (en) | 2020-09-25 |
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| CN201810363819.2A Expired - Fee Related CN108267285B (en) | 2018-04-22 | 2018-04-22 | Three-section folding wing dynamic characteristic experimental device using steering engine |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2739605B1 (en) * | 1995-10-04 | 1997-12-26 | Roy Janick | FOLDABLE VERSATILE FRAME FOR LIGHT SAILING TANK |
| CN103123293A (en) * | 2012-12-24 | 2013-05-29 | 中国航空工业空气动力研究院 | Drive-embedded dynamic folding morphing wing |
| CN104897355B (en) * | 2015-06-23 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Folded wing non-linear flutter test device |
| CN105547618B (en) * | 2015-12-03 | 2018-02-13 | 北京机械设备研究所 | A kind of modal analysis method based on folding rudder face rudder system |
| CN105620721B (en) * | 2016-01-30 | 2018-02-23 | 江苏润侃瑞科技有限公司 | A kind of miniature self-service airfoil fold mechanism |
| CN106596020B (en) * | 2016-12-30 | 2023-06-30 | 北京工业大学 | Folding wing dynamics characteristic experimental device |
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