CN112572763A - Reversing mechanism for bidirectional variable trailing edge wing - Google Patents
Reversing mechanism for bidirectional variable trailing edge wing Download PDFInfo
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- CN112572763A CN112572763A CN202011447676.7A CN202011447676A CN112572763A CN 112572763 A CN112572763 A CN 112572763A CN 202011447676 A CN202011447676 A CN 202011447676A CN 112572763 A CN112572763 A CN 112572763A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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Abstract
The invention discloses a reversing mechanism for a bidirectional variable trailing edge wing, and belongs to the technical field of aerospace equipment. The reversing mechanism is arranged between a fixed section and a deformation section of the bidirectional variable trailing edge wing and mainly comprises an upper sliding sheet 1, a lower sliding sheet 2, an electromagnet installation block 3, a spring pre-tightening transition block 4, a spring group and a limiting block 5. Through the relative locking and sliding of the upper sliding sheet and the lower sliding sheet, the chord length of the upper side or the lower side is increased, the resistance of the bidirectional deformation is reduced, and the stability of the bidirectional deformation is improved. Experiments prove that the electromagnet on one side is electrified through the power supply, the clamping pin is popped out, and the sliding sheet is locked, so that the reversing is realized, and the deformation resistance is reduced. Through a plurality of tests, the reversing action can be realized, and the energy consumption is low because the power is turned on and off instantly once.
Description
Field of the invention
The invention belongs to the technical field of aerospace equipment, and particularly relates to a bidirectional variable trailing edge wing.
Prior Art
Morphing wing technology has since its introduction gone through two stages in total. The morphing wing in the first stage is driven by a traditional mechanical structure, and although aerodynamic performance under different flight environments can be better obtained, the main driving modes are hydraulic driving, motor driving and pneumatic driving, so that the main driving modes mostly have the problems that the driving structure is complex and heavy, the driving structure is not flexible enough, and the driving structure is difficult to be used for a small unmanned aerial vehicle. With the proposal of intelligent materials and the continuous improvement of control theory, the deformable wing gradually changes from a traditional rigid deformation mode to a flexible intelligent deformation mode. The novel intelligent deformable wing technology mainly utilizes intelligent materials such as Shape Memory Alloy (SMA) and piezoelectric ceramic as drivers, utilizes a modern control theory algorithm to perform deformation control, and has great advantages compared with the traditional rigid deformation technology, such as fast response, simple structure and the like. The deformable wing can adjust the state of the wing in different flight environments like birds, so that good performance can be maintained under the conditions that the environment changes greatly and various tasks can be performed. For the bidirectional variable trailing edge wing, the bidirectional variable trailing edge wing deflects upwards or downwards along a vertical wing according to requirements, and for the movement, in order to reduce unnecessary loss of driving force, a reversing mechanism suitable for the bidirectional variable trailing edge wing structure is added between a fixed section and a deformation section of the bidirectional variable trailing edge wing. The working mechanism of the reversing mechanism is as follows: when the trailing edge of the wing deflects upwards, the reversing mechanism can increase the lower side chord length, and when the trailing edge of the wing deflects downwards, the reversing mechanism can increase the upper side chord length, so that the utilization rate of the driving force is improved, and therefore, the reversing mechanism is a non-negligible structure of the bidirectional variable trailing edge wing. The prior article proposes a reversing structure for switching the state of the fixed end of the alloy wire by using the suction force of a sucker type electromagnet. However, there are problems with this mechanism in practical applications: firstly, when the electromagnet is in a non-working state, the alloy fixed end sliding blocks at two ends are in a free state in a chord direction, and the restoring capability is only maintained by the composition materials of the trailing edge structure; secondly, the small-size sucker type electromagnet has insufficient suction force, the suction force is smaller and smaller along with the increase of the pulled distance, and the small-size sucker type electromagnet can be completely separated under the action of certain wind load or other external force to recover the free state, so that the control is failed; finally, in the working process, the electromagnet module needs to be always kept in the electrified state to keep the two sides tensioned and balanced, and the power consumption is large in the actual working process and is not suitable for the actual working state of the aircraft.
Therefore, on the basis, aiming at the existing problems, the iron core bayonet lock locking type reversing mechanism is provided to improve the stability of the reversing mechanism and bidirectional deflection.
Disclosure of Invention
In order to achieve a bidirectional deformation and to improve the reliability thereof, it is an object of the invention to provide a reversing mechanism for a bidirectional variable trailing edge wing.
In order to achieve the purpose, the reversing mechanism for the bidirectional variable trailing edge wing is arranged between a fixed section and a deformation section of the bidirectional variable trailing edge wing;
the reversing mechanism mainly comprises an upper sliding sheet 1, a lower sliding sheet 2, an electromagnet mounting block 3, a spring pre-tightening transition block 4, a spring group and a limiting block 5; the upper sliding piece 1 and the lower sliding piece 2 are correspondingly arranged in parallel, and an upper clamping groove 6 and a lower clamping groove 7 are respectively arranged on the upper sliding piece 1 and the lower sliding piece 2; a miniature self-holding type push-pull electromagnet is arranged in the electromagnet mounting block 3, the whole electromagnet mounting block is arranged between the upper sliding sheet 1 and the lower sliding sheet 2, and the miniature self-holding type push-pull electromagnet controls an iron core bayonet lock to be switched in the upper bayonet lock 6 or the lower bayonet lock 7;
an upper groove and a lower groove are respectively formed in the side wall of the connecting part of the spring pre-tightening transition block 4 and the deformation section, which are connected with the fixed section of the wing, and when the two grooves are in butt joint, the two grooves are in butt joint to form an upper through groove 11 and a lower through groove 12;
after the reversing mechanism is installed, the reversing mechanism is fixed in a shell at the joint of a wing fixing section and a wing deformation section, and an upper sliding sheet 1 and a lower sliding sheet 2 of the reversing mechanism can freely slide in an upper through groove 11 and a lower through groove 12 respectively; one end of a reversing mechanism spring group is fixed in a spring fixing hole 9 or 10 of the upper sliding sheet 1 or the lower sliding sheet 2, and the other end of the reversing mechanism spring group is fixed in the wing fixing section through a spring pre-tightening transition block 4; the reversing mechanism limiting block 5 is arranged at the front end of the wing deformation section and ensures that the upper sliding piece 1 and the lower sliding piece 2 are limited in sliding in the chord direction.
The working process is as follows: when the wing deformation section generates upward deflection movement, the lower side chord length of the wing surface needs to be relatively increased in order to reduce deformation resistance because the lower part of the wing surface generates larger deformation relatively upwards. At the moment, the self-holding push-pull electromagnet locks an iron core bayonet lock in the upper bayonet 6, the upper sliding sheet 1 is in a locking state, and the lower sliding sheet 2 slides towards the wing tip direction under the driving of the deformation of the wing deformation section, so that the lower part of the wing surface of the wing deformation section deforms; conversely, when the airfoil deforming section produces a downward deflecting motion, the airfoil upper chord length needs to be relatively increased in order to reduce the deformation resistance, since more deformation occurs above the airfoil relative to below. At the moment, the locking pin of the self-holding push-pull electromagnet is locked in the lower clamping groove 7, the lower sliding sheet 2 is in a locking state, and the upper sliding sheet 1 slides towards the wing tip direction under the driving of the deformation of the wing deformation section, so that the upper part of the wing surface of the wing deformation section is deformed.
The invention has the beneficial effects that: aiming at the deformation requirement of the bidirectional variable trailing edge wing, a reversing mechanism is ingeniously designed between a fixed section and a deformation section of the bidirectional variable trailing edge wing, and the chord length of the upper side or the lower side is increased through the relative locking and sliding of an upper sliding sheet and a lower sliding sheet, so that the resistance of bidirectional deformation is reduced, and the stability of the bidirectional deformation is improved. Experiments prove that the electromagnet on one side is electrified through the power supply, the clamping pin is popped out, and the sliding sheet is locked, so that the reversing is realized, and the deformation resistance is reduced. Through a plurality of tests, the reversing action can be realized, and the energy consumption is low because the power is turned on and off instantly once.
Drawings
FIG. 1 is a schematic structural view of a reversing mechanism for a bi-directionally variable trailing edge wing provided by the present invention.
In the figure, 1-an upper slide sheet, 2-a lower slide sheet, 3-an electromagnet installation block, 4-a spring pre-tightening transition block, 5-a limiting block, 6-an upper clamping groove, 7-a lower clamping groove and 8-an alloy wire fixing end; 9. 10-spring fixing hole, 11-upper through groove and 12-lower through groove.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
The following detailed description of the reversing structure for the bidirectional variable trailing edge wing provided by the invention is provided in combination with the accompanying drawings and the specific implementation examples.
As shown in FIG. 1, the reversing mechanism of the present embodiment is used for reversing a shape memory alloy driven, bi-directionally variable trailing edge wing. The reversing mechanism mainly comprises an upper sliding sheet 1, a lower sliding sheet 2, an electromagnet mounting block 3, a spring pre-tightening transition block 4, a spring group and a limiting block 5; the upper sliding piece 1 and the lower sliding piece 2 are correspondingly arranged in parallel, and an upper clamping groove 6 and a lower clamping groove 7 are respectively arranged on the upper sliding piece 1 and the lower sliding piece 2; a miniature self-holding type push-pull electromagnet is arranged in the electromagnet mounting block 3, the whole electromagnet mounting block is arranged between the upper sliding sheet 1 and the lower sliding sheet 2, and the miniature self-holding type push-pull electromagnet controls an iron core bayonet lock to be switched in the upper bayonet lock 6 or the lower bayonet lock 7;
an upper groove and a lower groove are respectively formed in the side wall of the joint of the spring pre-tightening transition block and the deformation section, which are connected with the wing, and when the two grooves are in butt joint, the two grooves are in butt joint to form an upper through groove 10 and a lower through groove 11;
after the reversing mechanism is installed, the reversing mechanism is fixed in a shell at the joint of the wing fixing section and the wing deformation section, and an upper sliding sheet 1 and a lower sliding sheet 2 of the reversing mechanism can freely slide in an upper through groove 10 and a lower through groove 11 formed in the wing fixing section and the wing deformation section respectively; the reversing mechanism spring group comprises 5 springs which are symmetrically distributed in parallel, one ends of the springs are fixed in spring fixing holes 9 or 10 at one end of the upper sliding sheet 1 or the lower sliding sheet 2, the other ends of the springs are fixed in the wing fixing section through a spring pre-tightening transition section 4 and used for providing certain pre-tightening force, and the lateral acting force transmitted to the electromagnet locking pin by the sliding sheet in the deformation section is counteracted, so that the stability of the reversing mechanism is improved; the reversing mechanism limiting block 5 is arranged at the front end of the wing deformation section and ensures that the upper sliding piece 1 and the lower sliding piece 2 are limited in sliding in the chord direction.
Because the wing in this embodiment is driven by shape memory alloy, the memory alloy wires are respectively arranged on the upper wing surface and the lower wing surface, the arrangement direction of the memory alloy wires is consistent with the wingspan direction, if the trailing edge of the wing needs to deflect upwards, the electromagnet for controlling the lower sliding sheet is electrified to release the electromagnet core bayonet lock, so that the lower sliding sheet is in a free sliding state, then the shape memory alloy wires arranged on the upper side are heated, at the moment, the alloy wires can generate deformation, a certain driving force is provided to drive the trailing edge of the wing to deflect upwards, and the lower unlocked sliding sheet can be driven to slide due to the relative increase of the chord length of the lower wing, so that the action of the trailing edge of; similarly, if need the wing to deflect downwards, at first through for the electro-magnet circular telegram release electro-magnet iron core bayonet lock of control upside gleitbretter, make the upside gleitbretter be in can the free sliding state, the electro-magnet reverse circular telegram of giving control downside gleitbretter pops out the dead downside gleitbretter of iron core bayonet lock, then heat the shape memory alloy silk that the downside was arranged, the alloy silk can produce deformation this moment, provide certain drive power and drive the wing trailing edge and deflect downwards, because the relative increase of upside wing chord length, can drive the slide slip piece that does not lock of upside and slide, thereby accomplish the action that the wing trailing edge deflected downwards.
Claims (1)
1. The reversing mechanism is used for the bidirectional variable trailing edge wing and is arranged between the fixed section and the deformation section of the bidirectional variable trailing edge wing; the reversing mechanism is characterized by mainly comprising an upper slide sheet 1, a lower slide sheet 2, an electromagnet mounting block 3, a spring pre-tightening transition block 4, a spring group and a limiting block 5; the upper sliding piece 1 and the lower sliding piece 2 are correspondingly arranged in parallel, and an upper clamping groove 6 and a lower clamping groove 7 are respectively arranged on the upper sliding piece 1 and the lower sliding piece 2; a miniature self-holding type push-pull electromagnet is arranged in the electromagnet mounting block 3, the whole electromagnet mounting block is arranged between the upper sliding sheet 1 and the lower sliding sheet 2, and the miniature self-holding type push-pull electromagnet controls an iron core bayonet lock to be switched in the upper bayonet lock 6 or the lower bayonet lock 7;
an upper groove and a lower groove are respectively formed in the side wall of the connecting part of the spring pre-tightening transition block 4 and the deformation section, which are connected with the fixed section of the wing, and when the two grooves are in butt joint, the two grooves are in butt joint to form an upper through groove 11 and a lower through groove 12;
after the reversing mechanism is installed, the reversing mechanism is fixed in a shell at the joint of a wing fixing section and a wing deformation section, and an upper sliding sheet 1 and a lower sliding sheet 2 of the reversing mechanism can freely slide in an upper through groove 11 and a lower through groove 12 respectively; one end of a reversing mechanism spring group is fixed in a spring fixing hole 9 or 10 of the upper sliding sheet 1 or the lower sliding sheet 2, and the other end of the reversing mechanism spring group is fixed in the wing fixing section through a spring pre-tightening transition block 4; the reversing mechanism limiting block 5 is arranged at the front end of the wing deformation section and ensures that the upper sliding piece 1 and the lower sliding piece 2 are limited in sliding in the chord direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011447676.7A CN112572763B (en) | 2020-12-09 | 2020-12-09 | Reversing mechanism for bidirectional variable trailing edge wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011447676.7A CN112572763B (en) | 2020-12-09 | 2020-12-09 | Reversing mechanism for bidirectional variable trailing edge wing |
Publications (2)
| Publication Number | Publication Date |
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| CN112572763A true CN112572763A (en) | 2021-03-30 |
| CN112572763B CN112572763B (en) | 2022-10-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011447676.7A Active CN112572763B (en) | 2020-12-09 | 2020-12-09 | Reversing mechanism for bidirectional variable trailing edge wing |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020100842A1 (en) * | 2000-11-11 | 2002-08-01 | Juan Perez | Mechanism for at least regionally adjusting the curvature of airfoil wings |
| CN101693467A (en) * | 2009-10-13 | 2010-04-14 | 南京航空航天大学 | Self-adapting morphing trailing edge based on SMA |
| JP2013173417A (en) * | 2012-02-24 | 2013-09-05 | Fuji Heavy Ind Ltd | Variable wing structure |
| US20140312168A1 (en) * | 2013-01-28 | 2014-10-23 | The Boeing Company | Control Surface for Creating Variable Camber Along a Wing |
| CN111152912A (en) * | 2020-01-09 | 2020-05-15 | 南京航空航天大学 | Rigidity compensation device for flexible wing and working method thereof |
| CN210618452U (en) * | 2019-05-28 | 2020-05-26 | 上海歌尔泰克机器人有限公司 | Variable-inclination winglet and aircraft |
| US20200307768A1 (en) * | 2019-03-26 | 2020-10-01 | Embraer S.A. | Lateral roller assemblies for wing leading edge slat tracks |
| CN112009726A (en) * | 2020-09-07 | 2020-12-01 | 西北工业大学 | Wing surface unfolding mechanism and pretreatment method of shape memory alloy thereof |
-
2020
- 2020-12-09 CN CN202011447676.7A patent/CN112572763B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020100842A1 (en) * | 2000-11-11 | 2002-08-01 | Juan Perez | Mechanism for at least regionally adjusting the curvature of airfoil wings |
| CN101693467A (en) * | 2009-10-13 | 2010-04-14 | 南京航空航天大学 | Self-adapting morphing trailing edge based on SMA |
| JP2013173417A (en) * | 2012-02-24 | 2013-09-05 | Fuji Heavy Ind Ltd | Variable wing structure |
| US20140312168A1 (en) * | 2013-01-28 | 2014-10-23 | The Boeing Company | Control Surface for Creating Variable Camber Along a Wing |
| US20200307768A1 (en) * | 2019-03-26 | 2020-10-01 | Embraer S.A. | Lateral roller assemblies for wing leading edge slat tracks |
| CN210618452U (en) * | 2019-05-28 | 2020-05-26 | 上海歌尔泰克机器人有限公司 | Variable-inclination winglet and aircraft |
| CN111152912A (en) * | 2020-01-09 | 2020-05-15 | 南京航空航天大学 | Rigidity compensation device for flexible wing and working method thereof |
| CN112009726A (en) * | 2020-09-07 | 2020-12-01 | 西北工业大学 | Wing surface unfolding mechanism and pretreatment method of shape memory alloy thereof |
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| CN112572763B (en) | 2022-10-18 |
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