CN107792343A - The optimization of folding wing - Google Patents
The optimization of folding wing Download PDFInfo
- Publication number
- CN107792343A CN107792343A CN201610830956.3A CN201610830956A CN107792343A CN 107792343 A CN107792343 A CN 107792343A CN 201610830956 A CN201610830956 A CN 201610830956A CN 107792343 A CN107792343 A CN 107792343A
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- China
- Prior art keywords
- wing
- covering
- diaphragm
- rib
- braced
- Prior art date
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- Pending
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- 238000005457 optimization Methods 0.000 title abstract description 5
- 210000000988 bone and bone Anatomy 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 description 2
- 208000019901 Anxiety disease Diseases 0.000 description 1
- 230000036506 anxiety Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/54—Varying in area
- B64C3/546—Varying in area by foldable elements
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tents Or Canopies (AREA)
Abstract
The title of the present invention is " optimization of folding wing ", by taking：Cancel tail point sliding block, make Diaphragm-braced rib succinctly complete, the epipleural bone of upper surface covering 9 and Diaphragm-braced rib 8 is slidably connected, the lower rib of lower surface covering 10 and Diaphragm-braced rib 8 is slidably connected, upper and lower surface covering only does locally-attached technical measures in trailing edge, covering longitudinal tensile stretches problem caused by when solving wing deformation, so as to eliminate the tail point sliding block of Diaphragm-braced rib；By taking nervous rope assisting tension device in covering, nervous rope assisting tension device outside covering, to the longitudinal stretching dynamics of covering when adding wing expansion.
Description
The title of the present invention is that " optimization of folding wing " belongs to aviation field.
Background of invention：
The present invention is to " folding wing " (number of patent application：201610228024.1；201620324195.X) carry out
Optimal improvements.
Folding wing mainly by：Foldable, expansion deformation wing support frame, Diaphragm-braced rib, covering, wing move
Make device composition.Wherein Diaphragm-braced rib forms and keeps wing vertical section aerodynamic configuration, before Diaphragm-braced rib front end and wing
Edge beam is articulated and connected, and multigroup Diaphragm-braced rib collectively forms wing aerodynamic profile, and covering adheres to and connects leading edge of a wing beam and illiteracy
Cutaneous branch stake rib, airfoil outer surface is formed, covering can be along Diaphragm-braced rib table under the constraint of Diaphragm-braced rib when wing deforms
Face is slided, and when being deformed to adapt to wing, two adjacent groups Diaphragm-braced rib catercorner length changes to the covering being attached thereto
Produce stretching, there is a tail point sliding block to be arranged on Diaphragm-braced rib afterbody, tail point sliding block in the case where Diaphragm-braced rib constrains slidably,
Can be when wing deforms as the situation of covering Tensile extends or shortens the length of Diaphragm-braced rib, so that covering will not
By excessive tensile, the main function that when wing deforms covering is tail point sliding block by excessive tensile is avoided.Pass through other skills
Art measure can equally play a part of sliding block, and simpler, and here it is the target that the present invention pursues
The content of the invention：
The purpose of the present invention is：Cancel tail point sliding block, take new technical measures to solve covering caused by when wing deforms
Longitudinal tensile stretches problem.
The method provided by the invention is mainly characterized in that：Diaphragm-braced rib is made up of upper and lower two ribs, upper and lower two rib front ends and wing
Leading edge beam is articulated and connected, and the rear end of upper and lower two ribs is joined together to form complete tail point, no tail point sliding block, forms and protects
Hold wing vertical section aerodynamic configuration.Multigroup Diaphragm-braced rib and wing support frame collectively form complete wing aerodynamic profile,
Bear the load of covering transmission.
Further；Covering is attached to leading edge of a wing beam and Diaphragm-braced rib outer surface, forms airfoil outer surface, bears to fly
Pneumatic load during row device flight, covering are divided into upper surface of the airfoil covering and wing lower surface covering, and they respectively connected illiteracy
The epipleural bone of cutaneous branch stake rib and lower rib, are to be slidably connected between covering and Diaphragm-braced rib, and when wing deforms, upper and lower surface is covered
Skin each slides under the constraint of Diaphragm-braced rib along epipleural bone and lower rib surface, and covering is subject to during adapting to wing deformation
Stretching.
Further；Upper and lower surface covering does local connection in trailing edge.
Further；When wing support frame folds, the Diaphragm-braced rib being attached thereto and covering is driven to collapse, each group is covered
Horizontal spacing reduces between cutaneous branch stake rib, and diagonal distance increases, and under the constraint of Diaphragm-braced rib, covering is along Diaphragm-braced rib table
Face is slided, and Diaphragm-braced rib tail point position is stretched out outside covering, so that covering will not be by excessive when wing-folding collapses
Stretching；When wing support frame deploys, the Diaphragm-braced rib being attached thereto and covering is driven to deploy, between each group Diaphragm-braced rib
Horizontal spacing increases, and diagonal distance reduces, and covering slides along Diaphragm-braced rib surface, gradually spreads out and tenses, and stretches out covering
Outside Diaphragm-braced rib tail point portion rebounds to design attitude.
Further；Nervous rope assisting tension in covering：By nervous rope in one, one end connection wing root, other end connection
Wingtip, centre are connected in series each group Diaphragm-braced rib tail point, and upper and lower surface covering in each tie point at trailing edge position.
During wing-folding, interior nervous rope relaxation, covering not being caused to stretch, after wing expansion, interior nervous rope is tightened up, while with each group
Diaphragm-braced rib tail point is the strong point, is to pull point with each tie point on covering, by covering to Diaphragm-braced rib tail point
Direction tenses.
Further；Nervous rope assisting tension outside covering：By an outer nervous rope, one end connection wing root, other end connection
Wingtip, centre are connected in series each tie point of the upper and lower surface covering at trailing edge position.During wing-folding, outer nervous Suo Song
Relax, covering is not caused to stretch, after wing expansion, outer nervous rope is tightened up, while pulls each tie point on covering, will be covered
Skin tenses to Diaphragm-braced rib tail point direction.
Brief description of the drawings：
Fig. 1 --- structural plan perspective view during wing-folding state；
Fig. 2 --- structural plan perspective view during half deployed condition of wing；
Fig. 3 --- structural plan perspective view during wing full deployed condition；
Fig. 4 --- skin drawing form plan during wing-folding state；
Fig. 5 --- skin drawing form plan during half deployed condition of wing；
Fig. 6 --- skin drawing form plan during wing full deployed condition；
Fig. 7 --- A-A profiles；
Fig. 8 --- B-B profiles；
Fig. 9 --- nervous rope assisting tension form plan in covering during wing-folding state；
Figure 10 --- nervous rope assisting tension form plan in covering during half deployed condition of wing；
Figure 11 --- nervous rope assisting tension form plan in covering during wing full deployed condition；
Figure 12 --- C-C profiles；
Figure 13 --- nervous rope assisting tension form plan outside covering during wing-folding state；
Figure 14 --- nervous rope assisting tension form plan outside covering during half deployed condition of wing；
Figure 15 --- nervous rope assisting tension form plan outside covering during wing full deployed condition；
Figure 16 --- D-D profiles；
Figure 17 --- unmanned plane plan during wing-folding state；
Figure 18 --- unmanned plane plan during half deployed condition of wing；
Figure 19 --- unmanned plane plan during wing full deployed condition.
Numbered in accompanying drawing：
1 --- transverse beam；2 --- longitudinal beam；3 --- leading edge of a wing beam；4 --- trailing edge beam；5 --- slide rail；
6 --- fixedly connected part；7 --- sliding block；8 --- Diaphragm-braced rib；9 --- upper surface covering；10 --- lower surface covering；
11 --- interior nervous rope；12 --- outer nervous rope.
Embodiment：
The present invention realizes its invention mesh by implementing following technical measures.
Structural plan perspective view when Fig. 1 is wing-folding state, structural plan is had an X-rayed when Fig. 2 is half deployed condition of wing
Figure, structural plan perspective view when Fig. 3 is wing full deployed condition, in figure：Wing support frame is vertical by a transverse beam 1, one
To parts such as beam 2, leading edge of a wing beam 3, trailing edge beam 4, slide rail 5, fixedly connected part 6, sliding blocks 7, by being hinged and sliding
(transverse beam 1, longitudinal beam 2 can increase or decrease according to the demand of wing, quantity, most for the dynamic triangle truss of connected mode
Small number is that zero), the truss is maintaining the plane of wing and section shape, support Diaphragm-braced rib and skin, bear
The pneumatic load that covering transmits, the truss can fold and drive Diaphragm-braced rib and skin synchronization action, realize wing
Fold, the purpose of expansion.
Diaphragm-braced rib 8 is made up of upper and lower two ribs, and upper and lower two rib front ends and leading edge of a wing beam 3 are articulated and connected,
The rear end of upper and lower two ribs is joined together to form complete tail point, no tail point sliding block, forms and keeps wing vertical section gas
Dynamic profile.Multigroup Diaphragm-braced rib 8 and wing support frame collectively form complete wing aerodynamic profile.
Fig. 7 is Fig. 6 A-A profiles, as shown in fig. 7, covering is attached to leading edge of a wing beam 3 and the appearance of Diaphragm-braced rib 8
Face, airfoil outer surface is formed, covering is divided into upper surface covering 9 and lower surface covering 10, and they respectively connected Diaphragm-braced rib 8
Epipleural bone and lower rib, be to be slidably connected between Diaphragm-braced rib 8；Fig. 8 is Fig. 6 B-B profiles, and Fig. 8 is from cross section
Wing support frame and Diaphragm-braced rib 8, upper surface covering 9, lower surface covering 10 are demonstrated by the mutual pass of the position of slide rail 5
System.
After wing-folding, covering is limited by longitudinal stretching by two adjacent groups Diaphragm-braced rib catercorner length, now,
Upper surface covering 9 and lower surface covering 10 each slide along the epipleural bone of Diaphragm-braced rib 8 and lower rib, beyond catercorner length
Partial Diaphragm-braced rib is stretched out outside covering, as shown in Figure 4；When wing deploys, covering is by wing support frame and covering branch
The stretching of stake rib, horizontal and vertical to deploy simultaneously, under the constraint of Diaphragm-braced rib 8, covering longitudinally deploys along Diaphragm-braced rib 8
Epipleural bone and lower rib slide, the Diaphragm-braced rib of outer portion for stretching out covering is gradually retracted into covering, as shown in Figure 5；Machine
After the wing is fully deployed, covering is horizontal, longitudinal direction is deployed in place, and Diaphragm-braced rib 8 retracts to design attitude, as shown in Figure 6.
Using nervous rope assisting tension in covering, can make folding wing upon deployment covering by stronger longitudinal direction
Stretching, nervous rope assisting tension facility connects wingtip by nervous rope 11 in one, one end connection wing root, the other end in covering, in
Between be connected in series each group Diaphragm-braced rib 8 tail point and upper and lower surface covering trailing edge position each tie point.Wing
After folding, interior nervous rope 11 relaxes, and covering is not caused to stretch, as shown in Figure 9；When wing deploys, interior nervous rope 11 is with machine
The expansion of the wing is gradually tightened up, while using each group Diaphragm-braced rib tail point as the strong point, what it is with each tie point on covering is
Point is pulled, upper covering 9, lower covering 10 are stretched to the tail point direction of Diaphragm-braced rib 8, shown in Figure 10；After wing is fully deployed, cover
Skin is horizontal, longitudinal direction is deployed in place, as shown in figure 11；Figure 12 is illustrated after wing is fully deployed from section, and interior nervous rope 11 is to upper
The stretching of covering 9 and lower covering 10.
Using nervous rope assisting tension outside covering, can making folded wing, covering is drawn by stronger longitudinal direction upon deployment
Stretch, nervous rope assisting tension facility is middle by an outer nervous rope 12, one end connection wing root, other end connection wingtip outside covering
It is connected in series each tie point of upper surface covering 9 and lower surface covering 10 at trailing edge position.After wing-folding, outer anxiety
Rope 12 relaxes, and covering is not caused to stretch, as shown in figure 13；When wing deploys, outer nervous rope 12 is gradual with the expansion of wing
It is tightened up, while pulls covering in each tie point of trailing edge, by upper covering 9, lower covering 10 to the tail point of Diaphragm-braced rib 8
Direction stretches, shown in Figure 14；After wing is fully deployed, covering is horizontal, longitudinal direction is deployed in place, as shown in figure 15；Figure 16 is from section
Illustrate after wing is fully deployed, stretching of the outer nervous rope 12 to upper covering 9 and lower covering 10.
The present invention has following major advantage：
1st, tail point slider part is eliminated so that folding wing structure optimization.
2nd, after tail point sliding block removes, make the structure of Diaphragm-braced rib 8 more complete, be advantageous to increase its intensity.
3rd, interior nervous rope assisting tension facility or outer nervous rope assisting tension facility are passed through, by increasing capacitance it is possible to increase folding wing exhibition
To the longitudinal stretching of covering in open procedure, be advantageous to make wing tighten skin after deploying.
4th, the present invention is applied to folding wing, and generally, folding wing has upper surface covering 9 with simultaneously
Skin 10, when air drag caused by the wing support frame of some aircraft is smaller, folding wing can be with
Only there is upper surface covering 9.
Purposes of the present invention：
The present invention is applied to folding wing.
Folding wing can have wing unmanned vehicle, individual lift device, hovercar etc. applied to all kinds of.
Case study on implementation：
Figure 17, Figure 18, Figure 19 are the designs applied using the folding wing of the present invention on a kind of unmanned plane；
Unmanned plane plan when Figure 17 is wing-folding state；
Unmanned plane plan when Figure 18 is half deployed condition of wing；
Unmanned plane plan when Figure 19 is wing full deployed condition.
Claims (7)
1. a kind of folding wing, including foldable or expansion deformation wing support frame, Diaphragm-braced rib 8, covering, its
It is characterized in：Diaphragm-braced rib 8 is made up of upper and lower two ribs, and upper and lower two rib front ends and leading edge of a wing beam 3 are articulated and connected, on
The rear end of lower two ribs is joined together to form complete tail point, no tail point sliding block, forms and keeps wing vertical section pneumatic
Profile, multigroup Diaphragm-braced rib 8 and wing support frame collectively form complete wing aerodynamic profile.
2. folding wing according to claim 1, it is characterized in that：Covering is attached to leading edge of a wing beam 3 and Diaphragm-braced
The outer surface of rib 8, airfoil outer surface is formed, covering is divided into upper surface covering 9 and lower surface covering 10, and they respectively connected covering
The epipleural bone of ribs 8 and lower rib, are to be slidably connected between Diaphragm-braced rib 8.
3. folding wing according to claim 1, it is characterized in that：When wing deforms, upper surface covering 9 and lower surface
Covering 10, each slided under the constraint of Diaphragm-braced rib 8 along epipleural bone and lower rib surface, to adapt to covering when wing deforms
The stretching being subject to.
4. folding wing according to claim 1, it is characterized in that：Upper surface covering 9 and lower surface covering 10 are in wing
Trailing edge does local connection.
5. folding wing according to claim 1, it is characterized in that：Nervous rope assisting tension facility is by one in covering
Nervous rope 11, one end connection wing root, the other end connection wingtip, centre be connected in series each group Diaphragm-braced rib 8 tail point and up and down
Skin is in each tie point at trailing edge position, and when wing deploys, interior nervous rope 11 is with the gradual quilt of expansion of wing
Tense, while using each group Diaphragm-braced rib tail point as the strong point, with each tie point on covering to pull point, by upper covering
9th, lower covering 10 stretches to the tail point direction of Diaphragm-braced rib 8.
6. folding wing according to claim 1, it is characterized in that：Nervous rope assisting tension facility is outer by one outside covering
Nervous rope 12, one end connection wing root, other end connection wingtip, centre is connected in series upper surface covering 9 and lower surface covering 10 exists
Each tie point at trailing edge position, when wing deploys, outer nervous rope 12 is gradually tightened up with the expansion of wing, is drawn simultaneously
Dynamic covering trailing edge each tie point, by upper surface covering 9, lower surface covering 10 to the tail point direction of Diaphragm-braced rib 8
Stretching.
7. folding wing according to claim 1, it is characterized in that：Air drag caused by wing support frame compares
Hour, folding wing only can have upper surface covering 9.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610830956.3A CN107792343A (en) | 2016-09-03 | 2016-09-03 | The optimization of folding wing |
| US15/479,301 US10696376B2 (en) | 2016-04-05 | 2017-04-05 | Foldable wing and rotocraft and glider using the same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610830956.3A CN107792343A (en) | 2016-09-03 | 2016-09-03 | The optimization of folding wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107792343A true CN107792343A (en) | 2018-03-13 |
Family
ID=61530188
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610830956.3A Pending CN107792343A (en) | 2016-04-05 | 2016-09-03 | The optimization of folding wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107792343A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109334949A (en) * | 2018-08-28 | 2019-02-15 | 南京航空航天大学 | A kind of morphing can be changed the shape control system and method for camber trailing edge formations |
| CN111824394A (en) * | 2020-07-27 | 2020-10-27 | 及兰平 | Folding wing with folding trailing edge flap |
| CN117842342A (en) * | 2024-03-06 | 2024-04-09 | 四川迅联达智能科技有限公司 | Outer surface conformal system of fixed wing aircraft and aircraft |
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| GB191126855A (en) * | 1911-11-30 | 1912-11-28 | Gustav Voigt | Improvements in Flying Machines. |
| WO1988000152A1 (en) * | 1986-07-08 | 1988-01-14 | Guex Jean Claude | Foldable wing, particularly for slope flight |
| US5474257A (en) * | 1993-11-23 | 1995-12-12 | Usbi Co. | Deployable wing |
| US5884863A (en) * | 1995-10-26 | 1999-03-23 | United Technologies Corporation | Method and apparatus for deploying a wing |
| FR2723718B1 (en) * | 1994-08-22 | 1999-06-25 | Morel Pierre Emile Francois | PENDULAR ULTRA-LIGHT WING OR VEHICLE WITH RAPID FOLDING AND FOLDING AND REDUCED SIZE. |
| US6283409B1 (en) * | 1999-10-18 | 2001-09-04 | Usbi Co. | Sail closure mechanism for cross bar access deployable wing |
| US20090166477A1 (en) * | 2007-12-28 | 2009-07-02 | Samuel Hall Bousfield | Telescoping wing and airfoil control mechanism |
| US20110260004A1 (en) * | 2010-04-26 | 2011-10-27 | Charles Mullins | Parachute with One-Way Valve Device |
| CN204197271U (en) * | 2014-09-17 | 2015-03-11 | 南昌航空大学 | A kind of collapsible dynamic-delta-wing wing |
| CN205255921U (en) * | 2015-11-10 | 2016-05-25 | 刘奥宇 | Flight electric automobile |
| CN206243448U (en) * | 2016-09-03 | 2017-06-13 | 及兰平 | Folding wing without Diaphragm-braced rib tail point sliding block |
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2016
- 2016-09-03 CN CN201610830956.3A patent/CN107792343A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB191126855A (en) * | 1911-11-30 | 1912-11-28 | Gustav Voigt | Improvements in Flying Machines. |
| WO1988000152A1 (en) * | 1986-07-08 | 1988-01-14 | Guex Jean Claude | Foldable wing, particularly for slope flight |
| US5474257A (en) * | 1993-11-23 | 1995-12-12 | Usbi Co. | Deployable wing |
| FR2723718B1 (en) * | 1994-08-22 | 1999-06-25 | Morel Pierre Emile Francois | PENDULAR ULTRA-LIGHT WING OR VEHICLE WITH RAPID FOLDING AND FOLDING AND REDUCED SIZE. |
| US5884863A (en) * | 1995-10-26 | 1999-03-23 | United Technologies Corporation | Method and apparatus for deploying a wing |
| US6283409B1 (en) * | 1999-10-18 | 2001-09-04 | Usbi Co. | Sail closure mechanism for cross bar access deployable wing |
| US20090166477A1 (en) * | 2007-12-28 | 2009-07-02 | Samuel Hall Bousfield | Telescoping wing and airfoil control mechanism |
| US20110260004A1 (en) * | 2010-04-26 | 2011-10-27 | Charles Mullins | Parachute with One-Way Valve Device |
| CN204197271U (en) * | 2014-09-17 | 2015-03-11 | 南昌航空大学 | A kind of collapsible dynamic-delta-wing wing |
| CN205255921U (en) * | 2015-11-10 | 2016-05-25 | 刘奥宇 | Flight electric automobile |
| CN206243448U (en) * | 2016-09-03 | 2017-06-13 | 及兰平 | Folding wing without Diaphragm-braced rib tail point sliding block |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109334949A (en) * | 2018-08-28 | 2019-02-15 | 南京航空航天大学 | A kind of morphing can be changed the shape control system and method for camber trailing edge formations |
| CN109334949B (en) * | 2018-08-28 | 2021-11-23 | 南京航空航天大学 | Shape control system and method for variable camber trailing edge structure of morphing wing |
| CN111824394A (en) * | 2020-07-27 | 2020-10-27 | 及兰平 | Folding wing with folding trailing edge flap |
| CN111824394B (en) * | 2020-07-27 | 2023-09-05 | 及兰平 | Folding wing with folding trailing edge flap |
| CN117842342A (en) * | 2024-03-06 | 2024-04-09 | 四川迅联达智能科技有限公司 | Outer surface conformal system of fixed wing aircraft and aircraft |
| CN117842342B (en) * | 2024-03-06 | 2024-05-14 | 四川迅联达智能科技有限公司 | Outer surface conformal system of fixed wing aircraft and aircraft |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
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Application publication date: 20180313 |