CN117141710A - Hypersonic folding airfoil surface gap air flow partition structure - Google Patents
Hypersonic folding airfoil surface gap air flow partition structure Download PDFInfo
- Publication number
- CN117141710A CN117141710A CN202311412795.2A CN202311412795A CN117141710A CN 117141710 A CN117141710 A CN 117141710A CN 202311412795 A CN202311412795 A CN 202311412795A CN 117141710 A CN117141710 A CN 117141710A
- Authority
- CN
- China
- Prior art keywords
- airfoil surface
- temperature
- folding
- resistant elastic
- elastic spacer
- 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.)
- Pending
Links
- 238000005192 partition Methods 0.000 title claims abstract description 16
- 125000006850 spacer group Chemical group 0.000 claims abstract description 43
- 238000010438 heat treatment Methods 0.000 claims abstract description 6
- 239000002184 metal Substances 0.000 claims description 5
- 230000000694 effects Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 4
- 238000000926 separation method Methods 0.000 claims description 4
- 239000013013 elastic material Substances 0.000 claims description 3
- 230000003685 thermal hair damage Effects 0.000 claims description 3
- 230000000903 blocking effect Effects 0.000 description 4
- 230000008646 thermal stress Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a hypersonic folding airfoil surface gap airflow partition structure, which solves the problems of high local heat flow and high temperature at a folding gap caused by the fact that high-speed hot airflow circulates along the folding gap after a folding airfoil surface is unfolded and locked. Mainly comprises a lower airfoil surface, an upper airfoil surface, a high-temperature-resistant elastic spacer, mounting screws and the like. One side of the end face of the lower airfoil surface is provided with a groove along the chord direction, one end of the high-temperature-resistant elastic spacer is inserted into the groove, and the other end of the high-temperature-resistant elastic spacer protrudes 3mm to 5mm from the surface of the groove. When the upper airfoil surface is unfolded to the unfolding locking position, the root part of the end surface of the upper airfoil surface extrudes and bends the high-temperature-resistant elastic spacer to form an airflow partition. The high-speed airflow passage of the folding wing surface folding gap is partitioned, so that the locking mechanism is prevented from being damaged at high temperature due to heating of the high-speed airflow, the high-speed airflow passage is particularly suitable for hypersonic folding wing surface structural design, the using range of the folding wing surface is effectively improved, and the structural reliability is improved.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a hypersonic folding airfoil surface gap airflow partition structure.
Background
To reduce the structural volume of an aircraft and increase the packing density of the aircraft, folding airfoils tend to be used, and the application of folding airfoils on hypersonic aircraft faces greater challenges and difficulties than low speed aircraft, the most important of which is that hypersonic folding airfoils face severe aerodynamic thermal environment and structural thermal stress problems. After the hypersonic folding airfoil surface is unfolded, a through hypersonic hot air flow is formed at a folding seam, a locking structure inside the seam can generate extremely high heat flow and temperature under the pneumatic action of the hypersonic hot air flow, the strength is seriously reduced, and great hidden danger is caused to the structural reliability.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a hypersonic folding airfoil surface gap airflow partition structure, which solves the problems of high local heat flow and high temperature at the folding gap caused by the circulation of high-speed hot airflow along the folding gap after the folding airfoil surface is unfolded and locked. Mainly comprises a lower airfoil surface, an upper airfoil surface, a high-temperature-resistant elastic spacer, mounting screws and the like. One side of the end face of the lower airfoil surface is provided with a groove along the chord direction, one end of the high-temperature-resistant elastic spacer is inserted into the groove, and the other end of the high-temperature-resistant elastic spacer protrudes 3mm to 5mm from the surface of the groove. When the upper airfoil surface is unfolded to the unfolding locking position, the root part of the end surface of the upper airfoil surface extrudes and bends the high-temperature-resistant elastic spacer to form an airflow partition. The high-speed airflow passage of the folding wing surface folding gap is partitioned, so that the locking mechanism is prevented from being damaged at high temperature due to heating of the high-speed airflow, the high-speed airflow passage is particularly suitable for hypersonic folding wing surface structural design, the using range of the folding wing surface is effectively improved, and the structural reliability is improved.
The technical scheme adopted by the invention for solving the technical problems comprises the following steps:
a hypersonic folding airfoil surface gap air flow partition structure comprises an upper airfoil surface 1, a locking mechanism 2, a high-temperature resistant elastic spacer 3, a screw 4 and a lower airfoil surface 5;
the locking mechanism 2 is arranged on the end face of the slightly lower part of the lower airfoil surface 5;
a groove is formed in one side of the end face of the slightly lower wing surface 5 along the chord direction;
one end of the high-temperature-resistant elastic spacer 3 is inserted into the groove, and the other end extends out from the end face of the slightly lower part of the lower airfoil surface 5;
the side surface of the lower airfoil surface 5, which is provided with a groove, is vertically provided with a plurality of screws 4, and the high-temperature-resistant elastic spacer 3 is fixed in the groove of the lower airfoil surface;
the upper airfoil surface 1 and the lower airfoil surface 5 are connected by a unfolding mechanism; when the upper airfoil surface 1 rotates to the locking position of the unfolding mechanism, the locking mechanism 2 acts to lock the upper airfoil surface 1 and the lower airfoil surface 5; the high-temperature-resistant elastic spacer 3 is pressed into the gap between the upper airfoil surface 1 and the lower airfoil surface 5 by the root of the upper airfoil surface 1 in the rotation process of the upper airfoil surface 1, and has a blocking effect on high-speed air flow penetrating through the gap, so that the pneumatic heating effect of the high-speed air flow on the structure of the locking mechanism 2 between the gaps is avoided, and further the thermal damage of the locking mechanism is avoided.
Preferably, the high temperature resistant elastic spacer 3 is a high temperature resistant metal elastic sheet, and is made of 60Si2Mn elastic material, and the thickness is between 0.3mm and 0.5 mm.
Preferably, the other end of the high-temperature resistant elastic spacer 3 extends from the end face of the lower airfoil 5 at the tip part by 3 mm-5 mm.
The beneficial effects of the invention are as follows:
according to the hypersonic folded airfoil surface gap airflow partition structure, the partition structure is arranged in the gap between the upper airfoil surface and the lower airfoil surface, so that high-speed airflow passing through the gap is blocked, the problem that the high-speed airflow penetrates through the gap between the upper airfoil surface and the lower airfoil surface after the hypersonic folded airfoil surface is unfolded to pneumatically heat the locking mechanism in the gap is solved, the locking mechanism is prevented from being damaged in heat intensity due to local high heat, the reliability of the hypersonic folded airfoil surface unfolding direction locking mechanism is greatly improved, and obstacles are cleared for application of the folded airfoil surface in the hypersonic aircraft field.
Drawings
FIG. 1 is a schematic view of a folding airfoil folding gap partition structure of the present invention.
FIG. 2 is a partial cross-sectional view of a partition structure of the present invention.
FIG. 3 is a schematic view of a partition structure of the folded airfoil of the present invention after deployment.
Description of the drawings: 1-an upper airfoil surface; 2-a locking mechanism; 3-high temperature resistant elastic spacers; 4-a screw; 5-lower airfoil.
Detailed Description
The invention will be further described with reference to the drawings and examples.
The hypersonic folded airfoil surface gap air flow partition structure provided by the invention mainly solves the problems that after a hypersonic aircraft folded airfoil surface is unfolded and locked, the hypersonic air flow can form a through air flow from a gap between a lower airfoil surface and an upper airfoil surface, so that a locking structure in the gap is pneumatically heated to generate local high temperature and thermal stress, and the strength and safety of the locking structure are affected.
In order to solve the problems, the hypersonic folding airfoil surface gap air flow partition structure mainly comprises a lower airfoil surface, an upper airfoil surface, a locking mechanism, a high-temperature resistant elastic spacer and mounting screws thereof; when the upper wing surface of the folding wing surface is in a folding state, a high-temperature-resistant elastic spacer is arranged on one side of the end surface of the lower wing surface of the folding wing surface along the chord direction, the high-temperature-resistant elastic spacer is parallel to the side surface of the lower wing surface, one end of the high-temperature-resistant elastic spacer is inserted into the end surface of the lower wing surface, and the other end of the high-temperature-resistant elastic spacer is exposed out of 3-5 mm. When the upper airfoil surface is unfolded to a locking position, the root end surface of the upper airfoil surface can touch the spacer and press the spacer into a gap between the upper airfoil surface and the lower airfoil surface, and the spacer slightly abuts against the upper airfoil surface all the time due to certain elasticity of the metal spacer, so that an airflow separation structure is formed; the rigidity of the locking mechanism can also form a larger blocking effect on air flow, so that the high-speed air flow is prevented from damaging an internal locking structure.
A groove is formed in one side of the end face of the lower airfoil surface at the slightly part along the chord direction and is used for installing a high-temperature-resistant elastic spacer;
the high temperature resistant elastic spacer is a high temperature resistant metal sheet, and is usually 60Si 2 Mn and other elastic materials, wherein one end of the spacer is inserted into the groove, and the other end of the spacer is exposed out of the end face of the lower airfoil surface;
the side surface of the lower airfoil surface, which is provided with a groove, is vertically provided with a plurality of screws for fixing the high-temperature-resistant elastic spacer;
the upper airfoil surface can rotate around the lower airfoil surface, and the spacer is pressed into the gap between the upper airfoil surface and the lower airfoil surface by the root of the upper airfoil surface in the process of rotating the upper airfoil surface to the locking position, thereby forming a blocking effect on high-speed air flow penetrating through the gap, avoiding pneumatic heating effect on a locking mechanism structure between the gaps when the high-speed air flow passes through the gap, and further avoiding thermal stress damage of the locking mechanism.
Examples:
referring to fig. 1-3, the invention provides an embodiment of a hypersonic folding airfoil gap air flow separation structure, which comprises an upper airfoil surface 1, a locking mechanism 2, a high-temperature resistant elastic spacer 3, a screw 4 and a lower airfoil surface 5.
The locking mechanism 2 is arranged on the end face of the slightly lower part of the lower airfoil surface 5;
a groove is formed in one side of the end face of the slightly lower wing surface 5 along the chord direction;
the high-temperature-resistant elastic spacer 3 is a high-temperature-resistant metal elastic sheet, one end of the high-temperature-resistant elastic spacer 3 is inserted into the groove, and the other end of the high-temperature-resistant elastic spacer is exposed out of the end face of the slightly lower airfoil surface 5;
the side surface of the lower airfoil surface 5, which is provided with a groove, is vertically provided with a plurality of screws 4, and the high-temperature-resistant elastic spacer 3 is fixed in the groove of the lower airfoil surface;
the upper airfoil surface 1 and the lower airfoil surface 5 are connected by a unfolding mechanism; when the upper airfoil surface 1 rotates to the unfolding locking position, the high-temperature-resistant elastic spacer 3 is pressed into the gap between the upper airfoil surface 1 and the lower airfoil surface 5 by the root of the upper airfoil surface 1 in the process that the upper airfoil surface 1 rotates to the unfolding position, and has a blocking effect on high-speed air flow penetrating through the gap, so that the pneumatic heating effect of the high-speed air flow on the structure of the locking mechanism 2 between the gaps is avoided, and further, the thermal damage of the locking mechanism is avoided.
Claims (3)
1. The hypersonic folding airfoil surface gap air flow partition structure is characterized by comprising an upper airfoil surface, a locking mechanism, a high-temperature-resistant elastic spacer, a screw and a lower airfoil surface;
the end face of the lower airfoil surface at the tip is provided with a locking mechanism;
a groove is formed in one side of the end face of the lower airfoil surface at the slightly part along the chord direction;
one end of the high-temperature-resistant elastic spacer is inserted into the groove, and the other end of the high-temperature-resistant elastic spacer extends out from the end face of the tip part of the lower airfoil;
the side surface of the lower airfoil surface, which is provided with a groove, is vertically provided with a plurality of screws, and the high-temperature-resistant elastic spacer is fixed in the groove of the lower airfoil surface;
the upper airfoil surface and the lower airfoil surface are connected by a unfolding mechanism; when the upper airfoil surface rotates to the locking position of the unfolding mechanism, the locking mechanism acts to lock the upper airfoil surface and the lower airfoil surface; the high-temperature-resistant elastic spacer is pressed into the gaps between the upper airfoil surface and the lower airfoil surface by the root of the upper airfoil surface in the rotation process of the upper airfoil surface, and plays a role in separating high-speed airflow penetrating through the gaps, so that pneumatic heating effect of the high-speed airflow on a locking mechanism structure between the gaps is avoided, and further thermal damage of the locking mechanism is avoided.
2. The hypersonic folding airfoil surface gap air flow separation structure according to claim 1, wherein the high-temperature resistant elastic spacer is a high-temperature resistant metal elastic sheet, and is made of 60Si2Mn elastic material, and the thickness is between 0.3mm and 0.5 mm.
3. The hypersonic folded airfoil surface gap air flow separation structure as claimed in claim 1, wherein the other end of the high-temperature resistant elastic spacer extends from the lower airfoil surface slightly to 3-5 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311412795.2A CN117141710A (en) | 2023-10-30 | 2023-10-30 | Hypersonic folding airfoil surface gap air flow partition structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311412795.2A CN117141710A (en) | 2023-10-30 | 2023-10-30 | Hypersonic folding airfoil surface gap air flow partition structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117141710A true CN117141710A (en) | 2023-12-01 |
Family
ID=88908400
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311412795.2A Pending CN117141710A (en) | 2023-10-30 | 2023-10-30 | Hypersonic folding airfoil surface gap air flow partition structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117141710A (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB402892A (en) * | 1932-08-15 | 1933-12-14 | Albert Henry Timmis | Improvements in or relating to means for eliminating draught through closed doorwaysand the like |
| US20100000991A1 (en) * | 2008-07-02 | 2010-01-07 | Henry Christopher P | Thermally activated variable stiffness composites for aircraft seals |
| DE102017113058A1 (en) * | 2017-06-14 | 2018-12-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Space transport aircraft and reentry aircraft |
| CN109322923A (en) * | 2018-09-27 | 2019-02-12 | 中浙高铁轴承有限公司 | A kind of oscillating bearing sealing structure |
| CN211145379U (en) * | 2019-12-06 | 2020-07-31 | 浙江宣达环境科技股份有限公司 | High-temperature flue gas butterfly valve and valve rod sealing structure thereof |
| CN111717366A (en) * | 2020-06-29 | 2020-09-29 | 中国商用飞机有限责任公司 | Sealing plug and sealing assembly comprising same |
| CN112977800A (en) * | 2021-03-24 | 2021-06-18 | 中国科学院力学研究所 | Folding wing for hypersonic aircraft |
| CN213502874U (en) * | 2020-11-13 | 2021-06-22 | 北京海利天梦科技有限公司 | Wing folding structure of unmanned aerial vehicle |
| KR20210109963A (en) * | 2020-02-28 | 2021-09-07 | 주식회사 플라썸 | Windproof gasket for window and door with fine dust blocking effect |
| CN113581446A (en) * | 2021-08-17 | 2021-11-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Telescopic folding device and wing |
| CN113830286A (en) * | 2021-09-18 | 2021-12-24 | 中国商用飞机有限责任公司 | Aileron actuation structure and wing comprising an aileron actuation structure |
| US20220024558A1 (en) * | 2019-05-24 | 2022-01-27 | Airbus Operations Limited | Arrangement for avoiding clashing between an actuation assembly and an upper cover of a folding wing tip |
| GB2601767A (en) * | 2020-12-09 | 2022-06-15 | Airbus Operations Ltd | Aircraft hinge assembly |
| CN116305584A (en) * | 2023-03-30 | 2023-06-23 | 中航(成都)无人机系统股份有限公司 | Control surface installation optimization method and structure |
-
2023
- 2023-10-30 CN CN202311412795.2A patent/CN117141710A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB402892A (en) * | 1932-08-15 | 1933-12-14 | Albert Henry Timmis | Improvements in or relating to means for eliminating draught through closed doorwaysand the like |
| US20100000991A1 (en) * | 2008-07-02 | 2010-01-07 | Henry Christopher P | Thermally activated variable stiffness composites for aircraft seals |
| DE102017113058A1 (en) * | 2017-06-14 | 2018-12-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Space transport aircraft and reentry aircraft |
| CN109322923A (en) * | 2018-09-27 | 2019-02-12 | 中浙高铁轴承有限公司 | A kind of oscillating bearing sealing structure |
| US20220024558A1 (en) * | 2019-05-24 | 2022-01-27 | Airbus Operations Limited | Arrangement for avoiding clashing between an actuation assembly and an upper cover of a folding wing tip |
| CN211145379U (en) * | 2019-12-06 | 2020-07-31 | 浙江宣达环境科技股份有限公司 | High-temperature flue gas butterfly valve and valve rod sealing structure thereof |
| KR20210109963A (en) * | 2020-02-28 | 2021-09-07 | 주식회사 플라썸 | Windproof gasket for window and door with fine dust blocking effect |
| CN111717366A (en) * | 2020-06-29 | 2020-09-29 | 中国商用飞机有限责任公司 | Sealing plug and sealing assembly comprising same |
| CN213502874U (en) * | 2020-11-13 | 2021-06-22 | 北京海利天梦科技有限公司 | Wing folding structure of unmanned aerial vehicle |
| GB2601767A (en) * | 2020-12-09 | 2022-06-15 | Airbus Operations Ltd | Aircraft hinge assembly |
| CN112977800A (en) * | 2021-03-24 | 2021-06-18 | 中国科学院力学研究所 | Folding wing for hypersonic aircraft |
| CN113581446A (en) * | 2021-08-17 | 2021-11-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Telescopic folding device and wing |
| CN113830286A (en) * | 2021-09-18 | 2021-12-24 | 中国商用飞机有限责任公司 | Aileron actuation structure and wing comprising an aileron actuation structure |
| CN116305584A (en) * | 2023-03-30 | 2023-06-23 | 中航(成都)无人机系统股份有限公司 | Control surface installation optimization method and structure |
Non-Patent Citations (1)
| Title |
|---|
| 王振峰等: "航天器高温热密封设计方法及性能评价", 宇航学报, vol. 39, no. 07, pages 793 - 800 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10184340B2 (en) | Geared turbofan engine having a reduced number of fan blades and improved acoustics | |
| US9017037B2 (en) | Rotor with flattened exit pressure profile | |
| US9228442B2 (en) | Turbine airfoil tip shelf and squealer pocket cooling | |
| US9284845B2 (en) | Turbine airfoil tip shelf and squealer pocket cooling | |
| US2920864A (en) | Secondary flow reducer | |
| US9102397B2 (en) | Airfoils including tip profile for noise reduction and method for fabricating same | |
| EP3150803B1 (en) | Airfoil and method of cooling | |
| US10677066B2 (en) | Turbine blade with airfoil tip vortex control | |
| CN111771048B (en) | Structure having a profile with inclined serrations | |
| EP3170974A1 (en) | Turbine blade with airfoil tip vortex control | |
| CN117141710A (en) | Hypersonic folding airfoil surface gap air flow partition structure | |
| Madasseri Payyappalli et al. | Effect of tandem blading in contra-rotating axial flow fans | |
| Erickson | Wind tunnel investigation of the interaction and breakdown characteristics of slender-wing vortices at subsonic, transonic, and supersonic speeds | |
| Simoes et al. | Application of a free vortex wake model to a horizontal axis wind turbine | |
| CN208216978U (en) | A kind of aircraft horizontal tail root vortex generator | |
| Van Ness et al. | Tip clearance flow visualization of a turbine blade cascade with active and passive flow control | |
| Veldhuis et al. | Novel passive and active flow control for high lift | |
| Vaczy et al. | A study of the leading edge vortex and tip vortex on prop-fan blades | |
| Leavitt | Effect of empennage location on twin-engine afterbody-nozzle aerodynamic characteristics at Mach Numbers from 0.6 to 1.2 | |
| Van der Burg et al. | Low speed maximum lift and flow control | |
| CN117963131A (en) | Heat protection structure suitable for deformed wing aircraft and deformed wing aircraft | |
| Agnew et al. | Linear and nonlinear aerodynamics of three-surface aircraft concepts | |
| Favier et al. | Unsteady interactional effects between a propeller and a fixed wing | |
| Wood | Section characteristics of a finite, swept circulation control airfoil | |
| Perry | A review of some published data on the external-flow jet-augmented flap |
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 |