CN113720217A - Be applied to thermal-insulated folding rudder of hypersonic flight - Google Patents
Be applied to thermal-insulated folding rudder of hypersonic flight Download PDFInfo
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- CN113720217A CN113720217A CN202110836914.1A CN202110836914A CN113720217A CN 113720217 A CN113720217 A CN 113720217A CN 202110836914 A CN202110836914 A CN 202110836914A CN 113720217 A CN113720217 A CN 113720217A
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- rudder
- shaft
- control surface
- rotating shaft
- heat
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Thermal Insulation (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a heat-insulation folding rudder applied to hypersonic flight, which comprises a control surface and a control shaft for unfolding the control surface, wherein the control shaft comprises a bearing, a lower shell, an upper shell, a connecting shaft, a high silica shaft sleeve, a spring and a rotating shaft; when the folding rudder is not unfolded, a rudder shaft for unfolding and locking the folding rudder is converged in a cabin body of the missile, so that the thermal protection difficulty of the folding rudder can be greatly reduced; in addition, after the folding rudder is unfolded, the high-silica shaft sleeve is unfolded and locks the folding rudder, and the mechanism is simple and reliable; meanwhile, the high silica shaft sleeve can cover the connecting shaft, the rotating shaft, the bottom of the control surface and other parts exposed in the air, so that the thermal protection pressure of the control system is reduced; therefore, the heat insulation folding rudder can well solve the problems of heat insulation and bearing of the control surface, unfolding of the folding rudder, locking of the folding rudder and heat insulation of an unfolding mechanism when a missile flies at a hypersonic speed.
Description
Technical Field
The invention belongs to the technical field of hypersonic flight vehicles, and particularly relates to a heat-insulation folding rudder applied to hypersonic flight.
Background
Hypersonic aircrafts have become the focus of modern aerospace scientific and technical research. With the continuous increase of the flying speed, the pneumatic heating effect of the aircraft is more and more obvious. The effect of heat on hypersonic aircraft has not been negligible. For a hypersonic aircraft, the control surface is the weakest link. On one hand, the control surface needs to deflect to play a role of balancing force or moment, so that the load is larger; on the other hand, the temperature near the rudder is very high, and the aerodynamic heating effect is more obvious, so that the control surface is easier to ablate relative to other parts of the aircraft, the aerodynamic appearance is damaged, and the mechanical property of the air rudder is reduced. An air vane with thermal insulation and capable of bearing load is of no great significance to hypersonic missiles.
The air rudder is an important executive component of a missile guidance system and can be divided into a folding rudder and an unfolding rudder according to whether a control surface is folded or not. The foldable rudder has the advantages of small volume, high adaptability with a launching device and the like, and gradually becomes the mainstream of the air rudder of the missile. The folding rudder generally comprises a bearing assembly, a driving shaft, a rudder surface, a positioning and locking mechanism and the like. When the missile flies at a hypersonic speed, the front edge of a control surface and a control shaft exposed in the air have stagnation points to form a high-temperature area, and the aerodynamic heat becomes worse due to a semi-closed cavity commonly existing in a folded rudder. The mechanical properties of the control surface, the control shaft and the locking mechanism are sharply reduced due to high temperature, and the overall performance of the air rudder is determined by heat prevention and heat insulation treatment in a high-temperature area.
The prior art relates to hypersonic folded rudders, which are mostly coated by heat-insulating materials and supported by metal frameworks. When the rudder flies at hypersonic speed, air between the metal frameworks is heated by pneumatic heat, the air is heated to expand, and the rudder is easy to lose effectiveness due to pressure generated by the expansion of the air on the heat insulation material. The problem of air expansion can be solved by making holes in the control surface, but the strength of the control surface is reduced. Secondly, the locking mechanism and the unfolding mechanism of the existing folding rudder are both arranged in the rudder surface, and the manner can cause the rudder surface to have a semi-closed cavity or a gap. These semi-enclosed cavities and gaps can exacerbate the aerodynamic heat that can burn out the locking or deployment mechanism of the rudder, thereby rendering the rudder ineffective or even burning out.
Disclosure of Invention
In order to solve the problems, the invention provides the heat-insulation folding rudder applied to hypersonic flight, which can greatly reduce the heat protection pressure of a rudder system.
A heat insulation folding rudder applied to hypersonic flight comprises a control surface and a control shaft for unfolding the control surface, wherein the control shaft is protected in a cabin section by a heat protection layer of a missile cabin body 9, and comprises a bearing 1, a lower shell 2, an upper shell 3, a connecting shaft 7, a high silica shaft sleeve 8, a spring 10 and a rotating shaft 11;
the lower shell 2 and the upper shell 3 are fixedly connected to form a cylindrical sleeve, then the cylindrical sleeve is fixedly connected to the inner wall of the missile cabin body 9 through the upper end of the upper shell 3 and is aligned to a control surface mounting hole on the missile cabin body 9, and meanwhile, a rotating shaft 11 which is externally sleeved with a spring 10 is integrally arranged in the cylindrical sleeve; the upper end of the rotating shaft 11 penetrates through the upper shell 3 and the rudder surface mounting hole in sequence and then forms a hinge joint with the bottom of the rudder surface through the connecting shaft 7, and the lower end penetrates through the lower shell 2 and then is connected with an external steering engine system; when the control surface is restrained by external force to be in a folded state, the outer part of the high silica shaft sleeve 8 is matched with the upper shell 3 to form a shaft hole, the spring 10 is tightly pressed on the spring mounting seat of the lower shell 2, meanwhile, the inner part of the high silica shaft sleeve 8 is matched with the rotating shaft 11 to form a shaft hole, and the high silica shaft sleeve 8 can do linear and rotary motion along the axis of the rotating shaft 11; when the control surface loses external force to restrict and is expanding, the high silica shaft sleeve 8 moves linearly upwards along the rotating shaft 11 under the driving of the spring 10; after the control surface is completely unfolded, the spring 10 presses the high silica shaft sleeve 8 into the control surface mounting hole and props against the lower end surface of the control surface.
Further, the control surface comprises a glass fiber reinforced plastic control surface 4, a titanium alloy framework 5 and alumina foam 6;
the glass fiber reinforced plastic rudder surface 4 is coated on the outer layer of the titanium alloy framework 5 as a thermal protection material of the folding rudder, and the alumina foam 6 is filled in the gap in the titanium alloy framework 5.
Furthermore, the alumina foam and the titanium alloy framework are fixed by molding through silica fiber and phenolic resin.
Further, the thickness of the glass fiber reinforced plastic control surface 4 is determined according to the aerodynamic heat, and the size of the titanium alloy framework 5 is determined according to the strength load.
Further, the upper shell 3 is connected with the inner wall of the missile cabin 9 through screws.
Has the advantages that:
1. the invention provides a heat-insulation folding rudder applied to hypersonic flight, wherein when the folding rudder is not unfolded, a rudder shaft for unfolding and locking the folding rudder is converged in a cabin body of a missile, so that the heat protection difficulty of the folding rudder can be greatly reduced; in addition, after the folding rudder is unfolded, the high-silica shaft sleeve is unfolded and locks the folding rudder, and the mechanism is simple and reliable; meanwhile, the high silica shaft sleeve can cover the connecting shaft, the rotating shaft, the bottom of the control surface and other parts exposed in the air, so that the thermal protection pressure of the control system is reduced; therefore, the heat insulation folding rudder can well solve the problems of heat insulation and bearing of the control surface, unfolding of the folding rudder, locking of the folding rudder and heat insulation of an unfolding mechanism when a missile flies at a hypersonic speed.
2. The invention provides a heat-insulation folding rudder applied to hypersonic flight, which is characterized in that glass fiber reinforced plastics are used as a heat protection material of the folding rudder to be coated on the outermost layer, a framework is made of titanium alloy as a material to be used as a bearing part of the folding rudder, and gaps among the titanium alloy are filled by adopting alumina foam, so that the heat bearing and bearing capacity of a rudder surface can be greatly improved, and the heat-insulation folding rudder has a better heat insulation effect.
3. The invention provides a heat-insulating folding rudder applied to hypersonic flight, which is characterized in that firstly, based on the characteristics of low density of alumina foam, good heat-insulating property, alumina ceramic generated by sintering with silicon dioxide at high temperature and the like, the rudder is used as a filler, and the mass of a rudder system is increased less; secondly, the aluminum oxide can absorb partial heat to reduce the temperature of the titanium alloy, so that the heat resistance of the whole control surface is improved; finally, the alumina reacts with the silicon dioxide in the glass fiber reinforced plastic at high temperature to absorb partial heat, and the generated alumina ceramic has good heat insulation performance so as to reduce the heat transfer to the titanium alloy framework.
4. The invention provides a heat-insulation folding rudder applied to hypersonic flight, wherein a rudder shaft of the folding rudder, namely an unfolding and locking mechanism of the folding rudder, is protected in a cabin section by a heat protection layer of a missile cabin body, so that the difficulty of the heat protection design of the folding rudder can be effectively reduced.
5. The invention provides a heat-insulation folding rudder applied to hypersonic flight, wherein when a control surface is unfolded, a spring drives a high-silica shaft sleeve to move linearly upwards so as to jack the control surface, and after the control surface is completely unfolded, the spring presses the high-silica shaft sleeve into a control surface mounting hole and props against the lower end surface of the control surface, so that the axial movement of the high-silica shaft is limited and the folding rudder is locked; therefore, the folding rudder disclosed by the invention shares a set of spring and a high silica shaft sleeve for unfolding and locking, has a simple structure, reduces the unfolding and locking control difficulty of the folding rudder, and can save the cost.
Drawings
FIG. 1 is a schematic structural view of a foldable rudder capable of insulating heat during hypersonic flight according to the present invention;
FIG. 2 is a folded rudder in a folded state;
fig. 3 is a detail of the interior of the folded rudder in a folded state;
FIG. 4 is a folded rudder in an unfolded state;
FIG. 5 is a detail of the interior of the folded rudder in the unfolded state;
1-bearing, 2-lower shell, 3-upper shell, 4-glass fiber reinforced plastic control surface, 5-titanium alloy skeleton, 6-alumina foam, 7-connecting shaft, 8-high silica shaft sleeve, 10-spring and 11-rotating shaft.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application.
As shown in fig. 1, a foldable rudder capable of insulating heat during hypersonic flight comprises: the rudder surface and the rudder shaft. The control surface structure can be divided into three parts, namely a glass fiber reinforced plastic control surface 4, a titanium alloy framework 5 and alumina foam 6. Firstly, on the premise of determining the aerodynamic shape of the air rudder, the thermal insulation materials of the front edge and the control surface of the air rudder, namely the thickness of the glass fiber reinforced plastic control surface 4, are determined according to aerodynamic heat calculation, the size of the titanium alloy framework 5 is determined according to strength load, alumina foam is adopted to fill the gap between the titanium alloy frameworks, and the titanium alloy and the alumina foam are molded according to the size of the thermal insulation materials by using glass fiber reinforced plastic. That is, the invention adopts the titanium alloy framework 5 as a bearing component, the alumina foam 6 is used for filling the gap between the titanium alloy framework 5, the density of the alumina foam 6 is lower than that of the titanium alloy framework, and the alumina foam is used as a filler to increase the mass of the rudder system slightly; the heat insulation performance of the alumina foam 6 is good, and the heat transferred from the glass fiber reinforced plastic control surface 4 can be absorbed; the alumina foam 6 and the silicon dioxide fiber contained in the glass fiber reinforced plastic control surface 4 can react at high temperature to absorb heat, so that the heat is reduced to be transferred to the titanium alloy framework, the titanium alloy is prevented from being failed due to overhigh temperature, and the heat resistance of the whole control system is further improved. The glass fiber reinforced plastic control surface 4 is formed on the surfaces of the titanium alloy framework 5 and the alumina foam 6 by adopting the silicon dioxide fibers and the phenolic resin, the glass fiber reinforced plastic has good heat insulation performance, and the pneumatic heat generated by hypersonic speed can be effectively reduced and transferred to the inside of the control surface.
The rudder shaft structure of the invention can be divided into a bearing 1, a lower shell 2, an upper shell 3, a connecting shaft 7, a high silica shaft sleeve 8, a spring 10 and a rotating shaft 11. Wherein, the lower shell 2 and the upper shell 3 can form a cylindrical sleeve by screw connection. The outer part of the high silica shaft sleeve 8 is matched with the upper shell 3 through a shaft hole, and the high silica shaft sleeve 8 makes linear and rotary motion along the axis of the upper shell 3; the high silica shaft sleeve 8 is matched with the rotating shaft 11 through a shaft hole, and the high silica shaft sleeve 8 makes linear and rotary motion along the axis of the rotating shaft 11; the high silica shaft sleeve 8 is connected with the lower shell 2 through a spring 10, and the spring 10 provides driving force for the linear motion of the high silica shaft sleeve 8. The bearing 1 and the lower shell 2 are matched with each other through a shaft hole, the bearing 1 and the rotating shaft 11 are matched with each other through the shaft hole, and sliding friction between the rotating shaft 11 and the lower shell 2 can be reduced through the bearing 1. The spring 10 is seated on the spring mount of the lower case 2. The upper shell 3 is fixedly connected with the missile cabin body 9 through screws. Two ends of the rotating shaft 11 respectively penetrate through a cylindrical sleeve formed by the lower shell 2 and the upper shell 3, the upper end of the rotating shaft is hinged with the titanium alloy framework 5 in the control surface through the connecting shaft 7, and the lower end of the rotating shaft is connected with the steering engine system.
As shown in fig. 2 and fig. 3, when the foldable rudder is in a folded state, an external force is required to be applied, the force makes the glass fiber reinforced plastic control surface 4 cling to the outer surface of the cabin, if the glass fiber reinforced plastic control surface is limited in the launching tube by the launching tube wall before launching, the control surface will act on the high silica shaft sleeve 8 to apply a downward force, that is, the high silica shaft sleeve 8 will be compressed downward by the control surface along the axial direction of the rotating shaft 11, so that the high silica shaft sleeve 8 is compressed by the spring 10, and the whole foldable rudder is in a folded state.
When external constraint force is not existed, such as a missile is launched from a launching tube, the folded rudder is unfolded, the spring 10 pushes the silica bushing 8 upwards along the axis of the rotating shaft 11, namely, the compressed spring 10 drives the silica bushing 8 to move upwards along the axial direction of the rotating shaft 11, and the control surface is gradually unfolded under the thrust of the bushing, as shown in fig. 4 and 5. When 8 up end of silica axle sleeves and control surface contact, the folding rudder is opened completely and is locked, and the control surface only has the degree of freedom of revoluting 11 rotations at this moment. After the control surface is completely unfolded, the high silica shaft sleeve 8 covers the connecting shaft 7, the rotating shaft 11 and the titanium alloy framework 5 exposed in the air and is hidden in the cabin of the missile.
The present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof, and it will be understood by those skilled in the art that various changes and modifications may be made herein without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (5)
1. The heat-insulation folding rudder applied to hypersonic flight is characterized by comprising a control surface and a control shaft for unfolding the control surface, wherein the control shaft is protected in a cabin section by a heat protection layer of a missile cabin body (9), and comprises a bearing (1), a lower shell (2), an upper shell (3), a connecting shaft (7), a high silica shaft sleeve (8), a spring (10) and a rotating shaft (11);
the lower shell (2) and the upper shell (3) are fixedly connected to form a cylindrical sleeve, then the cylindrical sleeve is fixedly connected to the inner wall of the missile cabin body (9) through the upper end of the upper shell (3) and aligned to a control surface mounting hole on the missile cabin body (9), and meanwhile, a rotating shaft (11) sleeved with a spring (10) is integrally arranged in the cylindrical sleeve; the upper end of the rotating shaft (11) penetrates through the upper shell (3) and the control surface mounting hole in sequence, then is hinged with the bottom of the control surface through the connecting shaft (7), and the lower end of the rotating shaft penetrates through the lower shell (2) and then is connected with an external steering engine system; when the control surface is restrained by external force and is in a folded state, the outer part of the high silica shaft sleeve (8) is matched with the upper shell (3) through a shaft hole, the spring (10) is tightly pressed on the spring mounting seat of the lower shell (2), meanwhile, the inner part of the high silica shaft sleeve (8) is matched with the rotating shaft (11) through the shaft hole, and the high silica shaft sleeve (8) can do linear and rotary motion along the axis of the rotating shaft (11); when the control surface loses external force to restrict and is expanding, the high silica shaft sleeve (8) is driven by the spring (10) to do upward linear motion along the rotating shaft (11); after the control surface is completely unfolded, the high silica shaft sleeve (8) is pressed into the control surface mounting hole by the spring (10) and props against the lower end face of the control surface.
2. The insulated folded rudder for hypersonic flight according to claim 1, characterised in that it comprises a fiberglass reinforced plastic rudder (4), a titanium alloy skeleton (5) and alumina foam (6);
the glass fiber reinforced plastic rudder surface (4) is coated on the outer layer of the titanium alloy framework (5) as a thermal protection material of the folding rudder, and the alumina foam (6) is filled in the gap in the titanium alloy framework (5).
3. The heat-insulating folded rudder applied to hypersonic flight as claimed in claim 2, wherein the aluminum oxide foam and the titanium alloy framework are fixed by molding through silica fiber and phenolic resin.
4. An insulated rudder unit for hypersonic flight according to claim 2 characterised in that the thickness of the control surface (4) of glass fibre reinforced plastic is determined on the basis of the aerodynamic heat and the dimensions of the titanium alloy frame (5) are determined on the basis of the strength load.
5. An insulated rudder unit for hypersonic flight according to claim 1 characterised in that the upper shell (3) is attached to the inner wall of the hull (9) of the missile by means of screws.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110836914.1A CN113720217B (en) | 2021-07-23 | 2021-07-23 | Be applied to thermal-insulated folding rudder of hypersonic flight |
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| CN202110836914.1A CN113720217B (en) | 2021-07-23 | 2021-07-23 | Be applied to thermal-insulated folding rudder of hypersonic flight |
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| CN113720217A true CN113720217A (en) | 2021-11-30 |
| CN113720217B CN113720217B (en) | 2023-04-14 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114426094A (en) * | 2022-04-06 | 2022-05-03 | 北京凌空天行科技有限责任公司 | Foldable air rudder of hypersonic aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPS6312500U (en) * | 1986-07-11 | 1988-01-27 | ||
| JPH063096A (en) * | 1992-06-23 | 1994-01-11 | Mitsubishi Heavy Ind Ltd | Extensible steering wing of missile |
| CN104422350A (en) * | 2013-08-28 | 2015-03-18 | 上海精密计量测试研究所 | Foldable control surface and anti-defense missile using the same |
| CN204286240U (en) * | 2014-10-27 | 2015-04-22 | 北京航天长征飞行器研究所 | A kind of light composite material missile wing structure with near closed hollow ring |
| US20160187112A1 (en) * | 2014-12-31 | 2016-06-30 | Agency For Defense Development | Shell |
| CN106352746A (en) * | 2016-10-18 | 2017-01-25 | 湖北航天技术研究院总体设计所 | Folding fin automatic and synchronous unlocking driving device |
| CN111664756A (en) * | 2020-05-12 | 2020-09-15 | 上海机电工程研究所 | Structure suitable for air rudder and steering engine system connection |
| CN113022842A (en) * | 2021-03-26 | 2021-06-25 | 中国科学院宁波材料技术与工程研究所 | High-temperature-resistant high-bearing foldable air rudder |
-
2021
- 2021-07-23 CN CN202110836914.1A patent/CN113720217B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6312500U (en) * | 1986-07-11 | 1988-01-27 | ||
| JPH063096A (en) * | 1992-06-23 | 1994-01-11 | Mitsubishi Heavy Ind Ltd | Extensible steering wing of missile |
| CN104422350A (en) * | 2013-08-28 | 2015-03-18 | 上海精密计量测试研究所 | Foldable control surface and anti-defense missile using the same |
| CN204286240U (en) * | 2014-10-27 | 2015-04-22 | 北京航天长征飞行器研究所 | A kind of light composite material missile wing structure with near closed hollow ring |
| US20160187112A1 (en) * | 2014-12-31 | 2016-06-30 | Agency For Defense Development | Shell |
| CN106352746A (en) * | 2016-10-18 | 2017-01-25 | 湖北航天技术研究院总体设计所 | Folding fin automatic and synchronous unlocking driving device |
| CN111664756A (en) * | 2020-05-12 | 2020-09-15 | 上海机电工程研究所 | Structure suitable for air rudder and steering engine system connection |
| CN113022842A (en) * | 2021-03-26 | 2021-06-25 | 中国科学院宁波材料技术与工程研究所 | High-temperature-resistant high-bearing foldable air rudder |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114426094A (en) * | 2022-04-06 | 2022-05-03 | 北京凌空天行科技有限责任公司 | Foldable air rudder of hypersonic aircraft |
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| CN113720217B (en) | 2023-04-14 |
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