CN111731467A - Grid rudder and aircraft - Google Patents
Grid rudder and aircraft Download PDFInfo
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- CN111731467A CN111731467A CN202010623602.8A CN202010623602A CN111731467A CN 111731467 A CN111731467 A CN 111731467A CN 202010623602 A CN202010623602 A CN 202010623602A CN 111731467 A CN111731467 A CN 111731467A
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- 238000005192 partition Methods 0.000 claims abstract description 36
- 230000008646 thermal stress Effects 0.000 abstract description 11
- 238000009826 distribution Methods 0.000 abstract description 10
- 239000000463 material Substances 0.000 abstract description 9
- 230000000694 effects Effects 0.000 description 4
- 230000007704 transition Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a grid rudder and an aircraft, comprising: a plurality of partitions connected to each other, the plurality of partitions forming a grid structure; the partition board is provided with a windward side and a leeward side along two ends of an intersecting line of the partition board, at least one part of the windward side is provided with a notch, and the absolute value of the slope of a tangent line of the outer surface where the notch is located is continuously reduced along the direction of the windward side and the leeward side. The flow guide curved surface is formed at the windward end, so that the square arrangement at the windward end is avoided, and under a high supersonic speed environment, on one hand, the pressure difference resistance and the friction resistance are reduced, the power efficiency is improved, the total heat generated by the windward end is reduced, and the structural strength of the material of the grid structure is ensured; on the other hand, the situation of local high heat generated by the protruding parts such as edges and corners under the condition that air flow generates friction is improved, the aerodynamic heat of the grid structure is reduced, the heat environment distribution of the grid structure is improved, the temperature distribution uniformity is improved, the structure thermal stress is reduced, and the strength performance is optimized.
Description
Technical Field
The invention relates to the technical field of aircraft design, in particular to a grid rudder and an aircraft.
Background
The grid structure is mainly used for air-to-air, ground-to-ground missiles and carrier rocket escape towers and serves as an aerodynamic stabilizing surface (grid wing) or a control surface (grid rudder).
The design of current grid rudder mainly considers aerodynamic characteristic and structural strength, does not consider the influence of aerodynamic heating problem. The former grid rudder has short working time, the flying speed of the aircraft is lower, and the aerodynamic heat problem is not outstanding. With the application of the grid rudder to hypersonic aircrafts and recoverable rockets, the flight speed is remarkably increased, and the thermal environment problem of the grid rudder is increasingly prominent.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect that the grid rudder in the prior art has a severe thermal environment when flying at a high speed, thereby providing the grid rudder and an aircraft.
The invention provides a grid rudder, which is suitable for being arranged on an aircraft and comprises:
a plurality of partitions connected to each other, the plurality of partitions forming a grid structure;
the partition board is provided with a windward side and a leeward side along two ends of an intersecting line of the partition board, at least one part of the windward side is provided with a notch, and the absolute value of the slope of a tangent line of the outer surface where the notch is located is continuously reduced along the direction of the windward side and the leeward side.
The parts of the windward side corresponding to the notches are arranged in an equal radius mode.
The radius of the notch is equal to half of the thickness of the partition plate.
The notches are symmetrically arranged relative to the partition board along the windward side and the leeward side.
The notches are symmetrically arranged on the windward side and the leeward side.
The grid structure is arranged in a shape like a Chinese character 'jing'.
The thickness range of the clapboard is 2 mm-8 mm.
The invention also provides an aircraft comprising:
a main body;
the grid rudders are rotatably connected to the main body and are provided with a storage position parallel to the longitudinal axis of the main body and a working position perpendicular to the longitudinal axis.
The technical scheme of the invention has the following advantages:
1. the invention provides a grid rudder, which is suitable for being arranged on an aircraft and comprises: a plurality of partitions connected to each other, the plurality of partitions forming a grid structure; the partition board is provided with a windward side and a leeward side along two ends of an intersecting line of the partition board, at least one part of the windward side is provided with a notch, and the absolute value of the slope of a tangent line of the outer surface where the notch is located is continuously reduced along the direction of the windward side and the leeward side.
The grid structure that comprises a plurality of baffles sets up on the aircraft, under hypersonic environment, the edge of windward side department can take place violent friction with high-speed air current, can make the local temperature of edge rise fast on the one hand, the material metal of grid structure takes place to soften, structural strength descends and probably takes place to warp under the exogenic action, and on the other hand, the high temperature of edge can produce the difference in temperature with other positions departments around, leads to local thermal stress increase, exceeds the ultimate stress of material, makes structure fracture or takes place creep deformation.
The notches are formed on the windward side, and the absolute value of the tangent slope of the outer surface where the notches are located is continuously reduced, so that a flow guiding curved surface is formed on the outer surface at the position of the windward side in the arrangement mode; on the other hand, the situation of local high heat generated by the protruding parts such as edges and corners under the condition that air flow generates friction is improved, the aerodynamic heat of the grid structure is reduced, the heat environment distribution of the grid structure is improved, the temperature distribution uniformity is improved, the structure thermal stress is reduced, and the strength performance is optimized.
2. The invention provides a grid rudder, wherein the parts of the windward side corresponding to the notches are arranged in an equal radius mode.
The notch is a round chamfer with the same radius formed on the windward side, so that the notch is simple and easy to arrange and convenient to process and manufacture; on the other hand, the uniformity of the notch on the flow guide effect and the heat conduction effect is guaranteed by the arrangement, the unbalance of thermal stress is avoided, and the stability of the working strength is guaranteed.
3. The invention provides a grid rudder, wherein the radius of a gap is equal to half of the thickness of a partition plate.
The radius of the gap is equal to half of the thickness of the partition plate, and the windward side is a cylindrical half side surface, so that on one hand, a windward plane facing airflow or a transition edge end between the windward plane and the gap can be prevented from being generated on the windward side, the aerodynamic appearance of the windward side is effectively improved, the occurrence of local high heat flow and air turbulence caused by high-speed friction between the transition edge end and air is avoided, the wind resistance caused by the windward plane is reduced, the heat flow distribution of the windward side is effectively improved, the heat flow distribution of the lattice wall is more uniform, the excessive temperature difference of the windward side structure is avoided, the local thermal stress of the structure is improved, and the structure is cracked or deformed in a creep mode; on the other hand sets up like this and makes the round chamfer angle and the radius of check wall both sides all the same for pneumatic pressure and the high heat flow that windward side both sides received are the same, avoid appearing atress unbalance and violent difference in temperature, have improved the aerodynamic performance of check wall, have avoided windward side both sides thermal stress's unbalance, have guaranteed the stability of check wall material working strength.
4. The invention provides a grid rudder, wherein notches are symmetrically arranged on the windward side and the leeward side.
On one hand, due to the fact that the sectional area of the leeward side along the movement direction is gradually reduced, the pressure difference resistance between the windward side and the leeward side is reduced, the overall aerodynamic appearance of the partition plate is improved, and the vortex region influencing the movement stability of the grid rudder is prevented from being formed at the leeward side; on the other hand, the windward side and the leeward side are provided with symmetrical notches simultaneously, so that the partition board or the grid structure is more convenient to assemble, and the reduction of the yield caused by the arrangement of the windward side and the leeward side is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic perspective view of a grid structure provided in an embodiment of the present invention;
FIG. 2 is a side view of the lattice structure shown in FIG. 1;
FIG. 3 is a schematic view of the structure of the partition plates in the lattice structure shown in FIG. 1;
FIG. 4 is a schematic structural view of another embodiment of a spacer in the grid structure of FIG. 1;
description of reference numerals:
1-a separator; 2-windward side; 3-leeward side; 4-notch.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Referring to fig. 1 to 4, the present embodiment provides a grid rudder, which is suitable for being installed on an aircraft, and includes a plurality of partition boards 1 connected to each other, wherein the plurality of partition boards 1 form a grid structure, in the present embodiment, the grid structure is arranged in a grid shape like a "well", as an alternative embodiment, the grid structure can be adjusted in shape according to control requirements, for example, the grid structure is arranged in other shapes like a diamond grid, and in addition, a fixing frame is further enclosed outside the grid structure.
The partition board 1 is provided with a windward side 2 and a leeward side 3 along two ends of an intersecting line, the windward side 2 is arranged at the front end of the movement direction of the grid rudder in the working state, the leeward side 3 is arranged at the rear end of the movement direction of the grid rudder in the working state, at least one part of the windward side 2 is provided with a notch 4, and the absolute value of the slope of the tangent line of the outer surface where the notch 4 is located is continuously reduced along the direction from the windward side 2 to the leeward side 3.
The grid structure that comprises a plurality of baffles 1 sets up on the aircraft, under hypersonic environment, the edge of windward side 2 department can take place violent friction with high-speed air current, can make the local temperature of edge rise fast on the one hand, the material metal of grid structure takes place to soften, structural strength descends and probably takes place to warp under the exogenic action, and on the other hand, the high temperature of edge can produce the difference in temperature with other positions departments around, leads to local thermal stress increase, exceeds the ultimate stress of material, makes structure fracture or takes place creep deformation.
The gap 4 is formed on the windward side 2, and as the absolute value of the tangent slope of the outer surface of the gap 4 is continuously reduced, a flow guiding curved surface is formed on the outer surface of the windward side 2 in the arrangement mode, compared with the windward side 2 arranged in a square mode, the gap is arranged in a hypersonic environment, on one hand, the pressure difference resistance received by the windward side 2 is reduced through the curved surface design, the total heat generated by the windward side 2 is reduced, and the structural strength of the material of the grid structure is ensured; on the other hand, the situation of local high heat generated by the protruding parts such as edges and corners under the condition that air flow generates friction is improved, the aerodynamic heat of the grid structure is reduced, the heat environment distribution of the grid structure is improved, the temperature distribution uniformity is improved, the structure thermal stress is reduced, and the strength performance is optimized.
In the present embodiment, the notches 4 are symmetrically arranged with respect to the partition board 1 along the direction from the windward side 2 to the leeward side 3. As an alternative embodiment, the recess 4 can also be provided along one side of the windward side 2.
In this embodiment, the parts of the windward side 2 corresponding to the notches 4 are arranged in a rounded corner shape, and the rounded radii are equal. The notch 4 is a round chamfer with the same radius formed on the windward side 2, so that the structure is simple and easy to implement, the processing and the manufacturing are convenient, and the cost is reduced; on the other hand, set up like this and guaranteed breach 4 homogeneity on water conservancy diversion and heat conduction effect, avoided the unbalance of thermal stress, guaranteed working strength's stability. As an alternative embodiment, the part of the windward side 2 corresponding to the notch 4 may be provided in an elliptical shape.
In the present embodiment, the radius of the gap 4 is equal to half of the thickness of the partition board 1, and the windward side 2 is a cylindrical half side.
On one hand, the arrangement can avoid the occurrence of a wind shielding plane facing the air flow on the windward side 2 or a transition edge end between the wind shielding plane and the notch 4, effectively improves the aerodynamic appearance of the windward side 2, not only avoids the occurrence of local high heat flow and air turbulence caused by high-speed friction between the transition edge end and the air, but also reduces the wind resistance caused by the wind shielding plane, effectively improves the heat flow distribution of the windward side 2, ensures that the heat flow distribution of the lattice wall is more uniform, avoids the overlarge temperature difference of the structure of the windward side 2, improves the local thermal stress of the structure, and ensures that the structure is cracked or deformed in a creeping way; on the other hand sets up like this and makes the round chamfer angle and the radius of check wall both sides all the same for pneumatic pressure and the high heat flow that 2 both sides of windward side received are the same, avoid appearing atress unbalance and violent difference in temperature, have improved the aerodynamic performance of check wall, have avoided 2 both sides of windward side thermal stress's unbalance, have guaranteed the stability of check wall material working strength.
In the embodiment, the notches 4 are symmetrically arranged on the windward side 2 and the leeward side 3, so that on one hand, because the sectional area of the leeward side 3 is gradually reduced along the motion direction, the pressure difference resistance between the windward side 2 and the leeward side 3 is reduced, the overall aerodynamic appearance of the partition plate 1 is improved, and an eddy current area influencing the motion stability of the grid rudder is prevented from being formed at the leeward side 3; on the other hand, the windward side 2 and the leeward side 3 are provided with the symmetrical notches 4 simultaneously, so that the partition board 1 or the grid structure can be assembled conveniently, and the situation that the windward side 2 and the leeward side 3 are assembled inversely to reduce the yield is avoided.
As an alternative embodiment, the notch 4 may be provided only on the windward side 2, as shown in fig. 4.
In the experiment, the height is 40km, the Mach number is 5, the flight time is 20s, and the following table shows the variation trend of the thermal effect of the grid along with the variation of the thickness of the grid rudder is shown as table 1:
| grid rudder thickness/mm | Highest heat flow | Average heat flow kW/m2 | Maximum temperature/. |
| 2 | 1799 | 1259.3 | 568 |
| 4 | 1272 | 890.4 | 455.7 |
| 6 | 1039 | 727.3 | 394.3 |
| 8 | 899 | 629.3 | 356.9 |
| 10 | 804 | 562.8 | 327.1 |
| 12 | 735 | 514.5 | 305.8 |
Based on a 4mm thick grid rudder, the following table shows the variation trend of the average heat flow, the maximum heat flow and the maximum temperature of the grid rudder along with the variation of the size of the fillet at the notch 4:
| fillet size/mm | Mean heat flowkW/m2 | Maximum heat flow kW/m2 | Maximum temperature/. degree.C |
| 0 | 890.4 | 1272 | 455.7 |
| 0.2 | 880.3 | 1208.4 | 440.3 |
| 0.5 | 865.2 | 1081.2 | 407.5 |
| 1 | 800.3 | 928.56 | 363.7 |
| 1.5 | 720.3 | 801.36 | 326.3 |
| 2 | 600.6 | 640 | 275.4 |
From the trend tables 1 and 2, the average heat flow of the grid rudder gradually decreases with the increase of the thickness of the grid rudder and also decreases with the increase of the fillet size.
Meanwhile, due to the material limit and the mass limit of the aircraft, the thickness of the partition board 11 ranges from 2mm to 8mm, and in the embodiment, the thickness of the partition board 11 ranges from 8mm as a preferred embodiment.
There is also provided in this embodiment an aircraft, the particular form of aircraft including, but not limited to, missiles or rockets and the like, the aircraft including: the rocket body and a plurality of the grid rudders, the grid rudders are rotatably connected to the rocket body, and the grid rudders are provided with storage positions parallel to the longitudinal axis of the rocket body and working positions perpendicular to the longitudinal axis and suitable for attitude control of the aircraft.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (8)
1. A grid rudder adapted to be provided on an aircraft, comprising:
a plurality of partitions (1) connected to each other, the plurality of partitions (1) forming a grid structure;
the wind-resistant partition board is characterized in that a windward surface (2) and a leeward surface (3) are oppositely arranged on the partition board (1) along two ends of an intersecting line of the partition board (1), at least one part of the windward surface (2) is provided with a notch (4), and the absolute value of the tangent slope of the outer surface where the notch (4) is located is continuously reduced along the direction from the windward surface (2) to the leeward surface (3).
2. Grid rudder according to claim 1, characterised in that the parts of the windward side (2) corresponding to the notches (4) are arranged with equal radius.
3. Grid rudder according to claim 2, characterised in that the radius of the notch (4) is equal to half the thickness of the partition (1).
4. Grid rudder according to one of the claims 1-3, characterised in that the gaps (4) are arranged symmetrically with respect to the partition (1) in the direction of the windward side (2) towards the leeward side (3).
5. Grid rudder according to one of the claims 1-3, characterised in that the gaps (4) are arranged symmetrically on the windward side (2) and the leeward side (3).
6. The lattice rudder of claim 1, wherein the lattice structure is arranged in a "groined" configuration.
7. Grid rudder according to claim 1, characterised in that the partition (1) has a thickness in the range of 2-8 mm.
8. An aircraft, characterized in that it comprises:
a main body;
a plurality of grid rudders as claimed in any one of claims 1 to 7 rotatably connected to said body, said grid rudders having a stowed position parallel to the longitudinal axis of said body and an operative position perpendicular to said longitudinal axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010623602.8A CN111731467A (en) | 2020-06-30 | 2020-06-30 | Grid rudder and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010623602.8A CN111731467A (en) | 2020-06-30 | 2020-06-30 | Grid rudder and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN111731467A true CN111731467A (en) | 2020-10-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010623602.8A Pending CN111731467A (en) | 2020-06-30 | 2020-06-30 | Grid rudder and aircraft |
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| CN (1) | CN111731467A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112389634A (en) * | 2020-11-27 | 2021-02-23 | 北京宇航系统工程研究所 | Heat-proof front edge grid rudder under medium-high heat flow condition |
| CN112796889A (en) * | 2020-12-30 | 2021-05-14 | 中国航发沈阳发动机研究所 | Structure for preventing temperature rise of connecting piece stirring airflow |
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| EP0593987A1 (en) * | 1992-10-22 | 1994-04-27 | Daimler-Benz Aerospace Aktiengesellschaft | Variable square air intake duct |
| CN1187794A (en) * | 1995-05-11 | 1998-07-15 | 危姆派尔国家机械建筑设计局 | Rocket with lattice control surfaces and lattice control surface for rocket |
| US20060237595A1 (en) * | 2004-06-01 | 2006-10-26 | Deutsches Zentrum Fur Luft- Und Raumfahrt E.V. | Wing for an aircraft or spacecraft |
| US20070102568A1 (en) * | 2005-07-21 | 2007-05-10 | Raytheon Company | Ejectable aerodynamic stability and control |
| AU2007354665B2 (en) * | 2006-11-30 | 2013-06-13 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
| CN208897309U (en) * | 2018-09-12 | 2019-05-24 | 北京星际荣耀空间科技有限公司 | A kind of leading edge part sweepback type grid airvane and play flight device |
| CN110260726A (en) * | 2019-05-28 | 2019-09-20 | 上海宇航系统工程研究所 | A kind of grid rudder arrangement |
-
2020
- 2020-06-30 CN CN202010623602.8A patent/CN111731467A/en active Pending
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| EP0593987A1 (en) * | 1992-10-22 | 1994-04-27 | Daimler-Benz Aerospace Aktiengesellschaft | Variable square air intake duct |
| CN1187794A (en) * | 1995-05-11 | 1998-07-15 | 危姆派尔国家机械建筑设计局 | Rocket with lattice control surfaces and lattice control surface for rocket |
| US20060237595A1 (en) * | 2004-06-01 | 2006-10-26 | Deutsches Zentrum Fur Luft- Und Raumfahrt E.V. | Wing for an aircraft or spacecraft |
| US20070102568A1 (en) * | 2005-07-21 | 2007-05-10 | Raytheon Company | Ejectable aerodynamic stability and control |
| AU2007354665B2 (en) * | 2006-11-30 | 2013-06-13 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
| CN208897309U (en) * | 2018-09-12 | 2019-05-24 | 北京星际荣耀空间科技有限公司 | A kind of leading edge part sweepback type grid airvane and play flight device |
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| Title |
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| 张亮，王淑华，姜贵庆: "钝化前缘对栅格翼激波干扰与热流分布的影响", 《宇航学报》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112389634A (en) * | 2020-11-27 | 2021-02-23 | 北京宇航系统工程研究所 | Heat-proof front edge grid rudder under medium-high heat flow condition |
| CN112389634B (en) * | 2020-11-27 | 2022-12-27 | 北京宇航系统工程研究所 | Grid rudder with heat-proof front edge under condition of medium and high heat flows |
| CN112796889A (en) * | 2020-12-30 | 2021-05-14 | 中国航发沈阳发动机研究所 | Structure for preventing temperature rise of connecting piece stirring airflow |
| CN112796889B (en) * | 2020-12-30 | 2022-04-01 | 中国航发沈阳发动机研究所 | Structure for preventing temperature rise of connecting piece stirring airflow |
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Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Applicant after: Beijing Star glory Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Applicant before: BEIJING I-SPACE TECHNOLOGY Co.,Ltd. Applicant before: Beijing Star glory Technology Co.,Ltd. |
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Application publication date: 20201002 |