CN114234734A - Pneumatic layout of microminiature missile - Google Patents
Pneumatic layout of microminiature missile Download PDFInfo
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- CN114234734A CN114234734A CN202111597503.8A CN202111597503A CN114234734A CN 114234734 A CN114234734 A CN 114234734A CN 202111597503 A CN202111597503 A CN 202111597503A CN 114234734 A CN114234734 A CN 114234734A
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- tail
- head
- missile
- ratio
- duck rudder
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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
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- 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
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
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- 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
- F42B10/02—Stabilising arrangements
- F42B10/26—Stabilising arrangements using spin
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The invention discloses a micro missile aerodynamic layout, which comprises an oval head, a duck rudder and a rotary tail wing assembly, wherein the duck rudder is arranged on the oval head; the oval head is arranged on the head of the bullet; the duck rudder is arranged on the projectile body and is close to the oval head; the rotating tail wing assembly is rotatably arranged at the tail end of the projectile body; the missile adopts the pneumatic layout of the microminiature missile disclosed by the invention, so that higher maneuvering performance can be provided, and the maximum normal overload is 3-5 g; the invention can avoid the arrangement of steering engines around the engine spray pipe, get rid of the dependence on a large-torque steering engine and solve the problem of severe size constraint in the design of the microminiature missile; by adopting the design scheme of the rotating tail wing, the tail wing can rotate around the elastic shaft, so that the problem of control adverse effect caused by the washing flow of the duck rudder is solved; the adoption of both the oval head and the ship-shaped tail can greatly reduce the flying resistance of the missile and increase the lift-drag ratio.
Description
Technical Field
The invention relates to the technical field of missiles, in particular to a pneumatic layout of a microminiature missile.
Background
The existing micro missile pneumatic layout design faces severe size constraint, and because the missile diameter is small, no steering engine installation space exists near an engine tail nozzle, so that the normal layout cannot be applied to the micro missile, and only two options of full-motion missile wing layout and canard layout are left.
When the requirement on the maneuvering performance of the missile is higher, the fatality of the layout of the full-motion missile wing has the following defects: the full-motion missile wing is positioned near the mass center, so that the control efficiency is low, and the requirement of high maneuverability cannot be met; the hinge moment of the full-moving wing is large, the output torque of the steering engine is required to be large, and the large-torque steering engine cannot meet the strict diameter constraint of the microminiature missile.
The duck-type layout has the advantages of high control efficiency and small hinge moment, and can meet the requirements of the microminiature missile on maneuverability and space size constraint. However, the aerodynamic profile design still faces difficulties: firstly, the problem of rolling control adverse effect can be caused when the control surface is positioned in front of the main lifting surface; secondly, the severe axial dimension constraint of the microminiature missile causes the duck rudder current washing to generate nonlinear interference on the empennage, and how to achieve the balance between maneuverability and stability on the premise of higher operation efficiency.
Therefore, it is necessary to develop a micro missile aerodynamic configuration to solve the above problems.
Disclosure of Invention
The invention aims to solve the problems and designs a pneumatic layout of a microminiature missile.
The invention realizes the purpose through the following technical scheme:
a micro-missile aerodynamic configuration comprising:
an oval head; the oval head is arranged on the head of the bullet;
a duck rudder; the duck rudder is arranged on the projectile body and is close to the oval head;
a rotating tail assembly; the rotating tail assembly is rotatably arranged at the tail end of the projectile body.
Specifically, the oval head includes spherical head and transition circular arc portion, and the one end of spherical head is connected with the first end of transition circular arc portion, and the second end and the projectile head of transition circular arc portion are connected.
Preferably, the duck rudder comprises four full-motion rudders.
The rotary tail wing assembly comprises a ship-shaped tail part, a bearing I, four rectangular tail wings, a bearing II and a tail cover, wherein the four rectangular tail wings are arranged on an annular mounting shell, the bearing I and the bearing II are sleeved on the ship-shaped tail part, and the annular mounting shell is arranged outside the bearing I and the bearing II; the tail cover is arranged at the tail end of the ship-shaped tail part.
Preferably, in the oval head: the curvature radius of the spherical head is SR/D0.3-0.5; the radius of curvature of the arc section is R1/D2-5; the ratio of the length of the oval head to the full shot length is 0.12-0.15 for L3/L1.
Preferably, in the duck rudder: the ratio of the distance from the rear edge of the duck rudder to the vertex of the head to the full-elastic length is 0.25-0.3 when L2/L1 is equal to zero; the ratio of the extension length to the diameter of the duck rudder is LD/D (0.5-2); the aspect ratio of the duck rudder is 1-3; the ratio of the root chord length to the tip chord length of the duck rudder is b2/b1 which is 4-8; the ratio of the thickness of the duck rudder to the elastic diameter is c2/D which is 0.02-0.05.
Preferably, in the rotary tail assembly: the length-diameter ratio of the tail part of the ship is B2/D which is 0.8-1.2; the contraction ratio of the tail of the ship is D1/D is 0.8-0.9; the distance from the rear edge of the rectangular tail wing to the top point of the head is L1; the ratio of the span length of the rectangular tail wing to the bullet diameter is LD/D1-3; the aspect ratio of the rectangular empennage is 1-3; the ratio of the chord length of the rectangular tail wing root to the chord length of the rectangular tail wing tip is b2/b1 which is 1-1.5; the ratio of the thickness of the rectangular tail wing to the spring diameter is c2/D which is 0.02-0.05.
The invention has the beneficial effects that:
1. the pneumatic layout of the microminiature missile disclosed by the invention can provide higher maneuvering performance, and the maximum normal overload is 3-5 g.
2. The pneumatic layout of the microminiature missile disclosed by the invention avoids the arrangement of steering engines around an engine spray pipe, gets rid of the dependence on a high-torque steering engine, and solves the problem of severe size constraint in the design of the microminiature missile.
3. The pneumatic layout of the microminiature guided missile disclosed by the invention breaks through the design thinking inertia of a conventional duck rudder with a slightly smaller root and a larger aspect ratio, and innovatively provides the duck rudder with a large root tip ratio and a small aspect ratio, so that the guided missile reaches the balance between maneuverability and stability under high operation efficiency, and the operation stability ratio is 0.8-1.2.
4. The invention discloses a micro-miniature missile pneumatic layout, which adopts a design scheme of a rotary tail wing, wherein the tail wing can rotate around a missile shaft, and the problem of control adverse effect caused by current washing of a duck rudder is solved.
5. The invention discloses a micro-missile aerodynamic layout, which adopts an oval head part and a ship tail part to reduce the missile flight resistance to a greater extent and increase the lift-drag ratio.
6. The pneumatic layout of the microminiature missile disclosed by the invention designs the characteristic sizes of the duck rudder and the empennage in a matching manner, provides a robust pneumatic appearance for the microminiature missile, and has a strong military application prospect.
Drawings
FIG. 1 is a perspective view of the aerodynamic layout of a microminiature missile of the present invention;
FIG. 2 is a front view of the pneumatic layout of the microminiature missile of the present invention;
FIG. 3 is a schematic view of a rotary tail assembly of the present invention.
In the figure: 1. an oval head; 2. a duck rudder; 3. a rotating tail assembly; 4. a boat-shaped tail; 5. a bearing I; 6. a tail wing; 7. a bearing II; 8. and a tail cover.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the 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.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "inside", "outside", "left", "right", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the present invention are conventionally placed in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is also to be noted that, unless otherwise explicitly stated or limited, the terms "disposed" and "connected" are to be interpreted broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The following detailed description of embodiments of the invention refers to the accompanying drawings.
As shown in fig. 1-3, a micro missile aerodynamic configuration comprises:
an oval head 1; the oval head 1 is mounted on the head of the bullet;
a duck rudder 2; the duck rudder 2 is arranged on the projectile body and close to the oval head 1;
a rotating tail assembly 3; the rotating tail assembly 3 is rotatably mounted at the tail end of the projectile body.
The oval head 1 comprises a spherical head and a transition circular arc part, one end of the spherical head is connected with the first end of the transition circular arc part, and the second end of the transition circular arc part is connected with the projectile body head. The spherical head and the transition arc part are in smooth transition, so that the flight resistance can be reduced to the maximum extent.
The duck rudder 2 comprises four full-motion rudders. The four full-motion rudders are all airfoil surfaces with large root-tip ratio and small aspect ratio; the duck rudder is far away from the mass center, the control efficiency is high, enough normal overload can be provided, and the duck rudder has high maneuvering performance. The included angle between any two adjacent full-motion rudders is 90 degrees.
The rotary tail assembly 3 comprises a ship-shaped tail part 4, a bearing I5, four rectangular tail wings 6, a bearing II 7 and a tail cover 8, wherein the four rectangular tail wings 6 are arranged on an annular mounting shell, the bearing I5 and the bearing II 7 are sleeved on the ship-shaped tail part 4, and the annular mounting shell is arranged outside the bearing I5 and the bearing II 7; a tail cap 8 is mounted to the tail end of the boat form tail 4. The four rectangular tail wings are all in medium aspect ratio and small sweepback angle; the ship-shaped tail can obviously reduce the resistance of the projectile body and increase the lift-drag ratio. Bearing I5, bearing II 7 are used for rotatable support fin to this control that has solved duck rudder and has washed the flow and arouse is anti-effectual. Due to the matching design of the duck rudder and the rotary tail wing assembly, the pneumatic appearance reaches the balance between maneuverability and stability at high maneuvering efficiency. The included angle between any two adjacent rectangular tail wings 6 is 90 degrees.
Oval head 1: the curvature radius of the spherical head is SR/D0.3-0.5; the radius of curvature of the arc section is R1/D2-5; the ratio of the length of the oval head to the full shot length is 0.12-0.15 for L3/L1.
In the duck rudder 2: the ratio of the distance from the rear edge of the duck rudder 2 to the vertex of the head to the full-elastic length is 0.25-0.3 when L2/L1 is equal to the maximum length of the duck rudder; the ratio of the extension length to the diameter of the duck rudder 2 is LD/D (0.5-2); the aspect ratio of the duck rudder 2 is 1-3; the ratio of the chord length of the duck rudder 2 to the chord length of the tip is b2/b1 which is 4-8; the ratio of the thickness of the duck rudder 2 to the diameter of the spring is c2/D which is 0.02-0.05. The included angle between the longitudinal symmetrical surface of the duck rudder 2 and the elastic shaft is 0 degree.
Rotating tail assembly 3: the length-diameter ratio of the ship-shaped tail part 4 is B2/D which is 0.8-1.2; the contraction ratio of the ship-shaped tail 4 is D1/D is 0.8-0.9; the distance from the rear edge of the rectangular tail wing 6 to the top point of the head is L1; the ratio of the extension length of the rectangular tail wing 6 to the diameter of the bullet is LD/D1-3; the aspect ratio of the rectangular tail wing 6 is 1-3; the ratio of the chord lengths of the 6 rectangular tail wings to the chord length of the tip is b2/b1 which is 1-1.5; the ratio of the thickness of the rectangular tail fin 6 to the spring diameter is c2/D which is 0.02-0.05. The included angle between the longitudinal symmetrical surface of the rectangular tail wing 6 and the spring shaft is 0 degree.
Claims (7)
1. A microminiature missile aerodynamic configuration, comprising:
an oval head (1); the oval head (1) is arranged on the head of the bullet;
a duck rudder (2); the duck rudder (2) is arranged on the projectile body and close to the oval head (1);
a rotating tail assembly (3); the rotating tail assembly (3) is rotatably arranged at the tail end of the projectile body.
2. A micro-missile aerodynamic configuration as claimed in claim 1, characterised in that the ovoid head (1) comprises a spherical head and a transitional circular arc, one end of the spherical head being connected to a first end of the transitional circular arc and a second end of the transitional circular arc being connected to the projectile head.
3. A micro-missile aerodynamic configuration as claimed in claim 1, characterised in that the duck rudder (2) comprises four full-motion rudders.
4. The pneumatic layout of a microminiature missile as claimed in claim 1, wherein the rotating tail assembly (3) comprises a ship-shaped tail part (4), a bearing I (5), four rectangular tail wings (6), a bearing II (7) and a tail cover (8), wherein the four rectangular tail wings (6) are arranged on an annular mounting shell, the bearing I (5) and the bearing II (7) are sleeved on the ship-shaped tail part (4), and the annular mounting shell is arranged outside the bearing I (5) and the bearing II (7); the tail cover (8) is arranged at the tail end of the ship-shaped tail part (4).
5. A microminiature missile aerodynamic configuration as claimed in claim 2, characterized in that in the ovoid head (1): the curvature radius of the spherical head is SR/D0.3-0.5; the radius of curvature of the arc section is R1/D2-5; the ratio of the length of the oval head to the full shot length is 0.12-0.15 for L3/L1.
6. A microminiature missile aerodynamic configuration as claimed in claim 3, characterized in that in the duck rudder (2): the ratio of the distance from the rear edge of the duck rudder (2) to the vertex of the head to the full-elastic length is 0.25-0.3 (L2/L1); the ratio of the extension length to the diameter of the duck rudder (2) is LD/D (0.5-2); the aspect ratio of the duck rudder (2) is 1-3; the ratio of the root chord length to the tip chord length of the duck rudder (2) is b2/b1 which is 4-8; the ratio of the thickness to the diameter of the duck rudder (2) is c2/D which is 0.02-0.05.
7. A microminiature missile aerodynamic configuration as claimed in claim 4, characterized in that in the rotating tail assembly (3): the length-diameter ratio of the ship-shaped tail (4) is B2/D which is 0.8-1.2; the contraction ratio of the ship-shaped tail (4) is D1/D which is 0.8-0.9; the distance from the rear edge of the rectangular tail wing (6) to the top point of the head is L1; the ratio of the extension length of the rectangular tail wing (6) to the diameter of the bullet is LD/D1-3; the aspect ratio of the rectangular tail wing (6) is 1-3; the ratio of the root chord length to the tip chord length of the rectangular tail wing (6) is b2/b1 which is 1-1.5; the ratio of the thickness of the rectangular tail wing (6) to the diameter of the bullet is c2/D which is 0.02-0.05.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111597503.8A CN114234734A (en) | 2021-12-24 | 2021-12-24 | Pneumatic layout of microminiature missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111597503.8A CN114234734A (en) | 2021-12-24 | 2021-12-24 | Pneumatic layout of microminiature missile |
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| CN114234734A true CN114234734A (en) | 2022-03-25 |
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| CN202111597503.8A Pending CN114234734A (en) | 2021-12-24 | 2021-12-24 | Pneumatic layout of microminiature missile |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6202958B1 (en) * | 1998-06-19 | 2001-03-20 | Diehl Stiftung & Co. | Mounting arrangement for the pivotally openable rudder blades of a guided missile |
| US20040011920A1 (en) * | 2000-07-03 | 2004-01-22 | Stig Johnsson | Fin-stabilized guidable missile |
| US20040232278A1 (en) * | 2003-05-23 | 2004-11-25 | Geswender Chris Eugene | Missile with odd symmetry tail fins |
| CN102155885A (en) * | 2010-12-31 | 2011-08-17 | 北京威标至远科技发展有限公司 | Cruise target projectile |
| CN112923805A (en) * | 2021-01-20 | 2021-06-08 | 西北工业大学 | Pneumatic layout of small high-mobility missile |
| CN214701950U (en) * | 2021-04-13 | 2021-11-12 | 北京威标至远科技发展有限公司 | Air-ground type target bomb |
-
2021
- 2021-12-24 CN CN202111597503.8A patent/CN114234734A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6202958B1 (en) * | 1998-06-19 | 2001-03-20 | Diehl Stiftung & Co. | Mounting arrangement for the pivotally openable rudder blades of a guided missile |
| US20040011920A1 (en) * | 2000-07-03 | 2004-01-22 | Stig Johnsson | Fin-stabilized guidable missile |
| US20040232278A1 (en) * | 2003-05-23 | 2004-11-25 | Geswender Chris Eugene | Missile with odd symmetry tail fins |
| CN102155885A (en) * | 2010-12-31 | 2011-08-17 | 北京威标至远科技发展有限公司 | Cruise target projectile |
| CN112923805A (en) * | 2021-01-20 | 2021-06-08 | 西北工业大学 | Pneumatic layout of small high-mobility missile |
| CN214701950U (en) * | 2021-04-13 | 2021-11-12 | 北京威标至远科技发展有限公司 | Air-ground type target bomb |
Non-Patent Citations (3)
| Title |
|---|
| 岳彩芬;: "美国"麻雀"空对空导弹的发展概况及结构、性能与使用特点", 航空兵器, no. 1 * |
| 郭振华,董长虹: "导弹***总体方案设计的研究", 北京航空航天大学学报, no. 06 * |
| 郭振华: "用RAMS法研究空空导弹***的方案设计", ***工程理论与实践, no. 11, pages 1 - 3 * |
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