CN104615813A - Design method applied to guided missile with grid fins and used for reducing pressure center variation - Google Patents
Design method applied to guided missile with grid fins and used for reducing pressure center variation Download PDFInfo
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- CN104615813A CN104615813A CN201510037302.0A CN201510037302A CN104615813A CN 104615813 A CN104615813 A CN 104615813A CN 201510037302 A CN201510037302 A CN 201510037302A CN 104615813 A CN104615813 A CN 104615813A
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Abstract
The invention discloses a design method applied to a guided missile with grid fins and used for reducing the pressure center variation. The design method comprises the following steps that step1, the general parameters, general indexes and design constraints of the guided missile are determined; step2, the shape of the grid fin surfaces of the guided missile is determined; step3, strake wings are additionally arranged at the positions, on the front sides of the grid fins, of the body of the guided missile, and the geometric parameters of the strake wings are determined; step4, on the premise that the geometric parameters of the strake wings are invariable, the distance d between the strake wings and the folded grid fin surfaces is determined. According to the design method, the strake wings are additionally arranged on the front sides of the grid fins, and meanwhile design is performed according to the geometric parameters of the strake wings, the positions of the strake wings on the body of the guided missile and the maximum expansion length of the strake wings, so that the pressure center variation is well reduced in the actual use of the guided missile with the grid fins, and the problem that from the folded state to the unfolded state of the grid fin surfaces of the guided missile with the grid fins, the pressure center variation of the whole guided missile is too large, and consequently controllability and stability are difficult to coordinate is solved.
Description
Technical field
The present invention relates to a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity.
Background technology
Grid rudder rudder face in guided missile is embedded in by numerous thin cell walls the many lift surface system formed in frame, it has better lift performance in given space, and it is convenient folding, also there is the little advantage of hinge moment simultaneously, carried out large quantity research in grid rudder application aspect therefore both at home and abroad.In the prior art, as shown in Figure 1, 2, 3, Fig. 1 is that in prior art, on band raster rudder guided missile, grid rudder rudder face is the schematic diagram of folded state, Fig. 2 is the position relationship schematic diagram that the external envelope geometry of grid rudder and missile airframe when grid rudder rudder face is folded state on band raster rudder guided missile in prior art limits, and Fig. 3 is that in prior art, on band raster rudder guided missile, grid rudder rudder face is the schematic diagram of deployed condition; Wherein, grid rudder rudder face is 10 ', and body is 20 ', and external envelope geometry is restricted to 30 '.
For interior bullet design of burying in absolutely empty bullet or shrapnel, application grid rudder needs to solve a great problem: namely grid rudder rudder face due to chord length less, after folding, outstanding body height is not high, the lift that grid rudder rudder face provides so is in a folded configuration contributed less, grid rudder rudder face by folded state to deployed condition, can bring entirely suppress the heart comparatively large after move, after the pressure heart of guided missile, the amount of moving may reach more than 20% of full bullet body length when guided missile supersonic flight, meet so simultaneously and be separated initial and the requirement of end mobile control and stability, can become more difficult.In prior art, general solution has two kinds: one to be pass through ballistic design, the separation of guided missile and end mobile are carried out under different Mach number and height, although this method can avoid the excessive problem brought of pressure heart change, but significantly limit the ballistic design of guided missile, have impact on the fight capability of guided missile; Two is adopt other auxiliary control measure such as appearance control, and this method greatly can increase Missile Preliminary quality, control the complicacy of difficulty and structural design.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity; Namely before grid rudder, strake wing is increased, simultaneously by the geometric parameter of strake wing, the strake wing position on missile airframe and the maximum length design of strake wing, band raster rudder guided missile is made to obtain the effect of good reduction pressure heart variable quantity in actual use, to solve in band raster rudder guided missile grid rudder rudder face by folded state to deployed condition, guided missile suppresses the problem that the excessive and control and stability that is that bring of heart change is difficult to coordinate entirely.
For solving the problems of the technologies described above, the present invention adopts following technical proposals:
For reducing a method for designing for the band raster rudder guided missile of pressing heart variable quantity, comprise the steps:
Step 1, determines the population parameter of guided missile, overall objective and design constraint;
Step 2, determines the grid rudder rudder face profile in guided missile;
Step 3, the missile airframe on front side of grid rudder increases strake wing, and determines the geometric parameter of strake wing;
Step 4, under the prerequisite that the geometric parameter of strake wing is constant, determines the distance d between strake wing and the grid rudder rudder face in folded state.
Further, described method also comprises:
Step 5, after increasing strake wing, determines the aerodynamic characteristics numerical of guided missile profile, for determining whether the aerodynamic characteristics numerical of the guided missile profile after increasing strake wing meets the overall objective of guided missile simultaneously.
Step 6, adjustment strake wing profile and grid rudder rudder face profile, until meet the overall objective of determined guided missile in step 1, also meet when grid rudder rudder face is folded state, the pressure heart of missile airframe the most simultaneously.
Further, the population parameter of guided missile comprises Shell body quality, body barycenter, design Mach number and design spatial domain.
Further, the overall objective of guided missile comprises when the permissible load factor of grid rudder rudder face on guided missile under being deployed condition, pressure heart designing requirement and control and stability requirement, and when the steady state stability requirement of grid rudder rudder face on guided missile under being folded state.
Further, when the design constraint of guided missile comprises not band raster rudder missile airframe geometrical constraint and when the body external envelope geometry restriction of grid rudder rudder face on guided missile under in folded state.
Further, the geometric parameter of grid rudder rudder face profile comprises the grid number of grid in the lifting area of grid rudder rudder face, the chord length of grid rudder rudder face, the spacing of grid rudder rudder face, grid rudder rudder face, and the rudder wall section shape of grid rudder rudder face.
Further, the grid rudder rudder face profile in guided missile is determined in described step 2, be specially: according to population parameter and the design constraint of guided missile determined in step 1, determine to meet the grid rudder rudder face profile of the overall objective of grid rudder rudder face under being deployed condition on guided missile.
Further, the chord length of the geometric parameter edge cover strip wing of strake wing, the length of strake wing and strake wing section shape, wherein the length of strake wing adopts when the maximum length in the body external envelope geometry restriction of grid rudder rudder face on guided missile under in folded state.
Further, in described step 4 under the constant prerequisite of the geometric parameter of strake wing, determine the distance d between strake wing and the grid rudder rudder face in folded state, be specially: change the distance d between strake wing and grid rudder rudder face, determine on missile airframe without design strake wing and on missile airframe, be designed with strake wing two kinds of situations under the pressure heart of missile airframe, draw difference between the two, thus the amount of moving after drawing the pressure heart increasing missile airframe after strake wing further; The amount of moving after the pressure heart relatively corresponding to different distance, when after the pressure heart, the amount of moving is maximum, corresponding strake wing is optimum distance d with the spacing of the grid rudder rudder face in folded state, and now strake wing position the most rearward, and strake wing is little on the impact of grid rudder rudder face aerodynamic interference.
Further, the method adjusting strake wing profile and grid rudder rudder face profile in described step 6 comprises:
If when grid rudder rudder face is deployed condition, the pressure heart position of missile airframe is unreasonable, then changed the lift contribution of grid rudder rudder face by the geometric parameter adjustment of grid rudder rudder face profile;
If when grid rudder rudder face is folded state, the pressure heart position of missile airframe is unreasonable, then adjust the chord length b of strake wing, but the distance between strake wing and the grid rudder rudder face in folded state still adopts the distance d obtained in step 4, and the length of strake wing still adopts the length of determined strake wing in step 3.
The present invention compared with prior art, has following actively useful effect:
1, the method for designing of band raster rudder guided missile provided by the present invention, the configuration design parameter avoiding band raster rudder guided missile is too much, the complicated unworkable problem of design process, by increasing the method for designing of strake wing before grid rudder, realization rapidly and efficiently can reduce the object of pressing heart variable quantity.
2, the band raster rudder guided missile by going out designed by the present invention, affects less on Missile Preliminary and control performance; Be specially to ensure grid rudder rudder face deployed condition pressure heart position, grid rudder rudder face lifting area needs to reduce, grid rudder steerage decreases, but because strake wing is less for moving contribution after the large attack angle pressure heart, the change of grid rudder rudder face lifting area is less, under large attack angle, control and stability does not have and significantly reduces, and can not affect larger on overall and control performance.
3, the strake wing physical dimension increased in the present invention is little, increase little to guided missile quality, be specially: owing to have employed the strake wing of maximum length, optimum position, the pressure heart contribution ability utilizing strake wing to reach to greatest extent, strake wing area is less simultaneously, and the full quality that plays can not significantly increase.
4, the present invention can not increase Missile Preliminary and control design case complicacy, and based on the present invention, grid rudder rudder face can be reduced and entirely suppress heart variation range by folded state to deployed condition, especially successful under Low Angle Of Attack, the decrease of pressure heart variation range can reach more than 10% of full bullet body length.
5, reach body pressure heart variable quantity by the configuration design of guided missile itself to regulate, reduce the difficulty of control and stability design, do not need by other auxiliary control measure, also do not need to limit ballistic design, obviously can not increase Missile Preliminary and control design case complicacy.
Accompanying drawing explanation
Fig. 1 is that in prior art, on band raster rudder guided missile, grid rudder rudder face is the schematic diagram of folded state.
Fig. 2 is the position relationship side view that the external envelope geometry of grid rudder and missile airframe when grid rudder rudder face is folded state on band raster rudder guided missile in prior art limits.
Fig. 3 is that in prior art, on band raster rudder guided missile, grid rudder rudder face is the schematic diagram of deployed condition.
Fig. 4 is method flow schematic diagram of the present invention.
Fig. 5 is position when grid rudder rudder face is folded state on band raster rudder guided missile in the present invention between grid rudder rudder face and strake wing and structural representation.
Fig. 6 is the position relationship schematic diagram that the external envelope of grid rudder rudder face, strake wing and missile airframe when grid rudder rudder face is folded state on band raster rudder guided missile in the present invention limits.
Fig. 7 is the position relationship side view that the external envelope of grid rudder rudder face, strake wing and missile airframe when grid rudder rudder face is folded state on band raster rudder guided missile in the present invention limits.
Fig. 8 is the band raster rudder guided missile without strake wing, and its grid rudder rudder face entirely suppresses the comparative graph of the heart when in folded state with when in deployed condition.
Fig. 9 is the grid rudder guided missile with strake wing, and its grid rudder rudder face entirely suppresses the comparative graph of the heart when in folded state with when in deployed condition.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described.
As shown in Fig. 4 to Fig. 9, a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity, guided missile adopts the control of grid rudder tail, and in the guided missile initial flight stage, grid rudder rudder face keeps folded state, and after initial flight section terminates, grid rudder rudder face launches.
The method for designing concrete steps of described guided missile are as follows:
Step 1, determines the population parameter of guided missile, overall objective and design constraint;
The population parameter of guided missile comprises body 1 quality, body 1 barycenter, design Mach number and design spatial domain; The overall objective of guided missile comprises when the permissible load factor of grid rudder rudder face 2 on guided missile under being deployed condition, pressure heart designing requirement and control and stability requirement, and when the steady state stability requirement of grid rudder rudder face 2 on guided missile under being folded state; When the design constraint of guided missile comprises not band raster rudder missile airframe 1 geometrical constraint and when the body 1 external envelope geometry restriction 3 of grid rudder rudder face 2 on guided missile under in folded state; As shown in Figure 6,7, when grid rudder rudder face 2 is in folded state missile airframe 1 external envelope space constraint 3 for maximum gauge be the circle of D.
Step 2, determines grid rudder rudder face 2 profile in guided missile, is specially: according to population parameter and the design constraint of guided missile determined in step 1, determines to meet the grid rudder rudder face profile of the overall objective of grid rudder rudder face 2 under being deployed condition on guided missile.The geometric parameter of grid rudder rudder face profile comprises the grid number of grid in the lifting area of grid rudder rudder face, the chord length of grid rudder rudder face 2, the spacing of grid rudder rudder face, grid rudder rudder face, and the rudder wall section shape of grid rudder rudder face.
Step 3, the missile airframe on front side of grid rudder increases strake wing 4, and determines the geometric parameter of strake wing 4; The chord length of the geometric parameter edge cover strip wing of strake wing 4, the length of strake wing and strake wing section shape, wherein the length of strake wing adopts when the maximum length in the body external envelope geometry restriction 3 of grid rudder rudder face 2 on guided missile under in folded state; Namely maximum length L and the grid rudder of strake wing 4 are that to limit diameter D identical for body external envelope geometry under folded state, i.e. L=D.
Step 4, under the prerequisite that the geometric parameter of strake wing 4 is constant, determine the distance d between strake wing 4 and the grid rudder rudder face 2 in folded state, be specially: change the distance d between strake wing 4 and grid rudder rudder face 2, determine on missile airframe without design strake wing and on missile airframe, be designed with strake wing two kinds of situations under the pressure heart of missile airframe, draw difference between the two, thus the amount of moving after drawing the pressure heart increasing missile airframe after strake wing further; The amount of moving after the pressure heart relatively corresponding to different distance, when after the pressure heart, the amount of moving is maximum, corresponding strake wing 4 is optimum distance d with the spacing of the grid rudder rudder face 2 in folded state, and now strake wing 4 position the most rearward, and strake wing 4 is little on the impact of grid rudder rudder face 2 aerodynamic interference.
Step 5, increases after strake wing 4, determines the aerodynamic characteristics numerical of guided missile profile, for determine the aerodynamic characteristics numerical of the guided missile profile after increasing strake wing 4 whether to meet in step 1 simultaneously determine the overall objective of guided missile.Be specially: permissible load factor, the pressure heart characteristic of guided missile, the control and stability of guided missile of guided missile when obtaining under grid rudder rudder face 2 is in deployed condition, and the steady state stability characteristic of guided missile time under grid rudder rudder face 2 is in folded state.
Step 6, adjustment strake wing profile and grid rudder rudder face profile, until meet the overall objective of determined guided missile in step 1, also meet when grid rudder rudder face 2 is in folded state, the pressure heart of missile airframe 1 is the most simultaneously; Method of adjustment is specifically:
If when grid rudder rudder face 2 is in deployed condition, the pressure heart position of missile airframe 1 is unreasonable, then changed the lift contribution of grid rudder rudder face 2 by the geometric parameter adjustment of grid rudder rudder face profile;
If when grid rudder rudder face 2 is in folded state, the pressure heart position of missile airframe 1 is unreasonable, then adjust the chord length b of strake wing 4, but the distance between strake wing 4 and the grid rudder rudder face 2 in folded state still adopts the distance d obtained in step 4, and the length of strake wing 4 still adopts the length L of determined strake wing 4 in step 3.
The step 5 that iterates is to step 6, until establishment meets the band edge strip flyer lead bullet profile scheme of Missile Preliminary index.
The present invention, by increasing strake wing before grid rudder, can obtain the guided missile profile scheme of the band strake wing meeting Missile Preliminary index.Fig. 7 is the band raster rudder guided missile without strake wing, and its grid rudder rudder face entirely suppresses the comparative graph of the heart when in folded state with when in deployed condition; Fig. 8 is the grid rudder guided missile with strake wing, and its grid rudder rudder face entirely suppresses the comparative graph of the heart when in folded state with when in deployed condition.Wherein horizontal ordinate α is the angle of attack, and ordinate is for entirely to suppress heart XCP, and XCPzk represents grid rudder and entirely suppress heart result of calculation when in folded state, and XCPzd represents grid rudder and entirely suppress heart result of calculation when in folded state.Can find out, no matter be not with strake wing scheme or band strake wing scheme, grid rudder rudder face launch after entirely suppress the heart all can obviously after move, maximum the reaching of scheme amount of moving after Low Angle Of Attack presses down the heart without strake wing plays 20% of body length entirely, but adopt after there is the scheme of strake wing, the decrease that Low Angle Of Attack presses down heart variation range can reach more than 10% of full bullet body length, and pressure heart variable quantity reduces greatly, Be very effective.
The present invention have employed the strake wing position of optimum position on maximum length in the restriction of body external envelope geometry and bullet when strake wing configuration design, make use of the pressure heart contribution ability that strake wing may reach to greatest extent, the strake wing area increased is less, and making entirely to play quality increases little; Because strake wing is less for moving contribution after the large attack angle pressure heart, grid lift of rudder area change is less, and under large attack angle, control and stability does not have larger reduction, can not affect larger on Missile Preliminary and control performance; In sum, the present invention reaches body pressure heart variable quantity by the configuration design of guided missile itself and regulates, and reduces the difficulty of control and stability design, does not need by other auxiliary control measure, do not need to limit ballistic design, obviously can not increase Missile Preliminary and control design case complicacy yet.
The word in description orientation adopted herein " on ", D score, "left", "right" etc. are all convenience in order to illustrate based on the orientation in accompanying drawing shown in drawing, in actual device, these orientation may be different due to the disposing way of device.
In sum, embodiment of the present invention only provides a kind of embodiment of the best, technology contents of the present invention and technical characterstic disclose as above, but the personage being familiar with the technology still may do the various replacement and the modification that do not deviate from creation spirit of the present invention based on disclosed content; Therefore, protection scope of the present invention is not limited to the technology contents that embodiment discloses, therefore all equivalence changes done according to shape of the present invention, structure and principle, be all encompassed in protection scope of the present invention.
Claims (10)
1., for reducing a method for designing for the band raster rudder guided missile of pressing heart variable quantity, it is characterized in that comprising the steps:
Step 1, determines the population parameter of guided missile, overall objective and design constraint;
Step 2, determines the grid rudder rudder face profile in guided missile;
Step 3, the missile airframe on front side of grid rudder increases strake wing, and determines the geometric parameter of strake wing;
Step 4, under the prerequisite that the geometric parameter of strake wing is constant, determines the distance d between strake wing and the grid rudder rudder face in folded state.
2. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 1, it is characterized in that, described method also comprises:
Step 5, after increasing strake wing, determines the aerodynamic characteristics numerical of guided missile profile, for determining whether the aerodynamic characteristics numerical of the guided missile profile after increasing strake wing meets the overall objective of guided missile simultaneously.
Step 6, adjustment strake wing profile and grid rudder rudder face profile, until meet the overall objective of determined guided missile in step 1, also meet when grid rudder rudder face is folded state, the pressure heart of missile airframe the most simultaneously.
3. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 1, is characterized in that, the population parameter of guided missile comprises Shell body quality, body barycenter, design Mach number and design spatial domain.
4. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 1, it is characterized in that, the overall objective of guided missile comprises when the permissible load factor of grid rudder rudder face on guided missile under being deployed condition, pressure heart designing requirement and control and stability requirement, and when the steady state stability requirement of grid rudder rudder face on guided missile under being folded state.
5. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 1, it is characterized in that, when the design constraint of guided missile comprises not band raster rudder missile airframe geometrical constraint and when the body external envelope geometry restriction of grid rudder rudder face on guided missile under in folded state.
6. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 1, it is characterized in that, the geometric parameter of grid rudder rudder face profile comprises the grid number of grid in the lifting area of grid rudder rudder face, the chord length of grid rudder rudder face, the spacing of grid rudder rudder face, grid rudder rudder face, and the rudder wall section shape of grid rudder rudder face.
7. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 1, is characterized in that,
Determine the grid rudder rudder face profile in guided missile in described step 2, be specially: according to population parameter and the design constraint of guided missile determined in step 1, determine to meet the grid rudder rudder face profile of the overall objective of grid rudder rudder face under being deployed condition on guided missile.
8. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 1, it is characterized in that, the chord length of the geometric parameter edge cover strip wing of strake wing, the length of strake wing and strake wing section shape, wherein the length of strake wing adopts when the maximum length in the body external envelope geometry restriction of grid rudder rudder face on guided missile under in folded state.
9. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 1, is characterized in that,
In described step 4 under the constant prerequisite of the geometric parameter of strake wing, determine the distance d between strake wing and the grid rudder rudder face in folded state, be specially: change the distance d between strake wing and grid rudder rudder face, determine on missile airframe without design strake wing and on missile airframe, be designed with strake wing two kinds of situations under the pressure heart of missile airframe, draw difference between the two, thus the amount of moving after drawing the pressure heart increasing missile airframe after strake wing further; The amount of moving after the pressure heart relatively corresponding to different distance, when after the pressure heart, the amount of moving is maximum, corresponding strake wing is optimum distance d with the spacing of the grid rudder rudder face in folded state, and now strake wing position the most rearward, and strake wing is little on the impact of grid rudder rudder face aerodynamic interference.
10. a kind of method for designing for reducing the band raster rudder guided missile of pressing heart variable quantity according to claim 2, is characterized in that,
The method adjusting strake wing profile and grid rudder rudder face profile in described step 6 comprises:
If when grid rudder rudder face is deployed condition, the pressure heart position of missile airframe is unreasonable, then changed the lift contribution of grid rudder rudder face by the geometric parameter adjustment of grid rudder rudder face profile;
If when grid rudder rudder face is folded state, the pressure heart position of missile airframe is unreasonable, then adjust the chord length b of strake wing, but the distance between strake wing and the grid rudder rudder face in folded state still adopts the distance d obtained in step 4, and the length of strake wing still adopts the length of determined strake wing in step 3.
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| CN106568356A (en) * | 2016-10-27 | 2017-04-19 | 浙江理工大学 | Missile rudder surface control mechanism |
| CN107651185A (en) * | 2017-08-21 | 2018-02-02 | 上海机电工程研究所 | It is a kind of to press the heart be with the supersonic aircraft of control adjustment |
| CN107844643A (en) * | 2017-10-25 | 2018-03-27 | 北京电子工程总体研究所 | Guided missile presses heart mutation analysis method under a kind of missile airframe elastic deformation |
| CN110837259A (en) * | 2018-08-16 | 2020-02-25 | 中国人民解放军战略支援部队航天工程大学 | Composite control scheme of built-in type air-launched rocket pre-launching attitude pitching channel |
| CN110837259B (en) * | 2018-08-16 | 2022-05-27 | 中国人民解放军战略支援部队航天工程大学 | Composite control scheme of built-in type air-launched rocket pre-launching attitude pitching channel |
| CN110906807A (en) * | 2019-12-13 | 2020-03-24 | 北京中科宇航探索技术有限公司 | Embedded pneumatic control plane for rocket and control method thereof |
| CN113959269A (en) * | 2021-11-17 | 2022-01-21 | 航天科工微电子系统研究院有限公司 | Grid empennage kinetic energy interceptor for intensive formation |
| CN114879718A (en) * | 2022-07-12 | 2022-08-09 | 南京理工大学 | Method for controlling an aircraft with a grid rudder |
| CN114879718B (en) * | 2022-07-12 | 2022-09-13 | 南京理工大学 | Method for controlling an aircraft with a grid rudder |
| CN117172077A (en) * | 2023-10-27 | 2023-12-05 | 西安现代控制技术研究所 | Non-ablative transverse folding tail rudder structure of supersonic missile and design method thereof |
| CN117172077B (en) * | 2023-10-27 | 2024-02-20 | 西安现代控制技术研究所 | Non-ablative transverse folding tail rudder structure of supersonic missile and design method thereof |
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