CN104598696B - A kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust - Google Patents
A kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust Download PDFInfo
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- CN104598696B CN104598696B CN201510065577.5A CN201510065577A CN104598696B CN 104598696 B CN104598696 B CN 104598696B CN 201510065577 A CN201510065577 A CN 201510065577A CN 104598696 B CN104598696 B CN 104598696B
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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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/80—Technologies aiming to reduce greenhouse gasses emissions common to all road transportation technologies
- Y02T10/82—Elements for improving aerodynamics
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Abstract
The invention discloses a kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust, comprise the steps：Step 1, the population parameter of guided missile and the pressure heart design objective of guided missile are determined；Step 2, it is determined that contour structures without endpiece guided missile；Step 3, increase by an endpiece in the afterbody of missile airframe, and determine the contour structures with endpiece guided missile.The present invention solves the pressure heart and the design challenges of the bad matching of barycenter that the design of high-speed missile fixed profile is brought, and especially solves guided missile in separation initial flight stage stability and mobile process maneuverability while requires high Missile Design problem.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of high-speed missile configuration design side for being used to press the heart to adjust
Method.
Background technology
The pressure heart and barycenter matched design are the weights of high-speed missile (main flight Mach number is more than 1.0) collectivity Scheme Design
Content is wanted, the good pressure heart and barycenter matching performance are to ensuring guided missile while with good mobility and stability with very big
Effect.But for flight Mach number span is big and the big high-speed missile of barycenter change, obtain good the pressure heart and barycenter
It is often relatively difficult with performance.
High-speed missile is typically designed using fixed profile at present, so under identical Mach number and attitude angle, guided missile pressure
The heart is constant, and barycenter is constantly changing with fuel consumption, and this pressure nonadjustable configuration design of the heart often limits pressure
The heart and barycenter matching performance, and then influence the ballistic flight performance of guided missile and overall operational performance.
It is relatively full in the guided missile separation initial flight stage for the guided missile separated from female bullet, or the guided missile of launched by airplane
The charge material heart needs to ensure certain steady state stability, and guided missile relatively unloaded barycenter in the end game needs to ensure necessarily motor-driven
Property, because the relatively fully loaded barycenter of guided missile zero load barycenter typically has certain reach change, designed using fixed profile, met simultaneously
Separation initial flight stage stability and mobile process maneuverability will become difficult.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust；Should
Method solves the pressure heart and the design challenges of the bad matching of barycenter that the design of high-speed missile fixed profile is brought, and especially solves and leads
Bullet requires high Missile Design problem simultaneously in separation initial flight stage stability and mobile process maneuverability.
In order to solve the above technical problems, the present invention uses following technical proposals：
A kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust, it comprises the steps：
Step 1, the population parameter of guided missile and the pressure heart design objective of guided missile are determined；
Step 2, it is determined that contour structures without endpiece guided missile；
Step 3, increase by an endpiece in the afterbody of missile airframe, and determine the contour structures with endpiece guided missile.
Further, methods described also includes：
Step 4, the practical flight scheme of guided missile is determined, specifically, in the initial flight stage after guided missile separation, now lead
Bullet is flown with the identified configuration state with endpiece guided missile in step 3, for increasing the steady of guided missile initial flight stage
It is qualitative；
Terminate in the guided missile initial flight stage or end mobile need obtain high maneuver when, shedding the work of separating mechanism
Under, endpiece separates from the afterbody of guided missile, and hereafter during maneuvering flight, guided missile is with identified without endpiece in step 2
The configuration state of guided missile is flown, so that is suppressed heart reach during maneuvering flight entirely, and is ensured good maneuverability.
Further, the population parameter of the guided missile includes guided missile initial flight stage and maneuvering flight after isolation
Flight Mach number, height and the angle of attack in the case of two kinds of journey；
The pressure heart design objective of the guided missile includes guided missile initial flight stage and maneuvering flight process two after isolation
The pressure heart design requirement of guided missile in the case of kind.
Further, the contour structures without endpiece guided missile are determined in the step 2, are specially：Determined according to step 1
The population parameter of guided missile and the pressure heart design objective of guided missile, design meet that guided missile presses heart design requirement during maneuvering flight
The contour structures without endpiece guided missile, it includes determining by determining body bus geometric parameter and rudder face geometric parameter
Guided missile profile；Wherein body bus geometric parameter includes body maximum gauge, body length and body bus curvilinear equation；Institute
State the section shape of chord length of the rudder face geometric parameter including rudder face, the length of rudder face and rudder face.
Further, the step 3 is specifically, the afterbody in missile airframe increases by an endpiece, and determines band endpiece guided missile
Contour structures, the contour structures with endpiece guided missile meet the pressure heart for the population parameter and guided missile that guided missile is determined in step 1
Design objective.
Further, the contour structures of the endpiece are the tail skirt structure with angle of flare θ, at the ending of the tail skirt structure
A diameter of D2, tail skirt structure section start a diameter of D1；The angle of flare is θ, and θ>0°；At the ending of tail skirt structure
The ratio between diameter D1 of section start of diameter D2 and tail skirt structure is D2/D1, and D2/D1>1.0.
Further, in the diameter D1 of the section start of tail skirt structure and the step 2 determined by without endpiece guided missile
Body base diameter D is equal.
The present invention compared with prior art, has following positive beneficial effect：
1st, the present invention is designed using separable endpiece, is designed by guided missile shape variable so as to reach the mesh that the pressure heart is adjusted
's.
2nd, the inventive method is simple, sheds separation and is easily achieved；Endpiece is designed in body most afterbody, and it is easily real to shed separation
It is existing, preceding bomb body will not be produced and significantly interfered with.
3rd, the pressure heart regulating effect of guided missile is obvious, and regulated quantity is easy to adjust as needed, is specially：By in guided missile
Afterbody increase endpiece, endpiece from guided missile centroid distance farther out, the pressure heart regulating effect of guided missile can become apparent from；By straight to tail skirt
Footpath and expansion angle are adjusted, and can be readily available the pressure heart regulated quantity for meeting to be actually needed.
Brief description of the drawings
Fig. 1 is the outline structural diagram of the invention with endpiece guided missile.
Fig. 2 is for band endpiece guided missile in the present invention with existing without endpiece guided missile initial flight stage and motor-driven after isolation
Guided missile presses heart property calculation comparative result figure in the case of two kinds of flight course.
Embodiment
Illustrate the embodiment of the present invention below in conjunction with the accompanying drawings.
As shown in Figure 1, 2, a kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust, it comprises the steps：
Step 1, the population parameter of guided missile and the pressure heart design objective of guided missile are determined；
The population parameter of the guided missile includes guided missile two kinds of feelings of initial flight stage and maneuvering flight process after isolation
Flight Mach number, height and the angle of attack under condition；
The pressure heart design objective of the guided missile includes guided missile initial flight stage and maneuvering flight process two after isolation
The pressure heart design requirement of guided missile in the case of kind.
Step 2, it is determined that contour structures without endpiece guided missile；Specially：The overall ginseng of guided missile according to determined by step 1
Number and the pressure heart design objective of guided missile, design meet guided missile pressed during maneuvering flight heart design requirement without endpiece guided missile
Contour structures, it includes determining guided missile profile by determining the bus geometric parameter of body 1 and rudder face geometric parameter；Wherein
The bus geometric parameter of body 1 includes the maximum gauge of body 1, the length of body 1 and the bus curvilinear equation of body 1；The rudder face is several
The section shape of chord length of what parameter including rudder face, the length of rudder face and rudder face.
Step 3, increase by an endpiece 2 in the afterbody of missile airframe 1, and determine the contour structures with endpiece guided missile；Specifically,
Contour structures with endpiece guided missile meet the pressure heart design objective of the population parameter that guided missile is determined in step 1 and guided missile.
The contour structures of the endpiece 2 are the tail skirt structure with angle of flare θ, a diameter of at the ending of the tail skirt structure
D2, tail skirt structure section start a diameter of D1；The angle of flare is θ, and θ>0°；Diameter D2 at the ending of tail skirt structure with
The ratio between diameter D1 of section start of tail skirt structure is D2/D1, and D2/D1>1.0；
In the present embodiment, as shown in figure 1, angle of flare θ=25 ° of tail skirt structure, the diameter at the ending of tail skirt structure
The ratio between D2 and diameter D1 of section start of tail skirt structure is D2/D1=1.5, the diameter D1 of the section start of tail skirt structure and the step
The base diameter D of body 1 determined by rapid 2 without endpiece guided missile is equal.
Step 4, the practical flight scheme of guided missile is determined, specifically, in the initial flight stage after guided missile separation, now lead
Bullet is flown with the identified configuration state with endpiece guided missile in step 3, for increasing the steady of guided missile initial flight stage
It is qualitative；
Terminate in the guided missile initial flight stage or end mobile need obtain high maneuver when, shedding the work of separating mechanism
Under, endpiece 2 separates from the afterbody of body 1, and hereafter during maneuvering flight, guided missile is with identified not magnetic tape trailer in step 2
The configuration state of section guided missile is flown, so that is suppressed heart reach during maneuvering flight entirely, and is ensured good manipulation
Property.
As shown in Fig. 2 be directed to different flight Mach numbers, band endpiece guided missile and not magnetic tape trailer by aerodynamic numerical simulation calculation
Guided missile pushes heart characteristic to section guided missile in Low Angle Of Attack in the case of two kinds of initial flight stage and maneuvering flight process after isolation, schemes
Abscissa is Mach number Ma in 2, and ordinate is to suppress heart XCP entirely；From the point of view of result of calculation contrast, using setting with endpiece guided missile
Meter compares the design without endpiece guided missile, and guided missile suppresses the heart and substantially moved afterwards entirely, and Low Angle Of Attack moves after pushing the heart under different Mach number
Amount all reaches 5%, it is contemplated that shifting amount is smaller after barycenter, so in guided missile initial flight stage after isolation, the static-stability of guided missile
Degree can significantly increase, increase about 4.5%.
Using the present invention, increase the separable endpiece 2 in tail skirt structure in missile tail, guided missile can be improved and separated
Guided missile steady state stability in journey, it is more beneficial for stabilization and separates, while after endpiece 2 separates from body 1, suppresses heart reach entirely, make
Guided missile steady state stability will not be excessive when obtaining maneuvering flight, ensure that good maneuverability.
What the word " on ", " under " in description orientation, "left", "right" etc. were for explanation used by herein facilitates base
For orientation in accompanying drawing shown in drawing, in actual device these orientation may due to device disposing way and
It is different.
In summary, embodiment of the present invention only provides a kind of optimal embodiment, in technology of the invention
Hold and technical characterstic has revealed that as above, but one skilled in the art scholar is still potentially based on disclosed content and made
Various replacements and modification without departing substantially from creation spirit of the present invention；Therefore, protection scope of the present invention is not limited to disclosed in embodiment
Technology contents, therefore equivalence changes that all shape under this invention, construction and principle are done, be encompassed by the protection model of the present invention
In enclosing.
Claims (6)
1. a kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust, it is characterised in that comprise the steps：
Step 1, the population parameter of guided missile and the pressure heart design objective of guided missile are determined；
Step 2, it is determined that contour structures without endpiece guided missile；
Step 3, increase by an endpiece in the afterbody of missile airframe, and determine the contour structures with endpiece guided missile；
Methods described also includes：
Step 4, determine the practical flight scheme of guided missile, specifically, guided missile separation after the initial flight stage, now guided missile with
Configuration state with endpiece guided missile determined by step 3 is flown, for increasing the stability in guided missile initial flight stage；
Terminate in the guided missile initial flight stage or end mobile need obtain high maneuver when, shedding the effect of separating mechanism
Under, endpiece is separated from the afterbody of guided missile, and hereafter during maneuvering flight, guided missile is led with identified in step 2 without endpiece
The configuration state of bullet is flown, so that suppresses heart reach during maneuvering flight entirely.
A kind of 2. high-speed missile Exterior Surface Design for being used to press the heart to adjust according to claim 1, it is characterised in that institute
Stating the population parameter of guided missile includes flight of the guided missile after isolation in the case of two kinds of initial flight stage and maneuvering flight process
Mach number, height and the angle of attack；
The pressure heart design objective of the guided missile includes guided missile two kinds of feelings of initial flight stage and maneuvering flight process after isolation
The pressure heart design requirement of guided missile under condition.
A kind of 3. high-speed missile Exterior Surface Design for being used to press the heart to adjust according to claim 1, it is characterised in that institute
The contour structures determined in step 2 without endpiece guided missile are stated, are specially：According to determined by step 1 population parameter of guided missile with
The pressure heart design objective of guided missile, design meet guided missile press during maneuvering flight heart design requirement without endpiece guided missile outside
Shape structure, it includes determining guided missile profile by determining body bus geometric parameter and rudder face geometric parameter；Wherein body
Bus geometric parameter includes body maximum gauge, body length and body bus curvilinear equation；The rudder face geometric parameter bag
Include the section shape of the chord length of rudder face, the length of rudder face and rudder face.
A kind of 4. high-speed missile Exterior Surface Design for being used to press the heart to adjust according to claim 1, it is characterised in that institute
Step 3 is stated specifically, the afterbody in missile airframe increases by an endpiece, and determines the contour structures with endpiece guided missile, the band endpiece
The contour structures of guided missile meet the pressure heart design objective of the population parameter that guided missile is determined in step 1 and guided missile.
A kind of 5. high-speed missile Exterior Surface Design for being used to press the heart to adjust according to claim 1, it is characterised in that institute
The contour structures for stating endpiece are the tail skirt structure with angle of flare θ, a diameter of D2, tail skirt structure at the ending of the tail skirt structure
Section start a diameter of D1；The angle of flare is θ, and θ>0°；Diameter D2 and tail skirt structure at the ending of tail skirt structure
The ratio between diameter D1 of section start is D2/D1, and D2/D1>1.0.
A kind of 6. high-speed missile Exterior Surface Design for being used to press the heart to adjust according to claim 5, it is characterised in that tail
The diameter D1 of the section start of skirt structure is equal with the identified body base diameter D without endpiece guided missile in the step 2.
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| CN201510065577.5A CN104598696B (en) | 2015-02-09 | 2015-02-09 | A kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust |
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| CN201510065577.5A CN104598696B (en) | 2015-02-09 | 2015-02-09 | A kind of high-speed missile Exterior Surface Design for being used to press the heart to adjust |
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| CN104598696B true CN104598696B (en) | 2017-12-19 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105799949B (en) * | 2016-05-12 | 2018-05-15 | 上海微小卫星工程中心 | A kind of pressure heart design method, attitude control method and the system of Asia orbiter |
| CN107891979B (en) * | 2017-09-28 | 2019-10-18 | 中国运载火箭技术研究院 | A kind of adjustable tranquilizer of hypersonic aircraft |
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| CA2670325C (en) * | 2006-11-30 | 2013-06-11 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
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| CA2670325C (en) * | 2006-11-30 | 2013-06-11 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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