GB2604077A - Pitching moment coefficient and center-of-pressure coefficient correction method for rocket projectile, and storage medium - Google Patents
Pitching moment coefficient and center-of-pressure coefficient correction method for rocket projectile, and storage medium Download PDFInfo
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- GB2604077A GB2604077A GB2207206.0A GB202207206A GB2604077A GB 2604077 A GB2604077 A GB 2604077A GB 202207206 A GB202207206 A GB 202207206A GB 2604077 A GB2604077 A GB 2604077A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
Provided are a pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile, and a storage medium. The correction method is applicable to rocket/missile like launch vehicle having axisymmetric rotating forming body shape, and tailless layouts or +-shaped or X-shaped tail layouts, and comprises the following steps: obtaining aerodynamic characteristic parameters of a rocket/missile in an original configuration (S1); obtaining shape change data of a rocket/missile like launch-vehicle (S2); constructing a pitching moment coefficient model and a center-of-pressure coefficient model of the rocket/missile in an improved configuration (S3); and inputting the aerodynamic characteristic parameters of the rocket/missile in the original configuration and the shape change data of the rocket/missile like launch-vehicle into the pitching moment coefficient model and the center-of-pressure coefficient model of the rocket/missile in the improved configuration to obtain the pitching moment coefficient and the center-of-pressure coefficient of the rocket/missile in the improved configuration, so as to shorten the design period and reduce the design cost (S4). The correction method can get rid of the dependence on a wind tunnel test and a complex calculation process, greatly shorten the design period, reduce the design cost, and improve the design efficiency.
Description
Description
PITCHING MOMENT COEFFICIENT AND CENTER-OF-PRESSURE COEFFICIENT CORRECTION METHOD FOR ROCKET /MISSILE, AND STORAGE MEDIUM
Technical Field
The disclosure belongs to the technical field of coefficient correction of rocket/missile like launch vehicle, and in particular relates to a pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile, and 10 a storage medium.
Background Art
Under the action of air, a launch vehicle moving in the atmosphere will produce aerodynamic forces including lift and drag. In engineering, the aerodynamic forces received by the launch vehicle in the atmosphere are usually normalized and written in the form of aerodynamic coefficients, which are collectively referred to as aerodynamic characteristics. The pitching moment coefficient and the center-of-pressure coefficient in the aerodynamic characteristics of the launch vehicle affect the stability and maneuverability of the launch vehicle, and play an important role in the design of the launch vehicle. When the configuration of the launch vehicle changes, the aerodynamic characteristics of the launch vehicle also change accordingly, thus affecting the flight performance of the launch vehicle.
With the advancement of computer technologies and test technologies, the ways and means of obtaining aerodynamic characteristics of launch vehicle are constantly enriched 25 and improved. In engineering, wind tunnel test technologies and numerical calculation technologies are usually used to obtain the aerodynamic characteristics of launch vehicle.
Description
The wind tunnel test technologies require that a scaled model of alaunch vehicle be designed and processed, and the scaled model of the launch vehicle be installed in wind tunnel test equipment for blowing test, so as to measure the aerodynamic characteristics of the launch vehicle and obtain the pitching moment coefficient and center-of-pressure coefficient of the launch vehicle. However, when the configuration of the launch vehicle changes, if the aerodynamic characteristics of the launch vehicle are obtained by means of wind tunnel tests, it is necessary to redesign and process the test model of the launch vehicle, and re-run the wind tunnel tests, which will inevitably lead to the increase of cost and the lengthening of calculation period.
Numerical calculation technologies require that a mathematical model be established according to the shape of the launch vehicle. The calculation methods usually include engineering experience calculation methods and CFD calculation methods based on solving N-S equations. The engineering experience calculation method is generally used for the calculation in an initial stage of a scheme, which is fast but has low precision.
The calculation progress of the CFD calculation method can meet engineeiing requirements, but the time for calculation pre-processing and calculation is relatively long compared with the engineering experience calculation method; in addition, if the configuration of the launch vehicle changes, pre-processing needs to be performed again, and the flow field of the new configuration needs to be recalculated, so that the cost and calculation period will inevitably increase.
Summary of the Invention
In order to overcome the problems existing in the related art at least to a certain extent, the disclosure provides a pitching moment coefficient and center-of-pressure 25 coefficient correction method for a rocket /missile, and a storage medium.
According to a first aspect of embodiments of the disclosure, the disclosure provides
Description
a pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile, which is applicable to rocket/missile like launch vehicle having axisymmetric rotating forming body shape, and tailless layouts or +-shaped or X-shaped tail layouts, the method comprising the following steps: obtaining aerodynamic characteristic parameters of a rocket /missile in an original configuration; obtaining shape change data of a rocket /missile like launch vehicle; constructing a pitching moment coefficient model and a center-of-pressure coefficient model of the rocket /missile in the improved configuration; and inputting the aerodynamic characteristic parameters of the rocket /missile in the original configuration and the shape change data of the rocket /missile into the pitching moment coefficient model and the center-of-pressure coefficient model of the rocket /missile in the improved configuration to obtain the pitching moment coefficient and the center-of-pressure coefficient of the rocket /missile in the improved configuration, so as to shorten the design period and reduce the design cost.
In the above-mentioned pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile, the obtained aerodynamic characteristic parameters of the rocket /missile in the original configuration comprise a pitching moment coefficient and a center-of-pressure coefficient of the rocket /missile in the original configuration.
In the above-mentioned pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile, the obtained shape change data of the rocket /missile like launch vehicle comprises the reference length change amount between the rocket /missile in the original configuration and a rocket /missile in an improved configuration.
Further, the constructed pitching moment coefficient model of the rocket /missile in
Description
the improved configuration is: A/ = C ref mz,olel f tir old toil iref mew ref ii en' the constructed center-of-pressure coefficient model of the rocket /missile in the improved configuration is: "- Almok, where represents the pitching moment coefficient of the rocket /missile in the original configuration, C"--'ild-wil represents the pitching moment coefficient of the tail of the rocket /missile in the original configuration, /rei'°id represents the reference length of the rocket /missile in the original configuration, l?efMrn represents the reference o length 1 rehizem Ire" AC' of the rocket /missile in the improved configuration, Al represents the reference length change amount between the rocket /missile in the original configuration and the rocket /missile of the improved configuration, X141,01d represents the center-of-pressure coefficient of the rocket /missile in the original configuration, and represents a normal force coefficient of the rocket /missile, wherein the normal force coefficient of the rocket /missile in the original configuration is equal to that of the rocket /missile in the improved configuration Furthermore, the specific construction process of the pitching moment coefficient model of the rocket /missile in the improved configuration is as follows: according to the expression of the pitching moment coefficient Cm, of the rocket zo /missile: (2",_ -go,,cref where M, represents the pitching moment of the rocket /missile, q-represents the flight dynamic pressure of the rocket /missile, Se* represents the reference area, and ref represents the reference length;
Description
the pitching moment coefficient configuration is obtained as follows: of the rocket /missile in the improved (:,", 411/ new qx,S,,i1"f z where ',new represents the pitching moment of the rocket /missile in the improved configuration,J'VIzflewtw" represents the pitching moment of the head of the rocket /missile in the improved configuration, AIz represents the pitching moment of the tail of the rocket /missile in the improved configuration, and z---P represents the pitching moment generated by a surface protrusion on the rocket body of the rocket /missile in the improved configuration; 1 0 since the pitching moment of the head of the rocket /missile in the original configuration and the pitching moment generated by a surface protrusion on the rocket body of the rocket /missile in the original configuration are not affected by length adjustment, there is: = 11/1,nEn Z,old,p = Z mew,p so the pitching moment coefficient C-,new of the rocket /missile in the improved configuration is further obtained as follows: A/1 Z old,nose 1/1 Z.ofcl.p Z.new.tal qcoS rejlrej "e", A/1z according to the relationship N between the distance from a pressure center to a moment reference point, the normal force N and the pitching moment Aliz received by the rocket /missile, the pitching moment of the tail of the rocket /missile in the improved configuration is obtained as follows: Al7,fiew -Nntrw cp before and after the length of the rocket /missile changes, the normal force coefficient generated by the tail remains unchanged, there is:
Description
T
Icp new la d 7.old tail 1 ref plc; nil = Ar = AT old fad tail where N"ery,'"il represents the normal force of the tail of the rocket /missile in the improved configuration, 7.-viad represents the pitching moment of the tail of the rocket /missile in the improved configuration, 1ci'me31'" represents the distance from the pressure center of the tail of the rocket /missile in the improved configuration to the moment reference point; iV1d.aj11 represents the normal force of the tail of the rocket /missile in the original configuration, A/z/ild-mu represents the pitching moment of the tail of the rocket /missile in the original configuration, and 1 rd 'I'm 'tall represents the reference length of the tail of the rocket /missile in the original configuration; so the pitching moment of the tail of the rocket /missile in the improved configuration is further obtained as follows: Z A4 oldtad LVI Z.old Jail (1 + A/ ) I cp,new.tod ref,old 1 ref,old Jail A/ re, I,old;ail Z old / ref. .old Jail the pitching moment coefficient model of the rocket /missile in the improved configuration is further obtained as follows:
Description
0 + Af Z,01,,,p +z old tail + ,o1 ta! Sref 'ref mew A4Z ± phi Z old tad ref_old lreJ el+ Al ref \ 'ref.old nf "old,,, ref,new Al ref ild jail 2,old,tail EsS"/".fpl, refold ref,olactral 1 ref,new qrS",1", C,: old Cm: old it *n=.7" old = rnz,old ref,tzew Al"f Furthermore, the specific construction process of the center-of-pressure coefficient model of the rocket /missile in the improved configuration is as follows: x. =-according to the relationship C, between the center-of-pressure coefficient XcP, the pitching moment coefficient ( in, of the rocket /missile and the normal force coefficient ( -v of the rocket /missile, as well as the pitching moment coefficient model of the rocket /missile in the improved configuration, the center-of-pressure coefficient model of the rocket /missile in the improved configuration is obtained as follows: 1re. told c (7 rer.t ' in z,o1
X
ref new AIr CA, /ref,old cp,old I ref "cm, According to a second aspect of embodiments of the disclosure, the disclosure further provides a computer storage medium that stores a computer program, wherein the computer program, when executed by a processor, causes the steps of the pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile according to any one of the above-mentioned methods to be implemented.
According to a third aspect of embodiments of the disclosure, the disclosure further provides a server comprising a memory and a processor, wherein the memory stores an
Description
executable program, and the processor implements the steps of the pitching moment coefficient arid center-of-pressure coefficient correction method for a rocket /missile according to any one of above-mentioned methods when invoking the executable program.
According to the above-mentioned specific implementations of the disclosure, it can be known that at least the following beneficial effects are obtained: in the disclosure, with respect to length changes of rocket/missile like launch vehicle having axisymmetric rotating forming body shape, and tailless layouts or +-shaped or X-shaped tail layouts, based on aerodynamic characteristic parameters of a rocket/missile like launch vehicle in an original configuration, a center-of-pressure coefficient and a pitching moment coefficient of a rocket /missile in an improved configuration are obtained. The disclosure can solve the problems of high cost and long period caused by obtaining aerodynamic characteristic parameters for the improved configuration based on wind tunnel test and numerical calculation, and can quickly and accurately obtain the center-of-pressure coefficient and the pitching moment coefficient of the rocket /missile in the improved configuration after the length of the rocket /missile changes, such that the calculation of distributed aerodynamic characteristics of the rocket /missile can get rid of the dependence on the wind tunnel test and complicated calculation process, thus greatly shortening the design period, reducing the design cost and improving the design efficiency.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and illustrative only and are not intended to limit the scope of what is claimed in the disclosure.
Brief Description of the Drawings
The accompanying drawings, which are attached below, form part of the
Description
specification of the disclosure, illustrate embodiments of the disclosure, and together with the description of the specification, serve to explain the principles of the disclosure.
FIG. I is a flowchart of a pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile according to an embodiment of the disclosure.
FIG. 2 is a schematic diagram of the change of the configuration of a rocket /missile in a pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile according to an embodiment of the disclosure.
FIG. 3 is a result comparison chart between the pitching moment coefficient 10 obtained by testing a rocket in an improved 3-level configuration and the pitching moment coefficient obtained by correction based on the original 4-level configuration according to an embodiment of the disclosure, where -n represents a curve of the pitching moment coefficient obtained by correction based on the original 4-level configuration, and represents a curve of the pitching moment coefficient obtained by testing the rocket in the improved 3-level configuration.
FIG. 4 is a result comparison chart between the center-of-pressure coefficient obtained by testing a rocket in an improved 3-level configuration mid the center-ofpressure coefficient obtained by correction based on the original 4-level configuration according to an embodiment of the disclosure, where represents a curve of the pitching moment coefficient obtained by correction based on the original 4-level configuration, and represents a curve of the pitching moment coefficient obtained by testing the rocket in the improved 3-level configuration.
Detailed Description of Embodiments
In order to make the purpose, technical solutions and advantages of the embodiments of the disclosure more clearly understood, the spirit of the contents
Description
disclosed in the disclosure will be clearly described below with reference to the accompanying drawings and detailed descriptions. Any person skilled in the art, after knowing the embodiments of the disclosure, can make changes and modifications by the technology taught in the disclosure, without departing from the spirit and scope of the disclosure.
The illustrative embodiments and descriptions of the disclosure are used to explain the disclosure, but are not intended to limit the disclosure. In addition, elements/members with the same or similar reference numerals used in the drawings and the embodiments are intended to represent the same or similar parts.
As used herein, "first", "second", etc., do not specifically refer to the order or sequence, nor are they used to limit the disclosure, but are only used to distinguish elements or operations described in the same technical terms.
As used herein, directional terms, such as -up", -down" -left", -right", "front" or "back", etc., only refer to the directions in the drawings. Therefore, the directional terms used are intended to be illustrative and not intended to limit the creation.
As used herein, "comprising", "including", "having", "containing", and the like, are open-ended terms, meaning "including but not limited to".
As used herein, "and/or" includes any and all combinations of the stated things.
As used herein, "multiple" includes "two" and -two or more"; and as used herein, 20 "multiple groups" includes "two groups-and "two or more groups-.
As used herein, terms substantially", -about" and the like are used to modify any quantity or error that can vary slightly, but these slight changes or errors will not change its essence. In general, the range of the slight changes or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other numerical values. Those skilled in the art should understand that the aforementioned values can be adjusted according to actual needs, and are not limited
Description
thereto.
Certain terms used to describe the disclosure are discussed below or elsewhere in this specification to provide those skilled in the art with additional guidance in the description of the disclosure.
Most of the rocket bodies of rocket launchers and the /missile bodies of missile-like launch vehicle have axisymmetric rotating forming body shape, and having tailless layouts or tailed layouts. Most of the tails of the rocket launchers or missile-like launch vehicle with tails are in forms of +-shaped or X-shaped layout. In the design process of launch vehicle with such characteristics, the main configuration changes are changes in the length of the rocket body or the missile body, changes in the shape of the missile head, and changes in the geometry of the tail suiface. The configuration changes will have an impact on the aerodynamic characteristics of the launch vehicle.
With respect to the length change of the above-mentioned rocket /missile launch vehicle, in the pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile provided in the embodiments of the disclosure, based on aerodynamic characteristic data of an rocket/missile in an original configuration, a pitching moment coefficient and a center-of-pressure coefficient of a rocket/missile in an improved configuration after the length change are obtained. As shown in FIG. 1, the method comprises the following steps: Si. obtaining aerodynamic characteristic parameters of a rocket/missile in an original configuration; S2. obtaining shape change data of a rocket/missile like vehicle; S3. constructing a pitching moment coefficient model and a center-of-pressure coefficient model of the rocket/missile in the improved configuration; and 54. inputting the aerodynamic characteristic parameters of the rocket/missile in the original configuration and the shape change data of the rocket/missile like vehicle into
Description
the pitching moment coefficient model and the center-of-pressure coefficient model of the rocket/missile in the improved configuration to obtain the pitching moment coefficient and the center-of-pressure coefficient of the rocket/missile in the improved configuration, so as to shorten the design period and reduce the design cost.
For rocket/missile like launch vehicle having axisymmetric rotating forming body shape, and tailless layouts Or +-shaped or X-shaped tail layouts, the pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile provided in the embodiments of the disclosure is not limited to the correction calculation of the longitudinal center-of-pressure coefficient and the longitudinal pitching moment coefficient, but can also be used for the correction calculation of the lateral center-of-pressure coefficient and the lateral yaw moment.
In the above step S 1, the obtained aerodynamic characteristic parameters of the rocket/missile in the original configuration comprise a pitching moment coefficient and a center-of-pressure coefficient of the rocket/missile in the original configuration.
In the above step 52, the obtained shape change data of the rocket/missile like launch vehicle comprises the reference length change amount Alrej between the rocket/missile in the original configuration and a rocket/missile in an improved configuration.
In the above step S3, when the shape change data of the rocket/missile like vehicle comprises the reference length change amount between the rocket/missile in the original 20 configuration and the rocket/missile in the improved configuration, the constructed pitching moment coefficient model of the rocket/missile in the improved configuration is: ref Aid ACT 17.,old ± ,old,tail j IPermit, tjgf the constructed center-of-pressure coefficient model of the rocket/missile in the 25 improved configuration is:
Description
Al (2).
retold C ma old toil rel X cp,old
C N
rej mew,new In Equation (1) and Equation (2), ,° represents the pitching moment coefficient of the rocket/missile in the original configuration, ems/Juinu represents the pitching moment coefficient of the tail of the rocket/missile in the original configuration, represents the reference length of the rocket/missile in the original configuration represents the reference length /"T, = + Al,."f of the rocket/missile in the improved configuration, A/ represents the reference length change amount between the rocket/missile in the original configuration and the rocket/missile of the improved configuration, XLP."'d represents the center-of-pressure coefficient of the rocket/missile o in the original configuration, and CA' represents a normal force coefficient of the rocket/missile, wherein the normal force coefficient of the rocket/missile in the original configuration is equal to that of the rocket/missile in the improved configuration.
For rocket/missile like launch vehicle having axisymmetric rotating forming body shape, and tailless layouts or +-shaped or X-shaped tail layouts, the normal force and pitching moment are mainly generated by the head, the column section, the surface protrusion on the rocket body, and the tail of the rocket/missile. Especially when flying at a small angle of attack, the contribution of the column section to the normal force is small, which can be ignored relative to the head and tail, and the normal force generated by the surface protrusion on the rocket body is not affected by the change in the length of the rocket body. Therefore, it can be considered that the normal forces are all provided by the head, the surface protrusion on the rocket body, and the tail of the rocket/missile.
Taking the correction of the longitudinal center-of-pressure coefficient and the longitudinal pitching moment coefficient as an example, the construction process of the pitching moment coefficient model and the center-of-pressure coefficient model of the rocket/missile in the improved configuration in the pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile provided in the CJ l?e
Description
embodiments of the disclosure will be described in detail.
As shown in FIG. 2, corresponding to the original configuration of the rocket/missile and the improved configuration after the length change, the various parameters are distinguished by subscripts "old" and "new" respectively.
The theoretical cusp of the rocket/missile is taken as the moment reference point, the normal force received by the rocket/missile is N, the pitching moment is M-, the / distance from the pressure center to the moment reference point is c9, the center-of-pressure coefficient is XcP, the flight dynamic pressure of the rocket/missile is q-, the reference area is Sref, and the reference length is l'''' . The following relationship exists io between the various parameters: (7-
X = C, z
0-)S ref I ref = C, yceS", Alz (3) In Equation (3), m7 represents the pitching moment coefficient of the rocket/missile; and CA' represents the normal force coefficient of the rocket/missile.
For the rocket/missiles in the original configuration and the improved configuration, 15 the following relationship between the normal force and the normal force coefficient can be obtained as follows: V old,nose 1oj nose N nose IV old;ail = N = N tad N = N = N pnnep 1V old,b IV new,b (4) In Equation (4), °kJ, n° se represents the normal force of the head of the rocket/missile in the original configuration, and N'^-,'"'s" represents the normal force of
Description
the head of the rocket/missile in the improved configuration; °IdPH represents the normal force of the tail of the rocket/missile in the original configuration, and Nneu represents the normal force of the tail of the rocket/missile in the improved configuration; L'id,P represents the normal force generated by the surface protrusion on the rocket body of the rocket/missile in the original configuration, and IV "e"/' represents the normal force generated by the surface protrusion on the rocket body of the rocket/missile in the improved configuration; and Ncild,' represents the normal force of the column section of the rocket/missile in the original configuration, and N'my.' represents the normal force of the column section of the rocket/missile in the improved configuration The normal force '°1d of the rocket/missile in the original configuration is: N,1,1 = N "H. " + N N old,plad (5) The normal force coefficient of the rocket/missile in the original configuration is: C N.old =CN -±C +C.
old, nose,oldtall, A, old, p (6) The normal force Nnew of the rocket/missile in the improved configuration is: N77011, Arnel + N toil (7) The normal force coefficient A,new of the rocket/missile in the improved configuration is: =C CN,new N,netv, nose + CA,,new, Before and after the configuration adjustment of the rocket/missile, there is the following relationship between the normal force and the normal force coefficient of the rocket/missile: N "id = n"v = N = (9) According to Equation (3), the expansion equations of the distance 1 tp,old from the 25 pressure center of the rocket/missile in the original configuration to the moment reference point, the center-of-pressure coefficient X(P.Old, and the pitching moment coefficient II (8)
Description
Cine.old are respectively as follows: ± " Z old " A/12 old toil ± Icp,old A'T N'oid C=0/ C mz,old,nose C mid cml ± ±C in-old cm& cp.old = N,old C7N z,ota Atzoij;,o3e ± Z,old zrel ± Ai Z,olo 7,p C ryri.old qrrS rel 1 ref.eld 5' re rei In Equation (10), Equation (11) and Equation ( 1 2), Mz represents the pitching moment of the rocket/missile in the original configuration, 41"hi,m'se represents the pitching moment of the head of the rocket/missile in the original configuration, -"L represents the pitching moment of the tail of the rocket/missile in the original configuration, Mi °kJ " represents the pitching moment generated by the surface lo protrusion on the rocket body of the rocket/missile in die original configuration; Cmz.°1d represents the pitching moment coefficient of the rocket/missile in the original configuration, Cffi12,0u,"05e represents the pitching moment coefficient of the head of the rocket/missile in the original configuration, inz,"/"" represents the pitching moment coefficient of the tail of the rocket/missile in the original configuration, inz."N,P represents the pitching moment coefficient generated by the surface protrusion on the rocket body of the rocket/missile in the original configuration; /cP-"'d represents the distance from the pressure center of the rocket/missile in the original configuration to the moment reference point, and /ref "b1 represents the reference length of the rocket/missile in the original configuration; and q-represents the flight dynamic pressure of the rocket/missile, and.5'4 represents the reference area.
According to Equation (3), the expansion equations of the distance from the pressure center of the rocket/missile in the improved configuration to the moment reference point, the center-of-pressure coefficient Xcm-, and the pitching moment
Description
C
coefficient " new are respectively as follows: Y7 M Z,new.nose M Z.new,tarl Z.newp Z.new nose Z,new.tcal Z,new.p cp,new ne N new jolt N w nose new,p AT C'
X
new Is rct Aef Z,ne nose ± Ad Z newiwl Z 7ETV,P qt Sr,/1,4 In Equation (13), Equation (14) and Equation (15), represents the pitching moment of the rocket/missile in the improved configuration, Ali 'IwIt'n°se represents the pitching moment of the head of the rocket/missile in the improved configuration, Alz,"e"vall represents the pitching moment of the tail of the rocket/missile in the improved configuration, and Mz,new'P represents the pitching moment generated by a surface protrusion on the rocket body of the rocket/missile in the improved configuration; C"'Z. 'nen represents the pitching moment coefficient of the rocket/missile in the improved configuration, Cm1,e","ose represents the pitching moment coefficient of the head of the rocket/missile in the improved configuration, (7-,-,/ad represents the pitching moment coefficient of the tail of the rocket/missile in the improved configuration, nr112141P represents the pitching moment coefficient generated by the surface protrusion on the rocket body of the rocket/missile in the improved configuration; and IcP.neH represents the distance from the pressure center of the rocket/missile in the improved configuration to the moment reference point, and /-f*-" represents the reference length of the rocket/missile in the improved configuration.
Since the pitching moment of the head of the rocket/missile in the original configuration and the pitching moment generated by the surface protrusion on the rocket body of the rocket/missile in the original configuration are not affected by length adjustment, there is: (13) (14) (15)
Description
{ Al r / Jild,,,,,,, -VI 7,old,p M 7,frien,p (16) so the pitching moment coefficient Cmr'n' of the rocket/missile in the improved configuration is obtained from Equation (15) and Equation (16) as follows: C f7,11011" SIM + 7 lkjull M Z,ne q"S 'ref,flL'FL' q"S (17) Since the length change of the rocket/missile has little effect on the air flow around the tail, according to Equation (3), the normal force coefficient generated by the tail remains unchanged, there is: In Equation (18), represents the normal force of the tail of the rocket/missile in the improved configuration, ,""/ represents the pitching moment of the tail of the rocket/missile in the improved configuration, 1 clime" "" represents the distance from the pressure center of the tail of the rocket/missile in the improved configuration to the moment reference point; "htecin represents the normal force of the tail of the rocket/missile in the original configuration, 0 represents the pitching moment of the tail of the rocket/missile in the original configuration, and represents the reference length of the tail of the rocket/missile in the original configuration.
The pitching moment of the tail of the rocket/missile in the improved configuration is obtained from Equation (18) as follows: Z.new.tazI cp xely tail Z,old tail ri nil -ref,old jail ail -N 001(171 Ntazl 014,nose Z,old.1) if (18)
Description
11/1,old,tail + A/ A/IZOId tail = p,mnv tail nje ref,old Sad ref,old = laid,tail Z,oldtol ref phi tail (19) As can be seen from Equation (19), the pitching moment of the tail of the rocket/missile in the improved configuration can be expressed by the pitching moment of the tail of the rocket/missile in the original configuration.
Therefore, the pitching moment coefficient of the rocket/missile in the improved configuration is obtained from Equation (17) and Equation (19) as follows: M,old,nose,old p Z M Z,old,nose Al ref Z Mzoijm,i +AIZOId tail polo& ,uni y"5"1",f,"" (20) As can be seen from Equation (20), the pitching moment coefficient of the rocket/missile in the improved configuration can be expressed by the pitching moment lo coefficient of the rocket/missile in the original configuration.
The pitching moment coefficient model of the rocket/missile in the improved configuration is further obtained from Equation (20) as follows:
C
IVIZ,n1d.tad 1, ,ola' C ntz,ot old fail 1 ref,o1c1 nhnne iref,new ( tiv2S,"fl"r",c, Alref ref,old C,o( ref.old 1ref moi Z.old M Z,old tail Al, 1ref,oI d Aid = enr,ohl (21) The center-of-pressure coefficient model of the rocket/missile in the improved 15 configuration is obtained from Equation (21) as follows:
Description
C mz,old + Cmz,old, 71 Air,"
X CA,
Xcp.old (22) As can be seen from Equation (21) and Equation (22), both the pitching moment coefficient and the center-of-pressure coefficient of the rocket/missile in the improved configuration can be expressed by the pitching moment coefficient, the center-of-pressure coefficient, the reference length, and the length increment of the rocket/missile in the original configuration, that is, the pitching moment coefficient and the center-ofpressure coefficient of the rocket/missile in the improved configuration can be obtained by correction of the pitching moment coefficient and the center-of-pressure coefficient of the rocket/missile in the original configuration.
In the pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile provided in the embodiments of the disclosure, it is possible to obtain, based on aerodynamic characteristic parameters of an rocket/missile in an original configuration, a pitching moment coefficient and a center-of-pressure coefficient of a rocket/missile in an improved configuration after the length change, which can make the calculation of the aerodynamic characteristic parameters of the rocket/missile to get rid of the dependence on the wind tunnel test and numerical calculation, thus greatly shortening the design period, reducing the design cost, and improving the design efficiency.
The pitching moment coefficient and center-of-pressure coefficient correction 20 method for a rocket/missile provided in the embodiments of the disclosure will be described below in conjunction with an actual development process of a certain type of a rocket launcher.
In a design stage of a certain type of rocket launcher, a 4-level configuration is used,
Description
and the improved configuration is a 3-level configuration. The length of the rocket is changed from the original 16.524 m to 19.727 m, and the length is increased by 3.203 m. In addition, the shape of the head of the entire rocket, the diameter of the rocket body, the size and shape of the tail and the relative position on the rocket body remain unchanged, which accords with the applicable scope of the pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile provided in the embodiments of the disclosure.
Taking the inertial force Ma = 1.5, the angle of attack a = 20, 4°, 6°, and the angle of sideslip 1 = 0° as an example, based on the existing normal force coefficient (Iv the pitching moment coefficient Cm.= , the center-of-pressure coefficient X6P, the pitching moment coefficient (7inz n"' of the tail, and the reference length /-1 of the entire rocket in the original configuration, and the reference length Tref and the length increment AC of the rocket in the improved configuration, the pitching moment coefficient and the center-of-pressure coefficient 'ir, of the rocket in the improved configuration are 15 obtained through the correction method of the disclosure. The pitching moment coefficient and the center-of-pressure coefficient X'P of the rocket in the original 4-level configuration are as shown in Table 1. The reference lengths and correction coefficients of the rockets in the 4-level configuration and the 3-level configuration are as shown in Table 2. The comparison between the test data of the improved 3-level configuration at Ma=1.5 and the calculation results of the correction method of the disclosure are as shown in Table 3.
Table 1 Statistics table of original 4-level configuration at Ma=1.5, pitching moment coefficient Cr, and center-of-pressure coefficient XcP a (0)C A cp C;rta11C, 2 0.2329 -0.1266 -0.5436 -0.0811 -0.3482 4 0.4808 -0.2609 -0.5426 -0.1502 -0.3124
Description
6 0.7491 -0.3980 -0.5313 -0.2099 -0.2802 1.3740 -0.7232 -0.5263 -0.3121 -0.2271 Table 2 Reference lengths and correction coefficients for the 4-level configuration and 3-level configuration 4-level reference 3-level reference A/ Fre A/ .11 ref rq lengthirer length inu rei 16.5240 19.7270 3.2030 0.8376 0.1624 Table 3 Comparison between test data of improved 3-level configuration at Ma=1.5 and calculation results of correction algorithm a (o) X (7, (51r 2 0.2220 -0.1165 -0.5249 -0.1108 -0.5119 4.9356 -1.3079 4 0.4734 -0.2455 -0.5187 -0.2300 -0.5053 6.3037 -1.3426 6 0.7480 -0.3825 -0.5114 -0.3545 -0.4905 7.3266 -2.0826 1.4131 -0.7196 -0.5093 -0.6534 -0.4778 9.1947 -3.1483 As can be seen from Table 3, FIG. 3 and FIG. 4, on the basis of the existing data of the rocket in the original 4-level configuration, though the comparison between the pitching moment coefficient or and the center-of-pressure coefficient Xel' obtained o by the correction method of the disclosure and the test data of the rocket in the improved 3-level configuration, it can be known that the error of the pitching moment coefficient is about 5%-10%, the error of the center-of-pressure coefficient is about 1.3%-3.2%, the correction error has an increasing trend with the increase of the angle of attack, and when the angle of attack is not more than 6°, better data can be obtained through the correction 15 method of the disclosure. When the angle of attack is greater than 6°, the separation area on the leeward side of the rocket body expands, and the non-linear lift generated by
Description
viscous separation leads to a condition that changes in the normal force and pitching moment of the rocket cannot be ignored. Considering the engineering calculation and use, the precision of aerodynamic characteristic data is generally 109/0-15%, when the angle of attack is less than or equal to 6°, better calculation results can be obtained by using the correction method of the disclosure; and when the angle of attack is greater than 6°, although the precision of the data obtained by the correction and calculation decreases, it still has a strong reference value and guiding significance in engineering application.
In an exemplary embodiment, the embodiment of the disclosure further provides a computer storage medium, which is a computer-readable storage medium, for example, a memory containing a computer program, and the above-mentioned computer program can be executed by a processor, so as to implement the steps of the aforementioned pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile.
In an exemplary embodiment, the embodiment of the disclosure further provides a server, which comprises a memory and a processor, wherein the memory stores an executable program, and the processor implements the steps of the aforementioned pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile when invoking the executable program.
The above embodiments of the disclosure may be implemented in various hardware, software coding, or a combination of both. For example, the embodiments of the disclosure may also represent program codes for executing the above method in a digital signal processor (Digital Signal Processor, DSP). The disclosure may also relate to various functions performed by computer processors, digital signal processors, microprocessors, or field programmable gate arrays (Field Programmable Gate Arrays, FPGAs). The above-mentioned processor may be configured in accordance with the disclosure to perform specific tasks by executing machine-readable software codes or
Description
firmware codes that define the specific methods disclosed herein. The software codes or firmware codes may be developed to represent different programming languages and different formats or forms. They also can represent software codes compiled for different target platforms. However, different code styles, types and languages of software codes and other types of configuration codes to perform tasks in accordance with the disclosure do not depart from the spirit and scope of the disclosure.
The above descriptions are only illustrative of the specific embodiments of the disclosure. Without departing from the concept and principles of the disclosure, any equivalent changes and modifications made by those skilled in the art shall fall within the
io protection scope of the disclosure.
Claims (7)
- Claims I. A pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile, which is applicable to rocket/missile like launch vehicle having axi symmetric rotating forming body shape, and tailless layouts or +-shaped or X-shaped tail layouts, characterized by comprising: obtaining aerodynamic characteristic parameters of a rocket/missile in an original configuration, which comprise a pitching moment coefficient and a center-of-pressure coefficient of the rocket/missile in the original configuration; obtaining shape change data of a rocket/missile like launch vehicle, which comprises a reference length change amount between the rocket/missile in the original configuration and a rocket/missile in an improved configuration; constructing a pitching moment coefficient model and a center-of-pressure coefficient model of the rocket/missile in the improved configuration; and inputting the aerodynamic characteristic parameters of the rocket/missile in the original configuration and the shape change data of the rocket/missile into the pitching moment coefficient model and the center-of-pressure coefficient model of the rocket/missile in the improved configuration to obtain the pitching moment coefficient and the center-of-pressure coefficient of the rocket/missile in the improved configuration, so as to shorten the design period and reduce the design cost.
- 2. The pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile according to claim 1, characterized in that the constructed pitching moment coefficient model of the rocket/missile in the improved configuration is: 1, .old ( / 1.0 f.12011) where C-."' represents the pitching moment coefficient of the rocketmissile in the original configuration, Cinz-°'4,tail represents the pitching moment coefficient of the tail of the rocket/missile in the original configuration, 1 ref,old represents the reference length Claims of the rocket/missile in the original configuration, ref'"r# represents the reference length A/ of the rocket/missile in the improved configuration, I e 1,nen= cold ± A/ and ref represents the reference length change amount between the rocket/missile in the original configuration and the rocket/missile of the improved configuration.
- 3. The pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile according to claim 2, characterized in that the constructed center-of-pressure coefficient model of the rocket/missile in the improved configuration is: Xcp,"" = Xcp.uhl.old C leni Ain"-new C CI mew where XcPidd represents the center-of-pressure coefficient of the rocket/missile in the original configuration, and Cv represents a normal force coefficient of the rocket/missile, wherein the normal force coefficient of the rocket/missile in the original configuration is equal to that of the rocket/missile in the improved configuration.
- 4. The pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile according to claim 2, characterized in that the specific construction process of the pitching moment coefficient model of the rocket/missile in the improved configuration is as follows: according to the expression of the pitching moment coefficient Cm, of the rocket/missile: C,,,_ -q5,.ef where M, represents the pitching moment of the rocket/missile, qt represents the flight dynamic pressure of the rocket/missile, Sr':f represents the reference area, and ref represents the reference length; the pitching moment coefficient C-,new of the rocket/missile in the improved configuration is obtained as follows: Claims Aiz new 1V1z w ew,eur ±Mzwew M Z,new,p IflZ a qx,S"flref,eis.where Alz'nny represents the pitching moment of the rocket/missile in the improved configuration, 7 arell,nose represents the pitching moment of the head of the rocket/missile in the improved configuration, L 'nrri Jail represents the pitching moment of the tail of the rocket/missile in the improved configuration, and represents the pitching moment generated by a sitrface protrusion on the body of the rocket/missile in the improved configuration; and since the pitching moment of the head of the rocket/missile in the original configuration and the pitching moment generated by a surface protrusion on the body of the rocket/missile in the original configuration are not affected by length adjustment, there is: Z oldnose Zmen,nose 1/A1 Z pler,p = A4 Z,new.p so the pitching moment coefficient "^s,-of the rocket/missile in the improved configuration is further obtained as follows: At, Al +Z!rid A 4-Zywayail ToSreflmrpew /, according to the relationship =v of the distance from a pressure center to a moment reference point, the normal force N and the pitching moment received by the rocket/missile, the pitching moment of the tail of the rocket/missile in the improved configuration is obtained as follows: A4 nni. foil Arnei,raiI cp,nevl before and after the length of the rocket/missile changes, the normal force coefficient generated by the tail remains unchanged, there is: ClaimsTcp new toll 7.ohi tail 1 ref,old.rad = Ar = AT olctrad tail where N e' represents the normal force of the tail of the rocket/missile in the improved configuration, "7 ne" mil represents the pitching moment of the tail of the rocket/missile in the improved configuration, / represents the distance from the pressure center of the tail to the moment reference point of the rocket/missile in the improved configuration; N0Adi011 represents the normal force of the tail of the o ta rocket/missile in the original configuration, MZ Id il, represents the pitching moment of the tail of the rocket/missile in the original configuration, and I re-'tali represents the reference length of the tail of the rocket/missile in the original configuration; so the pitching moment of the tail of the rocket/missile in the improved configuration is further obtained as follows: the pitching moment coefficient model of the rocket/missile in the improved configuration is further obtained as follows: JAIZ,o/d,tai/ z,om fad (7 m met+ ;ail ref at 1 ref,old 1 refold jail Act -A/1 ± 7,old Z.old, 1 ref old jail Claims 0 + Af Z,old,p + AIz old tail + ,o1 ta! S1 'refmew 1,"4-"id 2,old,tail Alf 'refold t." f,jd jail Al"f \ lrehhew qc"S"flreipl, ref,olactral 1 ref,new ref old ref,,, ref.new C old Cm: old it IVIZ ±old Z old tad *n=.7" old = C rnz,old ref,tzew
- 5. The pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile according to claim 4, characterized in that the specific construction process of the center-of-pressure coefficient model of the rocket/missile in the improved configuration is as follows: Al"i ile iii according to the relationship x" t X, : of the center-of-pressure coefficient P, the pitching moment coefficient Cm: of the rocket/missile and the normal force coefficient Cw of the rocket-missile, as well as the pitching moment coefficient model of the rocket/missile in the improved configuration, the center-of-pressure coefficient model of the rocket/missile in the improved configuration is obtained as follows:
- 6. A computer storage medium, characterized by storing a computer program which, when executed by a processor, leads to implementation of the steps of the pitching moment coefficient and center-of-pressure coefficient correction method for a rocket/missile according to any one of claims 1-5.
- 7. A server, characterized by comprising a memory and a processor, wherein the memory stores an executable program which, when invoked by the processor, leads to old mz 71011,CAT = Xcp,old * ref,r A/ tail ref Cy Claims implementation of the steps of the pitching moment coefficient and center-of-pressure coefficient correction method for a rocket /missile according to any one of claims 1-5.
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| PCT/CN2020/132800 WO2021098886A1 (en) | 2019-11-19 | 2020-11-30 | Pitching moment coefficient and center-of-pressure coefficient correction method for rocket projectile, and storage medium |
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| CN114486158B (en) * | 2021-12-30 | 2023-10-17 | 中国航天空气动力技术研究院 | Quick pre-estimating method for initial throwing condition of separation compatibility of machine and bullet of embedded weapon |
| CN114813030B (en) * | 2022-05-05 | 2023-06-16 | 南京理工大学 | Wind tunnel high rotator rotating speed posture adjusting and correcting capability test board |
| CN115577659A (en) * | 2022-12-11 | 2023-01-06 | 北京宇航系统工程研究所 | Pulse pressure environment design method and device based on similar configuration data |
| CN116183154B (en) * | 2023-04-24 | 2023-06-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Ultra-large attack angle wind tunnel test method for slender body model |
| 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 |
| CN117147093B (en) * | 2023-10-30 | 2024-01-23 | 中国航空工业集团公司沈阳空气动力研究所 | Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft |
| CN117951922B (en) * | 2024-03-26 | 2024-06-14 | 西安现代控制技术研究所 | Remote guidance rocket online aerodynamic coefficient identification method |
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