CN114036651A - Low-resistance minor-caliber rotating body bullet body and design method - Google Patents
Low-resistance minor-caliber rotating body bullet body and design method Download PDFInfo
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- CN114036651A CN114036651A CN202210025718.0A CN202210025718A CN114036651A CN 114036651 A CN114036651 A CN 114036651A CN 202210025718 A CN202210025718 A CN 202210025718A CN 114036651 A CN114036651 A CN 114036651A
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Abstract
The invention is suitable for the technical field of aerodynamic layout design of aircrafts, and provides a low-resistance secondary caliber rotation body bullet body and a design method thereof, wherein the bullet body comprises a secondary caliber bullet body and a rectifying section; a transition section is arranged between the secondary caliber bullet body and the rectifying section; the diameter of the first end of the transition section is equal to the diameter R of the secondary caliber projectile1The diameter of the second end of the transition section is equal to the diameter R of the first end of the rectifying section2And R is1>R2(ii) a The end surface of the second end of the rectifying section is in a quincunx shape; the excircle diameter of the quincunx end surface is equal to the first end diameter R of the rectifying section2The diameter of the inner circle of the plum blossom-shaped end face is R3，R3=D/2+A，R3<R2D is the diameter of the outlet of the engine, and A is a set value. The design scheme of the invention can ensure that the body assembly of the spinning body is not additionally increasedThe length of the tail vane is ensured to be unchanged, and the aerodynamic resistance of the projectile body under the conditions of subsonic flight, straddle flight, hypersonic flight and hypersonic flight is effectively reduced.
Description
Technical Field
The invention relates to the technical field of aerodynamic layout design of aircrafts, in particular to a low-resistance sub-caliber rotating body bullet body and a design method thereof.
Background
The resistance is the component of aerodynamic force acting on an aircraft in the speed direction, is one of the key parameters of aircraft design, is always opposite to the speed direction, and for a remote aircraft taking a solid rocket engine as main power, the working time of the engine in the active section of the aircraft is generally short, the aircraft is in a passive section of unpowered flight state for most of the time, and the resistance has great influence on key technical indexes such as the range and the falling speed of the aircraft, so how to reduce the aerodynamic resistance of the aircraft is of great importance in the design of the aircraft. The layout scheme of the axisymmetric revolution body is used as the most common pneumatic layout form of the missile, has the characteristics of large internal volume, simple structural design and low heat-proof design difficulty, the pneumatic resistance of the scheme is closely related to the head curve and the tail shape of the revolution body, and for the research on the resistance reduction of the head curve of the revolution body, more research works are carried out at home and abroad at present to form various head curve shapes such as a Karman curve, a power body, a double cone and the like; for the research of the rear body drag reduction, related researchers provide a pneumatic layout design scheme for the rear body contraction drag reduction of a rotary body, and the drag reduction scheme achieves the purpose of reducing the pneumatic resistance by locally modifying the rear cylindrical missile body of the tail vane.
In recent years, launching of a launching canister/launching box becomes one of main launching modes of a rotating body missile, and one of key problems to be solved in pneumatic layout design is the pneumatic layout design problem under the strict geometric space constraint at the launching initial stage. The control surface is used as a main pneumatic component for the rotating body missile to fly, the design of the control surface needs to meet the requirement of full missile stability matching under the condition of a wide speed domain, generally speaking, the properly increased control surface extension length is beneficial to improving the flight stability and the control efficiency of the control surface, but the overlarge extension length cannot meet the requirement of a box type/cylinder type launching platform and can bring larger aerodynamic resistance, so that the difficulty of increasing the control surface extension length and reducing the flight resistance under the condition of meeting the launching geometric constraint is the difficulty of the pneumatic design of the missile. The minor caliber rotation body is a pneumatic layout scheme that the diameter of a rotation body in a tail rudder mounting area is slightly smaller than that of a front body, so that the extended length of a control surface arranged on the minor caliber body can be properly increased, and the requirements of limited space launching and outer trajectory flight stability are met. For the secondary caliber missile body with the tail rudder, the length of the body of the rotating missile body can be additionally increased by the traditional rear body contraction design scheme, and the drag reduction design cannot be realized due to the limitation of the size of the nozzle of the engine.
Disclosure of Invention
In order to solve the defects of the prior art, the invention provides a low-resistance minor-caliber rotating body bullet body and a design method thereof, which specifically comprise the following steps:
a low-resistance secondary caliber rotating body bullet body comprises a secondary caliber bullet body and a rectifying section;
a transition section is arranged between the secondary caliber bullet body and the rectifying section; the diameter of the first end of the transition section is equal to the diameter R of the secondary caliber projectile1A second end diameter of the transition section is equal to a first end diameter R of the rectifying section2And R is1>R2；
The end surface of the second end of the rectifying section is in a quincunx shape;
four tail rudders are uniformly distributed on the rectifying section;
the excircle diameter of the quincuncial end face is equal to the first end diameter R of the rectifying section2The diameter of the inner circle of the quincuncial end face is R3，R3=D/2+A，R3<R2D is the diameter of the outlet of the engine, and A is a set value.
Further, the second end faces of the rectifying sections are located in the same plane.
Furthermore, the surface of the transition section is also provided with four streamline profiles, and the streamline profiles are enclosed by two end part arcs of the transition section and two side lines; the sidelines are respectively tangent to the two end part arcs of the transition section.
The invention also provides a design method of the low-resistance minor caliber rotation body bullet body, which comprises the following steps:
s10, determining key design parameters of the body of the sub-caliber rotating body;
setting the first cylindrical section as a secondary caliber projectile body, setting the length L of the first cylindrical section1And a radius R1(ii) a Setting the length L of the second cylindrical section2And a radius R2(ii) a The bevel angle of the transition section between the first cylindrical section and the second cylindrical section is set toα；R1>R2；
S20, designing a secondary caliber afterbody drag reduction rectifying surface in the 1/8 circular arc range
S21, finding the intersection of the first cylindrical section and the transition section and the upper intersection point of the symmetrical plane are defined asaFinding the radius R in the plane of the back section of the second cylindrical section3And the intersection point of the point and the symmetrical plane is defined as a point b; the intersection point of the cross section of the second cylindrical section and the transition section and the symmetry plane is defined as a point c; the upper intersection point of the rear section of the second cylindrical section and the symmetrical plane is defined as a point d; the intersection point of the connecting line of the ab two points and the connecting line of the cd two points is set as a point e;abconnecting wire andcdthe angle of the connecting line isβ；The point e is located on the second cylindrical section;
s22, rotating the acd three points around the bullet shaft by 1/8 circular arcs to obtainm、l、q IIIPoint;
e point is located andan arc ef is selected on the vertical section of the second cylindrical section, wherein the angle of ef is set toλ；
In a circular arcefInsert three points from point e to point f in turng、h、iSetting a circular arcegAt an angle ofδArc of circleghAt an angle ofεCircular archiAt an angle ofζCircular arcifAt an angle ofηArc of circle thereinifShould satisfy:2if ≥ L d (ii) a Wherein L isdThe maximum thickness of the root chord section of the tail vane is obtained; the curve e-g-h-i-f is the second section S2The curve of (d);
the curve a-m being a first section S1The curve of (d);
rotate point b around the elastic shaftθ，θ=δ+ε，To obtainnPoint, arc of circleifTranslating backward by a distance Q, the length of the distance Q is equal to that of de, obtaining an arc pq, and connecting the pointnAnd pointpConnected by a quadratic curve, the quadratic curve being in contact with the circular arcbnAndpqtangent to obtain a third section S3Curve of (2)b-n-p-q；
S23 connection pointaePoint, pointmfAs a connection of the first section S1And a second cross section S2A connecting point ofebPoint, pointhnPoint, pointipPoint, pointfqAs a connection to the second section S2And a third section S3The guide line generates a sub-caliber rear body resistance-reducing rectifying surface in the range of 1/8 circular arcs by a multi-section three-dimensional modeling method;
and S24, the designed secondary caliber rear body drag reduction rectifying surface in the 1/8 range is symmetrical and rotated by utilizing an axisymmetric relation, and a complete secondary caliber rotating body is obtained.
Further, step S22 is followed by the following steps: in a circular arcamGet a point from abovejCircular arcajAngle and arc ofegThe angles are consistent;
in a circular arcclGet a point from abovekCircular arcklAngle of (2)φIs a circular archiAnd arc of a circleifTo sum, i.e.φ=ζ+η，jkThe two points are connected by a quadratic curve, and the quadratic curve is connected with the circular arcajAnd arc of a circleklTangent to obtain the fourth sectionNoodle S4Curve of (2)a-j-k-l；
In step S23, the connection pointaePoint, pointjgPoint, pointkhPoint, pointlfAs a connection to the fourth sectionS 4 And a second cross sectionS 2 Truncated guide wire, point of attachmentebPoint, pointhnPoint, pointipPoint, pointfqAs a connecting second sectionS 2 And a third cross sectionS 3 The guide line (2) generates a sub-caliber rear body drag reduction rectifying surface in the range of 1/8 circular arcs by a multi-section three-dimensional modeling method.
Further, in step S10, the length of the transition segment is L4And satisfies the following relationship:
further, in step S23,a-e-bthe connecting line of (A) is a straight line,l-f-qthe connecting line of (2) is a straight line.
Further, the length of the second cylindrical segmentL 2 Greater than the length of the tail rudder root chordL 3 。
Further, the arc bn corresponds to a diameter R3，R3And (4) = D/2+ A, wherein D is the diameter of an engine outlet and A is a set value.
Compared with the prior art, the low-resistance secondary caliber spinning body bullet body and the design method thereof have the following beneficial effects:
1. the aerodynamic layout scheme suitable for drag reduction of the sub-caliber rear body of the rotating body with the tail rudder can effectively reduce the aerodynamic resistance of the body under the conditions of sub-flight, span flight, ultra-high flight and hypersonic flight without additionally increasing the total length of the body of the rotating body and ensuring that the installation area of the tail rudder is not changed;
2. the invention provides a pneumatic layout design method suitable for drag reduction of a rear body of a sub-caliber rotating body projectile body by utilizing the circumferential geometrical relationship of the rotating body sub-caliber projectile body and fully considering the tail rudder installation area limitation and the influences of tail rudder root chord thickness, root chord length and the like, and is beneficial to drag reduction design optimization of the aircraft.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is an elevation view of a low resistance sub-caliber spinning body projectile body configuration according to an embodiment of the present invention;
FIG. 2(a) is a top view of the control surface root chord;
FIG. 2(b) is a front view of the control surface root chord;
FIG. 3 is a three-dimensional view of the low resistance sub-caliber spinning body configuration of an embodiment of the present invention;
FIG. 4 is a rear elevation view of a low resistance sub-caliber swivel body configuration in accordance with an embodiment of the present invention;
FIG. 5 is a first schematic diagram of a first rectifying surface position determining process according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a second process for determining the position of the rectifying surface according to the embodiment of the present invention;
FIG. 7(a) is a schematic view of the relationship between the arc angles corresponding to the curves e-g-h-i-f;
FIG. 7(b) is a schematic view of the relationship between the arc angles corresponding to the curves a-j-m;
FIG. 7(c) is a schematic view of the relationship between the arc angles corresponding to the curve c-k-l;
FIG. 7(d) is a schematic view showing the relationship between the arc angles corresponding to the curves b-n-p-q;
FIG. 8 is the result of an 1/8 arc cross-section sub-bore aft body design;
FIG. 9 is a comparison of the drag of the 0 angle of attack original profile and the aft drag reduction profile of the present invention;
figure 10 is a comparison of the drag of a 10 angle of attack original profile with an aft body drag reduction profile of the present invention.
In the figure, 1-minor caliber rotation body is a missile body, 2-tail rudder, 3-rectifying section, 4-transition section and 5-rectifyingFace, 6-fourth sectionS 4 Curve of (7) -second sectionS 2 Curve of (8) -third sectionS 3 Curve (c) of (d).
Detailed Description
The following description provides many different embodiments, or examples, for implementing different features of the invention. The particular examples set forth below are illustrative only and are not intended to be limiting.
Example 1
The embodiment provides a low-resistance minor-caliber rotating body missile body, which comprises a minor-caliber missile body 1, a tail rudder 2 and a rectifying section 3; a transition section 4 is arranged between the secondary caliber projectile body 1 and the rectifying section 3; the first end diameter of the transition section 4 is equal to the diameter R of the secondary caliber projectile body 11The diameter of the second end of the transition section 4 is equal to the diameter R of the first end of the rectifying section 32And R is1>R2(ii) a The end surface of the second end of the rectifying section 3 is in a quincunx shape; namely the rear end of the bullet body is plum blossom-shaped; the four tail rudders are uniformly distributed on the rectifying section, and the axes of the tail rudders are parallel to the axis of the secondary caliber elastic body; are respectively arranged at the central positions of the four petals of the plum blossom; as shown in fig. 1 and 3;
the excircle diameter of the quincuncial end face is equal to the first end diameter R of the rectifying section2The diameter of the inner circle of the quincuncial end face is R3，R3=D/2+A，R3<R2Wherein D is the diameter of an outlet of the engine, and A is a set value; as shown in fig. 4. It is worth to be noted that the excircle diameter of the plum blossom-shaped end face referred to in the present application refers to the diameter of the most protruding part of the four plum blossom petals, that is, the diameter of the maximum diameter position of the plum blossom-shaped end face; the diameter of the inner circle of the quincunx end face refers to the diameter of a part except for the petal structure and is also the diameter of the position with the minimum diameter of the quincunx end face, namely, the size of the quincunx end face is between the diameter of the first end of the rectifying section and the diameter of the outlet of the engine, and the value A can be determined empirically, as shown in fig. 4.
Preferably, the four tail rudders are respectively arranged at the positions where the plum blossom-shaped structures intersect with the outer circle.
The second end faces of the fairing sections lie in the same plane, i.e. the plum blossom end faces lie in the same plane, which is a plane perpendicular to the axis of the body of the bullet, as shown in figure 3.
Preferably, the surface of the transition section is also provided with four streamline profiles, and the streamline profiles are enclosed by two end part arcs of the transition section and two side lines; the sidelines are respectively tangent to the two end part arcs of the transition section. Wherein, the two end part arcs of the transition section mean: 1. the first end is connected with the secondary caliber elastic body, and the second end is connected with the rectifying section; the sidelines are respectively tangent to the two end curves, and the specific design method is shown in the embodiment 3.
Example 2
The embodiment provides a method for designing a low-resistance minor-caliber rotating body bullet body, which comprises the following steps:
s10, determining key design parameters of the body of the sub-caliber rotating body;
setting the first cylindrical section as a secondary caliber projectile body, setting the length L of the first cylindrical section1And a radius R1(ii) a Setting the length L of the second cylindrical section2And a radius R2(ii) a The bevel angle of the transition section between the first cylindrical section and the second cylindrical section is set toα；R1>R2(ii) a As shown in fig. 1;
s20, designing a secondary caliber rear body drag reduction rectifying surface within the arc range of 1/8, as shown in figures 5 and 6;
s21, finding the intersection of the first cylindrical section and the transition section and the upper intersection point of the symmetrical plane are defined asaFinding the radius R in the plane of the back section of the second cylindrical section3And the intersection point of the point and the symmetrical plane is defined as a point b; the intersection point of the cross section of the second cylindrical section and the transition section and the symmetry plane is defined as a point c; the upper intersection point of the rear section of the second cylindrical section and the symmetrical plane is defined as a point d; the intersection point of the connecting line of the ab two points and the connecting line of the cd two points is set as a point e; the point e is located on the second cylindrical section; r3=D/2+A，R3<R2D is the diameter of the outlet of the engine, and A is a set value;
s22, rotating the acd three points around the bullet shaft by 1/8 circular arcs to obtainm、l、q IIIPoint;
a circular arc ef is selected on a vertical section of the point e and the second cylindrical section, wherein the angle of ef is set to beλ；
In a circular arcefInsert three points from point e to point f in turng、h、iSetting a circular arcegAt an angle ofδArc of circleghAt an angle ofεCircular archiAt an angle ofζCircular arcifAt an angle ofηArc of circle thereinifShould satisfy:2if ≥ L d as shown in fig. 7(a) -7 (d); wherein L isdThe maximum thickness of the root chord section of the tail rudder is shown in fig. 2(a) and 2 (b); the curve e-g-h-i-f is the second section S2The curve of (d);
the curve a-m being a first section S1The curve of (d);
rotate point b around the elastic shaftθ，θ=δ+ε，To obtainnPoint, arc of circleifTranslate backward a certain distance equal to de to obtain arc pq, and point pnAnd pointpConnected by a quadratic curve, the quadratic curve being in contact with the circular arcbnAndpqtangent to obtain a third section S3Curve of (2)b-n-p-q；
It is worth noting that the arcs d-p-q and b-n are two concentric circles of different diameters and located on the same section, which is a section perpendicular to the axis of the body of the bullet;
s23 connection pointaePoint, pointmfAs a connection of the first section S1And a second cross section S2A connecting point ofebPoint, pointhnPoint, pointipPoint, pointfqAs a connection to the second section S2And a third section S3The guide line (2) generates a sub-caliber rear body drag reduction rectifying surface in the range of 1/8 circular arcs by a multi-section three-dimensional modeling method, as shown in fig. 8;
and S24, carrying out symmetry and rotation on the designed secondary caliber rear body drag reduction rectifying surface within the range of 1/8 by utilizing an axisymmetric relation to obtain a complete secondary caliber rotation body.
It can be understood by those skilled in the art that after the sub-caliber background rectifying surface in the range of 1/8 is obtained, the sub-caliber background rectifying surface in the range of 1/4 can be obtained by turning along the symmetrical surface, and then the 1/4 rectifying surface is sequentially rotated by 90 degrees, 180 degrees and 270 degrees to obtain another 3/4 rectifying surface, so as to combine into a complete sub-caliber rotating body bullet body. Of course, the projectile body can be obtained by various methods from 1/8 times caliber rectifying surface to complete sub-caliber rotating body, such as rotating and then turning, and the method listed in the embodiment is not a limitation to the present invention.
Of course, the skilled person lays out four tail rudders 2 on the fairing section, the tail rudders may be arranged at the positions of q-f-m in the above steps as in step S23 or S24 according to the design convention, and the length L of the tail rudders3Is less than the length L of the second cylindrical section2。
Example 3
Compared with the embodiment 2, the difference of the embodiment is that the transition section is also provided with a streamline profile, and the design method comprises the following steps:
the following steps are performed after step S22:
in a circular arcamGet a point from abovejCircular arcajAngle and arc ofegThe angles are consistent;
in a circular arcclGet a point from abovekCircular arcklAngle of (2)φIs a circular archiAnd arc of a circleifTo sum, i.e.φ=ζ+η，jkThe two points are connected by a quadratic curve, and the quadratic curve is connected with the circular arcajAnd arc of a circleklTangent to obtain a fourth section S4Curve of (2)a-j-k-l；
In step S23, the connection pointaePoint, pointjgPoint, pointkhPoint, pointlfAs a connection to the fourth sectionS 4 And a second cross sectionS 2 A connecting point ofebPoint, pointhnPoint, pointipPoint, pointfqAs a connecting second sectionS 2 And a third cross sectionS 3 The guide wire generates a sub-caliber rear body drag reduction rectification in the range of 1/8 circular arcs by a multi-section three-dimensional modeling methodFace, as shown in fig. 6;
and S24, the designed secondary caliber rear body drag reduction rectifying surface in the 1/8 range is symmetrical and rotated by utilizing an axisymmetric relation, and a complete secondary caliber rotating body is obtained.
In this embodiment, aj and ck are the two end arcs of the transition section, jk is a side line, and a-j-k-c enclose a streamlined profile of 1/2.
Example 4
In this example, the method of example 3 was used to set L1=1000mm，R1=400mm，L2=400mm，R 2 =380mm, root chord length of tail rudderL 3 =380mm，L d =50mm，α=60°，L 4 =11.547mm，D=680mm, a =10mm, the length between de is 238mm,abconnecting wire andcdangle of lineβ=7°；λ=45°Circular arcegAngle of (2)δ=13.5°Circular arcghAt an angle ofε=13.5°Circular archiAt an angle ofζ=13.5°Circular arcifAt an angle ofη=4.5°，φ=ζ+η=18°，θ=δ+εThe low-resistance minor-caliber spinning body is designed, the aerodynamic resistance of the shape before and after resistance reduction is evaluated by adopting a numerical simulation method, the Mach number range is analyzed to be 0.4-8.0, the comparison condition of the original shape of the attack angle of 0 degree and the attack angle of 10 degree and the resistance of the designed shape of the rear body are respectively given in figures 9 and 10, the dotted line in the figures is the resistance reduction shape of the minor-caliber rear body, and the resistance reduction design scheme provided by the patent achieves a certain resistance reduction effect under different Mach numbers, compared with the original shape scheme, the resistance is reduced by about 20% at the attack angle of 0 degree and 0.9, reduced by about 8% at the attack angles of 1.2, 1.5 and 2, and reduced by about 1% at the attack angles of 5 and 8; at an angle of attack of 10 deg., the drag is reduced by about 15% at mach numbers 0.4 and 0.9, about 7% at mach numbers 1.2, 1.5 and 2, and about 1.5% at mach numbers 5 and 8.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (9)
1. A low-resistance minor caliber spinning body is characterized by comprising a minor caliber body and a rectifying section;
a transition section is arranged between the secondary caliber bullet body and the rectifying section; the diameter of the first end of the transition section is equal to the diameter R of the secondary caliber projectile1A second end diameter of the transition section is equal to a first end diameter R of the rectifying section2And R is1>R2；
The end surface of the second end of the rectifying section is in a quincunx shape;
four tail rudders are uniformly distributed on the rectifying section;
the excircle diameter of the quincuncial end face is equal to the first end diameter R of the rectifying section2The diameter of the inner circle of the quincuncial end face is R3，R3=D/2+A，R3<R2D is the diameter of the outlet of the engine, and A is a set value.
2. The low drag, secondary caliber swivel body of claim 1 wherein the second end faces of the fairing sections are in the same plane.
3. The low-resistance minor-caliber spinning body bullet according to claim 1 or 2, wherein the transition surface further comprises four streamline profiles, and the streamline profiles are enclosed by two end arcs and two side lines of the transition; the sidelines are respectively tangent to the two end part arcs of the transition section.
4. A design method of a low-resistance minor-caliber rotating body bullet body is characterized by comprising the following steps:
s10, determining key design parameters of the body of the sub-caliber rotating body;
setting the first cylindrical section as a secondary caliber projectile body, setting the length L of the first cylindrical section1And a radius R1(ii) a Setting the length L of the second cylindrical section2And a radius R2(ii) a The bevel angle of the transition section between the first cylindrical section and the second cylindrical section is set toα；R1>R2；
S20, designing a secondary caliber afterbody drag reduction rectifying surface in the 1/8 circular arc range
S21, finding the intersection of the first cylindrical section and the transition section and the upper intersection point of the symmetrical plane are defined asaFinding the radius R in the plane of the back section of the second cylindrical section3And the intersection point of the point and the symmetrical plane is defined as a point b; the intersection point of the cross section of the second cylindrical section and the transition section and the symmetry plane is defined as a point c; the upper intersection point of the rear section of the second cylindrical section and the symmetrical plane is defined as a point d; the intersection point of the connecting line of the ab two points and the connecting line of the cd two points is set as a point e; the point e is located on the second cylindrical section;
s22, rotating the acd three points around the bullet shaft by 1/8 circular arcs to obtainm、l、q IIIPoint;
a circular arc ef is selected on a vertical section of the point e and the second cylindrical section, wherein the angle of ef is set to beλ；
In a circular arcefInsert three points from point e to point f in turng、h、iSetting a circular arcegAt an angle ofδArc of circleghAt an angle ofεCircular archiAt an angle ofζCircular arcifAt an angle ofηArc of circle thereinifShould satisfy:2if ≥ L d (ii) a Wherein L isdThe maximum thickness of the root chord section of the tail vane is obtained; the curve e-g-h-i-f is the second section S2The curve of (d);
the curve a-m being a first section S1The curve of (d);
rotate point b around the elastic shaftθ，θ=δ+ε，To obtainnPoint, arc of circleifTranslating backward by a distance Q, the length of the distance Q is equal to that of de, obtaining an arc pq, and connecting the pointnAnd pointpConnected by a quadratic curve, the quadratic curve being in contact with the circular arcbnAndpqtangent to obtain a third section S3Curve of (2)b-n-p-q；
S23 connection pointaePoint, pointmfAs a connection of the first section S1And a second cross section S2A connecting point ofebPoint, pointhnPoint, pointipPoint, pointfqAs a connection to the second section S2And a third section S3The guide line generates a sub-caliber rear body resistance-reducing rectifying surface in the range of 1/8 circular arcs by a multi-section three-dimensional modeling method;
and S24, the designed secondary caliber rear body drag reduction rectifying surface in the 1/8 range is symmetrical and rotated by utilizing an axisymmetric relation, and a complete secondary caliber rotating body is obtained.
5. The design method according to claim 4, wherein in step S20, after step S22, the following steps are further performed: in a circular arcamGet a point from abovejCircular arcajAngle and arc ofegThe angles are consistent;
in a circular arcclGet a point from abovekCircular arcklAngle of (2)φIs a circular archiAnd arc of a circleifTo sum, i.e.φ=ζ+η，jkThe two points are connected by a quadratic curve, and the quadratic curve is connected with the circular arcajAnd arc of a circleklTangent to obtain a fourth section S4Curve of (2)a-j-k-l；
In step S23, the connection pointaePoint, pointjgPoint, pointkhPoint, pointlfAs a connection to the fourth sectionS 4 And a second cross sectionS 2 A connecting point ofebPoint, pointhnPoint, pointipPoint, pointfqAs a connecting second sectionS 2 And a third cross sectionS 3 The guide line (2) generates a sub-caliber rear body drag reduction rectifying surface in the range of 1/8 circular arcs by a multi-section three-dimensional modeling method.
6. The design method according to claim 5, wherein in step S10, the length of the transition section is L4And satisfies the following relationship:
7. the designing method according to claim 6, wherein, in step S23,a-e-bthe connecting line of (A) is a straight line,l-f- qthe connecting line of (2) is a straight line.
8. A design method according to any one of claims 4 to 6, wherein the length of the second cylindrical section is greater than the length of the first cylindrical sectionL 2 Greater than the length of the tail rudder root chordL 3 。
9. A design method according to any one of claims 4-6, characterized in that the arc bn corresponds to a diameter R3，R3And (4) = D/2+ A, wherein D is the diameter of an engine outlet and A is a set value.
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