A rudder tip and rudder shaft heat-resistant and reducing block and design method thereof

Abstract

The present invention relates to the technical field of aerodynamic layout design of aircraft, and discloses a heat-proof and heat-reducing block for a rudder tip and a rudder shaft and a design method thereof. The device comprises a projectile, a tail rudder, a rudder shaft and a heat-proof and heat-reducing block, wherein the tail rudder is distributed on the side of the projectile near the tail end, the rudder shaft is the central axis of the tail rudder, and the heat-proof and heat-reducing block is arranged at the front end of the tail rudder; the heat-proof and heat-reducing block is located in front of four tail rudders, symmetrically distributed in four quadrants, the front end intersects with the projectile to form an arc, the rear end face is perpendicular to the projectile surface, the width is greater than the diameter of the rudder shaft, the height is greater than the exposed height of the rudder shaft, and the installation position should keep a certain distance from the leading edge of the rudder. By adding a heat-proof and heat-reducing block at the front end of the tail rudder, the heat flow impact on the rudder tip and the rudder shaft can be reduced, and the aerodynamic thermal environment near the rudder tip and the rudder shaft can be improved, thereby improving the heat protection problem of the rudder tip and the rudder shaft of the aircraft.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft aerodynamic layout design, and in particular to a rudder tip and rudder shaft heat protection and reduction block and a design method thereof. Background Art

[0002] In order to make the aerodynamic control wing rudder of a high-speed aircraft rotate flexibly, there is a gap between the body and the wing rudder surface. The existence of the gap will cause high-speed hot air flow to enter, and produce a strong separation and reattachment area at the root of the rudder shaft, forming a high-heat, high-pressure, and high-shear harsh thermal environment, which is subject to extremely high aerodynamic heating, so high requirements are placed on the thermal protection of the rudder tip and rudder shaft. At present, the thermal control methods for high-speed aircraft mainly include passive thermal control technologies such as thermal control coatings, multi-layer thermal insulation systems, and ablation technology, as well as active thermal control technologies such as convection, sweat cooling, heat pipe technology, and thermophotovoltaics. Publicly published literature shows that the thermal control of hypersonic aircraft is mainly based on passive thermal control methods. Limited by the comprehensive thermal management and special structural requirements of hypersonic aircraft, the research on various new thermal control technologies is mostly in the exploratory stage.

[0003] At present, most of the domestic research on heat protection of rudder tips and rudder shafts adopts the traditional rudder shaft heat protection solution, that is, adding a rudder surface mounting platform between the missile body and the rudder surface, and adding a layout design of heat protection blocks on the rudder tips and rudder shafts. Although the traditional solution can reduce the heat flow impact on the air rudder tips and rudder shafts and improve the aerodynamic thermal environment near the rudder tips and rudder shafts, the resistance and weight are significantly increased. The resistance and weight have a great influence on key technical indicators such as the range and landing speed of the aircraft, so the traditional solution has obvious defects. Summary of the invention

[0004] The purpose of the present invention is to provide a rudder tip and rudder shaft heat protection and blocking block and a design method thereof to solve the above problems, and to improve the heat protection problem of the aircraft rudder tip and rudder shaft and the increase in resistance caused by adding heat protection components.

[0005] The technical scheme adopted by the present invention is as follows: a rudder tip and rudder shaft heat-resistant and reducing blocking block, comprising a projectile, a tail rudder, a rudder shaft and a heat-resistant and reducing blocking block, wherein the tail rudder is distributed on the side of the projectile near the tail end, the rudder shaft is the central axis of the tail rudder, and the heat-resistant and reducing blocking block is arranged at the front end of the tail rudder; the front end surface of the heat-resistant and reducing blocking block intersects with the projectile to form an arc, and the rear end surface of the heat-resistant and reducing blocking block is perpendicular to the surface of the projectile; the width of the heat-resistant and reducing blocking block is greater than the diameter of the projectile rudder shaft , and the height of the heat-resistant and heat-reducing blocking block is greater than the exposed height of the rudder shaft; there is a gap between the installation position of the heat-resistant and heat-reducing blocking block and the front end of the tail rudder, the distance is ; The exposed height of the rudder shaft is , the rear end height of the heat-resistant blocking block is ; The distance between the two end points of the rear end of the heat-reducing block is set to , the distance between the two end points of the rear top is set to ;

[0006] In order to meet the requirements of heat protection of rudder shaft and rudder tip, it is necessary to meet , , .

[0007] Furthermore, in order to make the resistance of the heat-proof and heat-reducing block smaller, its outer lines are set as curves; the two end points of the front end and the two end points of the rear end bottom of the heat-proof and heat-reducing block are connected on the surface of the projectile by curves, and the rear end top curve of the heat-proof and heat-reducing block is translated perpendicular to the projectile direction at the midpoint through the rear end bottom curve get.

[0008] Furthermore, in order to reduce the resistance of the heat-resistant and blocking block, the upper surface and side surfaces of the heat-resistant and blocking block are curved surfaces, and the rear end surface is a plane perpendicular to the projectile body.

[0009] Furthermore, a method for designing a heat-resistant and heat-reducing block for a rudder tip and a rudder shaft comprises the following steps:

[0010] S100: Determine the parameters of the projectile and the rudder shaft, and set the projectile length to The projectile diameter is , the rudder shaft diameter is , the exposed height of the rudder shaft is , the thickness of the tail rudder bottom is ,and ;

[0011] S200: Determine the parameters of the heat-resistant block and adjust the midpoint of the leading edge of the tail rudder Projected onto the outer surface of the missile, the point ,point To point The distance and the exposed height of the rudder shaft equal; point The distance from the midpoint of the rudder axis is ,point The midpoint of the bottom contour line of the rear end of the heat-resistant barrier The distance is ;point Translation in the direction of the projectile normal Get the midpoint of the top contour line of the rear end surface of the heat-resistant block ,point Pan forward Get the midpoint of the front face contour of the heat-resistant and heat-reducing block , and the straight line The angle with the projectile is ;

[0012] S300: Connecting the points in step S200 with curves and straight lines as the outer contour line of the heat-resistant and heat-reducing barrier block, and generating a three-dimensional outer contour surface of the heat-resistant and heat-reducing barrier block from the outer contour line of the heat-resistant and heat-reducing barrier block;

[0013] S400: The heat shield and tail rudder are symmetrical through an axisymmetric relationship.

[0014] By determining the relevant parameters of the projectile, rudder shaft and heat-resistant and anti-blocking block, and then determining the size, shape and position of the heat-resistant and anti-blocking block, the heat-resistant and anti-blocking block can be used to protect the heat and achieve the drag-reducing effect.

[0015] Furthermore, in step S200, the exposed height of the rudder shaft is , With point and Point distance The relationship is .

[0016] In order to further meet the needs of heat protection of the rudder shaft and rudder tip, Smaller than the midpoint of the bottom contour line of the rear end of the heat-resistant blocking block The midpoint of the top contour line of the rear end surface of the heat-resistant block The distance between , midpoint of the rudder leading edge Projected onto the outer surface of the missile, the point ,point The distance from the midpoint of the rudder axis is , Determined by the size of the rudder shaft and tail rudder.

[0017] Further, in step S200, the point , and Draw an arc for the midpoint; the specific steps include the following: As the midpoint, draw an arc on the projectile , endpoint To endpoint The distance is ; The arc By point As the starting point, translate in the direction of the projectile normal to point Get the arc ,in, For arc The midpoint and endpoint and endpoints The distance between ; with a point As the midpoint, draw an arc on the projectile , endpoint To endpoint The distance is ;in, .

[0018] The arc design can reduce the friction and resistance between the aircraft and the air when flying at high speed, thereby optimizing the aerodynamic performance of the aircraft. Especially at the front end of the aircraft, the arc shape can better guide the airflow, avoid the generation of strong shock waves, and thus reduce shock wave resistance. The arc shape can also more effectively disperse and alleviate the high temperature generated during flight, reducing the thermal shock to the aircraft structure. The arc design can reduce the vibration and load of the aircraft during flight, thereby reducing the risk of structural fatigue and damage.

[0019] Furthermore, the arc Angle , arc Angle .

[0020] The arc-shaped tail rudder can more flexibly adjust the attitude and direction of the aircraft, thereby improving control accuracy and response speed, ensuring that the aircraft can fly stably under complex conditions. The arc-shaped tail rudder can better utilize the lift and thrust generated by the airflow, thereby optimizing the flight performance of the aircraft.

[0021] Furthermore, in order to make the size of the heat-resistant and heat-reducing barrier block more accurate and achieve better results, the endpoints in step S200 are connected with curves and straight lines to form the outer contour line of the heat-resistant and heat-reducing barrier block:

[0022] The endpoint With endpoint In plane The endpoints are connected by quadratic curves. With endpoint Also on the plane The inner part is connected by quadratic curves. and curve About Plane symmetry;

[0023] The endpoint and endpoints Connecting quadratic curves to form a curve , the endpoint and endpoints Connect the curves to form a quadratic curve ,curve and curve About Plane symmetry;

[0024] The endpoint and endpoints Connect the lines to form a straight line , the endpoint and endpoints Connect the lines to form a straight line ,straight line and straight line About Plane symmetry;

[0025] The curve , , , and straight line and Constitute the outer contour line of the heat-resistant and barrier-reducing block.

[0026] Furthermore, the outer contour line of the heat-resistant and barrier-reducing block is generated by a three-dimensional modeling method to generate the outer contour surface of the heat-resistant and barrier-reducing block:

[0027] The curve ,curve ,straight line and curve Connect to form a surface ;

[0028] The curve ,curve and straight line Forming Surface ;

[0029] The curve ,curve and straight line Forming Surface ;

[0030] The curve ,curve ,straight line and straight line Forming Surface ;

[0031] By surface , , , Form the outer contour of the heat-resistant and barrier-reducing block.

[0032] Furthermore, the curved surface and Surface About Plane symmetry.

[0033] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0034] 1. By adding a heat-resistant block to the leading edge of the tail rudder, the heat flow impact on the rudder tip and the rudder shaft can be reduced, and the aerodynamic thermal environment near the rudder tip and the rudder shaft can be improved, thereby improving the heat protection problem of the rudder tip and the rudder shaft of the aircraft.

[0035] 2. By adding the layout design of the rudder tip and rudder shaft heat protection blocks, it can not only solve the problem of rudder shaft heat protection, but also effectively reduce the aerodynamic resistance of the projectile under subsonic, transonic, supersonic and hypersonic flight conditions.

[0036] 3. The outer contour line and each end point of the outer contour surface of the heat protection and resistance block are all correlated with each point of the tail rudder, making full use of the geometric relationship between the rudder shaft and the heat protection and resistance block, and considering the heat protection and aerodynamic drag reduction problems of the rudder shaft, optimizing the heat protection and drag reduction design of the rudder shaft. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 It is an isometric view of the rudder tip and rudder shaft heat-proof and blocking block of the present invention;

[0038] Figure 2 It is a rear view of the rudder tip and rudder shaft heat-proof and reducing blocking block of the present invention;

[0039] Figure 3 It is a front view showing the installation and dimensions of the rudder shaft, rudder tip and heat-resistant and anti-blocking block of the present invention;

[0040] Figure 4 It is a top view of the installation and dimensions of the rudder shaft, rudder tip and heat-resistant and blocking block of the present invention;

[0041] Figure 5 A rear view of the rear end design of the heat-resistant and anti-blocking block of the present invention;

[0042] Figure 6 It is a rear view of the front end design of the heat-proof and anti-blocking block of the present invention;

[0043] Figure 7 An isometric view of the front end design of the heat-resistant and anti-blocking block of the present invention;

[0044] Figure 8 is a flow chart of the method of the present invention;

[0045] Fig. 9 The drag comparison result of the traditional shape of the present invention at an angle of attack of 0° and the heat-resistant and drag-reducing shape of the present invention;

[0046] Fig.10 The results of heat flow comparison between the rudder tip and the rudder shaft of the traditional shape of the present invention at a 0° attack angle and the heat-resistant and drag-reducing shape of the present invention.

[0047] Label description: 1. Projectile body; 2. Tail rudder; 3. Rudder shaft; 4. Rudder surface mounting platform; 5. Heat-resistant and heat-reducing block; 6. Rear end face of heat-resistant and heat-reducing block; 7. Left side curved surface of heat-resistant and heat-reducing block; 8. Right side curved surface of heat-resistant and heat-reducing block; 9. Upper surface of heat-resistant and heat-reducing block. DETAILED DESCRIPTION

[0048] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0049] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0050] like Figure 1 As shown, a rudder tip and rudder axis heat-resistant and blocking block comprises a projectile 1, a tail rudder 2 and a heat-resistant and blocking block 5. The tail rudder 2 is arranged on a rudder surface mounting platform 4, the central axis of the tail rudder 2 is the rudder axis 3, the tail rudder 2 is distributed on the side of the projectile 1 near the tail end, and the heat-resistant and blocking block 5 is arranged at the front end of the tail rudder 2. The tail rudder 2 is provided with four pieces, and the four tail rudders 2 are symmetrically distributed in four quadrants with the rudder axis 3 and the rays perpendicular to the rudder axis 3 as coordinate axes, and the heat-resistant and blocking blocks 5 are also symmetrically distributed in the four quadrants.

[0051] The layout design scheme of adding rudder tip and rudder shaft heat protection blocks can not only solve the problem of rudder shaft heat protection, but also effectively reduce the aerodynamic resistance of the projectile under subsonic, transonic, supersonic and hypersonic flight conditions.

[0052] like Figure 2-5 As shown, the front end surface of the heat-proof and heat-reducing blocking block 5 intersects with the projectile 1 to form an arc, and the rear end surface of the heat-proof and heat-reducing blocking block 5 is perpendicular to the surface of the projectile 1; the width of the heat-proof and heat-reducing blocking block 5 is greater than the diameter of the rudder shaft 3 of the projectile 1 , and the height of the heat-proof and heat-reducing blocking block 5 is greater than the exposed height of the rudder shaft 3, and the installation position of the heat-proof and heat-reducing blocking block 5 maintains a certain distance from the leading edge of the tail rudder 2; the upper surface and side surfaces of the heat-proof and heat-reducing blocking block 5 are both curved surfaces, and the rear end surface is a plane perpendicular to the projectile body 1.

[0053] There is a gap between the installation position of the heat-proof and heat-reducing blocking block 5 and the front end of the tail rudder 2, the distance is ; The exposed height of the rudder shaft 3 is , the rear end height of the heat-proof blocking block 5 is ; Heat-reducing barrier block 5 rear end bottom end point distance is set to , the distance between the two end points of the rear top is set to ;in, , , .

[0054] like Figure 3-8As shown, a method for designing a heat-resistant and anti-blocking block for a rudder tip and a rudder shaft comprises the following steps:

[0055] S100: Determine the parameters of the missile body 1 and the rudder axis, and set the length of the missile body 1 to , the diameter of projectile 1 is , the rudder shaft diameter is , the exposed height of the rudder shaft 3 is , the thickness of the bottom of the tail rudder 2 is ,and ;

[0056] S200: Determine the parameters of the heat-resistant block 5, and adjust the midpoint of the leading edge of the tail rudder 2 Projected on the outer surface of the projectile 1, the point ,point To point The distance between the exposed height of the rudder axis 3 equal; point The distance from the midpoint of the rudder axis 3 is ,point The midpoint of the bottom contour line of the rear end of the heat-proof and heat-reducing blocking block 5 The distance is ;point Translate in the direction of the normal of projectile 1 Get the midpoint of the top contour line of the rear end surface of the heat-resistant block ,point Pan forward Get the midpoint of the front end contour of the heat-resistant and blocking block 5 , and the straight line The angle between the projectile and the projectile 1 is ;

[0057] S300: Connecting the points in step S200 with curves and straight lines as the outer contour line of the heat-resistant and heat-reducing barrier block, and generating a three-dimensional outer contour surface of the heat-resistant and heat-reducing barrier block from the outer contour line of the heat-resistant and heat-reducing barrier block;

[0058] S400: The heat-resistant and anti-blocking block 5 and the tail rudder 2 are symmetrically arranged through an axisymmetric relationship.

[0059] In step S200, the exposed height of the rudder shaft 3 is With point and Point distance The relationship is , It is determined according to the size of the rudder shaft 3 and the tail rudder 2.

[0060] In step S200, the , and Draw an arc for the midpoint; the specific steps include the following: As the midpoint, draw an arc on the projectile 1 , endpoint To endpoint The distance is ;

[0061] The arc By point As the starting point, move in the direction of the normal of body 1 to point Get the arc ,in, For arc The midpoint and endpoint and endpoints The distance between ;

[0062] By point As the midpoint, draw an arc on the projectile 1 , endpoint To endpoint The distance is ;

[0063] in, .

[0064] The arc Angle , arc Angle .

[0065] The endpoints in step S200 are connected with curves and straight lines to form the outer contour line of the heat-resistant and blocking block 5:

[0066] The endpoint With endpoint In plane The endpoints are connected by quadratic curves. With endpoint Also on the plane The inner part is connected by quadratic curves. and curve About Plane symmetry;

[0067] The endpoint and endpoints Connecting quadratic curves to form a curve , the endpoint and endpoints Connect the curves to form a quadratic curve ,curve and curve About Plane symmetry;

[0068] The endpoint and endpoints Connect the lines to form a straight line , the endpoint and endpoints Connect the lines to form a straight line ,straight line and straight line About Plane symmetry;

[0069] The curve , , , and straight line and It forms the outer contour line of the heat-proof and barrier-reducing block 5.

[0070] The outer contour line of the heat-resistant and barrier block is generated by a three-dimensional modeling method to generate the outer contour surface of the heat-resistant and barrier block:

[0071] The curve ,curve ,straight line and curve Connect to form a surface ;

[0072] The curve ,curve and straight line Forming Surface ;

[0073] The curve ,curve and straight line Forming Surface ;

[0074] The curve ,curve ,straight line and straight line Forming Surface ;

[0075] By surface , , , It forms the outer contour of the heat-proof and barrier-reducing block 5.

[0076] The curved surface and Surface About Plane symmetry.

[0077] Example

[0078] Step 1: Determine the key design parameters of the missile body 1 and the rudder shaft 3, including the length of the missile body 1 , radius of projectile 1 , rudder axis 3 radius , rudder axis 3 exposed height , Tail rudder 2 bottom thickness ;

[0079] Step 2: Determine the key design parameters of the heat-resistant block 5. The specific values ​​are as follows: The distance between the heat-resistant block 5 and the tail rudder 2 , heat-resistant block 5 height , the length of the heat-proof blocking block 5 The angle between the heat-resistant blocking block 5 and the projectile 1 is ;

[0080] First, determine the installation position and size of the rudder shaft 3, rudder tip and heat-resistant blocking block 5. Projected on the surface of projectile 1, point ,point With point The distance is Exposed height with rudder axis 3 Same; point The midpoint of the bottom contour line of the rear end surface of the heat-proof and blocking block 5 The distance between the heat-resistant block 5 and the tail rudder 2 is ;point With point The distance is the height of the heat-proof blocking block 5 ,point With point The distance is the length of the heat-proof blocking block 5 , at this time the straight line The angle between the projectile and the projectile 1 is .

[0081] Then determine the typical endpoints of the heat-proof and blocking block 5, refer to Figure 7 ,by As the midpoint, draw an arc on the projectile 1 , whose angle is , endpoint With endpoint The distance is ; The arc By point The starting point is translated to point 1 in the normal direction of the projectile Get the arc , For arc The midpoint and endpoint and endpoints The distance between ;by As the midpoint, draw an arc on the projectile 1 , whose angle is , endpoint With endpoint The distance is , such as Figure 6 As shown;

[0082] Step three: connect each endpoint with curves and straight lines to construct the outer contour line of the heat-resistant and barrier-reducing block 5, and generate the contour surface of the heat-resistant and barrier-reducing block 5 using a three-dimensional modeling method.

[0083] First, connect the end points of the heat-proof and heat-reducing blocking block 5 with a straight line or a curve. With endpoint In plane The endpoints are connected by quadratic curves. With endpoint Also on the plane The inner part is connected by quadratic curves. and curve About Plane Symmetrical; on the surface of the projectile 1, Dot and Points are connected by quadratic curves to form curves , Dot and Points are connected by curves to form quadratic curves ,curve and curve About Plane symmetry; Dot and Points are connected by straight lines to form a straight line , Dot and Points are connected by straight lines to form a straight line ,straight line and straight line About Plane symmetry;

[0084] Then, the three-dimensional modeling method is used to generate the external surfaces of the heat-proof and heat-reducing barrier block 5, and the curve is transformed into the ,curve ,straight line and curve Connect to form a surface , that is, the rear end face 6 of the heat-resistant and blocking block; using a three-dimensional modeling method to curve ,curve and straight line Forming Surface , that is, the left side curved surface 7 of the heat-proof and blocking block; using a three-dimensional modeling method to ,curve and straight line Forming Surface , that is, the right side curved surface 8 of the heat-resistant and blocking block; using a three-dimensional modeling method to ,curve ,straight line and straight line Forming Surface , i.e. the upper surface 9 of the heat-proof and heat-reducing barrier block;

[0085] It should be noted that the front end of the heat-proof and heat-reducing blocking block is an arc formed by connecting the upper surface 9 of the heat-proof and heat-reducing blocking block and the projectile 1. , the lower end surface of the heat-proof and blocking block coincides with the surface of the projectile 1; the curved surface and Surface About Plane symmetry.

[0086] Finally, the surface , , , The outer contour of the heat-resistant and barrier block is as follows: Figure 7 As shown;

[0087] Step 4: Now the heat-resistant and heat-reducing blocking block 5 and the tail rudder 2 are symmetrically connected using an axial symmetry relationship to obtain a design scheme for the heat-resistant and heat-reducing blocking blocks for the rudder tip and the rudder shaft.

[0088] In order to verify the effectiveness of this embodiment, the aerodynamic drag of the traditional shape and the heat-resistant drag-reducing shape was evaluated by numerical simulation method, and the Mach number range was 0.4 to 7.0. Fig. 9 The drag comparison between the traditional shape and the heat-resistant drag-reducing shape at a 0° attack angle is given. In the figure, the square solid line is the traditional shape, and the triangle dotted line is the heat-resistant drag-reducing shape. It can be seen that the drag reduction design method proposed in this embodiment has achieved a certain drag reduction effect at different Mach numbers. Compared with the traditional shape, at a 0° attack angle, the drag is reduced by more than 15% at Mach numbers 0.4 and 0.8, the drag is reduced by about 10% at Mach numbers 1.2, 1.5 and 2, the drag is reduced by about 5% at Mach numbers 3 and 4, and the drag is reduced by more than 3% at Mach numbers 5, 6 and 7.

[0089] like Fig.10 As shown in the figure, for the heat protection problem of the rudder tip and rudder shaft, the thermal flux of the original shape and the heat protection and drag reduction shape were evaluated by numerical simulation method. Fig.10A comparison of the heat flux (Q) of the rudder tip and rudder shaft of the original shape and the heat-resistant drag reduction shape at a Mach number of 7 and an angle of attack of 0° is given. It can be seen that after installing the heat-resistant drag reduction block, the heat flux of the rudder tip and rudder shaft is significantly reduced, with the heat flux of the rudder tip decreasing by 78% and the heat flux of the rudder shaft decreasing by 86%.

[0090] Numerical simulation data show that the rudder tip and rudder shaft heat protection and blocking block and its design method provided in this embodiment can effectively reduce the resistance of the aircraft and can also significantly reduce the heat flow of the rudder tip and rudder shaft, and improve the aerodynamic thermal environment near the rudder tip and rudder shaft.

[0091] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A heat-resistant and anti-blocking block for a rudder tip and a rudder shaft, characterized in that: It includes a missile body, a tail rudder, a rudder shaft and a heat-resistant and heat-reducing blocking block. The tail rudder is distributed on the side of the missile body near the tail end. The rudder shaft is the central axis of the tail rudder. The heat-resistant and heat-reducing blocking block is arranged at the front end of the tail rudder. The front end surface of the heat-proof and heat-reducing block intersects with the projectile to form an arc, and the rear end surface of the heat-proof and heat-reducing block is perpendicular to the surface of the projectile; the width of the heat-proof and heat-reducing block is greater than the diameter of the rudder shaft of the projectile , and the height of the heat-proof and heat-reducing blocking block is greater than the exposed height of the rudder shaft; There is a gap between the installation position of the heat-resistant block and the front end of the tail rudder. The distance is ; The exposed height of the rudder shaft is , the rear end height of the heat-resistant blocking block is ; The distance between the two end points of the rear end bottom of the heat-reducing block is set to , the distance between the two end points of the rear top is set to ; in, , , .

2. A rudder tip and rudder shaft heat protection and blocking block according to claim 1, characterized in that: The two end points of the front end and the two end points of the rear end bottom of the heat-proof and heat-reducing blocking block are connected on the surface of the projectile by a curve, and the rear end top curve of the heat-proof and heat-reducing blocking block is translated at a distance perpendicular to the projectile direction at the midpoint through the rear end bottom curve. get.

3. A rudder tip and rudder shaft heat protection and blocking block according to claim 1, characterized in that: The upper surface and side surfaces of the heat-resistant and anti-blocking block are curved surfaces, and the rear end surface is a plane perpendicular to the projectile body.

4. A method for designing a heat-resistant and anti-heat-reducing block for a rudder tip and a rudder shaft, using a heat-resistant and anti-heat-reducing block for a rudder tip and a rudder shaft as claimed in any one of claims 1 to 3, characterized in that: The method comprises the following steps: S100: Determine the parameters of the projectile and the rudder shaft, and set the projectile length to The projectile diameter is , the rudder shaft diameter is , the exposed height of the rudder shaft is , the thickness of the tail rudder bottom is ,and ; S200: Determine the parameters of the heat-resistant block and adjust the midpoint of the leading edge of the tail rudder Projected onto the outer surface of the missile, the point ,point To point The distance and the exposed height of the rudder shaft equal; point The distance from the midpoint of the rudder axis is ,point The midpoint of the bottom contour line of the rear end of the heat-resistant barrier The distance is ;point Translation in the direction of the projectile normal Get the midpoint of the top contour line of the rear end surface of the heat-resistant block ,point Pan forward Get the midpoint of the front face contour of the heat-resistant and heat-reducing block , and the straight line The angle with the projectile is ; S300: Connecting the points in step S200 with curves and straight lines as the outer contour line of the heat-resistant and heat-reducing barrier block, and generating a three-dimensional outer contour surface of the heat-resistant and heat-reducing barrier block from the outer contour line of the heat-resistant and heat-reducing barrier block; S400: The heat shield and tail rudder are symmetrical through an axisymmetric relationship.

5. A method for designing heat-resistant and anti-blocking blocks for rudder tips and rudder shafts according to claim 4, characterized in that: In step S200, the exposed height of the rudder shaft is , With point and Point distance The relationship is .

6. A method for designing heat-resistant and anti-blocking blocks for rudder tips and rudder shafts according to claim 4, characterized in that: In step S200, the , and Draw an arc for the midpoint; the specific steps include the following: As the midpoint, draw an arc on the projectile , endpoint To endpoint The distance is ; The arc By point As the starting point, translate in the direction of the projectile normal to point Get the arc ,in, For arc The midpoint and endpoint and endpoints The distance between ; By point As the midpoint, draw an arc on the projectile , endpoint To endpoint The distance is ; in, .

7. A method for designing heat-resistant and anti-blocking blocks for rudder tips and rudder shafts according to claim 6, characterized in that: The arc Angle , arc Angle .

8. A method for designing heat-resistant and anti-blocking blocks for rudder tips and rudder shafts according to claim 6, characterized in that: Connect the endpoints in step S200 with curves and straight lines to form the outer contour line of the heat-resistant and barrier-reducing block: The endpoint With endpoint In plane The endpoints are connected by quadratic curves. With endpoint Also on the plane The inner part is connected by quadratic curves. and curve About Plane symmetry; The endpoint and endpoints Connecting quadratic curves to form a curve , the endpoint and endpoints Connect the curves to form a quadratic curve ,curve and curve About Plane symmetry; The endpoint and endpoints Connect the lines to form a straight line , the endpoint and endpoints Connect the lines to form a straight line ,straight line and straight line About Plane symmetry; The curve , , , and straight line and Constitute the outer contour line of the heat-resistant and barrier-reducing block.

9. A method for designing heat-resistant and anti-blocking blocks for rudder tips and rudder shafts according to claim 8, characterized in that: The outer contour line of the heat-resistant and barrier block is generated by a three-dimensional modeling method to generate the outer contour surface of the heat-resistant and barrier block: The curve ,curve ,straight line and curve Connect to form a surface ; The curve ,curve and straight line Forming Surface ; The curve ,curve and straight line Forming Surface ; The curve ,curve ,straight line and straight line Forming Surface ; By surface , , , Form the outer contour of the heat-resistant and barrier-reducing block.

10. A method for designing heat-resistant and anti-blocking blocks for rudder tips and rudder shafts according to claim 9, characterized in that: The curved surface and Surface About Plane symmetry.

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