Forward folding tail rudder and its coupled design method of stability and maneuverability before and after folding

Abstract

The present invention belongs to the technical field of aerodynamic design of missile wings, and discloses a forward folding tail rudder and a method for coupling its stability and maneuverability before and after folding, including establishing geometric constraints of the folded state and the extended state of the tail rudder; taking the mounting space size of the folded state of the tail rudder as the design constraint to design and optimize the folded state of the tail rudder, and taking the maneuverability of the extended state of the tail rudder as the design constraint to design and optimize the extended state of the tail rudder; determining the hinge position; and determining the rotation axis position. The method for coupling its stability and maneuverability before and after folding of the forward folding tail rudder of the present invention comprehensively considers the shape parameters of the forward folding tail rudder in the folded and extended states, optimizes the aerodynamic performance of the tail rudder in the folded and extended states through an overall coupling design, improves the aerodynamic characteristics of a gliding aircraft with a forward folding tail rudder during the folding and extending process of the tail rudder, and has engineering practical value.

Description

Technical Field

[0001] The invention belongs to the technical field of missile wing aerodynamic design, and particularly relates to a forward folding tail rudder and a method for coupling the stability and maneuverability of the rudder before and after folding. Background Art

[0002] The tail rudder is one of the core components of a gliding aircraft, providing stability and control torque for the normal flight of the gliding aircraft.

[0003] With the development of stealth technology, gliding aircraft need to be stored in the embedded weapon bay, and the tail rudder is constrained by the mounting space and must be installed in a folded manner. The forward folding tail rudder is a common installation method. However, there is a huge difference in the aerodynamic performance of the tail rudder when it is folded and deployed, which brings great challenges to the flight control during launch and safe separation.

[0004] Currently, there is an urgent need to develop a forward folding tail rudder and a coupling design method for its stability and maneuverability before and after folding. Summary of the invention

[0005] One technical problem to be solved by the present invention is to provide a forward folding tail rudder and a method for coupling its stability and maneuverability before and after folding. Another technical problem to be solved by the present invention is to provide a forward folding tail rudder and a method for coupling its stability and maneuverability before and after folding to ensure that the stability and maneuverability requirements of the aircraft can be met before and after the tail rudder is folded.

[0006] The forward folding tail rudder of the present invention is located at the rear section of the body of the gliding aircraft;

[0007] The wing box of the forward folding tail rudder is fixed to the rear section of the missile body, and the wing surface of the tail rudder is fixed to the rotating shaft of the wing box. The wing surface rotates around the rotating shaft through a hinge to realize the folding and unfolding of the tail rudder; the rear section of the missile body is also provided with a groove matching the folded state of the tail rudder; when the tail rudder is folded, the trailing edge of the wing surface is flush with the top surface of the wing box, and the wing box forms a rectangular box body with a horizontal top surface;

[0008] Among them, the radius of the projectile is R; the length of the rudder surface when the rudder is retracted is L1; the length of the rudder surface when the rudder is extended is L2; ​​the maximum chord length of the rudder surface when the rudder is retracted is C1; the maximum chord length of the rudder surface when the rudder is extended is C2; the chord length of the wing tip when the rudder is extended is C3; the wing surface is a swept-edge wing, C2>C3; the horizontal distance between the hinge center and the rear side of the wing box is D1; ​​the vertical distance between the hinge center and the top surface of the wing box is D2.

[0009] The method for designing the coupling of stability and maneuverability of a forward folding tail rudder before and after folding of the present invention comprises the following steps:

[0010] S10. Establish geometric constraints for the rudder retracted state and the rudder deployed state;

[0011] The geometric constraints are as follows:

[0012] D1+D2=L1;

[0013] C2-D1 <R;

[0014] C1-D1+D2=L2;

[0015] S20. Design and optimize the rudder retracted state with the mounting space size of the rudder retracted as the design constraint, and design and optimize the rudder deployed state with the maneuverability of the rudder deployed as the design constraint;

[0016] S30. Determine the hinge position;

[0017] S40. Determine the position of the rotating shaft.

[0018] Furthermore, the design and optimization of the stern rudder retracted state using the mounting space size of the stern rudder retracted state as a design constraint condition of the S20 includes the following steps:

[0019] S201. Determine the rudder surface length L1 in the folded state;

[0020] The external envelope of the gliding aircraft body is determined according to the size of the embedded weapon bay, and then the rudder surface extension L1 in the rudder retracted state is determined according to the size of the external envelope in the rudder retracted state;

[0021] S202. Calculate the maximum chord length C1 of the rudder surface in the state of the rudder being retracted;

[0022] According to the stability requirements of the gliding aircraft when leaving the cabin, the maximum chord length C1 of the rudder surface in the rudder retracted state is calculated;

[0023] S203. Conduct numerical simulation and experimental analysis of static stability of rudder retracted state;

[0024] S204. Evaluate the performance of the rudder retracted state;

[0025] If the performance of the rudder retracted state meets the design index requirements, the maximum chord length C1 of the rudder retracted state is output; otherwise, the process returns to S202 to perform an iterative loop until the performance of the rudder retracted state meets the design index requirements.

[0026] Furthermore, the design and optimization of the rudder deployment state using the maneuverability of the rudder deployment state as a design constraint in S20 includes the following steps:

[0027] S211. Determine the rudder surface length L2 in the deployed state;

[0028] Determine the rudder surface extension length L2 in the rudder deployment state according to the maneuverability requirements of the rudder deployment state;

[0029] S212. Calculate the maximum chord length C2 of the rudder surface in the deployed state;

[0030] According to the maneuverability required by the aerodynamic performance of the rudder deployed state, calculate the maximum chord length C2 of the rudder surface in the rudder deployed state;

[0031] S213. Conduct numerical simulation and experimental analysis of static stability of rudder deployment state;

[0032] S214. Optimize the wing tip chord length C3 when the tail rudder is deployed;

[0033] According to the aerodynamic force distribution along the span of the wing surface, the chord length C3 of the wing tip in the deployed state of the tail rudder is optimized;

[0034] S215. Conduct performance evaluation of the rudder deployment status;

[0035] If the performance of the rudder deployment state meets the design index requirements, the maximum chord length C2 of the rudder deployment state control surface and the chord length C3 of the wing tip in the rudder deployment state are output; otherwise, the process returns to S212 for an iterative loop until the performance of the rudder deployment state meets the design index requirements.

[0036] The forward folding tail rudder and the method for coupling the stability and maneuverability thereof before and after folding of the present invention comprehensively consider the appearance parameters of the forward folding tail rudder in the folded and deployed states, optimize the aerodynamic performance of the tail rudder in the folded and deployed states through overall coupling design, improve the aerodynamic characteristics of the gliding aircraft with the forward folding tail rudder during the folding and deploying process of the tail rudder, and have practical engineering value. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1a It is a structural schematic diagram of the forward folding tail rudder of the present invention (the tail rudder is folded);

[0038] Figure 1b It is a structural schematic diagram of the forward folding tail rudder of the present invention (the tail rudder is deployed);

[0039] Figure 2a It is a schematic diagram of geometric parameters of the forward folding tail rudder of the present invention (projectile body);

[0040] Figure 2b Schematic diagram of geometric parameters of the forward folding tail rudder of the present invention (the tail rudder is folded);

[0041] Figure 2c Schematic diagram of geometric parameters of the forward folding tail rudder of the present invention (the tail rudder is deployed);

[0042] Figure 3A flow chart of the forward folding tail rudder and the method for coupling the stability and maneuverability thereof before and after folding according to the present invention;

[0043] In the figure, 1. missile body; 2. wing box; 3. wing surface; 4. hinge; 5. rotating shaft;

[0044] R: projectile radius; L1: rudder surface length when the rudder is retracted; L2: rudder surface length when the rudder is extended; C1: maximum rudder surface chord length when the rudder is retracted; C2: maximum rudder surface chord length when the rudder is extended; C3: wing tip chord length when the rudder is extended; D1: horizontal distance between the hinge center and the rear side of the wing box; D2: vertical distance between the hinge center and the top surface of the wing box. DETAILED DESCRIPTION

[0045] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0046] Example: Figure 1a , Figure 1b , Figure 2a~Figure 2c As shown, the forward folding tail rudder of this embodiment is located at the rear section of the body 1 of the gliding aircraft;

[0047] The wing box 2 of the forward folding tail rudder is fixed to the rear section of the missile body 1, and the wing surface 3 of the tail rudder is fixed on the rotating shaft 5 of the wing box 2. The wing surface 3 rotates around the rotating shaft 5 through the hinge 4 to realize the folding and unfolding of the tail rudder; the rear section of the missile body 1 is also provided with a groove matching the folded state of the tail rudder; in the folded state of the tail rudder, the trailing edge of the wing surface 3 is flush with the top surface of the wing box 2, and the wing box 2 forms a rectangular box body with a horizontal top surface;

[0048] Among them, the radius of the projectile 1 is R; the length of the rudder surface in the rudder retracted state is L1; the length of the rudder surface in the rudder extended state is L2; ​​the maximum chord length of the rudder surface in the rudder retracted state is C1; the maximum chord length of the rudder surface in the rudder extended state is C2; the chord length of the wing tip in the rudder extended state is C3; the wing surface 3 is a swept-edge wing, C2>C3; the horizontal distance between the center of the hinge 4 and the rear side of the wing box 2 is D1; ​​the vertical distance between the center of the hinge 4 and the top surface of the wing box 2 is D2.

[0049] like Figure 3 As shown, the method for coupling the stability and maneuverability of the forward folding tail rudder of this embodiment includes the following steps:

[0050] S10. Establish geometric constraints for the rudder retracted state and the rudder deployed state;

[0051] The geometric constraints are as follows:

[0052] D1+D2=L1;

[0053] C2-D1 <R;

[0054] C1-D1+D2=L2;

[0055] S20. Design and optimize the rudder retracted state with the mounting space size of the rudder retracted as the design constraint, and design and optimize the rudder deployed state with the maneuverability of the rudder deployed as the design constraint;

[0056] S30. Determine the position of hinge 4;

[0057] S40. Determine the position of the rotating shaft 5.

[0058] Furthermore, the design and optimization of the stern rudder retracted state using the mounting space size of the stern rudder retracted state as a design constraint condition of the S20 includes the following steps:

[0059] S201. Determine the rudder surface extension L1 in the folded state;

[0060] The outer envelope surface of the body 1 of the gliding aircraft is determined according to the size of the internal weapon compartment, and then the rudder surface extension L1 in the rudder retracted state is determined according to the size of the outer envelope surface in the rudder retracted state;

[0061] S202. Calculate the maximum chord length C1 of the rudder surface in the state of the rudder being retracted;

[0062] According to the stability requirements of the gliding aircraft when leaving the cabin, the maximum chord length C1 of the rudder surface in the rudder retracted state is calculated;

[0063] S203. Conduct numerical simulation and experimental analysis of static stability of rudder retracted state;

[0064] S204. Evaluate the performance of the rudder retracted state;

[0065] If the performance of the rudder retracted state meets the design index requirements, the maximum chord length C1 of the rudder retracted state is output; otherwise, the process returns to S202 to perform an iterative loop until the performance of the rudder retracted state meets the design index requirements.

[0066] Furthermore, the design and optimization of the rudder deployment state using the maneuverability of the rudder deployment state as a design constraint in S20 includes the following steps:

[0067] S211. Determine the rudder surface length L2 in the deployed state;

[0068] Determine the rudder surface extension length L2 in the rudder deployment state according to the maneuverability requirements of the rudder deployment state;

[0069] S212. Calculate the maximum chord length C2 of the rudder surface in the deployed state;

[0070] According to the maneuverability required by the aerodynamic performance of the rudder deployed state, calculate the maximum chord length C2 of the rudder surface in the rudder deployed state;

[0071] S213. Conduct numerical simulation and experimental analysis of static stability of rudder deployment state;

[0072] S214. Optimize the wing tip chord length C3 when the tail rudder is deployed;

[0073] According to the aerodynamic force distribution of the airfoil 3 along the span direction, the wing tip chord length C3 of the tail rudder in the deployed state is optimized;

[0074] S215. Conduct performance evaluation of the rudder deployment status;

[0075] If the performance of the rudder deployment state meets the design index requirements, the maximum chord length C2 of the rudder deployment state control surface and the chord length C3 of the wing tip in the rudder deployment state are output; otherwise, the process returns to S212 for an iterative loop until the performance of the rudder deployment state meets the design index requirements.

[0076] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the specification and implementation modes. For those familiar with the art, all features disclosed in the present invention, or steps in all methods or processes disclosed, except for mutually exclusive features and / or steps, can be combined in any way without departing from the principles of the present invention. The present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A design method for coupling stability and maneuverability of a forward folding tail rudder before and after folding, characterized in that: The forward folding tail rudder is located at the rear section of the body (1) of the gliding aircraft; The wing box (2) of the forward folding tail rudder is fixed to the rear section of the missile body (1), the wing surface (3) of the tail rudder is fixed to the rotating shaft (5) of the wing box (2), and the wing surface (3) rotates around the rotating shaft (5) through a hinge (4) to achieve the folding and unfolding of the tail rudder; the rear section of the missile body (1) is also provided with a groove matching the folded state of the tail rudder; in the folded state of the tail rudder, the trailing edge of the wing surface (3) is flush with the top surface of the wing box (2), and the wing box (2) forms a rectangular box body with a horizontal top surface; The radius of the missile body (1) is R; the length of the rudder surface when the rudder is retracted is L1; the length of the rudder surface when the rudder is deployed is L2; ​​the maximum chord length of the rudder surface when the rudder is retracted is C1; the maximum chord length of the rudder surface when the rudder is deployed is C2; the chord length of the wing tip when the rudder is deployed is C3; the wing surface (3) is a swept wing with leading edge, C2>C3; the horizontal distance between the center of the hinge (4) and the rear side of the wing box (2) is D1; ​​the vertical distance between the center of the hinge (4) and the top surface of the wing box (2) is D2; The method for designing the coupling of stability and maneuverability of the forward folding tail rudder before and after folding comprises the following steps: S10. Establish geometric constraints for the rudder retracted state and the rudder deployed state; The geometric constraints are as follows: D1+D2=L1; C2-D1 <R; C1-D1+D2=L2; S20. Design and optimize the rudder retracted state using the mounting space size of the rudder retracted state as a design constraint, including the following steps: S201. Determine the rudder surface length L1 in the folded state; The outer envelope of the body (1) of the gliding aircraft is determined according to the size of the internal weapon compartment, and then the rudder surface extension L1 in the rudder retracted state is determined according to the size of the outer envelope in the rudder retracted state; S202. Calculate the maximum chord length C1 of the rudder surface in the state of the rudder being retracted; According to the stability requirements of the gliding aircraft when leaving the cabin, the maximum chord length C1 of the rudder surface in the rudder retracted state is calculated; S203. Conduct numerical simulation and experimental analysis of static stability of rudder retracted state; S204. Evaluate the performance of the rudder retracted state; If the performance of the rudder retracted state meets the design index requirements, the maximum chord length C1 of the rudder retracted state is output; otherwise, the process returns to S202 for an iterative loop until the performance of the rudder retracted state meets the design index requirements; The design and optimization of the rudder deployment state are carried out with the maneuverability of the rudder deployed state as the design constraint, including the following steps: S211. Determine the rudder surface length L2 in the deployed state; Determine the rudder surface extension length L2 in the rudder deployment state according to the maneuverability requirements of the rudder deployment state; S212. Calculate the maximum chord length C2 of the rudder surface in the deployed state; According to the maneuverability required by the aerodynamic performance of the rudder deployed state, calculate the maximum chord length C2 of the rudder surface in the rudder deployed state; S213. Conduct numerical simulation and experimental analysis of static stability of rudder deployment state; S214. Optimize the wing tip chord length C3 when the tail rudder is deployed; According to the aerodynamic force distribution of the wing surface (3) along the span direction, the wing tip chord length C3 in the rudder deployment state is optimized; S215. Conduct performance evaluation of the rudder deployment status; If the performance of the rudder deployment state meets the design index requirements, the maximum chord length C2 of the rudder deployment state control surface and the chord length C3 of the wing tip in the rudder deployment state are output; otherwise, the process returns to S212 for an iterative loop until the performance of the rudder deployment state meets the design index requirements; S30. Determine the position of the hinge (4); S40. Determine the position of the rotating shaft (5).

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