A coupling research method for aerodynamic design and verification of a large aspect ratio foldable wing aircraft

Abstract

The present invention belongs to the technical field of aircraft design, and discloses a coupling research method for aerodynamic design and verification of a large aspect ratio foldable wing aircraft. The coupling research method includes determining the shape of the wing in a folded state; determining the shape of the wing in an expanded state; preliminarily establishing the aerodynamic shape of the wing, carrying out numerical simulation analysis of aerodynamic characteristics and gliding performance analysis; performing aerodynamic optimization design to determine the aerodynamic shape of the wing; performing wing structure design and optimization based on the aerodynamic shape of the wing; performing aerodynamic characteristic verification of the wing; performing safety analysis and verification to obtain a large aspect ratio foldable wing aircraft that meets the requirements of flutter safety and wing deployment safety. The coupling research method is based on the independent separation of aerodynamic design and verification work, and by coordinating the various sub-items of aerodynamic design and verification, it adjusts the work order, shortens the design cycle, reduces the design cost, and improves the design success rate, and has engineering practical value.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft design, and in particular relates to a method for coupling aerodynamic design and verification of an aircraft with large aspect ratio and foldable wings. Background Art

[0002] High aspect ratio foldable wings have excellent lift and lift-to-drag ratio characteristics and are widely used in the aerodynamic shape design of modern aircraft, especially the aerodynamic shape design of subsonic cruise aircraft and the aerodynamic shape design of gliding extended-range aircraft. Before the launch or release of the aircraft, the high aspect ratio foldable wings are in a folded state. After the launch or release, the high aspect ratio foldable wings are quickly unfolded to present a high aspect ratio gliding configuration. Due to space limitations, the relative thickness and plane shape of the high aspect ratio foldable wings are subject to strict constraints. These constraints are contradictory to the requirements of high normal overload capacity, excellent gliding performance, and matching of aircraft stability and maneuverability of the high aspect ratio wings, resulting in a high difficulty in the aerodynamic design of high aspect ratio foldable wing aircraft. At the same time, the success or failure of the aerodynamic design of high aspect ratio foldable wing aircraft must pass a series of evaluation and verification work. Generally, aerodynamic design and verification work are independent and separate. Even if there is a certain degree of coupling between aerodynamic design and verification, the unreasonable order of design and verification sub-items will directly lead to a longer aircraft aerodynamic design cycle, higher costs, or even cause the failure of the design work.

[0003] Currently, there is an urgent need to develop a coupled research method for aerodynamic design and verification of large aspect ratio foldable-wing aircraft. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a method for coupling aerodynamic design and verification of a large aspect ratio foldable wing aircraft to overcome the defects of the prior art.

[0005] The aerodynamic design and verification coupling research method of the large aspect ratio foldable wing aircraft of the present invention comprises the following steps:

[0006] S10. Determine the appearance of the wing in the folded state;

[0007] Analyze the dimensional constraints of the large aspect ratio foldable wing aircraft and determine the envelope size of the folded wing, including the length L, width D and height H of the folded wing envelope.

[0008] S20. Determine the shape of the wing in the deployed state;

[0009] Analyze the total weight, glide speed and flight distance constraints of the large aspect ratio foldable wing aircraft, preliminarily determine the wing sweep angle, plane shape and airfoil shape when the wing is deployed; and determine the body shape;

[0010] S30. Preliminarily establish the aerodynamic shape of the wing, conduct numerical simulation analysis of aerodynamic characteristics and glide performance analysis;

[0011] According to the shape of the missile body and considering the envelope size requirements of the wing folded state, the plane shape of the wing is further optimized, and the folding form and hinge axis position of the wing are determined;

[0012] According to the plane shape of the wing and the sweep angle and plane shape of the wing when the wing is deployed, an AA scheme is formed;

[0013] S40. Perform aerodynamic optimization design and determine the aerodynamic shape of the wing;

[0014] Based on the AA scheme, numerical simulation of the aerodynamic characteristics of the aircraft and analysis of the gliding performance are carried out; according to the results of the gliding performance analysis, the wing planform and airfoil shape of the AA scheme are aerodynamically optimized using the global optimization method of the proxy model or the adjoint optimization method based on the gradient until the gliding performance requirements are met, and the BB scheme is obtained;

[0015] S50. Design and optimize the wing structure according to the aerodynamic shape of the wing;

[0016] Determine the material and structural form of the BB solution, perform wing strength and flutter safety analysis based on numerical simulation, optimize and determine the material and structural form, and obtain the BB+CC solution that meets the strength and flutter safety requirements;

[0017] S60. Verify the aerodynamic characteristics of the wing;

[0018] The aerodynamic characteristic data of the large aspect ratio foldable wing aircraft is obtained through wind tunnel tests, and the gliding performance evaluation is carried out based on the aerodynamic characteristic data; if the pre-set requirements are not met, return to S40 and continue the aerodynamic optimization design until the large aspect ratio foldable wing aircraft meets the pre-set requirements, and finally determine the aerodynamic shape of the wing to obtain the DD+CC solution;

[0019] S70. Conduct safety analysis and verification to obtain a large aspect ratio foldable wing aircraft that meets the requirements of flutter safety and wing deployment safety;

[0020] Conduct flutter safety and wing deployment safety tests on the DD+CC scheme. Based on the test verification results, determine whether to continue optimizing the material and structural form of the DD+CC scheme. If further optimization is required, return to S50 for further iteration, and ultimately form a DD+EE scheme with an aerodynamic shape that meets the flutter safety and wing deployment safety requirements.

[0021] Furthermore, the S50 comprises the following steps:

[0022] S51. Evaluate the aerodynamic loads of the BB scheme through numerical simulation within the flight envelope;

[0023] S52. Preliminary determination of the materials and structural form of the BB scheme;

[0024] S53. Under the aerodynamic load determined in S51, perform finite element analysis to evaluate whether the strength of the wing meets the strength requirements. If not, optimize the material and structural form of the BB solution until the strength requirements are met;

[0025] S54. Conduct flutter safety analysis. If the flight envelope requirements are not met, continue to optimize the structural form and counterweight form of the BB solution to form a BB+CC solution that meets the strength and flutter safety requirements.

[0026] Furthermore, the S60 includes the following steps:

[0027] S61. Conduct wind tunnel test verification of aerodynamic characteristics of BB+CC scheme;

[0028] S62. Conduct static aeroelastic impact analysis on the BB+CC scheme;

[0029] S63. Carry out numerical simulation or wind tunnel test on the Reynolds number effect of the BB+CC scheme and conduct Reynolds number effect analysis;

[0030] S64. Establish a corrected aerodynamic database for the static aeroelasticity and Reynolds number effects of the BB+CC scheme;

[0031] S65. Conduct gliding performance evaluation of BB+CC scheme;

[0032] S66. Based on the wind tunnel test verification of the aerodynamic characteristics of S61 and the gliding performance evaluation results of S65, choose whether to further optimize the BB+CC scheme.

[0033] The large aspect ratio foldable wing aircraft aerodynamic design and verification coupling research method of the present invention realizes the standardization and comprehensiveness of the large aspect ratio foldable wing aircraft aerodynamic design and verification work and the rationality of the coupling sequence of each sub-item work, shortens the design cycle, improves the design quality, and has engineering practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 The present invention is a flow chart of the aerodynamic design and verification coupling research method of the large aspect ratio foldable wing aircraft. DETAILED DESCRIPTION

[0035] The present invention is further described in detail below with reference to the accompanying drawings and embodiments.

[0036] Example: Figure 1As shown, the aerodynamic design and verification coupling research method of the large aspect ratio foldable wing aircraft of this embodiment includes the following steps:

[0037] S10. Determine the appearance of the wing in the folded state;

[0038] Analyze the dimensional constraints of the large aspect ratio foldable wing aircraft and determine the envelope size of the folded wing, including the length L, width D and height H of the folded wing envelope.

[0039] S20. Determine the shape of the wing in the deployed state;

[0040] Analyze the total weight, glide speed and flight distance constraints of the large aspect ratio foldable wing aircraft, preliminarily determine the wing sweep angle, plane shape and airfoil shape when the wing is deployed; and determine the body shape;

[0041] S30. Preliminarily establish the aerodynamic shape of the wing, conduct numerical simulation analysis of aerodynamic characteristics and glide performance analysis;

[0042] According to the shape of the missile body and considering the envelope size requirements of the wing folded state, the plane shape of the wing is further optimized, and the folding form and hinge axis position of the wing are determined;

[0043] According to the plane shape of the wing and the sweep angle and plane shape of the wing when the wing is deployed, an AA scheme is formed;

[0044] S40. Perform aerodynamic optimization design and determine the aerodynamic shape of the wing;

[0045] Based on the AA scheme, numerical simulation of the aerodynamic characteristics of the aircraft and analysis of the gliding performance are carried out; according to the results of the gliding performance analysis, the wing planform and airfoil shape of the AA scheme are aerodynamically optimized using the global optimization method of the proxy model or the adjoint optimization method based on the gradient until the gliding performance requirements are met, and the BB scheme is obtained;

[0046] S50. Design and optimize the wing structure according to the aerodynamic shape of the wing;

[0047] Determine the material and structural form of the BB solution, perform wing strength and flutter safety analysis based on numerical simulation, optimize and determine the material and structural form, and obtain the BB+CC solution that meets the strength and flutter safety requirements;

[0048] S60. Verify the aerodynamic characteristics of the wing;

[0049] The aerodynamic characteristic data of the large aspect ratio foldable wing aircraft is obtained through wind tunnel tests, and the gliding performance evaluation is carried out based on the aerodynamic characteristic data; if the pre-set requirements are not met, return to S40 and continue the aerodynamic optimization design until the large aspect ratio foldable wing aircraft meets the pre-set requirements, and finally determine the aerodynamic shape of the wing to obtain the DD+CC solution;

[0050] S70. Conduct safety analysis and verification to obtain a large aspect ratio foldable wing aircraft that meets the requirements of flutter safety and wing deployment safety;

[0051] Conduct flutter safety and wing deployment safety tests on the DD+CC scheme. Based on the test verification results, determine whether to continue optimizing the material and structural form of the DD+CC scheme. If further optimization is required, return to S50 for further iteration, and ultimately form a DD+EE scheme with an aerodynamic shape that meets the flutter safety and wing deployment safety requirements.

[0052] Furthermore, the S50 comprises the following steps:

[0053] S51. Evaluate the aerodynamic loads of the BB scheme through numerical simulation within the flight envelope;

[0054] S52. Preliminary determination of the materials and structural form of the BB scheme;

[0055] S53. Under the aerodynamic load determined in S51, perform finite element analysis to evaluate whether the strength of the wing meets the strength requirements. If not, optimize the material and structural form of the BB solution until the strength requirements are met;

[0056] S54. Conduct flutter safety analysis. If the flight envelope requirements are not met, continue to optimize the structural form and counterweight form of the BB solution to form a BB+CC solution that meets the strength and flutter safety requirements.

[0057] Furthermore, the S60 includes the following steps:

[0058] S61. Conduct wind tunnel test verification of aerodynamic characteristics of BB+CC scheme;

[0059] S62. Conduct static aeroelastic impact analysis on the BB+CC scheme;

[0060] S63. Carry out numerical simulation or wind tunnel test on the Reynolds number effect of the BB+CC scheme and conduct Reynolds number effect analysis;

[0061] S64. Establish a corrected aerodynamic database for the static aeroelasticity and Reynolds number effects of the BB+CC scheme;

[0062] S65. Conduct gliding performance evaluation of BB+CC scheme;

[0063] S66. Based on the wind tunnel test verification of the aerodynamic characteristics of S61 and the gliding performance evaluation results of S65, choose whether to further optimize the BB+CC scheme.

[0064] 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 coupling research method for aerodynamic design and verification of a large aspect ratio foldable wing aircraft, characterized in that: The following steps are involved: S10. Determine the appearance of the wing in the folded state; Analyze the dimensional constraints of the large aspect ratio foldable wing aircraft and determine the envelope size of the folded wing, including the length L, width D and height H of the folded wing envelope. S20. Determine the shape of the wing in the deployed state; Analyze the total weight, glide speed and flight distance constraints of the large aspect ratio foldable wing aircraft, preliminarily determine the wing sweep angle, plane shape and airfoil shape when the wing is deployed; and determine the body shape; S30. Preliminarily establish the aerodynamic shape of the wing, conduct numerical simulation analysis of aerodynamic characteristics and glide performance analysis; According to the shape of the missile body and considering the envelope size requirements of the wing folded state, the plane shape of the wing is further optimized, and the folding form and hinge axis position of the wing are determined; According to the plane shape of the wing and the sweep angle and plane shape of the wing when the wing is deployed, an AA scheme is formed; S40. Perform aerodynamic optimization design and determine the aerodynamic shape of the wing; Based on the AA scheme, numerical simulation of the aerodynamic characteristics of the aircraft and analysis of the gliding performance are carried out; according to the results of the gliding performance analysis, the wing planform and airfoil shape of the AA scheme are aerodynamically optimized using the global optimization method of the proxy model or the adjoint optimization method based on the gradient until the gliding performance requirements are met, and the BB scheme is obtained; S50. Design and optimize the wing structure according to the aerodynamic shape of the wing; Determine the material and structural form of the BB solution, perform wing strength and flutter safety analysis based on numerical simulation, optimize and determine the material and structural form, and obtain the BB+CC solution that meets the strength and flutter safety requirements; S60. Verify the aerodynamic characteristics of the wing; The aerodynamic characteristics data of the large aspect ratio foldable wing aircraft were obtained through wind tunnel tests, and the gliding performance evaluation was carried out based on the aerodynamic characteristics data; If the preset requirements are not met, return to S40 and continue the aerodynamic optimization design until the large aspect ratio foldable wing aircraft meets the preset requirements, and finally determine the aerodynamic shape of the wing to obtain the DD+CC solution; S70. Conduct safety analysis and verification to obtain a large aspect ratio foldable wing aircraft that meets the requirements of flutter safety and wing deployment safety; Conduct flutter safety and wing deployment safety tests on the DD+CC scheme. Based on the test verification results, determine whether to continue optimizing the material and structural form of the DD+CC scheme. If further optimization is required, return to S50 for further iteration, and ultimately form a DD+EE scheme with an aerodynamic shape that meets the flutter safety and wing deployment safety requirements.

2. The aerodynamic design and verification coupling research method for a large aspect ratio foldable wing aircraft according to claim 1 is characterized in that: The S50 comprises the following steps: S51. Evaluate the aerodynamic loads of the BB scheme through numerical simulation within the flight envelope; S52. Preliminary determination of the materials and structural form of the BB scheme; S53. Under the aerodynamic load determined in S51, perform finite element analysis to evaluate whether the strength of the wing meets the strength requirements. If not, optimize the material and structural form of the BB solution until the strength requirements are met; S54. Conduct flutter safety analysis. If the flight envelope requirements are not met, continue to optimize the structural form and counterweight form of the BB solution to form a BB+CC solution that meets the strength and flutter safety requirements.

3. The aerodynamic design and verification coupling research method for a large aspect ratio foldable wing aircraft according to claim 1 is characterized in that: The S60 comprises the following steps: S61. Conduct wind tunnel test verification of aerodynamic characteristics of BB+CC scheme; S62. Conduct static aeroelastic impact analysis on the BB+CC scheme; S63. Carry out numerical simulation or wind tunnel test on the Reynolds number effect of the BB+CC scheme and conduct Reynolds number effect analysis; S64. Establish a corrected aerodynamic database for the static aeroelasticity and Reynolds number effects of the BB+CC scheme; S65. Conduct gliding performance evaluation of BB+CC scheme; S66. Based on the wind tunnel test verification of the aerodynamic characteristics of S61 and the gliding performance evaluation results of S65, choose whether to further optimize the BB+CC scheme.

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