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摘要:
高机动飞机的机动载荷是机体结构强度主要设计约束，对飞机的机体结构质量和飞行疲劳损伤情况影响较大。面向高机动飞机对更轻机体结构和更长飞行使用寿命的要求，提出以法向过载为反馈参数，通过操纵面动态偏转实施机翼机动载荷控制的方法，以常规布局高机动飞机的典型极限机动为研究对象，综合分析机翼操纵面偏转影响优选了载荷控制策略，并完成了不同门限启动控制策略的机翼机动载荷控制效果仿真分析。结果表明：以75%最大法向过载为启动门限，按选定的策略将操纵面动态偏转5°，即可达到将机翼弯矩峰值降低10%的控制效果，所提方法在降低高机动飞机机体承载能力要求和减轻高机动飞机机体疲劳损伤方面具有重要的应用潜力和前景。
Abstract:For high-maneuverability aircraft, maneuver loads constitute the primary design constraint for airframe structural strength, significantly impacting structural mass and fatigue damage accumulation. To address the requirements for lighter airframes and extended service life, a wing maneuver load control methodology was developed utilizing normal acceleration load factor as the feedback parameter and implementing active control surface deflection. Focusing on typical extreme maneuvers of conventional-configuration high-maneuverability aircraft, an optimal load control strategy was derived through systematic evaluation of wing control surface deflection effects, thereby establishing deflection parameters for subsequent simulations. Comparative analyses of wing maneuver load control effectiveness were conducted for multiple threshold-initiated strategies. Results demonstrate that initiating control at 75% of the maximum normal load factor and applying a 5° deflection command reduces peak wing bending moment by 10%. This approach shows significant potential in reducing structural load-bearing requirements and mitigating fatigue damage in high-maneuverability aircraft, supporting structural integrity enhancement.
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Key words:
- high mobility aircraft /
- flight load /
- maneuvering load control /
- wing bending moment /
- control strategy
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图 7 机翼根部弯矩随操纵面角度的变化
Figure 7. Variation of wing root bending moment with control strategy
图 8 机翼中部弯矩随操纵面角度的变化
Figure 8. Variation of bending moment in middle of wing with control strategy
图 9 右前缘襟翼铰链力矩随操纵面角度的变化
Figure 9. Variation of hinge moment of right leading edge flap with control strategy
图 10 左内侧襟副翼铰链力矩随操纵面角度的变化
Figure 10. Variation of hinge moment of left inner flap and aileron with control strategy
图 11 右内侧襟副翼铰链力矩随操纵面角度的变化
Figure 11. Variation of hinge moment of right inner flap and aileron with control strategy
图 12 左外侧副翼铰链力矩随操纵面角度的变化
Figure 12. Variation of hinge moment of left outboard aileron with control strategy
图 13 右外侧副翼铰链力矩随操纵面角度的变化
Figure 13. Variation of hinge moment of right outboard aileron with control strategy
表 1 机动载荷计算工况
Table 1. Maneuvering load calculation condition
序号 $ {\mathrm{\delta }}_{\mathrm{l}\mathrm{e}} $/（°） $ {\mathrm{\delta }}_{\mathrm{t}\mathrm{e}} $/（°） $ {\mathrm{\delta }}_{\mathrm{a}} $/（°） 1 0 0 0 2 0 0 −5～5 3 0 −5～5 −5～5 4 −5 0 0 5 −5 0 −5～5 6 −5 −5～5 −5～5 
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表 2 机翼载荷峰值控制效果与对平尾的影响
Table 2. Control effect of wing load peak and its influence on horizontal tail
序号 工况 机翼载荷相对变化量/% 平尾载荷相对变化量/% 1 无控制 0 0 2 门限5g启动 −11.3 2.5 3 门限6g启动 −10.7 1.8 4 门限7g启动 −4.5 1.0
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