Embedded flight parameter sensing system and calculation method for flying wing layout aircraft
Embedded flight parameter sensing system and calculation method for flying wing layout aircraft
- Neue Suche nach: WANG PENG
- Neue Suche nach: ZHAO JUNBO
- Neue Suche nach: WANG PENG
- Neue Suche nach: ZHAO JUNBO
The invention discloses an embedded flight parameter sensing system and a calculation method for a flying wing aircraft, and the method comprises the steps: (1), 10 pressure measurement holes pi (i = 1-10) are formed in the surface of a sharp leading edge, and the pressure of each pressure measurement hole is pi (i = 1-10); (2) establishing pressure data of 10 pressure measuring holes in the flight envelope by adopting a numerical modeling means; (3) establishing a nonlinear fitting relationship between pi (i = 1-6) and an attack angle based on a least square algorithm according to the pressure of the pressure measuring hole; (4) according to the fitting relation and real-time pressure input, an attack angle is output; (5) if the attack angle in the step (4) is greater than or equal to 0, establishing a nonlinear mapping relation between p1, p2, p3, p4, p8 and p10 and the Mach number, the sideslip angle and the static pressure based on a neural network algorithm, and executing a step (7); (6) if the attack angle in the step (4) is less than 0, establishing a nonlinear mapping relation between p1, p2, p3, p4, p7 and p9 and the Mach number, the sideslip angle and the static pressure based on a neural network algorithm; and (7) outputting the Mach number, the sideslip angle and the static pressure. The problem of high-precision atmosphere data acquisition under the condition that a stagnation point pressure measuring hole and a side edge pressure measuring hole cannot be configured is solved.
飞翼布局飞行器用嵌入式飞行参数传感系统及解算方法，包括：(1)在尖前缘表面配置10个测压孔pi(i＝1‑10)，各测压孔压力为pi(i＝1‑10)；(2)采用数值建模手段建立飞行包络内10个测压孔的压力数据；(3)根据测压孔的压力，基于最小二乘算法建立pi(i＝1‑6)与攻角的非线性拟合关系；(4)根据拟合关系和实时压力输入，输出攻角；(5)若步骤(4)中攻角≥0，基于神经网络算法建立p1,p2,p3,p4,p8,p10与马赫数、侧滑角及静压的非线性映射关系，执行步骤7；(6)若步骤(4)中攻角＜0，基于神经网络算法建立p1,p2,p3,p4,p7,p9与马赫数、侧滑角及静压的非线性映射关系；(7)输出马赫数、侧滑角及静压。解决了无法配置驻点测压孔及侧缘测压孔情形下高精度大气数据获取的难题。
Dokumentinformationen
Embedded flight parameter sensing system and calculation method for flying wing layout aircraft
飞翼布局飞行器用嵌入式飞行参数传感系统及解算方法
2024-04-05
Patent
Elektronische Ressource
Chinesisch
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