头锥结构在调整空天飞机的表面热流、温度和压力分布等方面发挥着重要作用。然而，目前的空天飞机头锥并不能随外部环境实时调整自身构型，无法使空天飞机获得实时最优的气动性能，极大地限制了其飞行的机动性和活动空间。设计可自如调整外形的可变体头锥机构、变形机构的实时锁定机构以及快速响应的变形驱动系统是空天飞机变体头锥设计的三大技术难点。为此，本项目将借鉴蜜蜂腹部灵活自如的变体能力，设计基于蜜蜂腹节肌肉-节间褶协同运动机制的变体头锥机构；研究腹部神经-肌肉的高效作动机制，给出腹部纵肌与环肌的笼式驱动模式，设计基于蜜蜂腹部肌肉群的分布式协同驱动布局；建立气动性能优化目标函数，对头锥的仿生设计进行参数灵敏度分析，获得各设计参数对空天飞机气动性能的影响程度，保证其在整个飞行过程获得最优的气动力、热特性，以提高空天飞行器的机动性能和作战效能。

The nose cone of aerospace plane plays an important role in adjusting the distribution of surface heat flux, temperature and pressure. However, the current nose cone of aerospace plane cannot respond optimally to the changes in the external environment, let alone obtain a real-time optimal aerodynamic performance. The constant structure of nose cone also greatly reduces the range of motion and flexibility. In this project, there are three major technical difficulties solved in the design of morphing nose cone, that is, the design of deformation mechanism, the real-time locking mechanism and the rapid-response deformation drive system. Firstly, we reveal the flexible deformation mechanism of honeybee abdomen. Secondly, a morphing nose cone is designed based on the synergistic effect of the terga/sterna, muscles and folded intersegmental membrane. Furthermore, the efficient mechanism of abdominal nerve-muscle actuation mechanism is revealed. Next, the power-distributed traction mode of morphing nose cone is designed based on the grid structure of abdominal muscles. At last, an optimal objective function of aerodynamic performance is established. In order to obtain the impact of morphing nose cone on the aerodynamic performance of aerospace plane, the parameter sensitivity of morphing nose cone is analyzed. The study will ensure the real-time optimal aerodynamic performance and improve the maneuvering performance and warfighting effectiveness of aerospace plane.