[1] Snigirev A, Snigireva I, Kohn V, et al. On the possibilities of X-ray phase contrast micro-imaging by coherent high-energy synchrotron radiation[J]. Rev Sci Instrum, 66, 5486-5492(1995).

[2] [2] Fetter S, Sessler A M, Cnwall M, et al. Countermeasures: A technical evaluation of the operational effectiveness of the planned US national missile defense system [EBOL]. [20231013]. https:drum.lib.umd.eduhle19034333.

[3] [3] Degges T G, Smith H J P. A high altitude infrared radiance model[R]. AFGLTR770271, 1977.

[4] Liu Tao, Jiang Weidong, Li Xiang, et al. Simulation calculation of synamic infrared radiation characteristics of the target in ballistic midcourse[J]. Infrared and Laser Engineering, 37, 955-958(2008).

[5] Wilkins S W, Gureyev T E, Gao D, et al. Phase-contrast imaging using polychromatic hard X-rays[J]. Nature, 384, 335-338(1996).

[6] Zhang Jun, Yang Hua, Ling Yongshun, et al. Theoretical analysis of temperature field on the surface of ballistic missile warhead in midcourse[J]. Infrared and Laser Engineering, 34, 582-586(2005).

[7] She Eryong, Ma Hongmei, Ding Yuzheng, et al. Design of midcourse surveillance and tracking simulation system for ballistic missile[J]. Aerospace Control, 25, 68-72(2007).

[8] Hu Wei, Yang Jianjun, Wang Sen, et al. TBM′s midcourse infrared radiation traits modeling and simulation[J]. Optoelectronic Technology, 29, 240-243(2009).

[9] Chen Naiguang. Temperature changing rule of ballistic missile[J]. Aerospace Electronic Warfare, 23, 5-8(2007).

[10] Lu Xiaofei, Sheng Jie. Review of surface temperature of ballistic missile in flight[J]. Infrared, 37, 1-6(2015).

[11] [11] Wang Zhen. Research on the thermalcontrol method f aircraft wings thermal perfmance analysis of the heat pipe [D]. Nanjing: Nanjing University of Aeronautics Astronautics, 2009. (in Chinese)

[12] Fay J A, Riddell F R. Theory of stagnation point heat transfer in dissociated air[J]. J Aero Sci, 25, 73-85(1958).

[13] Lees L. Laminar heat transfer over blunt nosed bodies at hypersonic flight speed[J]. Jet Propulsion, 26, 259-269(1956).

[14] [14] Zhang Z C. Hypersonic Aerothermodynamic Thermal Protection[M]. Beijing: National Defence Industry Press, 2003: 8485. (in Chinese)

[15] [15] Chen K K. Three dimensional nosetip shape changes in hypersonic flow. Part 1: Illustration of a mathe matical modelacteristic method[R]. AIAA73 0762, 1973.

[16] [16] Baker R L. Low temperature ablat nosetip shape change at angle of attack[R]. AIAA7290, 1972.

[17] Rong Yisheng, Liu Weiqiang. Reseach on accommodation parameter of linear bridging relation for blunt cone in transitional regime[J]. Acta Physica Sinica, 61, 040508(2012).

[18] [18] Engel C D, Praharaj S C. Miniver upgrade f the avid system. Volume 1: Lanmin user′s manual[R]. NASA CR172212,1983.

[19] Shi Anhua, Shi Weibo, Sun Haihao, et al. The effect of detector installing structure on wall temperature measurement of vehicle[J]. Journal of Experiments in Fluid Mechanics, 30, 32-36(2016).

[20] Guo Yijun. Analysis of ablative thermal response of charring material with engineering applications[J]. Acta Aerodynamica Sinica, 12, 94-99(1994).

[21] Shi Weibo, Sun Haihao, Yu Zhefeng, et al. The analysis of infrared radiation characteristics for HTV-2-like hypersonic gliding vehicle body[J]. Infrared, 43, 26-34(2022).