Thermal flight time of fuel heat management system for high speed vehicle

doi:10.11949/0438-1157.20191117

Abstract

Abstract:

At present, the airborne thermal load of high speed vehicle is increasing exponentially. But the temperature of the fuselage increases with the flight time due to the aerodynamic heating effect. These factors severely restrict the endurance of the high-speed vehicle and the working time of the electronic equipment. Fuel oil can be the preferred airborne heat sink because it is necessary to be carried liquid with large ratio heat capacity. The working temperature of fuel heat sink will be affected aerodynamic heating effect, consumption rate, flight time, comprehensively. In this paper, a fuel heat management system for high speed vehicle will be studied to analyze the influence of parameters design on the flight time. The dynamic characteristic equations were established for the fuel thermal management system. The concept of thermal fight time was further proposed to evaluate the flight time constrained by thermal load effect. The effects of the above factors and the design parameters on the fuel thermal management system were discussed in detail. The above work can provide a reference for the design and selection of the thermal management system for high speed vehicle.

Key words: high speed aircraft, heat management system, fuel heat sink, heat conduction, phase change, thermodynamics process

摘要：

目前高速飞行器机载热负荷呈指数上升趋势，而由于气动加热作用，机身温度随航时增长也持续上升，这两者严重限制了高速飞行器的续航时间和电子设备的使用时长。燃油作为飞行器所必须携带的大比热容液体工质，是机载热沉的优选。燃油热沉利用会受气动加热、耗油量、飞行时长的综合影响。本文以机载燃油热沉为核心，研究高速飞行器燃油热管理系统参数设计对飞行热航时的影响。建立了燃油-消耗性冷却剂热利用系统的动态特性方程，并提出热航时的概念以衡量热负荷作用下燃油不发生超温的飞行时长，详细讨论了上述各影响因素与热利用系统参数对热航时的影响。上述研究可为高速飞行器热管理系统设计选型提供参考。

关键词: 高速飞行器, 热管理系统, 燃油热沉, 热传导, 相变, 热力学过程

CLC Number:

V 245.3

Xiaodong YANG, Liping PANG, Rong A, Liang JIN. Thermal flight time of fuel heat management system for high speed vehicle[J]. CIESC Journal, 2020, 71(S1): 425-429.

杨晓东, 庞丽萍, 阿嵘, 金亮. 高速飞行器燃油热管理系统飞行热航时[J]. 化工学报, 2020, 71(S1): 425-429.

Figures/Tables 6

Fig.1 Structure of fuel heat management system

Table 1 Variable table

符号	变量	单位
E_cv	储存能	J
${\dot{Q}}_{a}$	气动加热量	W
${\dot{Q}}_{1}$	油箱流入控制体的能量	W
${\dot{Q}}_{h}$	机载热源发热量	W
${\dot{Q}}_{d}$	供给发动机能量	W
${\dot{Q}}_{c, m a x}$	蒸发器最大换热量	W
${\dot{m}}_{1}$	油箱出口燃油质量流量	kg·s^-1
T_e	附面层温度	K
T₁	油箱出口温度	K
U_a	附面层空气与燃油总传热系数	W·m^-2·K^-1
c_p	比定压热容	J·kg^-1·K^-1
${\dot{Q}}_{r}$	循环回路入控制体能量	W
${\dot{Q}}_{2}$	油箱流出控制体的能量	W
${\dot{Q}}_{3}$	进入消耗冷却剂换热器能量	W
ε_c	效能
${\dot{m}}_{r}$	循环回路燃油质量流量	kg·s^-1
T_ref	任意参考温度	K
T	燃油箱温度	K
T_lim	发动机油温限	K
A_a	油箱内壁瞬时润湿面积	m²

Table 1 Variable table

符号	变量	单位
E_cv	储存能	J
${\dot{Q}}_{a}$	气动加热量	W
${\dot{Q}}_{1}$	油箱流入控制体的能量	W
${\dot{Q}}_{h}$	机载热源发热量	W
${\dot{Q}}_{d}$	供给发动机能量	W
${\dot{Q}}_{c, m a x}$	蒸发器最大换热量	W
${\dot{m}}_{1}$	油箱出口燃油质量流量	kg·s^-1
T_e	附面层温度	K
T₁	油箱出口温度	K
U_a	附面层空气与燃油总传热系数	W·m^-2·K^-1
c_p	比定压热容	J·kg^-1·K^-1
${\dot{Q}}_{r}$	循环回路入控制体能量	W
${\dot{Q}}_{2}$	油箱流出控制体的能量	W
${\dot{Q}}_{3}$	进入消耗冷却剂换热器能量	W
ε_c	效能
${\dot{m}}_{r}$	循环回路燃油质量流量	kg·s^-1
T_ref	任意参考温度	K
T	燃油箱温度	K
T_lim	发动机油温限	K
A_a	油箱内壁瞬时润湿面积	m²

Fig.2 Relationship between design flight time and initial fuel carrying capacity

Fig.3 Relationship between initial fuel carrying capacity and thermal flight time

Fig.4 Influence of fuel flow limit on thermal flight time

Fig.5 Influence of fuel flow limit

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