Fig.1

Schematic diagram of new environmental control system configuration for supersonic civil aircraft

Fig.2

MIL-STD-210A atmospheric environmental temperature

Fig.3

Cabin pressure schedule

Fig.4

Schematic diagram of fuel tank model

Table 1

Basic information on supersonic platform

Fig.5

Supersonic civil aircraft mission profile

Table 2

Estimation of cabin heat load

Table 3

Parameters used for simulation of single set of environmental control system

Fig.6

Turbine performance curves

Fig.7

Compressor performance curves

Fig.8

Variation of supply air and fuel section temperature with proportion of recirculated air

Fig.9

Variation of heat exchange capacity of heat exchangers with proportion of recirculated air

Fig.10

Variation of air supply and fuel section temperature with initial fuel temperature

Fig.11

Variation of heat exchange capacity of heat exchangers with initial fuel temperature

Fig.12

Variation of supply air and fuel section temperature with heat load of cabin

Fig.13

Variation of heat exchange capacity of heat exchangers with heat load of cabin

Fig.14

Temperature and pressure of air supply at each node of environmental control system

Fig.15

Fuel temperature and pressure at each node of fuel thermal management system

Fig.16

Variation of temperature of air supply and fuel with time in supersonic cruise phase

Fig.17

Relationship between designed flight time and initial fuel mass during supersonic cruise phase

Fig.18

Relationship between thermal endurance and initial fuel mass under varying ram air flow rates

Fig.19

Relationship between thermal endurance and initial fuel temperature under varying ram air flow rates

Fig.20

Engine bleed air pressure and temperature in deceleration and descent stage

Fig.21

Fuel consumption and heat load change of lubricating oil system with time in decelerating and descent stage

Fig.22

Variation of temperature of gas supply and fuel partial nodes with time during descent phase without activating fuel circulation loop

Fig.23

Influence of circulating fuel flow rate and ram air flow rate on system thermal flight time

Table 4

Influence of m˙f,re， m˙ra on ECS/TMS performance and hot flight time

Fig.24

Variation of system parameters with time in Condition 1 to Condition 3 （m˙f,re=0.05 kg/s）

Fig.25

Variation of system parameters with time in Condition 4 to Condition 6 （m˙f,re=0.20 kg/s）

Fig.26

Variation of system parameters with time in Condition 7 to Condition 9 （m˙f,re=0.80 kg/s）