The spacecraft in the traditional yaw steering mode swings to and fro around the yaw axis with a certain angle leading to the spacecraft front or back directly exposed to the sunlight continuously. Therefore, this obstacle arises the urgent requirement for the thermal design of the equipment outside the spacecraft with extra weight and power loss cost. In the current study, the attitude control scheme of yaw steering with front and back pointing to the sun alternately is proposed, aimed at creating the better space thermal environment for the extravehicular equipment. In this mode, the spacecraft yaw-steers with the front pointing to the sun in one orbit period and the back pointing to the sun in the next orbit period with repeated circulating. So, regardless of the front or back of the spacecraft, the equipment all has more uniform temperature due to the uniformity originated from the sunlight, which could simplify the thermal design substantially. Especially for the equipment sensitive to the temperature changing, the large changing range of temperature could be avoided, which could increase the spacecraft reliability. Three attitude control methods of yaw steering with front and back pointing to the sun alternately are compared in the respects of power generation and propellant consumption. The method with the optimally aggregative indicator has been applied for Tianzhou-1 cargo spaceship in orbit successfully.