## 5 Conclusions  
In conclusion, this study proposes a novel thrust control configuration to optimize the landing stability of BWB aircraft with distributed electric BLI propulsors. In its passive state, the apparatus acts as a horizontal stabilizer, contributing to the overall stability of the aircraft. Upon its activation during landing, the device not only decelerates the aircraft, but also augments lift, effectively mitigating the issues of settlement and altitude loss. Ground-based testing yielded the following conclusions:  
1. The novel thrust control configuration can effectively adjust the thrust to 0 without adjusting the BLI fan speed of the propulsion system, improving the landing stability of BWB aircraft and solving the tightly coupled problem between lift and thrust caused by BLI fans sucking in the boundary layer. The challenge in using flaps and engine thrust reversers to decelerate electric BWB aircraft can be overcome.
2. The symmetrical deflection of both cascades of the thrust control configuration can increase lift and provide an upward moment. This indicates that the deflection of the thrust control configuration significantly changes the flow field state and can be adjusted to achieve the goal of augmenting lift and reducing drag in landing and approach use scenarios. The additional upward moment provided meets the requirements for larger attitude angles, which can replace the upward movement of elevators and improve aerodynamic efficiency.
3. The asymmetric deflection scheme can achieve a zero additional pitch moment with specific deflection angle combinations and effectively adjust the thrust to 20% while maintaining the original additional lift effects and producing some additional lift benefits. This method also achieves the objectives of augmenting lift and reducing drag without inducing additional changes in the pitch moment.  
This research received no external funding.  
Not applicable.  
\begin{table}
\begin{tabular}{p{113.8 pt} p{113.8 pt} p{113.8 pt} p{113.8 pt}} \hline \multicolumn{1}{p{113.8 pt}}{**To Maintain Lift and Reduce Speed**} & \multicolumn{1}{p{113.8 pt}}{**Traditional Tube-and-Wing Aircraft**[53, 54]} & \multicolumn{1}{p{113.8 pt}}{**Aeroengine-Powered BWB Aircraft with Novel Thrust Control Configuration**} \\ \hline Advantages & 1. Simple structure, easy to operate and maintain. 2. Mature design suitable for various applications. & 1. Greater lift augmentation due to central bellow flaps. 2. Reduced interference with roll and pitch control, enhancing stability. & 1. Enhanced landing safety and controllability with thrust control configuration. 2. Without additional pitch moments. 3. Suitable for electric BWB without a fuel engine. \\ \hline Disadvantages & 1. Difficult to use flaps and spoilers in BWB designs due to aerodynamic coupling between wings and fuselage. & 1. Belly flaps may cause flow separation. 2. Impossible to use engine thrust reversers in electric BWB aircraft. & 1. Complex structure increases the difficulty in design and maintenance. 2. Requires precise control to avoid instability. \\ \hline \end{tabular}
\end{table}
Table 1: Cont.  
Data Availability Statement: The original contributions presented in the study are included in the article, further inquiries can be directed to the corresponding author.  
The authors declare no conflicts of interest.