###### Abstract
[PERSON] and [PERSON] [37] discussed yaw control in aircraft with distributed electric propulsion, demonstrating that more engines allow for smaller tail planes and reduced fuel consumption. [PERSON] et al. [38] assessed BWB aircraft design, emphasizing stability, control, and performance trade-offs, and suggested a static stability criterion. [PERSON] et al. [39] used gradient-based optimization for improved wind tunnel testing and recommended design and optimization strategies for BWB aircraft with high lift and control surfaces. [PERSON] et al. [40] investigated the static stability in BWB-type aircraft with center-body leading-edge carving, showing stability across a wide range of attack angles and developing a methodology for determining the carving amount. [PERSON] et al. [41] investigated the impact of a new thrust reverser on the aerodynamic performance of a BWB propulsion system using numerical simulations. In the field of takeoff and landing safety research, [PERSON] et al. [42] developed a soft switching mode for eVTOL compound-wing UAVs to enhance their robustness and safety, using dynamic inversion to mitigate lift loss during deceleration, thereby ensuring smoother transitions and better passenger comfort. [PERSON] et al. [43] addressed the landing safety in a BWB RPV using a system-theoretic analysis to mitigate \"path sagging\" with a \"belly-flap\" control surface, which was confirmed as being effective in flight tests. [PERSON] et al. [44] examined the use of belly flaps in BWB airplanes to increase lift and address control challenges, which was validated by wind tunnel tests. [PERSON] et al. [45] studied externally blown elevons in BWB aircraft, showing their efficiency over conventional elevons through CFD methods. [PERSON] et al. [46] evaluated the aerodynamic performance of a BWB re-entry vehicle at low speeds, providing insights into the lift performances and vortex phenomena for static stability. [PERSON] et al. [47] used CFD to analyze the pitch control needed for landing in a blended-wing-body UCAV, exploring belly flaps to solve low-speed landing issues. Lastly, [PERSON] et al. [48] presented a landing safety prediction model for critical flight phases using pattern recognition, Markov chains, and a neural network with a genetic algorithm, which enhanced prediction precision. In the landing phase, an aircraft must use thrust reversers to augment drag and decelerate the aircraft. Conventional commercial airplanes primarily employ three types of thrust reversal mechanisms, as follows: bucket, cascade, and petal. However, these thrust control configurations tend to cause aircraft to stall due to the induced airflow disturbances, which are detrimental to the maintenance of lift on the wings. These disturbances in the airflow field can engender unstable flight conditions during landing, thereby elevating the risk of stalling and reducing the landing stability of BWB aircraft. In terms of research on thrust control, [PERSON] et al. [49] examined the use of a thrust reverser cascade in BWB300 civil airplanes; employing CFD, they found that it could be effectively applied to reduce landing distance, similar to in standard turbofan planes, but noted a design trade-off with an increased reverse mass flow and closingvelocity. [PERSON] et al. [50] delved into the dynamic modeling of this mechanism, noting nonlinearities due to clearance and flexibility; they highlighted that joint clearance and flexible parts affect the kinematics, dynamics, and vibration of the system, underscoring the importance of actuator synchronization. BLI fans, located on the upper surface of the aircraft, can ingest boundary-layer air, increasing the airflow velocity over the wings and reducing the pressure on the upper surface, thereby providing additional lift. However, BWB aircraft with distributed electric BLI propulsors face challenges in thrust control during landing, primarily due to the tight coupling between lift and thrust caused by the ingestion of boundary-layer air by the BLI fans.