System architecture design is crucial for forward design in aerostat system engineering, yet a comprehensive research framework has been lacking. This paper presents a new method for stratospheric airship architecture preliminary design and optimization trade-off, grounded in Model-Based Systems Engineering (MBSE) theory. Firstly, a requirement analysis for a stratospheric airship is conducted using SysML, leading to the analysis and acquisition of the airship’s mission architecture design. Additionally, a multidisciplinary coupling simulation platform is developed with MATLAB, and the architecture preliminary design’s Pareto front is derived using the NSGA-II algorithm. Finally, based on the Pareto optimization set, the TOPSIS algorithm is applied to derive the optimal architecture preliminary design scheme for the airship. The optimization results validate the accuracy of the architecture preliminary design obtained from the requirement analysis, the reliability of the multidisciplinary coupling simulation platform, and the feasibility of the optimization algorithms. This comprehensive study spans the requirement analysis to the optimal architecture scheme, providing theoretical reference and design guidance for the forward design of airship systems engineering.

Tethered balloon systems encounter various complex wind field environments during flight. To investigate the conditions under which the system can operate safely and smoothly, a longitudinal dynamic model for tethered balloon systems is established. The model incorporates a streamlined balloon shape with its aerodynamic center at the body’s center. Steady-state aerodynamic force coefficients are calculated through simulations and fitted to a function based on the angle of attack within a specified range. The complex cable model is simplified using the lumped mass method, considering the influence of branch cables on the main node position. Experimental results from windless oscillation tests on scaled tethered balloon systems are compared with numerical solutions obtained using the dynamic model under the same conditions, validating the feasibility of the model for simulating different wind field scenarios. Finally, the motion characteristics of tethered balloon systems in different wind fields are analyzed. The numerical simulation results show that in a horizontal step wind field, the cable tension and cable inclination angle increase with the wind speed, and the slower the wind field changes, the shorter the time required for system stabilization. Updrafts greatly increase the likelihood of balloon escape, while downdrafts greatly increase the likelihood of the system making contact with the ground. The findings of this study can provide a basis for selecting suitable wind field conditions and issuing risk warnings for tethered balloon systems.

The stratospheric airship is a vital platform in near-space applications, and achieving autonomous transfer has become a key research focus to meet the demands of diverse mission scenarios. The core challenge lies in planning feasible and efficient paths, which is difficult for traditional algorithms due to the time-varying environment and the highly coupled multi-system dynamics of the airship. This study proposes a deep reinforcement learning algorithm, termed reward-prioritized Long Short-Term Memory Twin Delayed Deep Deterministic Policy Gradient (RPL-TD3). The method incorporates an LSTM network to effectively capture the influence of historical states on current decision-making, thereby improving performance in tasks with strong temporal dependencies. Furthermore, to address the slow convergence commonly seen in off-policy methods, a reward-prioritized experience replay mechanism is introduced. This mechanism stores and replays experiences in the form of sequential data chains, labels them with sequence-level rewards, and prioritizes high-value experiences during training to accelerate convergence. Comparative experiments with other algorithms indicate that, under the same computational resources, RPL-TD3 improves convergence speed by 62.5% compared to the baseline algorithm without the reward-prioritized experience replay mechanism. In both simulation and generalization experiments, the proposed method is capable of planning feasible paths under kinematic and energy constraints. Compared with peer algorithms, it achieves the shortest flight time while maintaining a relatively high level of average residual energy.

This paper aims to investigate a new method that uses buoyant gas mixed with air to control the floating height of scientific balloons. Firstly, the static characteristics and thermophysical properties of mixed-gas balloons are analyzed. Subsequently, the inflation model and the thermal-dynamic coupled model are established. Furthermore, based on theoretical research, a GUI program is compiled to simulate the ascent of mixed-gas balloons. Finally, flight tests are conducted. As the balloon volume expands to the maximum, the vertical velocity begins to decay and eventually oscillates around 0 m/s, which is consistent with the simulation. In addition, there is a noticeable shift in which the balloon starts to float after climbing to the target altitude, and the difference values between the test and the simulation are less than 350 m. Moreover, the trajectory results are similar to the prediction, and the errors of the end position are less than 2.5 km in horizontal distance. Consequently, this paper provides guidance for balloon-designated ceiling height technology which can allow a single balloon system to be used for tests at multiple heights.

Purpose: The leveling process is a critical metric during the non-forming ascent phase, yet research in this area remains insufficient. This paper aims to propose a leveling model based on the correlation between leveling and volume expansion to address this issue. Furthermore, the effects of the leveling process on vertical velocity, temperature and pressure differential are analyzed, refining the prediction of the non-forming ascent for airships. Design/methodology/approach: The leveling model is integrated into the thermal-flight dynamic coupled prediction model. Variations in temperature, velocity and altitude during the ascent are analyzed. The validity of the model is validated by comparing results with those of other scholars. Furthermore, the effects of different trigger volumes and leveling rates are investigated. Findings: The leveling process increases the vertical projection area and reduces the climbing velocity. For an airship with a volume of 8,578 m³ and a ceiling height of 19.5 km, the preformed minimum vertical velocity is 18.7% to 40% lower than that of the nonleveling and the forming velocity is 20% lower. This forms a “step” in the velocity peak, which is strengthened as the leveling is achieved more quickly and earlier. Additionally, it also reduces the volume expansion, delays the initiation of super-pressure and alleviates the “supercooling” phenomenon, resulting in a helium gas supercooling temperature during forming that is 16% higher. Originality/value: A leveling model is presented for the non-forming ascent of airships. At the same time, both the supercooling phenomenon and the vertical velocity undergo “step” variations. These findings provide insights into the lateral control and pressure differential control of airships, as well as the prevention of cold adhesion during the ascent process.

Aerostats, operating persistently in near‐space, have garnered attention in remote sensing, communication relay, and disaster monitoring applications. Integrating large‐area conformal antenna arrays onto their envelope surfaces can enhance electromagnetic functionality while reducing the aerodynamic and structural penalties of externally mounted rigid antennas. However, deformation of the flexible envelope may alter the antennas’ geometry, input matching, and radiation characteristics. A deformation‐tolerant flexible conformal antenna array for near‐space aerostats is developed and mechanically and electromagnetically characterized under wind loading, cyclic bending, controlled curvature, and aerostat inflation. The sixteen‐element antenna array is integrated onto four aerostat models (scale, dolphin‐shaped, jellyfish‐shaped, and disc‐shaped). Across the four platforms, the largest within‐platform variation in measured |S ₁₁ | among the tested inflation states is 1.12 dB. Radiation‐pattern measurements reveal configuration‐dependent changes in gain, sidelobe level, and half‐power beamwidth after platform integration. Ground and low‐altitude flight tests demonstrate orientation‐dependent microwave signal reception, showing the potential of the array for near‐space communication and directional microwave sensing.