To reduce the ejection load and improve the launch accuracy of rockets， a telescopic canister gas ejection system was proposed. The dynamic characteristics of this ejection system were studied based on theoretical analysis and numerical calculation. The maximum relative error between the simulated and theoretical velocities of the rocket exiting the canister was -0.98%， and the accuracy of the finite element model of the ejection system was verified. Based on the finite element model， the depressurization effects of the ejection system and the effects of launch angle， thrust misalignment， and wind load on the rocket’s motion attitude and the inner canister’s vibrational response were investigated. The results show that compared to the single canister ejection system， the average and maximum depressurization effects of the ejection system are about 30.3% and 35.1%， respectively. Larger launch angle， thrust misalignment， and wind load indicate worse motion attitude of the rocket and vibrational response of the inner canister. The launch angle is the main factor affecting the launch accuracy of the rocket， and the maximum effect of the launch angle on the launch accuracy is 2.3 to 4.4 times that of the other two factors. The research can provide references for the design and optimization of telescopic canister gas ejection systems.

During the long-term storage of weapon launchers， creep will occur over time. The long-term storage of weapons and their launch process are simulated based on the finite element method to study the influence of creep on weapon launch. Meanwhile， the effects of launch angle and storage time on the creep in the launcher and the weapon launch process after storage are analyzed. The results show that the launcher ends the transient creep stage after about one year during storage and enters the steady-state creep stage. The weapon is deflected by the creep of the bottom carrying device， and the deflection is positively correlated with the launch angle and storage time. The weapon launched after long-term storage deviates from the initial launch axis， and the influence of creep on the launcher structure and the launch process of the weapon during storage cannot be ignored.

An improved unmanned aerial vehicle （UAV） low altitude penetration model based on safe flight space is presented to solve the problem of lack of combination with the characteristics of UAV after terrain preprocessing. A safe flight space is constructed to reduce terrain constraints and ensure the safe flight of UAV in low altitude penetration. The trajectory planning model is improved by combining with the characteristics of UAV to increase the stability of UAV flight process and the smoothness of planned trajectory. The particle swarm optimization （PSO） algorithm is used to simulate the two models before and after the improvement in complex elevation map to verify the rationality and effectiveness of the improved model.

With the advances in reconnaissance and reconnaissance-strike integrated technology， the transparency of the battlefield in modern warfare is increasing. The survival of military targets faces serious threats， and camouflage protection is an important prerequisite to ensure the survival on the battlefield. The inception， emergence， development and maturing of camouflage technology applications are reviewed； summarizes the research status of certain camouflage technologies such as stealth， sheltering， disruptive pattern-making， and faking. The analysis suggests that future camouflage technologies may incorporate multispectral compatibility， intelligent adaptation， and integrated designs. The paper provides important and valuable references to the R&D of military target camouflage technologies.