To address the issue of guidance information extraction for strapdown phased array seekers with radome errors， a guidance information extraction method based on Kalman filtering is investigated. Firstly， a relative motion model is established in the body line-of-sight coordinate system， incorporating the radome error slope into the model， regarding the maneuvering targets， then the Singer maneuver model is employed， the radome error slope measured offline is treated as a known quantity， and observability analysis is implemented for the system of angle measurement observations undertaken， providing a theoretical basis for guidance information extraction in the presence of radome errors. Next， according to the isolation rising caused by gyroscope and beam control delays， a gyroscope delay compensation method is adopted to reduce the impact of airframe attitude disturbances. Finally， comparative simulations on isolation with and without gyroscope delay compensation for gyroscope and beam control delays are performed along with simulation validation in a high-altitude interception scenario against maneuvering targets. The simulation results demonstrate that the missile's isolation performance is improved after radome error compensation and a smaller miss distance is achieved in high-altitude interception of maneuvering targets.

A specification and formal verification method is presented for dynamic failure modes in aerospace launch systems. The dynamic fault model designed through this approach enables real-time fault diagnosis systems in the aerospace field to possess diagnostic capabilities for complex and diverse fault characteristics. The dynamic fault models are represented by temporal facts， however， the complexity and abstract nature of temporal facts make them difficult to be validated through manual analysis or testing. By describing the semantics of temporal symptoms through temporal logic formulas， the correctness of the fault model is allowed to be verified through model checking methods. This verification process can be automated by using model checking tools. Moreover， the dynamic fault model does not require formal specifications， which allows domain experts to focus solely on domain-specific issues when constructing fault models. In aerospace engineering practice， the key properties of fault models through automated verification of model checking methods can provide domain experts with a reliable and verifiable mathematical approach for designing fault models.

An intelligent forecasting model based on ensemble learning， named iTransformer-XGBoost， is proposed in this paper to address the issue of precision limitations of traditional time series prediction models. Firstly， the Pearson correlation coefficient is employed to select the key features affecting time series data and construct an optimized input dataset. Then， the iTransformer model is utilized to capture long-term dependencies within the time series and generate preliminary prediction results. Meanwhile， the XGBoost algorithm is introduced to achieve nonlinear modeling of the time series data. Finally， a threshold-based combination strategy is applied to the prediction results fusion of iTransformer and XGBoost， thereby determining the integrated output and improving overall forecasting performance. The model is validated by using photovoltaic power-related data， and the experimental results demonstrate that the proposed approach achieves higher accuracy and stability in time series forecasting compared with traditional methods. Furthermore， it shows great potential for application in aerospace photovoltaic scenarios.

To address the issue of low test coverage caused by implicit test scenarios such as missing boundary conditions and exception handling in software requirement documents， a code-enhanced requirement analysis method is proposed. The code-requirement associations are established through the proposed method which is based on semantic vector similarity and LLM verification， and five types of implicit test scenarios （boundary conditions， error handling， resource management， state transitions and performance stress） are extracted from function call chains to enhance requirement descriptions， and the enhanced requirements are decomposed into test function points and scenario-driven test cases are generated. The results of experiments on open-source projects show that compared with the baseline method by using LLM directly， the significant improvements are achieved by using CERA method in comprehensive test quality and test requirement coverage， which maintains higher API test accuracy. The effectiveness of three core components： scenario extraction， two-stage matching strategy and BERT-based rough screening is verified through ablation experiments. The good adaptability on both parsing libraries and embedded systems is demonstrated by the results of proposed method applied that is particularly suitable for third-party testing and acceptance testing scenarios.

To address issue of the inefficiency in collaborative design of launch vehicles flight sequences， a model-based systems engineering （MBSE）based methodology is proposed for modeling launch vehicles flight sequence and the collaborative design mechanism is investigated for such flight sequence within an MBSE framework. By focusing on a representative two-stage configuration and non-booster based launch vehicles， the organizational relationships are analyzed among distinct flight phases throughout the vehicle's life-cycle and a hierarchical architecture global scheme is presented for flight sequence modeling. For each hierarchy level， based on the structural composition of the sequence command skeleton， a meta-modeling approach is developed to establish elementary models of flight sequence command signals. On the basis of these elementary models， a comprehensive MBSE model based on the entire procedure of launch vehicles flight sequence is designed. Furthermore， oriented to the collaborative design strategy for flight sequence in the MBSE framework， the model distribution and merging mechanisms based cooperative design of flight time sequence is implemented. This work lays a foundation for the full-scale digital transformation of launch vehicles design processes.

Excessive axle temperature of vehicle can lead to a series of issues that affect driving safety and is an important index for evaluating the environmental adaptability of special vehicles. An equipment axle temperature prediction method based on a thermal equilibrium model is proposed. A differential equation describing the thermal variation of vehicle axles is firstly formulated. Parameters of the equation are calibrated by utilizing experimentally acquired data， and the equation structure is further optimized. Consequently， axle temperature predictions with a margin of error below 3°C are achieved， thereby the challenging problem is to forecast axle temperature fluctuations in special vehicles， which is solved under diverse environmental conditions.

In order to standardize usage of static test tools， combining the automation with platform-based characteristics of tools， a static testing multi-tool collaborative analysis framework supporting distributed deployment and parallel analysis is designed； A remote driving technology based on a distributed architecture is proposed， which establishes a test task queue mechanism and tool scheduling mechanism and thereby enables programmatic control of remotely driven tool analysis； A multi-source information fusion technique is developed to achieve normalization， which realize filtering and integration of analysis results from multiple tools. By applying these technologies to static testing across various aerospace domains， testing efficiency and quality are effectively improved.

Aiming at the problems of over-segmentation and text adhesion in natural scene text detection algorithms based on image segmentation， a natural scene text detection algorithm based on a cross-level attention mechanism is proposed. By designing a cross-level attention module， the network's focus on key features and contextual information in high-resolution feature maps is enhanced by applying the proposed algorithm that thereby improves the integration capability for fragmented text. Through the design of a feature decomposition and reorganization module， the fused features are decomposed into high-frequency and low-frequency components that enhance the network's ability of distinguishing text boundary regions. After integrating these two modules into the baseline model， performance tests are implemented on two mainstream datasets. The experimental results show those of current mainstream algorithms are all surpassed， and compared to the baseline model， the missed detection rate and false alarm rate are both declined.

With the continuous applications expansion in the aerospace domain， the health management of complex equipment is oriented from scheduled maintenance towards data-driven predictive maintenance. A data-driven anomaly detection framework known as TS-ADF is proposed， which achieves effective identification of potential anomalies through the establishment of normal patterns， reconstructive analysis and feature fusion of multidimensional operational data. Specifically， preliminary screening is involved by using density peak clustering， deep features of time series are captured through LSTM-AE， and anomaly points are validated via time-frequency analysis and parameter variation analysis. Experimental results demonstrate the method's effectiveness in anomaly detection， which can serve intelligent health management and predictive maintenance of equipment.

Software factories can serve as key platforms for the efficient development of aerospace software. The dynamic interaction and real-time update of their frontend components have direct influence on development efficiency and resource utilization. Traditional fixed-time-interval refresh mechanisms are liable to cause resource waste or data latency issues， while existing semi-automatic adjustment methods struggle to adapt to complex scenarios in software factories， such as multiple component types， cross-network deployment and multi-environment deployment. An adaptive refresh algorithm is proposed for frontend components. The change values can be obtained by component differential comparison， and a CVI （Component volatility index）is established， which integrates short-term change trends with long-term average levels to quantify the volatility of business data， and scenario-specific adjustment strategies are designed. This algorithm can adapt to scenarios like multi-team collaboration and high-frequency component reuse， which effectively balances resource consumption and response efficiency and thus provides support for the efficient operation of software factories.

An universal program parsing and test coverage analysis technology is introduced for multi-architecture embedded processors， including program parsing for compilers of different architectures and universal data storage structure， a kind of fast program information retrieval algorithm and a universal test coverage analysis architecture. By taking multiple embedded software onboard system of the new-generation launch vehicle as validation targets， the verification of each technical aspect is implemented. The validation results show that the proposed method is compatible with multiple compiler standards and processor architectures， and the provided universal coverage test framework can meet the requirements of mainstream embedded processors. The proposed method is extensible and can be extended to applications to the software that has new target processor architectures in the future.

To address the issue of development requirement of trusted embedded systems， a trusted embedded hardware platform is designed， which is comprised of an full indigenous Root of Trust （RoT）， Loongson processors， Kunlun firmware and SylixOS domestic technology stack. On this basis， firstly， guided by an active defense philosophy， a dynamic runtime trusted verification mechanism is researched and designed for software code. Then， this mechanism performs real-time verification of software identity and code integrity both at program startup and execution， thereby preventing the execution of unauthorized programs or tampered code. Finally， a prototype of the trusted embedded platform is established and the proposed designs are validated. The experimental results demonstrate that the trustworthiness of equipment software can be effectively enhanced by using the proposed methodology.

The selection of stable spin angular velocity for aircraft is focused in this paper. A method for choosing a stable angular velocity based on the spin stability criterion of aircraft is researched and proposed. Through theoretical analysis of the coning motion dynamics of spinning vehicles， the coupled effects of static stability moment， Magnus moment， and damping moment on the directional stability of the projectile body are fundamentally revealed. Based on a coning motion angular dynamics model under the constraints of deviations between the center of mass and the center of pressure， a system characteristic equation is established and the Routh-Hurwitz stability criterion is then employed to formulate a dynamic stability criterion. Furthermore， on the basis of the traditional three-degree-of-freedom trajectory model， the derived dynamic stability criterion for coning motion is used to deduce the feasible region for the spin angular velocity. A stable spin rate scheme for the aircraft is subsequently designed based on this region. Numerical simulation results demonstrate that the coning motion divergence is effectively suppressed by using proposed method that simultaneously reduces control energy consumption in the pitch/yaw channels. The achievement presented hereinabove provide a technical pathway to directional stable flight with low-energy-consumption attitude control by applying the spin characteristics of aircraft， which can offer significant theoretical and practical value.

According to stability under target intelligence recognition under interference， a intelligence system testing method is proposed for uncertainty-metric-based guidance target mutation. Regarding interference scenarios that are typical in remote-sensing images， diverse object-level mutation strategies are combined with proposed method， specifically including object insertion， deletion， and replacement， for perturbing the original test data. Concurrently， it introduces model-predicted uncertainty metrics to guide the generation of efficient test cases， thereby， the original test set is augmented. Experiments are conducted by using the YOLOv5 model on the large-scale MAR20 aircraft remote-sensing dataset. The results demonstrate that the test datasets generated by our method which performs superior error-detection efficiency and are more effective at revealing latent defects in the model. Consequently， this approach offers a practical and effective means for robustness testing of object detection systems.

The issue of high-reliability numerical computation software is addressed in aerospace embedded systems being susceptible to floating-point bugs， and a static symbolic execution-based method is proposed for detecting floating-point bugs in numerical software. Through the method procedure， the floating-point expression is established by symbolization under related constraints， and interval computation and interval constraint propagation is introduced in non-relational numerical abstract domains， and math functions are symbolically modeled in order to improve the accuracy of detecting floating-point bugs. Regarding application to actual floating-point numerical software and aerospace testing， accuracy and efficiency are effectually improved， and multiple genuine floating-point bugs are successfully identified and confirmed by developers， which significantly enhances the reliability of aerospace software.

In response to the subjects of long development cycles， requirement verification difficulty， interfaces unclearness and processes amendment complexity in traditional system engineering development， the thrust regulation controller is taken as an example in this paper to conduct research on model-based design methods. MagicDraw known as tool is used for system modeling and behavior simulation， SCADE is used for the tool of software design and code automatic generation， and ModelCenter is used for joint simulation of system behavior model and software design model. It is an exploration and research on the specific implementation of model-based systems engineering in complex aerospace systems engineering. This method can serve as important application value for the development of complex control systems and the new ideas and technical paths are suggested to design the future spacecraft thrust adjustment control.

Regarding circular restricted three-body subject， a prediction method based on deep neural network is proposed for two impulse Earth-Moon transfer orbit. Firstly， three types of two-impulse transfer orbit family are selected， and the state quantities of each transfer orbit are used to establish two-impulse transfer orbit data set in which input state and predicted state of orbit are determined. Secondly， a deep neural network is constructed for orbit state prediction， and， each class of two-impulse transfer orbits in the data set is used as the training set， and the neural network is trained by the track data in the training set. Finally， according to the training results， the state quantities about transfer orbit are predicted by setting the initial state of the low-Earth orbit， and then the optimal Earth-Moon two-impulse transfer orbit in each orbit family is selected according to the prediction results. The simulation results show that the application of deep neural network can quickly predict initial state of orbit， and the prediction results have fairly smaller error intervals and can be applied to selection of optimal two-impulse transfer orbit.

In response to the impact of spaceborne radars installation error on data-fusion accuracy， a multi-radar spatial registration algorithm based on same target observations is proposed. The measurement vectors of the same target obtained by different tracking radars is processed by using this algorithm under a common reference coordinate system through cross-product operations， and the cross-product vectors are projected onto a specified plane to establish the relationship with the relative installation bias angles， and the unbiasedness of the least squares estimation algorithm is verified by analyzing the characteristics of derived observation errors. Through actual on-orbit satellite conditions based simulation experiments， the results demonstrate that the proposed method can reliably and rapidly achieve spatial registration of different radars without relying on satellite attitude measurement.

A majorant-based control method is proposed for quadrotor unmanned aerial vehicle trajectory tracking to enhance system robustness and tracking precision. Firstly， an extended state observer is designed for the position loop to compensate for the effects of external disturbances. Secondly， a position loop controller is developed via majorant systems. Furthermore， regarding the inherent cascade-control structure of quadrotor system， the design methodologies for both the observer and controller are concurrently applied to the attitude loop. Simulation results demonstrate that the proposed control method achieves convergence of the steady-state error to specified values， enables high-precision trajectory tracking and presents computational efficiency of practical implementation.

The precision contribution of the missile-borne hybrid inertial navigation system（HINS） in missile-borne platform application is researched in this paper. On the basis of clarifying the principle and characteristics of HINS， its theoretical advantages in the mission chain of missile usage are analyzed. The error models of HINS is provided and its propagation characteristics are both analyzed. The impact on the precision contribution of HINS is focused towards researches regarding the errors of inertial instrument， initial alignment errors， trajectory characteristics， rotation modulation schemes， the integrated navigation scheme and the other factors. The reasons for the different opinions on the precision advantages of HINS in the related professional fields are analyzed， and a much more reasonable evaluation scheme for the precision advantages of missile-borne HINS is further proposed to support and improve the precision evaluation system of missile-borne HINS， which can serve as important reference for the engineering application of missile-borne HINS.

Regarding the limitation of existing feedback gain designs based on specific nominal trajectories， a tracking guidance method for Mars powered descent in wide area based on control contraction metric （CCM） is proposed to match the emerging onboard trajectory planning capability. The CCM conditions for the powered descent model are analyzed. The CCM matrix and system dynamics are parameterized and approximated as polynomial functions， and then the CCM matrix is solved offline by using the method of sum of squares programming. During the flight， the control input is obtained through numerical integration based on the CCM matrix. The simulation results show that the nominal trajectories of different initial and final motion states and flight durations can be tracked by using the contraction control method under the conditions of specified range of mass and thrust.

The hyperbolic orbit plane of the planetary gravity assist is determined by the entry speed and escape speed and based on two-body dynamics. The engagement and escape hyperbolic orbit's asymptotic angle are adjusted by the height at the near-planet point. Combined with the accelerating/braking speed increment near the planet， the direction of the escape velocity is determined. Based on the conversion algorithm between the heliocentric elliptical orbit and the planet's hyperbolic orbit， as well as the iterative algorithm for the height near the planet， the transfer orbit is quickly calculated， and the parameters of the approach/escape hyperbolic orbit are determined. By taking the 2015 XF261 asteroid defense as an instance， a Venus-assisted transfer orbit design is implemented， and the transfer orbit， the transfer duration and velocity increment requirements of the probe are presented. The simulation results show that rapid calculation of the analytical solution of the planetary gravity-assisted transfer orbits can significantly reduce the search time for transfer orbit.

A meta-reinforcement learning method based on the universal policy-online system identifier structure is proposed to address the issue of terminal guidance with large environmental uncertainty and diverse task types. The method consists of a reinforcement learning training phase for the UP and a supervised learning phase for the OSI， and ensures reliable convergence of the training in multi-task environments through a phased transfer learning design and a pseudo-Monte Carlo-based small-variance policy gradient estimation， so that the resulting guidance policy can be adapted to varieties of terminal guidance task scenario. Simulation results show that the resulting guidance policy can meet the requirements of terminal position and path angle error in multiple terminal guidance scenarios.

In response to the automated testing of launch vehicles and short development cycle and high quality requirements of aerospace software， an automated testing method by using configuration files is designed for test and launch control system of launch vehicles in this paper. By modularizing the functions of test and launch control software system， reusable modules are abstracted such as human-computer interaction， data communication， flow driver， data interpretation and log recording， and the flow driver module is responsible for driving oneself by working with multiple independent modules that follow its own configuration files to implement business work. During improving system automated test capability， the software re-usability is improved and the software design complexity is reduced. Thus， the system reliability is guaranteed to be improved and development progress is accelerated.

A design methodology for launch vehicle trajectory planning systems is proposed，which is compatible with multiple trajectory software suites and enables rapid trajectory computation with extensive peripheral support functions. The system consists of five modules about planning calculation， integrated management， comprehensive analysis， planning database and visualization. Through the systematic integration of architectural design and algorithmic optimization， the critical conflicts are solved among computational efficiency， universality， and decision-making coordination in launch vehicle trajectory planning by using proposed design methodology which provides extendable technical support for high-density launch mission and offers significant engineering applicability as well as practical value.

In this paper， a distributed prescribed performance cooperative guidance law is proposed for multi-vehicle with input delay. In order to improve the guidance performance， a novel continuous prescribed performance method is developed， which ensures the system error satisfies both dynamic and steady-state performance. By integrating the continuous prescribed performance method with finite-time control theory， the cooperative guidance laws based on the line-of-sight direction and the line-of-sight normal direction are designed， which realize the simultaneous attack of multi-vehicle on stationary target. The simulation results show that the multi-vehicle can hit the stationary target in performance of prescribed dynamic and steady state by applying the proposed cooperative guidance law.

Regarding the multi-spacecraft formation flying， a distributed formation tracking control scheme that integrates active disturbance rejection control with prescribed performance control is proposed， considering model uncertainties and external disturbances. Firstly， based on the principle of active disturbance rejection control， an extended state observer is employed to estimate and compensate for system uncertainties and external disturbances. Secondly， a prescribed performance-based controller is designed to enable the multi-spacecraft system to form and maintain the desired formation configuration， while ensuring fixed-time convergence. On this basis， the stability of the closed-loop controlled system is proved by using Lyapunov theory. Comparative simulations are conducted to validate the superority of the proposed designed on transient and steady-state performance.

Aiming at solving the insufficient aerodynamic load margin， a load relief control method based on double-loop observer of force and moment is proposed for a new generation launch vehicle. The control swing angle compensation is formed through disturbing torque acquisition by usig structural observer in moment circle， which can effectively reduce attitude deviation； The attitude compensation angle is formed through disturbing force acquisition by using structural observer in force circle，which can effectively reduce velocity deviation and attack angle. The load relief effects of traditional accelerometer feed-back control in steady wind is improved by using this method that keeps load relief ability in shear wind and meanwhile promotes nominal trajectory tracking effect. The simulation results show that attitude deviation and velocity deviation is significantly decreased and load relief effect can reach by 20%， that can effectively increase the launch probability.

To address the issue of control performance degradation in vehicles under structural disturbances， aerodynamic parameter variations， and external environmental interference， a hybrid control approach that integrates the deep deterministic policy gradient （DDPG） algorithm with a traditional PID controller is proposed in this paper. The initial stable control capability is provided by PID controller， while the reinforcement learning strategy enables online adaptive tuning of the flight controller. A nonlinear dynamic simulation platform is established， which is based on the vehicle model. Experimental results demonstrate that， in typical altitude step-response control tasks， the method shortenes the system response time by 62.8%， with overshoot and steady-state error maintained within 1%. Even under complex conditions involving ±20% parameter variations， the system still retains high-precision control. Compared with the conventional PID controller， the proposed method shows superior performance in terms of response speed， stability and adaptability and can be served as reference for prospects of engineering application.

Regarding the aerodynamic-deformation-control multi-coupling problem encountered in high-speed morphing aircraft during dynamic morphing， a six-degree-of-freedom dynamic model is established and the aerodynamic moment coupling matrix is derived. The coupling strength of the roll， yaw and pitch channels is quantitatively analyzed， and the effect laws of angle of attack， Mach number， and deformation magnitude on coupling characteristics are systematically investigated. The results show that， for the given simulation case， the pitch channel is most significantly influenced by deformation， which presents a nonlinear increase followed by the growing deformation magnitude. The roll channel exhibits moderate coupling that is affected jointly by the angle of attack and Mach number， and the effect of coupling intensifies under low angle of attack and high Mach number conditions. In contrast， the yaw channel exhibits weak coupling among attitude angles， and that result shows that attitude angles coupling can be reasonably neglected in control design. Additionally， the analysis of control surface deflection coupling indicates that the roll and sideslip channels are decoupled， while the coupling degree in pitch control remains low and deformation has no significant impact on control coupling. These research results provide theoretical support for the decoupling control design and flight stability improvement of high-speed morphing aircraft.