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SHI A H , LI H Y , SHI W B , et al. Infrared radiation feature of near space hypersonic cruise vehicle [J ] . Acta Armamentarii , 2022 , 43 ( 4 ): 796 - 803 . (in Chinese) DOI: 10.12382/bgxb.2021.0105 http://doi.org/10.12382/bgxb.2021.0105 To meet the demand for optical characteristic data of near-space hypersonic cruise vehicles for the detectability analysis of space-based infrared early warning satellites and the design of future space-based infrared early warning satellitesthe flow-field parameters, body temperature, infrared radiation spectrum, infrared radiation luminance, and infrared radiation intensity of the hypersonic cruise vehicle like X-51A under the typical flight condition are studied based on the combined computation and analysis methods of hypersonic aerodynamics, combustion theory, heat transfer theory, gas radiation theory, and so on. The calculated results show that the radiation features of the hypersonic cruise vehicle like X-51A are influenced by the flight time and ballistic. The infrared radiation of the body is influenced obviously by the aerodynamic heating. The jet flame radiation of the vehicle using aviation kerosene as fuel has strong radiation band of CO₂, H₂O and CO with wavelength of 1.52 μm, 2.68 μm and 4.39 μm. The jet flame radiation contributes most to the total narrow-band radiation, including the strong characteristic radiation spectra of CO₂, H₂O and CO molecule. The body radiation of the vehicle dominates the total radiation at the wavelength band which doesn’t include the characteristic radiation spectra of CO₂, H₂O and CO molecule.

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王芳 , 林涛 , 张克 . 基于控制变量参数化的主动反拦截突防最优控制计算方法 [J ] . 航空学报 , 2015 , 36 ( 6 ): 2037 - 2046 . DOI: 10.7527/S1000-6893.2014.0359 http://doi.org/10.7527/S1000-6893.2014.0359 针对由于敌防空系统防御能力不断提高所带来的进攻导弹突防难题,提出主动反拦截突防(IAIP)的概念,以弥补传统机动突防仅考虑进攻导弹的逃逸而忽略其攻击任务的缺陷。根据IAIP制导的内涵,在综合考虑目标的机动性能、拦截导弹末段的拦截特性及进攻导弹的控制系统性能的基础上,建立进攻导弹-目标-拦截导弹的三体运动模型。将突防制导指令的设计等效为最优控制的求解,其中突防指令为实现燃料最省目标的最优解,进攻导弹的过载、拦截导弹的脱靶量、进攻导弹的攻击角、打击精度和突防后的视线角,分别为控制约束、路径约束和末端约束。借鉴控制变量参数化(CVP)方法将最优控制问题转化为非线性数学规划问题,并将路径约束离散化后采用序列二次规划(SQP)算法得到突防时机给定条件下制导指令的数值解。提出基于CVP的混合遗传算法(CVP-GA),用于求解最优突防时机及制导指令。仿真结果显示,采用IAIP最优控制算法的进攻导弹在成功突防后的打击精度仍可满足任务要求,且其燃料消耗相对于传统串联式突防方法降低了23.7%,验证了该方法的有效性及优越性。

WANG F , LIN T , ZHANG K . Control variable parameterization-based computational method for optimal control of initiative anti-interception penetration [J ] . Acta Aeronautica et Astronautica Sinica , 2015 , 36 ( 6 ): 2037 - 2046 . (in Chinese) DOI: 10.7527/S1000-6893.2014.0359 http://doi.org/10.7527/S1000-6893.2014.0359 To solve the problem caused by experiencing increases in defense capability of enemy antiaircraft system, the concept of initiative anti-interception penetration (IAIP) is proposed, to make up for the defects of the traditional penetration that only takes escape into account, while ignoring attack mission. According to the connotation of IAIP guidance, and considering the maneuver performance of target, terminal intercepting characteristics of interceptor missile and control system performance of attack missile, the three-body motion model, named attacker-target-interceptor, has been established, and the design of penetration guided command has been equivalent to solving nonlinear optimal control problem, where the penetration command is the solution of optimal control for minimizing fuel consumption, overload of attacker, miss distance of interceptor, attack angle, hit precision and angle of sight after penetration of attacker, are control constraint, path constraint and terminal constraint. After the optimal control problem is transformed into nonlinear integer programming model based on control variable parameterization (CVP) method and the continuous path constraint is simulated by scatter point, sequential quadratic program (SQP) algorithm is used to get the numerical solution of guidance commands under the condition of penetration occasion is given. An hydride genetic algorithm based on CVP (CVP-GA), is proposed to obtain the optimal penetration occasion and guided command. Simulation results show that hit accuracy of attacker used the optimal control of IAIP can still meet the mission requirements after successful penetration its fuel consumption is reduced by 23.7% compared with the traditional tandem penetration method, demonstrating the efficiency and superiority of the proposed method.

樊博璇 , 陈桂明 , 林洪涛 . 弹道导弹中段反应式机动突防规避策略 [J ] . 兵工学报 , 2022 , 43 ( 1 ): 69 - 78 .

FAN B X , CHEN G M , LIN H T . Mid-course reactive maneuver penetration and evading strategy of ballistic missile [J ] . Acta Armamentarii , 2022 , 43 ( 1 ): 69 - 78 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2022.01.008 http://doi.org/10.3969/j.issn.1000-1093.2022.01.008 The optimal maneuver penetration of ballistic missiles is studied to improve their penetration capability. Through the simplification and analysis of the motion model, it is determined whether the optimal penetration direction is located in the normal plane connecting the positions of ballistic missile and exoatmospheric kill vehicle. A multi-stage first-order differential motion equation is established based on the motion models of both offensive and defensive parties. The analytical expression of the optimal ballistic missile penetration time is obtained by solving this equation. The error limit of the model parameters that the penetration strategy can support is analyzed. In order to verify the correctness of the obtained optimal penetration time and optimal penetration direction, the two-dimensional and three-dimensional engagement simulations were carried out. The simulated results show that the evading strategy of short-time large pulse maneuver in the direction of the opposite position can be used to effectively penetrate the defense and achieve the maximum miss distance.

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ZHANG W Q , YU W B , LI J L , et al. Cooperative reentry guidance for intelligent lateral maneuver of hypersonic vehicle based on downrange analytical solution [J ] . Acta Armamentarii , 2021 , 42 ( 7 ): 1400 - 1411 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2021.07.007 http://doi.org/10.3969/j.issn.1000-1093.2021.07.007 A cooperative guidance law based on deep Q-learning network (DQN) algorithm for lateral maneuver of hypersonic vehicles is proposed to meet the requirement of cooperative saturation attack. The longitudinal and lateral guidance laws are deigned. The longitudinal lift-to-drag ratio is calculated to obtain the modulus of bank angle based on the high-precision longitudinal analytical solution. The lateral bank reversal logic is abstracted as a Markov decision process (MDP), and the reinforcement learning method can be used. A lateral intelligent maneuver decision-making device based on DQN algorithm is designed. The intelligent agent can be generated by offline training according to the mission requirements, and is called online to generate the sign of bank angle. Simulated results show that the proposed guidance law can autonomously generate bank angle reversals on-line, strictly meets the requirements of flight time constraints and energy management, and has high guidance accuracy and good mission adaptability. Compared with the coordinative reentry guidance law based on three-dimensional analytical solutions, the proposed guidance law is used to fully achieve the lateral maneuverability of vehicle and make it have higher penetration potential.

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