Guidance For Endo-atmosphiric TBM Interceptros

An atmospheric interceptor steered by reaction jets and aerodynamic tails is designedin the dissertation. Under the ground of TBM intercept, we designed homing guidancewith improved power reaching law of sliding mode variable structure control. The maincontents of the dissertation as follows:Firstly, based on the target-to-missile relative motion, we derived guidance model inthe plane and three-dimensional space, and pointed out the coupled reason inthree-dimensional space. Then, we gave the conditions and methods that thethree-dimensional guidance mode can be decoupled to longitudinal plane guidance andtransverse plane guidance. We introduced the concept of zero-effort miss (ZEM)because it’s difficult to calculate exactly the actual miss distance. Through the conceptof ZEM, we established the contact between miss distance and line-of-sight (LOS)angular rate in finite time.Secondly, we introduced the reaching law method to design sliding mode controlsystem, and analyzed their characteristics. Especially, we introduce the theory ofimproved power reaching law. In the plane, we designed the new sliding mode guidance(NSMG1) with the application of improved power reaching law. Then, we simulatedwith the traditional proportional guidance law (PN), adaptive sliding mode guidanceLaw (ASMG1) and NSMG1, and highlight NSMG2’s advantages. The target’sacceleration can’t be measured in the existing technical conditions, but NSMG1need it.So, we designed the target state observer to estimate the target’s acceleration basing onthe tracking differentiator (TD) in active disturbance rejection control (ADRC) theory.Then, because the interceptor flight within the atmosphere, it’s necessary toconsider the autopilot dynamic delay characteristics. In order to effectively compensatethe autopilot delayed impact, the interceptor control system is approximated one-orderinertia, and introduced to the guidance model. For the new model, we designed a newsliding mode guidance law (NSMG2) with improved power reaching law. In order toillustrate the importance to consider the autopilot dynamic delay characteristics, weapplied NSMG1to the new model for simulation. Then we applied NSMG2andadaptive sliding mode guidance law (ASMG2), which also have the ability tocompensate the autopilot dynamic delay, to the new mode for simulation, and tohighlight NSMG2’s advantages.Finally, head interception encountered two problems: terminal guidance time is tooshort and seeker optical side window face severe aerodynamic heating. In order to solvethe above two problems, we introduced a new guidance way: head pursuit interception. We applied NSMG1to head interception and head pursuit interception for simulation,and analyzed their difference. Then we applied NSMG2and ASMG2to head pursuitinterception, and highlight NSMG2’s advantages.