A model-free adaptive control is proposed for suboptimal guidance correction and control of a prototypical three-stage satellite carrier. For this sake, we consider a nominal guidance for the model of the system and design the adaptive control for a single-input multi-output system exposed to wind disturbance and measurement noise in the rates of inputs and outputs. Then, subsequent to the guidance correction, a differentiation model of the system is estimated and the control policy is realized under some profitable performance constraints to set the satellite in a desirable circular orbit. The simulation results readily reveal the efficiency of the proposed method and its robustness to uncertainties in the system.
MaLWangKShaoZ, et al.Direct trajectory optimization framework for vertical takeoff and vertical landing reusable rockets: case study of two-stage rockets. Eng Optim2019; 51: 627–645.
2.
KochAD. Fast, robust and near-optimal approximation of GTO trajectories and payload capacities of multistage rockets. CEAS Sp J2019; 11: 269–285.
3.
ChaiRTsourdosASavvarisA, et al.Review of advanced guidance and control algorithms for space/aerospace vehicles. Prog Aerosp Sci2021; 122: 100696.
4.
MenonPSweridukGOhlmeyerE. Optimal fixed-interval integrated guidance-control laws for hit-to-kill missiles. In: Proceedings of AIAA guidance, navigation, and control conference and exhibit. Texas: Austin, 2003, p. 5579.
5.
HeSWangWWangJ. Three-dimensional multivariable integrated guidance and control design for maneuvering targets interception. J Franklin Inst2016; 353: 4330–4350.
6.
WangXZhengYLinH. Integrated guidance and control law for cooperative attack of multiple missiles. Aerosp Sci Technol2015; 42: 1–11.
7.
CongZYun-jieW. Non-singular terminal dynamic surface control based integrated guidance and control design and simulation. ISA Trans2016; 63: 112–120.
8.
ZhaoDLiuXHanQ, et al.Blended methodology of lateral jet simultaneous with aerodynamic fin for integrated guidance and control of flight vehicle. In: Proceedings of 2020 15th IEEE Conference on Industrial Electronics and Applications (ICIEA), 2020, p. 367–372.
9.
ZhaoDLiuXHanQ, et al.The allocation control of lateral jet system of flight vehicle based on integrated guidance and control model. In: Proceedings of 2020 Chinese Control And Decision Conference (CCDC), 2973–2978. China: Hefei, 2020, p. 22–24.
10.
WangQRanMDongC. Robust partial integrated guidance and control for missiles via extended state observer. ISA Trans2016; 65: 27–36.
11.
LiGChaoTWangS, et al.Integrated guidance and control for the fixed-trim vehicle against the maneuvering target. Int J Control Autom Syst2020; 18: 1518–1529.
12.
YanHTanSHeY. A small-gain method for integrated guidance and control in terminal phase of reentry. Acta Astronaut2017; 132: 282–292.
13.
ZhaoTWangPLiuL, et al.Integrated guidance and control with L2 disturbance attenuation for hypersonic vehicles. Adv Sp Res2016; 57: 2519–2528.
14.
YanHHeY. Adaptive integrated guidance and control based on backstepping for the landing of reusable launch vehicles. IFAC-PapersOnLine2015; 48: 496–501.
15.
BrendelEHérisséBBourgeoisE. Optimal guidance for toss back concepts of reusable launch vehicles. In: Proceedings of EUCASS. Madrid, Spain, 2019.
16.
TianBFanWZongQ. Integrated guidance and control for reusable launch vehicle in reentry phase. Nonlinear Dyn2015; 80: 397–412.
17.
KisaboABAdebimpeAFSamuelSO. Pitch Control of a rocket with a novel LQG/LTR control algorithm. J Aircr Spacecr Technol2019; 3: 24–37.
18.
LiuXHuangWDuL. An integrated guidance and control approach in three-dimensional space for hypersonic missile constrained by impact angles. ISA Trans2017; 66: 164–175.
19.
SchultePZSpencerDA. Development of an integrated spacecraft guidance, navigation, & control subsystem for automated proximity operations. Acta Astronaut2016; 118: 168–186.
20.
WangWXiongSWangS, et al.Three dimensional impact angle constrained integrated guidance and control for missiles with input saturation and actuator failure. Aerosp Sci Technol2016; 53: 169–187.
21.
XinglingSHonglunW. Back-stepping active disturbance rejection control design for integrated missile guidance and control system via reduced-order ESO. ISA Trans2015; 57: 10–22.
22.
TavakoliFNovinzadehAB. Designing a closed-loop guidance system to increase the accuracy of satellite-carrier boosters’ landing point. Aerosp Sci Technol2018; 76: 242–249.
23.
ZhaoH. Terminal angular constraint integrated guidance and control for flexible hypersonic vehicle with dead-zone input nonlinearity. J BEIJING Inst Technol2020; 29: 489–503.
24.
WangXLiYZhangJ. A novel IGC scheme for RHV with the capabilities of online aerodynamic coefficient estimation and trajectory generation. Mathematics2021; 9: 172.
25.
HouZJinS. Model free adaptive control: theory and applications. CRC press, 2013.
26.
DuanLHouZYuX, et al.Data-driven model-free adaptive attitude control approach for launch vehicle with virtual reference feedback parameters tuning method. IEEE Access2019; 7: 54106–54116.
27.
WenmingNIEHuifengLIZhangR. Model-free adaptive optimal design for trajectory tracking control of rocket-powered vehicle. Chinese J Aeronaut2020; 33: 1703–1716.
