相对距离剖面高阶重塑的多约束末制导律

doi:10.7527/S1000-6893.2024.31405

Abstract

Abstract:

To address the problem of homing guidance with impact angle constraint or impact time constraint under the condition of limited field-of-view of missile’s seeker， a multi-constraint homing guidance law design method based on high-order reshaping of relative range profile is proposed. Firstly， an auxiliary variable containing only field-of-view angle is constructed for the two-dimensional plane homing guidance model， and a high-order polynomial with the reference missile-target relative range profile as the auxiliary variable is designed. Secondly， some profile parameters are solved by using the initial and terminal boundary conditions of guidance， and the expression forms of the parameters to be solved are given by performing terminal constraint integration on the auxiliary variable transformation equation. Furthermore， the impact angle constrained guidance law and impact time constrained guidance law driven by reference profile are given based on model transformation. At the same time， to ensure continuous attenuation of the seeker’s field-of-view， the conditions for the profile parameters to be satisfied are given. On this basis， the explicit representation form of the available sets of angle constraint and time constraint are derived. Different from the existing guidance law with profile reshaping， this paper designs a general n-order range profile reshaping guidance method， which can obtain wider achievable constraint sets， and is also convenient for designers/engineers to analyze the reshaping guidance law performance under arbitrary orders. In addition， to solve the profile deviation problem in the ideal profile reshaping process under uncertainty or disturbance， the guidance law is compensated for profile tracking deviation and is robustly corrected， thereby improving the multi-constraint guidance accuracy under complex working conditions. Finally， the effectiveness and robustness of the designed guidance law are verified through numerical simulation comparison analysis under various working conditions and Monte Carlo tests.

Key words: missile, homing guidance law, impact angle constraint, impact time constraint, field of view limit

CLC Number:

V448

Qinglei HU, Shuxin ZHANG, Tuo HAN, Qingyun WANG. Terminal guidance law under multiple constraints of high-order reshaping of relative range profile[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(6): 531405.

Figures/Tables 21

Fig.1

Fig.2

Table 1

Upper and lower bounds of ΓIT

n	上界	下界
4	$- 4 r 0 F 3 β 04 + 4 r 0 F 0 β 0 / 3 V M$	$4 F 3 r 0 V M β 04$
5	$- 5 r 0 F 4 β 05 + 5 r 0 F 0 β 0 / 4 V M$	$5 F 4 r 0 V M β 05$
6	$- 6 r 0 F 5 β 06 + 6 r 0 F 0 β 0 / 5 V M$	$6 F 5 r 0 V M β 06$

Table 1

Fig.3

Table 2

Table 3

Main simulation parameters

变量名称	数值
导弹初始位置 $x M 0, y M 0$ /km	（0，0）
目标初始位置 $x T 0, y T 0$ /km	（10，0）
导弹速度 $V M$ /（m·s^-1）	300

Table 3

Fig.4

Fig.5

Table 4

Simulation parameters for comparison of IACG laws

制导律	变量数值
BPN-IACG	$N = 3, τ = 2, b 1, m a x = 0.3 r a d / s$
ROG-IACG	$N = 0$

Table 4

Fig.6

Table 5

Simulation parameters for comparison of ITCG laws

制导律	变量数值
BSP-ITCG	$k 1 = 0.499, k 2 = 0.25, ϕ = 500, N = 3$
BPN-ITCG	$k 0 = 0.5, δ 1 = 0.005, δ 2 = 0.1$

Table 5

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

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Terminal guidance law under multiple constraints of high-order reshaping of relative range profile

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