Research on the navigation method of large-scale differential tail-control improvised guided munitions based on rotational speed constraints

In the process of launching guided projectile under the conventional system, it is difficult to effectively obtain the precise navigation parameters of the projectile in the high dynamic environment. Aiming at this problem, this paper describes a new system of guided ammunition based on tail spin re...

Celý popis

Uloženo v:
Podrobná bibliografie
Vydáno v:Defence technology Ročník 38; číslo 8; s. 155 - 170
Hlavní autoři: Liu, Ning, Zhao, Wenjiang, Wang, Yao, Shen, Kai, Su, Zhong, Qi, Wenhao, Xie, Yuedong
Médium: Journal Article
Jazyk:angličtina
Vydáno: Beijing Elsevier B.V 01.08.2024
KeAi Publishing Communications Ltd
Beijing Key Laboratory of High Dynamic Navigation Technology,Beijing Information Science and Technology University,Beijing,100192,China%Hua an Industry Group Co.,Ltd.,Qiqihar,161006,China%Integrated Navigation and Intelligent Navigation Laboratory,Beijing Institute of Technology,Beijing,100081,China%Beijing Institute of Technology,Beijing,100081,China
KeAi Communications Co., Ltd
Témata:
Accuracy
Algorithms
Ammunition
Combined navigation
Constraints
Control systems
Extended Kalman filter
Extended Kalman filter (EKF)
Flight tests
Guided projectiles
Hardware-in-the-loop simulation
High speed
Kalman filters
Launching
Military supplies
Military technology
Missile control
Navigation
Navigation systems
Neural networks
Parameter estimation
Process parameters
Projectiles
RPM constraints
Simulation
Spin dynamics
Spin reduction
Tail spin reduction
Velocity
Velocity errors
Tail spin reduction
Extended Kalman filter (EKF)
Guided projectiles
RPM constraints
Combined navigation
Extended Kalman filter(EKF)
ISSN:2214-9147, 2096-3459, 2214-9147
On-line přístup:Získat plný text
Tagy: Přidat tag
Žádné tagy, Buďte první, kdo vytvoří štítek k tomuto záznamu!
Popis
Shrnutí:In the process of launching guided projectile under the conventional system, it is difficult to effectively obtain the precise navigation parameters of the projectile in the high dynamic environment. Aiming at this problem, this paper describes a new system of guided ammunition based on tail spin reduction. After analyzing the mechanism of the ammunition's tail spin reduction, a navigation method of large scale difference tail control simple guided ammunition based on speed constraint is proposed. In this method, the corresponding navigation constraints can be carried out by combining the rotation speed state of the ammunition itself, and the optimal solution of navigation parameters during the flight of the missile can be obtained by Extended Kalman Filter (EKF). Finally, the performance of the proposed method was verified by the simulation environment, and the hardware-in-the-loop simulation test and flight test were carried out to verify the performance of the method in the real environment. The experimental results show that the proposed method can achieve the optimal estimation of navigation parameters for simple guided ammunition with large-scale difference tail control. Under the conditions of simulation test and hardware-in-loop simulation test, the position and velocity errors calculated by the method in this paper converged. Under the condition of flight test, the spatial average error calculated by the method described in this paper is 6.17 m, and the spatial error of the final landing point is 3.50 m. Through this method, the accurate acquisition of navigation parameters in the process of projectile launching is effectively realized.
Bibliografie:ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
content type line 14
ISSN:2214-9147
2096-3459
2214-9147
DOI:10.1016/j.dt.2024.02.005