Abstract:The purpose of this paper is to present a comprehensive multibody system dynamics model of a multiple launch rocket system (MLRS), and implement its simulation and experimental studies. The new version of transfer matrix method of multibody system and the launch dynamics theory are used in deriving the equations of motion coupled with rockets and barrels. The obtained model accounts for the complete process of the rockets’ ignition, movement in the barrels, airborne flight and landing. Launch dynamics of an 18… Show more
“…A salvo of 18 rockets with 1 s firing interval is addressed. It is supposed that Fpx, Fpy, and Fpz act with amplitudes of 10, 6, and 6 kN, respectively, on the launcher to simulate 18 rockets salvo firings within a period of 0.3 s. The proposed control algorithm (29) based on the SDM (28) is applied to the MSLDM (Li et al, 2018) to inspect its control performance. In addition, the PID control based on the MSLDM is investigated for the purpose of comparison.…”
Section: Simulation and Resultsmentioning
confidence: 99%
“…Table 3 shows the comparison of response values when each rocket is firing for Case 1 without control and with the FL control. Finally, the FL control (29) and PID control for Case 1 are applied to the MSLDM in (Li et al, 2018) for comparison. The simulated results are shown in Figure 7.Figure 4.Simulated results without control: (a, b) angular errors and (c, d) angular velocities of elevation and azimuth mechanisms for Case 1.Figure 5.Simulated results with feedback linearization control: (a, b) angular errors and (c, d) angular velocities of elevation and azimuth mechanisms for Case 1.Figure 6.Simulated results with feedback linearization control: (a, b) angular errors and (c, d) angular velocities of elevation and azimuth mechanisms for Case 2.…”
Section: 2 Results and Discussionmentioning
confidence: 99%
“…Table 3 shows the comparison of response values when each rocket is firing for Case 1 without control and with the FL control. Finally, the FL control (29) and PID control for Case 1 are applied to the MSLDM in (Li et al, 2018) for comparison. The simulated results are shown in Figure 7.…”
Section: Resultsmentioning
confidence: 99%
“…Though applying the proposed control strategy in this study to a complete MLRS model using a dynamics method different from that in the reference (Li et al, 2018) would offer further insight into the developed two-stage control defined by the simplified SDM model. However, we believe that adding a numerical simulation based on a different modeling approach would be unnecessary given that no matter which method of dynamic modeling, Newton-Euler method, transfer matrix method, or Lagrange method, they definitely yield equivalent equations and numeric calculations would yield exactly the same results.…”
Section: Resultsmentioning
confidence: 99%
“…The MLRS may be considered as multibody system consisting of launcher, carrier, and rocket being coupled with each other. Previous studies have achieved sophisticated dynamic models for MLRS (Bi et al, 2000; Li et al, 2018; Wang et al, 2006; Wei et al, 2011; Zhu and Zhang, 1995). It is well known that the control law is typically designed according to the dynamic model of the controlled object for the dynamics-based control approach.…”
Multiple launch rocket system, a type of launching platform used to launch kinetic load to hit the target, is an extremely complicated mechanical system with strong vibration because of the jet force. In this study, a nonlinear dynamic model and vibration control of a multiple launch rocket system are presented to reduce vibration and improve position accuracy. A simplified dynamic model of the multiple launch rocket system is derived using the Newton–Euler method, which facilitates the controller design considering the strong complexity of the multiple launch rocket system. On this basis, the feedback linearization technique is introduced to design a nonlinear controller based on the deduced dynamic model. The simulated and experimental results show that the simplified dynamic model–based control effectively can reduce vibration level of the launching system and make the azimuth and elevation angles reach the desired values with smaller error despite of each rocket’s jet force.
“…A salvo of 18 rockets with 1 s firing interval is addressed. It is supposed that Fpx, Fpy, and Fpz act with amplitudes of 10, 6, and 6 kN, respectively, on the launcher to simulate 18 rockets salvo firings within a period of 0.3 s. The proposed control algorithm (29) based on the SDM (28) is applied to the MSLDM (Li et al, 2018) to inspect its control performance. In addition, the PID control based on the MSLDM is investigated for the purpose of comparison.…”
Section: Simulation and Resultsmentioning
confidence: 99%
“…Table 3 shows the comparison of response values when each rocket is firing for Case 1 without control and with the FL control. Finally, the FL control (29) and PID control for Case 1 are applied to the MSLDM in (Li et al, 2018) for comparison. The simulated results are shown in Figure 7.Figure 4.Simulated results without control: (a, b) angular errors and (c, d) angular velocities of elevation and azimuth mechanisms for Case 1.Figure 5.Simulated results with feedback linearization control: (a, b) angular errors and (c, d) angular velocities of elevation and azimuth mechanisms for Case 1.Figure 6.Simulated results with feedback linearization control: (a, b) angular errors and (c, d) angular velocities of elevation and azimuth mechanisms for Case 2.…”
Section: 2 Results and Discussionmentioning
confidence: 99%
“…Table 3 shows the comparison of response values when each rocket is firing for Case 1 without control and with the FL control. Finally, the FL control (29) and PID control for Case 1 are applied to the MSLDM in (Li et al, 2018) for comparison. The simulated results are shown in Figure 7.…”
Section: Resultsmentioning
confidence: 99%
“…Though applying the proposed control strategy in this study to a complete MLRS model using a dynamics method different from that in the reference (Li et al, 2018) would offer further insight into the developed two-stage control defined by the simplified SDM model. However, we believe that adding a numerical simulation based on a different modeling approach would be unnecessary given that no matter which method of dynamic modeling, Newton-Euler method, transfer matrix method, or Lagrange method, they definitely yield equivalent equations and numeric calculations would yield exactly the same results.…”
Section: Resultsmentioning
confidence: 99%
“…The MLRS may be considered as multibody system consisting of launcher, carrier, and rocket being coupled with each other. Previous studies have achieved sophisticated dynamic models for MLRS (Bi et al, 2000; Li et al, 2018; Wang et al, 2006; Wei et al, 2011; Zhu and Zhang, 1995). It is well known that the control law is typically designed according to the dynamic model of the controlled object for the dynamics-based control approach.…”
Multiple launch rocket system, a type of launching platform used to launch kinetic load to hit the target, is an extremely complicated mechanical system with strong vibration because of the jet force. In this study, a nonlinear dynamic model and vibration control of a multiple launch rocket system are presented to reduce vibration and improve position accuracy. A simplified dynamic model of the multiple launch rocket system is derived using the Newton–Euler method, which facilitates the controller design considering the strong complexity of the multiple launch rocket system. On this basis, the feedback linearization technique is introduced to design a nonlinear controller based on the deduced dynamic model. The simulated and experimental results show that the simplified dynamic model–based control effectively can reduce vibration level of the launching system and make the azimuth and elevation angles reach the desired values with smaller error despite of each rocket’s jet force.
The multibody system transfer matrix method (MSTMM), a novel dynamics approach developed during the past three decades, has several advantages compared to conventional dynamics methods. Some of these advantages include avoiding global dynamics equations with a system inertia matrix, utilizing low-order matrices independent of system degree of freedom, high computational speed, and simplicity of computer implementation. MSTMM has been widely used in computer modeling, simulations, and performance evaluation of approximately 150 different complex mechanical systems. In this paper, the following aspects regarding MSTMM are reviewed: basic theory, algorithms, simulation and design software, and applications.Future research directions and generalization to more applications in various fields of science, technology, and engineering are discussed.
In order to study the structural dynamic response and the separation rule of launch tube and missile of the overhang cold launching system during launching, and provide a basis for the design of new overhang launching system, a dynamic model of the overhang cold launching system was established by using the rigid-flexible coupling method and multi-body dynamics according to the structural characteristics and ejection physical process of the overhang cold launching system. The accuracy and rationality of the modeling method proposed by this paper were validated against the test. Based on this, the dynamic response of ejection and outlet attitude were analysed. The results show that the dynamic model of overhang cold launching system can accurately reflect the vibration characteristics of the system. A large longitudinal displacement of the center of launch tube will occur during the ejection process. The oscillation frequency is relatively small, but the structural vibration caused by the ejection impact will have a great influence on the pitching attitude of the missile. The vibration response of the adjacent launch tube is small, which is beneficial for the continuous launching of the overhang launching system. The research results can provide a basis for the subsequent design of vibration reduction.
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