Nutation instability of spinning solid rocket motor spacecraft

Yang, Dan; Xiong, Yongliang; Ren, Qiao; Wang, Xianyong

doi:10.1016/j.cja.2017.06.005

Cited by 10 publications

(6 citation statements)

References 30 publications

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“…Mayoritas riset yang dituangkan dalam paper jurnal menggunakan static margin (SM) sebagai parameter umum untuk memeriksa kestabilan statik dalam arah sumbu longitudinal dan menggunakan jarak longitudinal [10] sebagai parameter tolok ukur efektifitasnya. Frekuensi osilasi yang besar mudah menyebabkan roket mengalami gerakan tak terkendali [11], oleh karenanya SM telah diteliti agar dibatasi rentang gesernya [12].…”

Section: Pendahuluanunclassified

Analisa Pengaruh Aerodinamika Pada Margin Stabilitas Mortir Latih 81 Mm Dengan Sistem Kompresi Udara

Imron¹,

Widodo

Purnowidodo

2022

JRM

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Mortar is one type of weapon used by Infantry units. One type of mortar that is widely used, especially in technical training, is the 81 mm mortar prototype produced by PT. Pindad, which has a 7.62 mm caliber munitions thruster with an average range of 110 meters. However, this mortar still has unstable aerodynamics. Therefore, this study was conducted to design a safe mortar prototype with a stability margin value, so it can determine the range and improve the troop skills. Computational fluid dynamic simulation was conducted through the ANSYS software to simulate important aerodynamic properties in this study. The angle variation of the barrel in firing used is 450,550 and 650 with compression pressure variation of 16,18, 20, 22, 24, 26, 28, 30, 32 bar. Meanwhile, the angle modification of the mortar fin is 330,440,550 and the aerodynamic simulation was carried out at 20, 30, 40 m/s speeds. The results showed that the design of an 81 mm mortar prototype which has a fin angle of 330 at a simulated speed of 20,30,40 m/s, an angle of attack of 450,550, 650 has the smallest drag force and lift force and the smallest number of postive pitch moments, but still has a standard margin of stability of about 1.57-1.81 caliber.

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Section: Pendahuluanunclassified

Analisa Pengaruh Aerodinamika Pada Margin Stabilitas Mortir Latih 81 Mm Dengan Sistem Kompresi Udara

Imron¹,

Widodo

Purnowidodo

2022

JRM

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“…where the first term on the right-hand side of Equation (17) evaluates to zero since n h is fixed in Q . Then, substituting for ω Q from Equation (16) in Equation (17) gives…”

Section: Angular Momentum Of a Variable Mass Systemmentioning

confidence: 99%

“…A control volume approach [8,9] to account for continuous mass variation subsequently emerged which has since become the modeling standard amongst the community of researchers on rocket flight dynamics. Recent work using the control volume formulation has focused on equation of motion formulation for general variable mass systems [10,11], modeling and analysis of rocket-type systems [12][13][14][15] and an abstraction of the rocket problem [16], and stability of transverse rotational motion in solid rocket motors [17]. The developments presented here on angular momentum also utilize this control volume formulation.…”

Section: Introductionmentioning

confidence: 99%

“…Since the Explorer-1 anomaly [18], the angular momentum property of spinning bodies has received significant attention in the field of spacecraft dynamics and controls as it provides a platform for attitude stability analysis [19,20] and informs innovative attitude control strategies, such as dual-spin satellites [21]. Angular momentum conservation of freely spinning bodies is the backbone that permits explicit solutions to the second Euler angle, or the nutation angle, of torque-free axisymmetric systems [22].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Angular momentum of free variable mass systems is partially conserved

Nanjangud

Eke

2018

Aerospace Science and Technology

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Variable mass systems are a classic example of open systems in classical mechanics with rockets being a standard practical example. Due to the changing mass, the angular momentum of these systems is not generally conserved. Here, we show that the angular momentum vector of a free variable mass system is fixed in inertial space and, thus, is a partially conserved quantity. It is well known that such conservation rules allow simpler approaches to solving the equations of motion. This is demonstrated by using a graphical technique to obtain an analytic solution for the second Euler angle that characterizes nutation in spinning bodies.

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“…This misalignment produces a disturbance torque that results in attitude instability and also thrust vector deviation from the desired inertial direction (Ayoubi, 2007; Kong et al, 2016; Martin and Longuski, 2014, 2015). Spin stabilized control is a simple structural method for use in orbital maneuvers of spacecraft (Kong et al, 2016; Morozov et al, 2016; Yang et al, 2017). The criteria in the spinning thrusting problem have been less energy utilization and optimum maneuver execution (McDonald et al, 2014; Safa et al, 2018).…”

Section: Introductionmentioning

confidence: 99%

Velocity pointing error reduction for symmetric spinning spacecraft via a two-burn scheme

Liao

Zhang

2019

Transactions of the Institute of Measurement and Control

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During axial thrusting of a symmetric spinning spacecraft, misalignment and center-of-mass offset can cause unwanted body-fixed torques. The two-burn scheme is applied to eliminate velocity pointing error. Solutions for angular velocity, Euler angle, and inertial velocity with nonzero initial conditions are derived in a new form for axisymmetric spacecraft with constant mass. Simulations show that the solutions closely match numerical simulations and the two-burn scheme decrease the velocity pointing error obviously. Based on the solutions, the effect of two-burn scheme is analyzed. The results show that the spacecraft will obtain the minimum velocity pointing error if the burn and coast times are controlled accurately. Also, the two-burn scheme allows for a lower spin rate and the spacecraft can be maneuvered at nonzero initial conditions compared with the continuous thrust scheme.

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Nutation instability of spinning solid rocket motor spacecraft

Cited by 10 publications

References 30 publications

Analisa Pengaruh Aerodinamika Pada Margin Stabilitas Mortir Latih 81 Mm Dengan Sistem Kompresi Udara

Analisa Pengaruh Aerodinamika Pada Margin Stabilitas Mortir Latih 81 Mm Dengan Sistem Kompresi Udara

Angular momentum of free variable mass systems is partially conserved

Velocity pointing error reduction for symmetric spinning spacecraft via a two-burn scheme

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