Hybrid Rocket Nozzle Erosion with Microaluminum-Added Fuel

Karakaş, Hakkı Muammer; Kahraman, Busra; Özkol, İbrahim; Karabeyoğlu, Arif

doi:10.2514/1.b38681

Cited by 1 publication

(2 citation statements)

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“…We use the incremental PID control algorithm to solve for this. The formula of recurrence for the incremental PID is obtained from the literature [18]:…”

Section: Incremental Pid Control Algorithmmentioning

confidence: 99%

“…Our team has added metals to fuels of hydroxyl-terminated polybutadiene (HTPB) to improve their performance. Adding 58% aluminum to HTPBbased fuels improves the specific impulse and regression rate [15,16], but large amounts of aluminum additives lead to nozzle ablation, uncertainty in regression rate, and the instability of combustion pressure [15,17,18] that directly yield unpredictable and unstable thrust and indirectly lead to debris emissions [5,19,20]. Therefore, we seek to compensate for nozzle ablation and oscillations in thrust by regulating the flow rate of the oxidizer from the perspective of the control system.…”

Section: Introductionmentioning

confidence: 99%

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Experimental Investigation into Closed-Loop Control for HTPB-Based Hybrid Rocket Motors

et al. 2023

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Space exploration greatly facilitates the development of advanced propulsion systems. Extensive research has shown that hybrid rocket motors have bright prospects for use in variable-thrust propulsion systems. However, the variable-thrust precision control of a hybrid rocket motor with a high-mass fraction of aluminum has not been adequately explored. In this paper, we propose a closed-loop control system for a high-performance laboratory-scale hybrid rocket motor, and verify its performance through tests on a hybrid rocket motor containing 98% hydrogen peroxide and hydroxyl-terminated polybutadiene with 58% of an aluminum additive. The results show that, first, the average value of thrust in the stable sections in the three stages were 400.7 N, 599.1 N, and 400.1 N when the target values were 400 N, 600 N, and 400 N, respectively. Second, the average thrust was stable, and the control error of the average value was better than 0.5%. Third, the real-time error in thrust was controlled to within ± 20 N with a steady-state error smaller than 5%. These results indicate that the proposed closed-loop control strategy for hybrid rocket motors with a high-mass fraction of aluminum can maintain a constant thrust and smooth transitions in case of variable thrust.

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“…We use the incremental PID control algorithm to solve for this. The formula of recurrence for the incremental PID is obtained from the literature [18]:…”

Section: Incremental Pid Control Algorithmmentioning

confidence: 99%