Reconstruction techniques for determining <i>O/F</i> in hybrid rockets

Saito, Yuji; Kamps, Landon T.; Tsuji, Ayumu; Nagata, Harunori

doi:10.2514/6.2021-3499

Cited by 2 publications

(2 citation statements)

References 22 publications

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“…The oxidizer-to-fuel ratio gradually increased in the third section of steady thrust, and this led to a gradual decrease in the specific impulse of the oxidizer, mainly because of the low mass flux and the reduced regression rate in the late stage of combustion. When calculating the control parameters, we assumed that the average specific im- In consideration of the thrust throttling operation of the motor, the reconstruction proposed in previous articles [35,36] was referred to in order to obtain the realtime c* and a more accurate regression rate and fuel flow rate, which is shown in Figure 16. Compared with the IRRM method, the OPTMA-FE-L method added real-time information about the thrust and took into account the real-time variation of c*.…”

Section: Discussionmentioning

confidence: 99%

“…The mass flow rate of the fuel did not vary greatly in each section of stable thrust due to the joint effects of the gradually decreasing regression rate and the gradually increasing area of combustion. In consideration of the thrust thro ling operation of the motor, the reconstruction technique proposed in previous articles [35,36] was referred to in order to obtain the realtime c* and a more accurate regression rate and fuel flow rate, which is shown in Figure 16. Compared with the IRRM method, the OPTMA-FE-L method added real-time information about the thrust and took into account the real-time variation of c*.…”

Section: Discussionmentioning

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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Section: Discussionmentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%