HYBRID PROPULSION SWIRL INJECTOR WITH CUSTOMIZABLE OXIDIZER FLOW CONTROL AND WIRELESS MONITORING

Abstract

The present invention relates to a hybrid propulsion system [100], particularly a swirl injector [102] in the hybrid propulsion system designed to optimize oxidizer and fuel mixing for enhanced combustion efficiency, stability, and thrust, with features including a modular design, pintle-controlled oxidizer flow, and integrated safety mechanisms. Said invention, featuring a modular circular body [104] with a customizable, removable bottom section [108], the injector [102] allows for adjustable pore configurations that optimize oxidizer and fuel mixing, enhancing combustion efficiency and stability. A pintle [106] mechanism precisely regulates oxidizer flow, moving upward during filling and downward during combustion. Further it is integrated with a solenoid-controlled fill stem [110], temperature [112] and pressure [114] sensors, and a wireless communication interface, the system ensures safe operation through real-time monitoring of oxidizer levels. The swirl injector offers adaptable, stable, and efficient propulsion, making it ideal for cost-effective satellite deployment and high-performance defense applications.

Specification

Description:FIELD OF THE INVENTION:
The present invention relates to a hybrid propulsion system, particularly a swirl injector in the hybrid propulsion system designed to optimize oxidizer and fuel mixing for enhanced combustion efficiency, stability, and thrust, with features including a modular design, pintle-controlled oxidizer flow, and integrated safety mechanisms.
BACKGROUND OF THE INVENTION:
In a solid propulsion system, the propellant and oxidizer are mixed, making it simple and ready for immediate use. However, this simplicity comes with significant safety concerns, as handling, logistics, and transportation require extensive safety measures, resulting in high costs. Additionally, in the event of accidental ignition, the system is highly explosive. Once the solid propellant is ignited, it cannot be controlled, throttled, or shut down; it will continue to burn until all the fuel is consumed. In contrast, liquid rocket propulsion systems use separate tanks for the oxidizer and fuel, both in a liquid state. This allows for easy control, throttling, and shutdown. However, these systems face challenges due to high manufacturing costs, complex designs involving numerous tubes, turbo pumps, and the need for a large workforce. If accidental ignition occurs, the risk of explosion is still high due to the nature of liquid fuels.
Hybrid propulsion systems offer a balanced alternative. They use separate tanks for the oxidizer and solid wax fuel, with a swirl injector positioned between them. The design allows for easy control, throttling, and shutdown, like liquid propulsion, but at approximately one-third of the cost. Hybrid systems do not require the complex manufacturing, maintenance, or extensive manpower associated with liquid propulsion. Moreover, in the event of accidental ignition, hybrid systems are safer as they are non-explosive and will only burn the fuel without a dangerous explosion, effectively having a zero TNT equivalent. This makes hybrid propulsion a cost-effective, safe, and efficient choice for modern aerospace applications.
KR101631891B1 discloses a pintle-swirl hybrid propellant injection device is installed on the inside of a housing forming a combustion chamber to inject a propellant towards the combustion chamber to optimize a mixing ratio of fuel/oxidizer of high-temperature high-pressure gas recirculating in the frontal and radial directions of the injection tip to allow efficient combustion.
US2023012171A1 discloses a propellant injector is adapted to be installed to a hybrid rocket engine and includes an injector casing, a tube and a plurality of blades configured to cause vortices toward a combustion chamber of the hybrid rocket engine when being driven to rotate.
US11391245B2 discloses a motor has an oxidizer injector, is mainly suitable for using in a combustion chamber, the oxidizer injector has a body having a first runner assembly to form a forward swirl and a second runner assembly arranged along an axis injects oxidizer into the combustion chamber to form a reverse swirl, so as to solve the problem of axial torsion imbalance in the combustion chamber.
However, the existing prior arts have considered the complex internal components and affected from stability and combustion issues.
Accordingly, there exists a need for a swirl injector for hybrid propulsion systems, particularly designed to optimize oxidizer and fuel mixing for enhanced combustion efficiency.

OBJECTS OF THE INVENTION

One or more of the problems of the conventional prior art may be overcome by various embodiments of the system and methods of the present invention.
The principal object of the present invention is to provide a swirl injector for hybrid propulsion systems that optimizes oxidizer and fuel mixing for enhanced combustion efficiency and stability.
Another object of the present invention is to incorporate a pintle mechanism that precisely controls oxidizer flow during filling and combustion phases.
One another object of the present invention is to offer a modular and customizable design that allows for easy adjustment of pore configurations based on mission requirements.
A further object of the present invention is to improve thrust output and reduce fuel consumption through efficient and stable combustion.
Another object of the present invention is to ensure safe and reliable operation with integrated sensors for monitoring temperature and pressure during the oxidizer filling process.
One another object of the present invention is to enable cost-effective deployment of hybrid propulsion systems in rockets and defense applications.
A further object of the present invention is to facilitate easy maintenance and adaptability through a removable and interchangeable injector section.
Other objects and advantages of the present disclosure will be more apparent from the following description, which is not intended to limit the scope of the present disclosure.

SUMMARY OF THE INVENTION

Thus, according to the basic aspect of the present invention, there is provided a hybrid propulsion system, comprising:

a swirl injector;
a modular circular injector body;
a pintle mechanism configured to regulate oxidizer flow during filling and combustion phases;
a customizable and removable bottom section allowing for adjustment of pore size and configuration;
a solenoid-controlled fill stem for precise oxidizer flow management and prevention of overfilling;
a temperature sensor integrated to monitor the oxidizer tank's temperature;
a pressure sensor configured to measure and control the oxidizer tank's internal pressure; and
a T8 LabJack device integrated into the ignition system for reliable and controlled ignition of the propulsion system.

Another aspect of the present invention, wherein the pintle mechanism moves upward during the oxidizer filling process and downward during combustion, ensuring precise oxidizer flow and stable combustion. The control is essential for ensuring that the correct amount of oxidizer enters the combustion chamber at the right time, maintaining combustion stability and performance.

Another aspect of the present invention, wherein the swirl injector includes nine small-diameter pores arranged at 30-degree intervals to generate a swirling motion that optimizes the mixing and atomization of fuel and oxidizer, leading to improved combustion efficiency. The 30-degree arrangement ensures an optimal swirling motion of the oxidizer, which enhances mixing with the fuel, resulting in more efficient combustion, higher thrust, and better overall system performance.

Another aspect of the present invention, wherein the modular circular injector body allows easy replacement of the bottom section for adjustment of pore configurations of three, six and nine mm based on mission requirements and operational conditions. The ability to replace the bottom section allows for customization of the injector's performance to meet specific mission needs. For example, different pore configurations can be used depending on whether the mission prioritizes thrust, fuel efficiency, or endurance.

Another aspect of the present invention, wherein the solenoid-controlled fill stem prevents overfilling by venting excess oxidizer and seals the filling ports during ignition. This prevents backflow of oxidizer, which could disrupt combustion or cause safety issues, ensuring a stable and efficient burn.

Another aspect of the present invention, wherein the temperature sensor is connected to a monitoring system that provides real-time temperature readings of the oxidizer tank to ensure safe and optimal operating conditions. By providing real-time data, the temperature sensor ensures that the system remains within safe operating limits, preventing overheating or unsafe temperature levels that could compromise the system's performance or safety.

Another aspect of the present invention, wherein the pressure sensor continuously monitors the internal pressure of the oxidizer tank to ensure stability and safe operation. The pressure sensor ensures that the oxidizer tank maintains a consistent pressure, which is vital for stable combustion and system safety. Sudden pressure changes could result in erratic combustion or even system failure, making this sensor critical for reliable performance.

The hybrid propulsion system of claim 1, wherein the wireless communication interface is configured to transmit real-time data regarding the oxidizer flow rate, temperature, and pressure to a ground control system for monitoring and adjustment. The ability to remotely monitor and adjust these parameters provides operators with the control needed to optimize system performance and ensure mission success.

Another aspect of the present invention, wherein the T8 LabJack device converts standard voltage to high voltage, enabling reliable and controlled ignition of the solid wax fuel. The reliable ignition is crucial for the propulsion system to operate as expected, and the LabJack device ensures that ignition occurs safely and predictably.

Another aspect of the present invention, further comprising a Zigbee-based ground supporting control system for wireless monitoring and control of key parameters, with real-time data displayed on a monitor for operational adjustments. The real-time data is displayed on a monitor, enabling operators to adjust during operation. Said feature adds another layer of control, improving system reliability and operational safety.

Another aspect of the present invention, designed to handle an average oxidizer flow rate of 754.3 g/s, achieving a peak thrust of 2000 N, a specific impulse of 217 s, and a total impulse of 22,940 Ns during a burn duration of 11.47 seconds. These metrics quantify the system's efficiency and performance, demonstrating its capabilities in real-world applications.

BRIEF DESCRIPTION OF THE DRAWINGS

Figure 1 illustrates an embodiment of various functional components of an assembled hybrid propulsion system along with integrated modules, according to the present invention.
Figure 2 illustrates an embodiment of various functional components of a hybrid propulsion system, according to the present invention.
Figure 3 illustrates an embodiment of an engine closure, according to the present invention.
Figure 4 illustrates an embodiment of an aft closure, according to the present invention.
Figure 5 illustrates an embodiment of a fill stem, according to the present invention.
Figure 6 illustrates an embodiment of an injector hub, according to the present invention.
Figure 7 illustrates an embodiment of an outer casing, according to the present invention.
Figure 8 illustrates an embodiment of a phenolic nozzle, according to the present invention.
Figure 9 illustrates an embodiment of a pintle, according to the present invention.
Figure 10 illustrates an embodiment of a pressure sensor, according to the present invention.
Figure 11 illustrates an embodiment of a solid wax fuel cartridge, according to the present invention.
Figure 12 illustrates an embodiment of a swirl injector assembly, according to the present invention.
Figure 13 illustrates an embodiment of a swirl injector, according to the present invention.
Figure 14 illustrates an embodiment of a temperature sensor, according to the present invention.

DETAILED DESCRIPTION OF THE INVENTION WITH REFERENCE TO THE ACCOMPANYING FIGURES

The present invention as herein provided a hybrid propulsion system [100], particularly a swirl injector in the hybrid propulsion system designed to optimize oxidizer and fuel mixing for enhanced combustion efficiency, stability, and thrust, with features including a modular design, pintle-controlled oxidizer flow, and integrated safety mechanisms.
Referring to Figures 1 and 2, in an embodiment, the functional components of the hybrid propulsion system assembled with various functional components illustrated. Said hybrid propulsion system, comprises of a swirl injector [102], a modular circular injector body [104], a pintle [106] mechanism configured to regulate oxidizer flow during filling and combustion phases, a customizable and removable bottom section [108] allowing for adjustment of pore size and configuration, a solenoid-controlled fill stem [110] for precise oxidizer flow management and prevention of overfilling, a temperature sensor [112] integrated to monitor the oxidizer tank's temperature, a pressure sensor [114] configured to measure and control the oxidizer tank's internal pressure, and a T8 LabJack [116] referred as an interfacing device integrated into the ignition system for reliable and controlled ignition of the propulsion system.

The hybrid propulsion system [100] is designed with a robust outer casing [148] made from a durable aluminum alloy, providing both structural integrity and lightweight characteristics. The cylindrical casing houses the key internal components: a swirl injector [102], an enhanced solid wax fuel cartridge [120], and a phenolic nozzle [122]. The swirl injector [102], positioned within a quarter section of the casing, features nine pores angled at 30 degrees to facilitate optimal mixing of the oxidizer with the fuel during combustion. Below this, the solid wax fuel cartridge [120] is securely placed, ensuring proper alignment within the combustion chamber. An ignition cable is attached to the fill stem, contacting the wax fuel to enable precise ignition.

The fill stem [110] is a critical component, equipped with two inlets [150] and two outlets [144]. One inlet [150] connects to a nitrous oxide (NOx) oxidizer supply, while the other connects to a gaseous oxygen (GOx) and nitrogen source for purging. The outlets [144] are aligned with the pintle mechanism inside the hybrid rocket injector. This design allows the fill stem [110] to push the pintle upwards during the oxidizer filling process, facilitating the flow of the oxidizer through the side ports into the upper storage section. The storage section can hold the oxidizer at pressures up to 58 bar, with vent tubes featuring 1mm diameter holes to release excess gas and maintain pressure equilibrium. A temperature sensor [112], for an instance thermocouple is strategically placed beneath the vent tubes to monitor the temperature, ranging from -80°C to -90°C. The phenolic nozzle [122] at the combustion chamber exit is precisely shaped to direct exhaust gases and generate thrust. The system is sealed with an aft closure [142], screwed to the back end of the outer casing, ensuring secure containment of all components during operation.

Referring to Figure 3, in an embodiment, the engine closure is illustrated. Said engine closure provisioned to cover the combustion chamber strategically.

Referring to Figure 4, in an embodiment, an aft closure [142] is illustrated. Said component that screws onto the back end (aft) of the outer casing [148]. Said component provisioned to seal the rear of the propulsion system, ensuring all gases are directed through the nozzle. It provides structural integrity and allows for easy assembly and disassembly for maintenance or inspection.

Referring to Figure 5, in an embodiment of a fill stem is illustrated. Said component provisioned with two inlets [150] and two outlets [144]. One inlet connects to the oxidizer (nitrous oxide, NOx), and the other connects to gaseous oxygen (GOx) and nitrogen for purging purposes. It facilitates the filling of the oxidizer into the storage section and allows for purging and ignition processes. During filling, it pushes the pintle upward to permit oxidizer flow. It also houses the ignition cable for initiating combustion.

Referring to Figure 6, in an embodiment of an injector hub [146] is illustrated. The injector hub, made from durable stainless steel (SS), acts as a vital connection point between the pintle and the swirl injector plate in hybrid propulsion systems. Its design supports flexible injector configurations, allowing for the use of interchangeable models tailored to specific mission requirements. It is serving as the main pathway for oxidizer delivery, the hub ensures a precise, efficient spray from the oxidizer tank, optimizing combustion and enhancing the propulsion system's adaptability for varied aerospace applications. The adaptability is crucial for mission-specific tuning, as it allows different injector configurations to be easily implemented, directly impacting the system's performance and efficiency.

Referring to Figure 7, in an embodiment of an outer casing [148] is illustrated. Said outer casing is constructed from an aluminum alloy, the outer casing provides a lightweight yet sturdy structure for the propulsion system. Its cylindrical shape is designed to house all internal components securely. It serves as the primary structural support, containing and protecting internal components such as the oxidizer storage, swirl injector, fuel cartridge, and nozzle. It maintains the integrity of the system under the stresses of launch and combustion.

Referring to Figure 8, in an embodiment of a phenolic nozzle [122] is illustrated. It is made from phenolic material, shaped to optimize the exhaust flow of combustion gases. Said nozzle directs the high-temperature gases produced during combustion out of the rocket, converting thermal energy into kinetic energy to generate thrust. Its shape and material withstand high temperatures and erosive gases.

Referring to Figure 9, in an embodiment of a pintle [106] is illustrated. Said pintle provisioned as a movable component within the injector that interacts with the fill stem.
During oxidizer filling, the pintle moves upward, allowing oxidizer flow into the storage section. After filling, it moves downward due to pressure differences, sealing the fill stem insertion point and redirecting oxidizer flow through the swirl injector during combustion.

Referring to Figure 10, in an embodiment of a pressure sensor [114] is illustrated. Said pressure sensor is connected to the NOx inlet on the fill stem. It measures the pressure of the oxidizer within the storage section in real-time. It helps monitor filling progress and ensures that the oxidizer is stored at the correct pressure (58 bar).

Referring to Figure 11, in an embodiment of a solid wax fuel cartridge [120] is illustrated. Said solid wax fuel cartridge enhanced wax-based solid fuel positioned below the swirl injector within the combustion chamber. It acts as the fuel source for the hybrid propulsion system. When ignited, it reacts with the oxidizer to produce the high-temperature gases needed for thrust.

Referring to Figure 12 and Figure 13, in an embodiment of a swirl injector [102] assembly is illustrated. It features nine multiple pores arranged at a 30-degree angle. It introduces the oxidizer into the combustion chamber in a swirling motion. This design enhances the mixing of the oxidizer with the solid fuel, promoting efficient and complete combustion.

Referring to Figure 14, in an embodiment of a temperature sensor [112] is illustrated. Said temperature sensor, for an instance a thermocouple positioned beneath the vent tubes within the oxidizer storage section. It monitors the temperature of the oxidizer, ensuring it remains within the desired range of -80°C to -90°C. It provides critical data to prevent thermal anomalies and maintain safe operating conditions.

WORKING MECHANISM:

The hybrid propulsion system operates through a meticulously controlled sequence. The process begins by filling the upper storage section with the oxidizer. The NOx is introduced through the fill stem [110], which moves the pintle [106] upward, allowing the oxidizer to flow through the fill stem's side ports and into the storage section. This continues until the pressure reaches 58 bar, with excess gas vented through the 1mm holes in the vent tubes. The thermocouple [110] ensures the temperature remains within the range of -80°C to -90°C for optimal conditions. The NOx inlet is equipped with a pressure sensor to monitor and display real-time pressure data.

Once the desired temperature and pressure are reached, nitrogen is purged through the fill stem into the solid fuel cartridge for 5 seconds to clear any residuals. Following the purge, gaseous oxygen is introduced into the combustion chamber, initiating the first phase of combustion with the wax fuel. This creates a controlled initial flame. Subsequently, the pressure from the upper oxidizer section causes the pintle [106] to move downward, sealing the fill stem's insertion point. The oxidizer then flows through the swirl injector's [102] nine pores, creating a vortex that ensures efficient mixing with the wax fuel. The resulting combustion generates intense heat and expanding gases, which are directed through the phenolic nozzle [122], producing thrust. This thrust propels the rocket upwards, with the high-pressure oxidizer flow ensuring consistent performance and optimal combustion.

PERFORMANCE ANALYSIS:

The experimental approach for testing the swirl injector focused on validating its ability to improve combustion efficiency and optimize fuel-oxidizer mixing, key factors in enhancing the performance of hybrid propulsion systems. The primary testing method employed was the hot fire static test, which allowed for an in-depth assessment of the injector's behavior and performance under real-world combustion conditions.

The swirl injector was integrated into a dedicated test stand that simulated real-world operational conditions. This setup included essential instrumentation, such as a load cell to measure thrust output, pressure sensors to monitor combustion stability, and high-speed cameras to observe flame behavior.
The test stand was designed to allow for quick adjustments and replacement of injector components, facilitating the testing of different configurations. This flexibility enabled a comprehensive evaluation of how various design parameters influenced performance.

The experimental process was organized into five phases, each focusing on optimizing the injector's characteristics to maximize performance. This structured approach ensured that all critical aspects of the design were thoroughly evaluated.
During these phases, different pore configurations (e.g., 3-pore, 6-pore, and 9-pore designs) were tested to analyze their effects on the swirling motion of the oxidizer and the subsequent interaction with the fuel. Adjustments were made based on data from each phase to refine the injector design.

Phase 1: Baseline testing to understand the initial performance with a standard pore design.
Phase 2: Introduction of varying pore sizes and arrangements to observe changes in mixing efficiency.
Phase 3: Adjustments to pore configurations to enhance the swirling motion and fuel atomization.
Phase 4: Extended tests under different oxidizer flow rates to assess adaptability and stability.
Phase 5: Final optimization and validation of the best-performing configuration for consistent thrust output and combustion stability.

Throughout the testing process, critical performance indicators were meticulously measured, including:
Thrust output is measured using the load cell to gauge the injector's effectiveness in generating consistent thrust.
Combustion stability is observed through sensors monitoring ignition delay, flame stability, and pressure oscillations to evaluate the reliability of the injector.
Fuel consumption is analyzed to determine how efficiently the injector mixed the fuel and oxidizer, leading to reduced waste and improved efficiency.

Table 1: illustrates the performance of said hybrid propulsion system
Parameter Value
Peak Thrust 2000 N
Average Oxidizer Flow Rate 754.3 g/s
Regression Rate 4.1 mm/s
Peak Chamber Pressure 36.2 bar
Run Tank Pressure 51.8 bar
Specific Impulse 217 seconds
Total Impulse 22,940 Ns
Burn Duration 11.47 seconds

The experimental results indicated that increasing the number of pores led to enhanced mixing and more efficient combustion, with the 9-pore design delivering the best performance. The increased swirl effect generated by multiple small-diameter pores facilitated thorough oxidizer and fuel mixing, resulting in improved thrust output. Additionally, the tests demonstrated that the swirl injector maintained stable combustion across a range of operating conditions, reducing risks associated with pressure oscillations and combustion instability. This consistent performance validated the injector's adaptability for diverse propulsion applications.

APPLICATIONS OF THE PRESENT INVENTION

The hybrid propulsion system offers several significant applications, particularly in the field of rocketry and aerospace. It provides a reliable and efficient solution for small- to medium-scale rocket launches, benefiting research, space exploration, and defense applications. The ability to store oxidizers at high pressure and achieve a controlled combustion process makes this system ideal for experimental launches and reusable rockets. Its design also supports hybrid missile technology, contributing to advancements in the development of India's missile systems. Additionally, the system's emphasis on safety-using pressure sensors, thermocouple monitoring, and vent tubes-ensures reliability in various operating conditions. This technology represents a step forward in hybrid propulsion, offering a versatile and cost-effective solution for achieving sustained thrust in aerospace missions.

TECHNICAL ADVANCEMENTS OF THE PRESENT INVENTION

The injector's 9-pore design, featuring 30° angled holes, ensures a nearly perfect combustion process with only a 2% propellant loss. The uniform oxidizer flow maximizes fuel-oxidizer mixing efficiency, resulting in high-energy output and reducing wastage, crucial for optimized propulsion in hybrid systems.

The present invention extends burn duration by an additional 0.9 seconds, allowing for more effective fuel utilization and prolonged propulsion cycles. The increase in burn time supports longer missions, as it allows the engine to sustain thrust for extended periods, contributing to mission success and fuel efficiency.

The precision-engineered pintle controls oxidizer flow to minimize combustion oscillations, significantly enhancing engine stability. The stabilization is key for maintaining consistent thrust, preventing performance fluctuations, and ensuring reliable engine operation in diverse operating conditions.

The embodiments herein and the various features and advantageous details thereof are explained with reference to the non-limiting embodiments in the following description. Descriptions of well-known components and processing techniques are omitted to not unnecessarily obscure the embodiments herein. The examples used herein are intended merely to facilitate an understanding of ways in which the embodiments herein may be practiced and to further enable those of skill in the art to practice the embodiments herein. Accordingly, the examples should not be construed as limiting the scope of the embodiments herein. While considerable emphasis has been placed herein on the components and component parts of the preferred embodiments, it will be appreciated that many embodiments can be made and that many changes can be made in the preferred embodiments without departing from the principles of the disclosure. These and other changes in the preferred embodiment as well as other embodiments of the disclosure will be apparent to those skilled in the art from the disclosure herein, whereby it is to be distinctly understood that the foregoing descriptive matter is to be interpreted merely as illustrative of the disclosure and not as a limitation.
, Claims:1. A hybrid propulsion system [100], comprising:
a swirl injector [102];
a modular circular injector body [104];
a pintle [106] mechanism configured to regulate oxidizer flow during filling and combustion phases;
a customizable and removable bottom section [108] allowing for adjustment of pore size and configuration;
a solenoid-controlled fill stem [110] for precise oxidizer flow management and prevention of overfilling;
a temperature sensor [112] integrated to monitor the oxidizer tank's temperature;
a pressure sensor [114] configured to measure and control the oxidizer tank's internal pressure; and
a T8 LabJack device [116] integrated into the ignition system for reliable and controlled ignition of the propulsion system.

2. The hybrid propulsion system as claimed in claim 1, wherein the pintle [106] mechanism moves upward during the oxidizer filling process and downward during combustion, ensuring precise oxidizer flow and stable combustion.

3. The hybrid propulsion system as claimed in claim 1, wherein the swirl injector [102] includes nine small-diameter pores arranged at 30-degree intervals to generate a swirling motion that optimizes the mixing and atomization of fuel and oxidizer.

4. The hybrid propulsion system as claimed in claim 1, wherein the modular circular injector body [104] allows easy replacement of the bottom section [108] for adjustment of pore configurations.

5. The hybrid propulsion system as claimed in claim 1, wherein the solenoid-controlled fill stem [110] prevents overfilling by venting excess oxidizer and seals the filling ports during ignition to prevent backflow.

6. The hybrid propulsion system as claimed in claim 1, wherein the temperature sensor [112] provides real-time temperature readings of the oxidizer tank.

7. The hybrid propulsion system as claimed in claim 1, wherein the pressure sensor [114] continuously monitors the internal pressure of the oxidizer tank.

8. The hybrid propulsion system as claimed in claim 1, wherein the hybrid propulsion system [100] is provisioned to transmit real-time data regarding the oxidizer flow rate, temperature [112], and pressure [114] to a ground control system [126] for monitoring and adjustment.

9. The hybrid propulsion system as claimed in claim 1, wherein the T8 LabJack device [116] converts standard voltage to high voltage, enabling reliable and controlled ignition of the solid wax fuel [120].

10. The hybrid propulsion system as claimed in claim 1, designed to handle an average oxidizer flow rate of 754.3 g/s, achieving a peak thrust of 2000 N, a specific impulse of 217 s, and a total impulse of 22,940 Ns during a burn duration of 11.47 seconds.

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