Write a python code that makes a schematic drawing of the engine in three projections
Front,
Side,
Top.
1. List of Materials for the Engine
To build a reliable and efficient MHPEPS, you need materials that can withstand high temperatures, have excellent electrical conductivity, and offer mechanical strength while being lightweight. Below is a detailed list:
a. Structural Materials
1.	Aluminum (Al)
o	Properties: Lightweight, good thermal conductivity, corrosion-resistant.
o	Use: Structural framework, casing, mounting brackets.
2.	Titanium (Ti)
o	Properties: High strength-to-weight ratio, excellent corrosion resistance, capable of withstanding high temperatures.
o	Use: Critical structural components, joints, and areas subject to high mechanical stress.
3.	Carbon Fiber Reinforced Polymer (CFRP)
o	Properties: Extremely high strength and stiffness, lightweight, good thermal properties.
o	Use: Composite panels, lightweight structural elements, protective housings.
b. Plasma Thruster Components
1.	Nickel-Chromium Alloys (e.g., Inconel)
o	Properties: High-temperature resistance (up to ~1300°C), excellent corrosion resistance.
o	Use: Ionization chamber walls, electrodes, plasma channels.
2.	Tantalum (Ta) and Tungsten (W)
o	Properties: Extremely high melting points, durable under intense thermal and mechanical stress.
o	Use: Electrodes, components directly interacting with plasma.
3.	Graphite
o	Properties: High thermal conductivity, good electrical conductivity, resilient against thermal shock.
o	Use: Anodes, cathodes, and other components exposed to plasma.
c. Thermal Management Materials
1.	Copper (Cu)
o	Properties: Superior thermal conductivity.
o	Use: Radiators, heat sinks, thermal conduits.
2.	Ceramic Materials (e.g., Aluminum Oxide, Silicon Carbide)
o	Properties: High thermal resistance, electrical insulation.
o	Use: Thermal barriers, insulation layers, heat-resistant components.
d. Electrical Components and Insulation
1.	Polyimide Films (e.g., Kapton)
o	Properties: High thermal stability, excellent electrical insulation.
o	Use: Insulating layers, flexible wiring, circuit boards.
2.	Silver and Gold
o	Properties: Excellent electrical conductivity, resistant to oxidation.
o	Use: Electrical contacts, connectors, high-performance wiring.
e. Electromagnetic Shielding Materials
1.	Mu-Metal or Other High-Permeability Alloys
o	Properties: Effective at shielding against electromagnetic interference (EMI).
o	Use: Shielding sensitive electronic components from plasma-generated EMI.





2. Structure of the MHPEPS Engine
The MHPEPS engine comprises several interconnected subsystems, each responsible for specific functions essential for propulsion. Here's a detailed breakdown:
a. Main Components
1.	Energy Generation Block
o	Subsystems:
o	Solar Panels: Capture solar radiation and convert it into electrical energy.
o	Nuclear Batteries (Optional): Provide a stable power source for missions in low-light conditions or longer durations.
o	Energy Manager: Controls and distributes generated power to various engine systems based on current demands.
2.	Plasma Propulsion Unit
o	Subsystems:
o	Ionization Chamber: Converts neutral propellant gas (e.g., xenon) into ions using high voltages.
o	Electrodes (Anode and Cathode): Generate electric fields that accelerate ions to produce thrust.
o	Gas Supply System: Includes valves and pumps to regulate the flow of propellant into the ionization chamber.
o	Radiators: Dissipate excess heat produced during ionization and acceleration processes.
3.	Thermal Management System
o	Subsystems:
o	Radiators: Large, high-thermal-conductivity surfaces to emit excess heat into space.
o	Heat Exchangers: Transfer heat from hot components to radiators efficiently.
o	Phase Change Materials (PCM): Absorb large amounts of heat during phase transitions to stabilize temperatures.
o	Active Cooling Systems (Optional): Use fluid-based cooling to manage heat loads dynamically.
4.	Structural Framework
o	Components:
o	Main Frame: The backbone of the engine, providing mechanical support to all other components.
o	Composite Panels: Lightweight panels that house internal components and provide aerodynamic protection.
o	Mounting Points: Interfaces where engines attach to the spacecraft structure.
5.	Control and Monitoring Unit
o	Subsystems:
o	Computers and Controllers: Execute control algorithms, manage subsystems, and process sensor data.
o	Sensors: Monitor parameters like temperature, pressure, thrust, and electrical currents.
o	PID Controllers: Maintain stable thrust output by adjusting energy and propellant flow based on sensor feedback.
b. Interaction Between Subsystems
1.	Energy Flow:
o	Solar panels and nuclear batteries generate electrical power.
o	The energy manager allocates power to the plasma propulsion unit and thermal management system based on real-time demands.
2.	Propulsion Mechanism:
o	The gas supply system introduces xenon into the ionization chamber.
o	High voltage between the anode and cathode ionizes the xenon gas, generating ions.
o	Electric fields accelerate these ions out of the thruster, producing thrust via Newton's third law.
3.	Heat Management:
o	Ionization and acceleration processes generate significant heat.
o	The thermal management system captures and dissipates this heat through radiators and heat exchangers to prevent overheating of structural and electronic components.
4.	Control Loop:
o	Sensors collect data on system performance and environmental conditions.
o	Control algorithms, primarily using PID controllers, adjust voltages and propellant flow rates to maintain desired thrust levels and optimize efficiency.
o	Feedback ensures that any deviations from set parameters are corrected in real-time.




3. Verbal Blueprint of the Engine
Imagine the MHPEPS engine as a multi-layered, integrated system where each layer and component plays a crucial role in the overall functioning of the propulsion mechanism.
a. Overall Layout
1.	Outer Shell:
o	Material: Carbon Fiber Reinforced Polymer (CFRP).
o	Function: Acts as the main protective casing, providing structural integrity while minimizing weight.
o	Features: Modular compartments for easy assembly and maintenance.
2.	Energy Generation Compartment:
o	Location: Central or one end of the engine module.
o	Components:
o	Solar Panels: Mounted outward-facing on the exterior to maximize sunlight exposure.
o	Nuclear Batteries: Enclosed within shielded sections for safety, providing backup power.
o	Wiring and Connectors: Run internally to distribute power to other subsystems.
3.	Propulsion System Compartment:
o	Location: Centrally located for balanced thrust and stability.
o	Components:
o	Ionization Chamber: Cylindrical chamber where xenon gas is ionized.
o	Electrodes (Anode and Cathode): Positioned at either end of the ionization chamber, connected to high-voltage power supplies.
o	Gas Supply Lines: Inlet for xenon gas, regulated by precision valves and pumps.
o	Thrust Nozzles: Openings through which accelerated ions exit, directed to produce thrust.
4.	Thermal Management Compartment:
o	Location: Adjacent to the propulsion system and energy generation areas.
o	Components:
o	Radiators: Flat, expansive panels optimized for radiating heat into space.
o	Heat Exchangers: Tubular systems that transfer heat from internal components to radiators.
o	Phase Change Material Containers: Integrated within structural walls to absorb transient heat spikes.
5.	Control and Monitoring Compartment:
o	Location: Separated from high-temperature areas to protect sensitive electronics.
o	Components:
o	Main Control Unit: Houses the central computer systems.
o	Sensor Arrays: Distributed throughout the engine to monitor operational parameters.
o	Interface Ports: For communication with the spacecraft's main systems.
6.	Structural Framework:
o	Material: Titanium for high-stress points, CFRP for lightweight areas.
o	Features: Reinforced joints and support beams connecting all compartments, ensuring rigidity and durability.
b. Functional Flow
1.	Power Generation and Distribution:
o	Solar panels absorb sunlight, converting it into electrical energy.
o	Nuclear batteries provide continuous power, especially during eclipses or prolonged missions.
o	The energy manager intelligently distributes power to the plasma thruster and thermal management systems based on real-time needs.
2.	Propulsion Mechanism:
o	Xenon gas is introduced into the ionization chamber via controlled flow rates.
o	High-voltage electrodes ionize the xenon atoms, creating positively charged ions.
o	An electric field accelerates these ions towards the thrust nozzle, ejecting them at high velocities to produce reactive thrust.
3.	Thermal Regulation:
o	Heat generated from ionization and ion acceleration is transferred to heat exchangers.
o	The thermal management system cools critical components by radiating excess heat through large, strategically placed radiators.
o	Phase change materials absorb and buffer sudden temperature increases, maintaining system stability.
4.	Control and Feedback Loop:
o	Sensors continuously monitor the engine’s performance, measuring parameters like thrust, temperature, and electrical currents.
o	Data is sent to the main control unit, which processes the information using PID controllers.
o	PID controllers adjust the high-voltage supply and gas flow rates to maintain desired operational parameters, ensuring efficient and stable thrust output.
c. Maintenance and Modularity
o	Modular Design: Each compartment is designed as a modular unit, allowing for easy replacement, upgrades, and repairs without disrupting the entire engine system.
o	Access Panels: Reinforced access points provide technicians with entry to internal components for maintenance.
o	Redundancy: Critical systems, such as power distribution and control units, have redundant pathways to ensure continued operation in case of individual component failures.