Aircraft engine twin electrical systems and methods

Abstract

The invention relates to an aircraft engine twin electrical system and method. The aircraft engine simulator comprises: a housing; the at least one actuator or the simulation actuator is arranged in the shell, and the at least one actuator or the simulation actuator is arranged in the shell; at least one sensor or simulation sensor, wherein the at least one sensor or simulation sensor is arranged in the shell; and a wired connection configured to connect the at least one actuator or emulation actuator and the at least one sensor or emulation sensor for communication with a component onboard the aircraft, the aircraft engine simulator is configured to replace an engine for a component on an aircraft having at least one missing or non-operating engine.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS

[0002] Claims the benefit of U.S. Provisional Patent Application No. 63 / 567,926, filed on March 20, 2024. This application is incorporated by reference in its entirety for all purposes. Technical Field

[0003] The technology herein relates to techniques applied during the aircraft assembly process so that final assembly and maintenance areas can be used. The technology also relates to components that simulate or emulate various aspects of an aircraft engine for the limited purpose of allowing further manufacturing of the aircraft before the engine has been installed. Background Art

[0004] Aircraft assembly and maintenance require activities to be performed within agreed deadlines, quality, and cost to ensure an uninterrupted assembly flow and reduce dependency on high-value-added components during the process. However, aircraft assembly lines are complex manufacturing systems where multiple components and subsystems come together to form a complete aircraft. Example assembly steps include:

[0005] •Structural Assembly: Assembling structural, wing and fuselage components.

[0006] •System Installation: Integration of electrical, hydraulic and avionics systems.

[0007] •Engine installation: The engine is assembled and attached to the fuselage.

[0008] •Final Assembly: All components are assembled and the aircraft is ready for testing.

[0009] • Testing and Quality Control: Aircraft undergo several tests to ensure airworthiness and quality.

[0010] The engines are typically manufactured / assembled by an off-site engine supplier. The manufactured engines are shipped to the aircraft manufacturer, bolted to the engine airframe, and their wiring harnesses are connected to various mating electrical connectors on the aircraft airframe's onboard wiring harness.

[0011] Numerous onboard systems on an aircraft monitor, support, and protect the engine. For example, an engine typically includes numerous sensors for monitoring the engine's status and condition, actuators for controlling and operating the engine, and the like. These sensors and actuators are electrically connected to various electronic control and monitoring systems on the aircraft. These various electronic control and monitoring systems on the aircraft cannot function, or function correctly, unless and until the engine is installed in the aircraft. However, it may sometimes be advantageous to perform manufacturing while delaying engine installation.

[0012] Example Figure 1The assembly line diagram shows the engine assembly process and when / where to install it. It shows that the engine relies on other stations that require electrical signals for the fuel, bleed air, fire, electrical, autothrottle, and hydraulic subsystems to operate properly. The fuel, bleed air, fire, electrical, autothrottle, and hydraulic subsystems cannot operate unless / until the engine is installed and these subsystems are connected to the engine.

[0013] In any process, there's a need to evolve new technological process effects. For example, the current final aircraft assembly process is looking for improvements to reduce operating costs. A related factor is increasing the work-in-process (WIP) of the aircraft manufacturing and maintenance process for the highest value-added item in production (in this case, the engine). Finding better ways to increase engine installation efficiency (such as by delaying engine installation) would benefit the manufacturing process.

[0014] Of course, since an aircraft cannot fly until its engines are installed and operational, any aircraft manufacturer relies on engine installation to complete the final assembly of the aircraft. The engines are electrically tested to ensure they function correctly and the aircraft is ready for flight. However, aircraft engine installation is a complex process that requires precision, attention to detail, and strict adherence to safety protocols. Moving or delaying engine installation to the final station or aircraft assembly time can reduce the final component's work-in-progress (WIP), but depending on the required testing, this is often not possible.

[0015] At the same time, aircraft manufacturers are constantly looking for ways to simulate and emulate the dynamic conditions of engines. However, these solutions often or typically use a computer with a circuit board for acquiring and stimulating electrical signals. For example, one approach provides a general-purpose simulator for aircraft engines that includes an industrial personal computer, data acquisition hardware based on the PXI platform, an instrument expansion box, a signal adapter unit, a DC voltage regulator, and special test cables. The simulation is performed in real time using software that contains a mathematical model of the engine. Disadvantages include:

[0016] •Need to access intellectual property information from engine manufacturers;

[0017] •Requires external energy source infrastructure for system operation;

[0018] •High implementation costs.

[0019] Another example method provides a system for real-time simulation of an aircraft engine environment, the system including a digital computer whose inputs are switched by a selection module included in the computer to corresponding sensors or a digital proxy bus configured to transmit digital proxy data generated by a real-time simulator. Disadvantages of this method include:

[0020] •Need to access intellectual property information from engine manufacturers;

[0021] •Requires external energy source infrastructure for system operation;

[0022] •An engine is required to complete the operation;

[0023] •High implementation costs.

[0024] Another aerospace engine performance simulation method for developing an aerospace engine simulation includes the following steps: acquiring a signal from each engine component, simulating each part of the engine in turn until the simulation result meets a judgment condition to create a mathematical model of the engine to be used as an algorithm of a digital engine simulator.

[0025] Disadvantages include:

[0026] •It is necessary to conduct tests using the engine in a real environment to build a mathematical model;

[0027] • Requires development of complex software to implement algorithms and signal stimulation;

[0028] •High implementation costs;

[0029] •Requires the use of industrial personal computers;

[0030] •Switches are needed to select between the signal generator and the actual physical component;

[0031] •Mathematical algorithms are needed to define the model used for simulation. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 An example assembly line image is shown illustrating an example prior art assembly process and when / where an engine is installed without the use of a simulator.

[0033] Figure 2 An example electric engine twin for an aircraft is shown, illustrating the electric engine twin integrated into the aircraft.

[0034] Figure 2A An example flow chart is shown.

[0035] Figure 3An example electric twin engine block diagram with system components is shown.

[0036] Figure 4A and Figure 4B An example assembled box schematic is shown, which illustrates an assembled view of the internal components of the box.

[0037] Figure 5 Example ground support equipment is shown, illustrating assembly equipment featuring a GSE.

[0038] Figure 6 An example interface harness is shown illustrating the wiring and its components. DETAILED DESCRIPTION

[0039] An electrical engine twin for an aircraft is a simulator or emulator of the electrical signals for the aircraft without dynamic changes in engine variables and is intended to ensure, guarantee, test and / or provide for the correct operation of the aircraft's fuel, bleed air, fire protection, electrical, autothrottle and hydraulic systems in the assembled condition.

[0040] The proposed system uses the same engine electrical components, such as sensors, actuators, and control computers, used in the engine's construction, supplemented by primary electrical components (e.g., resistors, inductors, capacitors, switches, relays, thermocouples) that provide electrical signals as sensors and / or actuators installed within the engine or that are not available separately. In one example, the system uses most of the same actuators and sensors found in the engine, but replaces a subset of these actuators and / or sensors that are difficult or impossible to obtain with alternative electronic circuits and components that emulate these subsets.

[0041] As mentioned above, aircraft engine installation is a complex process that requires precision, attention to detail, and strict adherence to safety protocols. In contrast, installing GSE (ground support equipment) is a simpler process because it does not require, for example, mechanical connections to large engines, limiting itself to only electrical and / or signal connections without connecting any hydraulic, fuel, fluid, air paths, or mechanical couplings.

[0042] Electrical and / or signal connections are made with the GSE of each pylon P (ie, a pair of GSEs, a first GSE of the left pylon P and a second GSE of the right pylon P). Figure 2The electrical connections formed in a production environment by interface wiring 102 between the pylon 10 and the GSE 100 are shown. The GSE 100 connected in this manner to the electrical connections 12 that are part of the pylon P / fuselage F ensures that electrical signals are supplied for proper operation of the aircraft's onboard systems (i.e., those onboard systems are "satisfied" and the GSE cannot be distinguished from an actual engine), but the aircraft cannot fly because the actual engine has not yet been installed / mounted / connected to its corresponding pylon P.

[0043] One embodiment features a development method and build system.

[0044] Example Method

[0045] An example method includes: determining which aircraft systems are dependent on the engine in a manufacturing or ground maintenance condition; identifying which signals are exchanged between these systems and the engine; identifying the sensors, actuators, and controllers involved; identifying the electrical interconnections of the components; measuring the electrical quantities (resistance, impedance, and capacitance) of the sensors; defining which sensors will be used and which sensors will be replaced with non-sensor electrical components; encapsulating all components in an external box to build a GSE; and building interface wiring based on an engine electrical interconnection diagram.

[0046] One embodiment provides a method and system for constructing an aircraft electric motor twin that will be able to replace (for limited purposes) the installation of an actual engine in a ground-based aircraft manufacturing or maintenance environment.

[0047] The approach involves identifying which electrical signals will be simulated to ensure correct operation of the fuel, bleed air, fire protection, electrical, autothrottle, and hydraulic systems in a plant environment without dynamic changes in the engine. Figure 2A An example development sequence for 200:

[0048] • Determine which aircraft systems are dependent on the engine (202) during manufacturing or ground maintenance conditions;

[0049] • Identify which signals are exchanged between these systems and the engine (204);

[0050] • Identify the sensors, actuators, and controllers involved (206);

[0051] • Identify the electrical interconnections of components (208);

[0052] •Measurement of electrical quantities of sensors (resistance, impedance and capacitance) (210);

[0053] • defining which sensors will be used and which sensors will be replaced with standard electrical components (212);

[0054] • Enclose all components in an external box to construct the GSE (214);

[0055] • Based on the engine electrical interconnection diagram, construct the interface wiring (216).

[0056] Which sensors, actuators, and controllers will depend on the specific engine design is identified in block 206. See, for example, USP 12180901; USP 12180895; USP 20240425187; USP 12168936; USP 12162613; USP 12188410; USP 12187444; USP 12140075; and Rajagopalan et al., “Propulsion Controls and Health Monitoring in General Aviation,” presented at session GA-8, AIAA / CAS International Air and Space Symposium and Exposition: The Next 100 Years, Dayton, Ohio, July 14-17, 2003 (AIAA 2003-2645). Aviation,” published online March 11, 2014, doi.org / 10.2514 / 6.2003-2645; and Rajagopalan, SAE Technical Paper 2004-01-3220, “Embedded Control and Software Development Technologies for Gas Turbine Engines,” 2004 (doi.org / 10.4271 / 2004-01-3220). They will also rely on the functionality of onboard electronics that interface with the engine in a production / manufacturing environment. In one embodiment, the GSE 100 “spoofs” aircraft onboard equipment into interconnecting with the GSE 100 rather than the actual aircraft engine. The GSE 100 “spoofs” the engine simulation to the onboard equipment for the limited purpose of operating the onboard equipment during at least one further production / manufacturing phase of the aircraft. The GSE 100 does not perform most of the functions of an actual engine. For example, a GSE does not consume fuel, provide thrust, generate heat, produce bleed air, produce exhaust, generate heat, etc., like an actual engine. However, in a production environment, operating an installed engine in a hangar to perform these functions would be dangerous. Therefore, the GSE 100 does not need to simulate an actual engine to perform these functions and intentionally does not have the ability to do so. Instead, the GSE 100 has only a limited set of functions designed to simulate the corresponding limited set of functions that an aircraft engine can perform while the aircraft is still being manufactured on the assembly line.The GSE 100 needs to simulate any functions of the aircraft engine that the aircraft engine cannot perform while the aircraft is still being built on the assembly line in the hangar.

[0057] Example System

[0058] An example aircraft engine simulator includes:

[0059] case;

[0060] at least one actuator or simulated actuator disposed within the housing;

[0061] at least one sensor or simulated sensor disposed within the housing; and

[0062] a wired connection configured to connect the at least one actuator or simulated actuator and the at least one sensor or simulated sensor for communicating with a component on the aircraft,

[0063] Therein, the aircraft engine simulator is configured to present a substitute for an engine non-operational state for the functionality of a component on an aircraft having at least one missing or non-operational engine.

[0064] The processor and / or control circuitry within the housing emulates the interface aspects of the processor and / or processing circuitry within the engine, rather than the engine control aspects.

[0065] The housing has the dimensions of a suitcase and includes a plurality of compartments.

[0066] The plurality of compartments includes a first compartment that is not accessible to a user and a second compartment that is accessible to a user.

[0067] Wired connections include multi-conductor wiring harnesses.

[0068] The simulated actuators and / or sensors include electronic components selected from the group consisting of resistors, capacitors, coils, switches, relays, and thermocouples.

[0069] The at least one actuator or simulated actuator comprises an actuator within the engine.

[0070] The at least one sensor or simulated sensor comprises a sensor within the engine.

[0071] The aircraft engine simulator does not require engine installation during manufacturing, the aircraft engine simulator does not require testing for identifying parameters, the aircraft engine simulator does not require an external energy source for operation, and the aircraft engine simulator is compatible with the configuration of the engine.

[0072] The wired interconnects are identical to the engine's certified diagram, and the components enclosed in the external box are identical to the engine.

[0073] An example aircraft engine simulation method includes: simulating an actuator interface of an aircraft engine, wherein at least a first component is disposed within a non-engine portable housing; simulating a sensor interface of an aircraft engine, wherein a second component is disposed within the non-engine portable housing; and connecting the first component and the second component for communication with an aircraft having at least one missing or non-operating engine to replace the at least one missing or non-operating engine for docking with other components on the aircraft, but not for propelling the aircraft.

[0074] The processor and / or control circuitry within the housing emulates the interface aspects of the processor and / or processing circuitry within the engine, rather than the engine control aspects.

[0075] The aircraft engine simulation method does not require engine installation during manufacturing, does not perform tests for identifying parameters, does not require an external energy source for operation, and is compatible with the configuration of the engine.

[0076] The connections are identical to the certified diagram for the engine.

[0077] The system electrical engine twin for an aircraft includes equipment 100 and an interface harness 102 for each simulated engine.

[0078] Figure 3 The equipment design details shown in the block diagram contain electrical components that ensure reliable operation of the aircraft in the manufacturing environment. Here are some example electrical components:

[0079] Sensors 102 include a temperature sensor 102a, a pressure sensor 102b, a flow sensor 102c, a vibration sensor 102d, an oil particle sensor 102e, a magnetic sensor 102f, a position sensor 102g, a fire detection sensor, a current sensor, and other sensors. These components are electrically connected to provide electrical signals for measuring physical quantities having static, trouble-free engine characteristics. As described above, the components may or may not be actual sensors. For example, in some cases, the components are identical sensors found in aircraft engines. In other cases, the components are not actual sensors, but rather non-sensing circuits and / or components that are not actual sensors and provide signal outputs and / or other characteristics that simulate the signal outputs / characteristics of actual sensors. As an example, a capacitive sensor can be simulated by a fixed or variable capacitor, a resistive sensor can be simulated by a fixed or variable resistor, an inductive sensor can be simulated by a fixed or variable inductor, a resistor-capacitor sensor can be simulated by a resistor-capacitor (RC) network, a resistor-inductor sensor can be simulated by a resistor-inductor (RL) network, and so on. Also, since the engines are never started while the aircraft is in the hangar, the simulated sensors can provide fixed outputs that represent the standby-non-operating state of the actual engines (e.g., the high temperature sensor will measure room temperature, the pressure sensor will measure ambient pressure, etc.).

[0080] The actuators 104 include an air induction valve 104a, an anti-ice valve 104b, a fuel valve 104c, and an ignition device. These components are included so that the aircraft system does not interpret failures and disable functions that will be used in a production environment. As described above, the GSE 100 may or may not include actual actuators. For example, in a system such as Figure 5 In some illustrated embodiments, the GSE 100 may include an actual actuator 104, which is identical to the corresponding actuator in a real engine, but in the GSE, only the actuator itself is controlled or actuated. This arrangement provides actuator characteristics identical to those of a real actuator in a real engine. In some embodiments, the GSE 100 includes circuits or components that emulate one or more real actuators (e.g., one or more real actuators not readily available outside the engine assembly). For example, the fuel valve 104c can be emulated by a suitably configured RLC network and relays, such that the RLC network and relays have the same voltage / current ratings and operating time delay as a real fuel valve, but at a significantly lower cost. In some embodiments, a real "bottom-swept" fuel valve that is unsuitable for use as a fuel valve (e.g., it leaks) can be used as the fuel valve actuator in the GSE 100 because it will behave electrically and operationally identically to a real fuel valve in a real engine. Fuel leaks are not a concern because, in the GSE, the valve will never need to deliver or regulate real fuel.

[0081] The electrical components 106 include resistors 106a, inductors 106b, capacitors 106c, switches 106d, relays 106e, and thermocouples 106g. As described above, these components are used to provide electrical signals and characteristics like actual sensors and / or actuators installed inside the engine and not sold separately.

[0082] Computer 108 includes a fuel control unit (FCU) 108a, a vibration control unit (VCU) 108b, and a full authority digital engine control (FADEC) 108c. These components provide discrete analog signal and data bus transmission and reception, which allows for trouble-free operation of aircraft systems. For example, one embodiment of GSE 100 provides one or more processors and / or other digital circuits that emulate the interface aspects of an electronic processor and / or digital circuit integrated into an aircraft engine during various states of the aircraft engine in a production environment within a hangar. Such emulated processors and / or digital circuits do not need to emulate the full functionality of the actual processors and / or digital circuits of an actual engine, execute all control algorithms of such actual processors and / or digital circuits, or provide the actual operational signals that an aircraft engine would provide during startup and operation, as the engine would never be operated in a hangar. Instead, in one embodiment, the emulated processors and / or digital circuits only emulate the external interface and communication aspects of the actual processors and / or digital circuits of an actual engine during limited, non-dynamic states of the engine, such as:

[0083] receiving messages sent from one or more aircraft onboard control systems and confirming whether the received messages are called by the communication protocol;

[0084] responding to the received message in the manner in which an actual engine control system would respond when the engine is in a non-operational state commanded by an onboard control system of the aircraft;

[0085] An information message is generated and provided to an aircraft onboard control system, the information message being of the type that the aircraft onboard control system would expect during an engine non-operating state in the absence of dynamic changes in engine variables.

[0086] As used herein, the term "engine non-operational state" means that the engine has not been started / fired, is not burning or consuming fuel, is not producing thrust, and is not supporting combustion and producing exhaust gas (e.g., for a gas turbine engine). An "engine non-operational state" may encompass states in which: (a) power is applied to the engine to activate certain internal components, (b) the engine operates or exercises internal actuators in response to control signals applied to the engine, (c) the engine provides information, such as sensor readings, in response to messages sent to the engine's integrated electronic control system; and (d) other active engine functions that the engine may provide while the aircraft is in the assembly hangar. In other words, as used herein, "non-operational" does not mean the complete absence of operation, but rather it excludes certain types of engine operations that would not or could not occur outside of an assembly line hangar environment, such as dynamic changes in engine variables that only occur when the engine has been started / fired (e.g., in the case of a gas turbine engine) to burn fuel to produce thrust.

[0087] Figure 4A 、 Figure 4B An example assembly of components inside a GSE "box" 100 is schematically shown, and two views are presented: a top plan view ( Figure 4A ) and bottom contour plot ( Figure 4B ).

[0088] Figure 4A Plan of the Figure 5 ): Shows an example housing of sensors (or circuits / components simulating sensors) 102, actuators (or circuits / components simulating actuators) 104, electrical components 106 (such as resistors, thermocouples, switches), and the electrical intelligence between these components. It also presents an example design of an interface harness 102 that connects 102 / 104 / 106 to wiring on the aircraft fuselage.

[0089] Figure 4B Contour diagram of (and see Figure 5 ): shows a lower partition 150L of the divider where components are available without user access; an upper partition 150U containing switches and wiring receptacles that are available for user operation and manipulation; and a cover 150C.

[0090] The device is characterized by Figure 4A / Figure 4B and Figure 5 The illustrated ground support equipment (GSE) is designed to facilitate use in aircraft operations and provides the following advantageous features and characteristics:

[0091] Mobility: The device can be used by a single operator, offers ease of assembly and disassembly, and easy storage.

[0092] Robustness: Meet the health conditions of the production environment, such as dust, humidity, drops, etc.

[0093] Maintainability: Facilitates the correction of problems and replacement of parts.

[0094] according to Figure 6 The interface harness 102 is composed of wires, connectors, clamps, protective sleeves and labels, and their function is to establish communication between the device and the aircraft, such as:

[0095] •Wire: An insulated conductor that carries electrical signals and / or power.

[0096] •Connector: A device that connects wires and cables to other components such as electrical panels, sensors, and actuators.

[0097] •Clamps: Secure wires and cables to the body or other components.

[0098] • Protective Sleeves: Shield wires and cables from environmental factors such as heat, moisture, and abrasion.

[0099] • Labels: Identify wires, cables, and connectors for easier maintenance and troubleshooting.

[0100] Example Benefits

[0101] During manufacturing, no engine installation is required, meeting PIPO and reducing WIP (Work in Process).

[0102] No testing is required to identify the parameters.

[0103] Easy to use in the field as it requires no external energy source for operation.

[0104] The system is identical to the engine configuration.

[0105] Robust system with low failure rate, as the components are aerospace and have low failure rate.

[0106] The design is simple and easy to manufacture as the electrical interconnections are identical to the certified diagrams and the components enclosed in one external box are identical to the engine.

[0107] All patents and publications cited herein are incorporated by reference as if expressly set forth herein.

[0108] While the invention has been described in connection with what are presently considered to be the most practical and preferred embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but on the contrary, the invention is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims

1. An aircraft engine simulator, comprising: case; at least one actuator or simulated actuator disposed within the housing; at least one sensor or simulated sensor, the at least one sensor or simulated sensor being disposed within the housing; as well as a wired connection configured to connect the at least one actuator or simulated actuator and the at least one sensor or simulated sensor for communicating with a component on the aircraft, Therein, the aircraft engine simulator is configured to present a substitute for an engine non-operational state for the functionality of a component on an aircraft having at least one missing or non-operational engine.

2. An aircraft engine simulator according to claim 1 further comprising a processor and / or control circuit within the housing, the processor and / or control circuit simulating interface aspects of the processor and / or processing circuit within the engine rather than engine control aspects.

3. The aircraft engine simulator according to claim 1, wherein: The housing has the dimensions of a suitcase and includes a plurality of compartments.

4. The aircraft engine simulator according to claim 3, wherein: The plurality of compartments includes a first compartment that is inaccessible to a user and a second compartment that is accessible to a user.

5. The aircraft engine simulator according to claim 1, wherein: The wired connection includes a multi-conductor wiring harness.

6. The aircraft engine simulator according to claim 1, wherein: The simulated actuators and / or sensors include electronic components selected from the group consisting of resistors, capacitors, coils, switches, relays, and thermocouples.

7. The aircraft engine simulator according to claim 1, wherein: The at least one actuator or simulated actuator comprises an actuator within the engine.

8. The aircraft engine simulator according to claim 1, wherein: The at least one sensor or simulated sensor comprises a sensor within the engine.

9. The aircraft engine simulator according to claim 1, wherein: The aircraft engine simulator does not require engine installation during manufacturing, does not require testing for identifying parameters, does not require an external energy source for operation, and is compatible with the configuration of the engine.

10. The aircraft engine simulator according to claim 1, wherein: The wired interconnects are identical to the certified diagram of the engine, and the components enclosed in the external box are identical to the engine.

11. An aircraft engine simulation method, comprising: An actuator interface for simulating an aircraft engine, wherein at least a first component is disposed within a non-engine portable housing; emulating a sensor interface of the aircraft engine, wherein a second component is disposed within the non-engine portable housing; and The first component and the second component are connected for communication with an aircraft having at least one missing or inoperative engine to replace the at least one missing or inoperative engine for docking with other components on the aircraft but not for propelling the aircraft.

12. The aircraft engine simulation method of claim 11, further comprising using the processor and / or control circuitry within the housing to simulate interface aspects of the processor and / or processing circuitry within the engine rather than engine control aspects.

13. The aircraft engine simulation method according to claim 11, wherein: The aircraft engine simulation method does not require engine installation during manufacturing, does not perform tests for identifying parameters, does not require an external energy source for operation, and is compatible with the configuration of the engine.

14. The aircraft engine simulation method of claim 11, further comprising identically connecting to a certified diagram of the engine.

15. A method comprising: Determine which aircraft systems are dependent on the engine in manufacturing or ground maintenance conditions; identifying which signals are exchanged between these systems and the engine; Identify the sensors, actuators, and controllers involved; Identify the electrical interconnections of components; measuring electrical quantities (resistance, impedance and capacitance) of the sensor; Define which sensors will be used and which sensors will be replaced with non-sensor electrical components; Enclose all components in an external box to build the GSE; as well as Construct the interface wiring based on the engine electrical interconnection diagram.

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