N+2 Electric Distributed Propulsion Aircraft for Terminal Area Operations
N+2 EDP Aircraft based on the ECO-150 designed during previous SBIR contracts with NASA. ESAero will re-design the aircraft with conventional non-superconducting electrical machines. Then, will specifically analyze the performance of the split-wing configuration in the Terminal Area. A synthesis and design tool for electric distributed propulsion, both superconducting and not, will be outlined for consideration in the future (Phase II).
Distributed Hybrid Electric Propulsion (DHEP) Studies
Leveraging the unique capability from ESAero's previous government work in this area, conventional electric machine architectures are being designed and sized for commercial comparison studies.
Distributed Propulsion Aircraft Design and Analysis
Distributed Propulsion Aircraft Design and Analysis to support Boeing R&T and their concepts. Analysis includes fan design, motor sizing, fan/motor placement and arrangement, weight analysis and performance prediction.
Instrumentation , Integration Support and Contracting for the SCEPTOR CAS Demonstrator
As a follow-on to the foundational LEAPTech effort (see below), ESAero is again the prime contractor for the Convergent Electric Propulsion Technology (CEPT) sub-project in the Convergent Aeronautics Solutions Project under the Transformative Aviation Systems Program for concept flight validation of transformational electric propulsion integration capabilities through a low cost retrofit demonstrator as a pathway to Ultra-Low Emission Commercial Aviation. Joby Aviation is again a key partner and subcontractor to support ESAero and NASA.
Design and Fabrication of a Hybrid Electric Integrated System Testbed (HEIST)
This effort supports NASA/Armstrong Flight Research Center’s research goal of setting up a small scale electric distributed propulsion test capability so that applied research into these technologies and design concepts can begin in the next two to three years. The original goal of this Phase III SBIR effort was to design and assemble a static test capability. However, the project has evolved and is in the process of being combined with the NASA Langley “LEAPTech” (Leading Edge Asynchronous Propellers Technology) Team Seedling demonstrator, where a full-scale HEDP wing will be built and tested at NASA Armstrong in conjunction with Joby Aviation. ESAero is the prime contractor and is providing instrumentation engineering design and assembly support to the AFRC electric propulsion team and will provide, manufacture, integrate and ground test various components of the test stand and associated ground test equipment.
Engineering Support on Global Observer and HALE/MALE Systems
Payload Engineering and Installation Support on Global Observer, a 65,000 foot altitude liquid hydrogen powered persistent unmanned aircraft system.
Mission Analysis, Payload Performance Prediction and Analysis
Working with various Payload vendors to estimate performance of their payloads on the Global Observer, including Radars, EO/IR, Large Format EO, Large Format IR, Comms packages, Hyperspectral Cameras, Onboard Storage and Computing, SIGINT, etc.
Engineering, Conceptual and Preliminary Design Support
Design and consulting services to support an unspecified program.
ConOps, Mission Analysis and Payload Performance
Concept of Operations Development, Performance Verification and Mission Analysis for unspecified program.
Phase I - Investigative Research, FMECA and PHM Modeling of Hybrid-Electric Distributed Propulsion System Architectures – General Atomics Subcontractor
Project to utilize reliability centered maintenance (RCM) applied to prognostics and health management (PHM) to yield significant improvement in HEDP system reliability, availability, safety and cost. This work identifies the tools and creates a generic methodology for the PHM of a HEDP system based on RCM and failure mode data of likely HEDP architecture components. General Atomics Intelligent Systems is a Subcontractor.
Phase II - ePHM System Development, Hardware-in-the-Loop Testing, Fault Tree, and FMECA Applied to and Integrated on NASA Hybrid Electric Testbeds
An intelligent prognostics and health management (ePHM) system will be designed and executed for the HEDP system on the NASA Dryden Hybrid Electric Integrated System Teststand (HEIST) (AirVolt optional), which will be developed as part of a parallel Phase III SBIR. Most developments in PHM surround air vehicle subsystems and avionics, specifically on the electronic board level, and many of these are integrated after the systems are designed. These developments have or are establishing the ability to monitor the degradation of a subsystem in real-time, making it conceivable that actionable information can be fed to a Integrated Autonomous Controller for self-repair decisions, leveraging the Propulsion Airframe Integration benefits. Reliability can be calculated and maintenance can be planned ahead of time rather than at the point of failure, significantly increasing safety. General Atomics, Electromagnetic Systems Group (GA) will continue to play a vital role.
MAKO Hybrid Airship Design, Analysis, Testing and LRIP
ESAero is supporting the design of the hybrid (helium bladder and wing, not electrical hybrid as above projects) MAKO airship. This includes a design, analysis and performance tool for the vehicle. ESAero is also conducting all flight testing on behalf of SofCoast, and will begin LRIP of the system in April 2012.
Small Advanced UAS Integration and Assembly
ESAero is supporting LMAero with logistics support on a small advanced UAS with integration and assembly services.
Small Advanced UAS Design and Procurement Support
ESAero is supporting LMAero with advanced vehicle design work and procurement support to support the quick reaction flight testing of the concept.
Hybrid Power System Optimization Tool: HyPSO — Phase VI
Continued modification of previous efforts to support Fixed Wing applications and More Electric Aircraft Initiatives
Hybrid Helicopter Trade Study Project — Phase IV
Phase IV is yet another continuation of the previous Phases. The optimization elements of the tool are being significantly improved, along with the creation of a MATLAB GUI. When complete, the tool is going to be adapted for Fixed Wing aircraft, with a focus on UAVs. The code will be further validated and refined for the fixed wing application.
Hybrid Systems Overview Project — Phase I, IIA and IIB, III
ESAero, technical lead and PM, identified opportunities and technology to reduce fuel consumption in Aerospace Applications using Electric-Hybrid Systems as they have been designed for automobiles. The Phase I three month study assessed the SOTA, evaluated and defined a system model for an aircraft. In Phase II, ESAero created databases and models for potential hybrid system engines and electric motors for use in a complete hybrid propulsion system design. The objective was to identify the highest performing hybrid propulsion system configuration. Phase III was a direct continuation of Phase II with the modification and execution of the optimization code. The design tool was verified and results analyzed.
OpenVSP Smart Conceptual Design Tool Improvements, Including Inboard Profile Visualization
This effort will build off of the momentum gained from OpenVSP 3.0 advancements by providing a selection of features that complement the newly available capabilities. Primarily, the work will improve OpenVSP's ability to rapidly create well defined configurations. New visualization options will be added to support the creation of inboard profiles. Meanwhile, a library of pre-defined components will be established for quick selection of common aircraft parts, subsystems and payloads. The capability to link the parameters that define each component will be enhanced to enable nonlinear, multivariate functions, and a predefined library of common relationships will be established. Finally, a moderate fidelity parasite drag build-up tool that utilizes the new degenerate geometry feature will be created and integrated into OpenVSP for seamless trade studies. Rob McDonald and JR Gloudemans will be major participants.
SIERRA "Ship B" Engine and Propeller Survey and Performance
NASA ESD had a requirement to "grow" the configuration for longer endurance. ESAero supported the new engine and propeller selections and performance for this effort, and the resulting recommendations were procured and integrated.
SIERRA Long-Range Configuration Study
In anticipation of long-range operations, ESAero conducted a configuration study to look at the structural and aerodynamic modifications possible to increase the size of SIERRA.
DoeTECH Performance Code and Flight Test to Analyze Different Configurations
A performance code was developed exclusively for the SIERRA UAV. The DoeTECH code, matched to existing flight test data (which was supported and data reduced by ESAero using DoeTECH), is used to analyze the different configurations being considered for long-range missions. Once a configuration is chosen and the modifications to the airframe are made, it helps analyze potential long-range missions for future mission planning. The code has been very successful in the role so far, including flights over the polar ice out of Svalbard, Norway.
Specific Hybrid System Design
Using SOTA Components in a vehicle configuration down selected during the Hybridization Planning, a full Hybrid System is being designed, integrated and analyzed to better refine and assess feasibility and performance improvements.
Air Vehicle Hybridization Planning
Full Air Vehicle Hybridization Design Engineering for multiple size and types of vehicles to create and support a technical and marketing plan. Hybridization Study will consider the entire system including electric motors, batteries, controllers, etc.
Hybrid Electric Air Vehicles Design and Evaluation
Electric Motor Focused Design and Analysis Engineering Support to General Atomics for the design of multiple Hybrid Electric Air Vehicle configurations. Analysis and Evaluation of General Atomics Electric Components for Insertion into existing and future Electric Hybrid Air Vehicles.
Advanced Conceptual Design Support
ESAero used the Brainernet process to support advanced vehicle requirements and designs. The process brought energy and creativity as a dynamic process to quickly lay out and sketch 5 notional air vehicle designs, from which conceptual designs are being created.
Design and Integration of a Distributed Fan Propulsion System within a Split-Wing
Based upon the work of ESAero's previous SBIR effort (see below), ESAero will study the detailed design and integration of a Superconducting Cryogenically Cooled TurboElectric Distributed Propulsion system into the split-wing of the ECO-150 configuration (right). Both the physical considerations of structure and weight, and the aerodynamic considerations of inlet, fan and nozzle design will be considered during this study.
Application of an ACEPS to Aerodynamically Efficient Subsonic Transport Aircraft
During this SBIR study, ESAero is going to study the design of regional airliners for Entry Into Service (EIS) in 2030. The propulsion technology that will be studied and integrated into these airframes will be an Advanced Cryogenic Electric Propulsion System, or ACEPS. The ESAero team will design and integrate this system into a 150 passenger and 250 passenger regional transport aircraft. A Phase II proposal has been submitted.
Data Reduction of Flight Test Data for FAA Certification of a Re-Engine
Analysis and reduction of digitally recorded flight test data from various test flights with varying scenarios. This effort is in support of the certification program for the re-engine of an "unspecified" aircraft.
Data Reduction of Evergreen International Supertanker Flight Data
Analysis and reduction of digitally recorded flight data from various test flights with varying flight scenarios. This was done in support of the Evergreen Supertanker.
747 Fuselage Stiffness and Mass Properties
Reverse engineering of the entire 747-200F fuselage to calculate stiffness and obtain the mass properties data for each fuselage station on the aircraft. This was done in support of the Evergreen Supertanker program.
Gulfstream II/III Engine Hushkit Certification Process
Data reduction and performance simulation/matching using Fortran software. All tasks performed are in the support of the FAA certification process for an engine hushkit used on both the Gulfstream II and Gulfstream III.
747 Wing Stiffness, Mass Properties &
1-G Dead Weight Shear Properties
Reverse engineering of two wing stations to calculate stiffness and obtain mass properties data at each of these stations where strain gages are located. Reverse Engineering and solid model creation of the wing fuel tanks to identify location of CG with varying fuel.
Hawaiian Airlines 767-300 Interior Reconfiguration
Support Engineering and Testing for the interior reconfiguration of four ex-Delta 767-300s with a Heath-Techna NuLook Interior. ESAero acted as liason engineers during the construction and installation of various interior components, including the galleys and class dividers.