Improved Hypersonic Aircraft Flight Control System

Aerospace

Improved Hypersonic Aircraft Flight Control System (LAR-TOPS-364)

Recessed, angled lift-augmenting magnetohydrodynamic patch electrode

Overview

Researchers at NASA’s Langley Research Center have designed an improved electrode-based system for guidance, navigation and control of aircraft or spacecraft moving at hypersonic speeds in ionizing atmospheres. The system is composed of two electrodes that are recessed into angled channels on the surface of a craft’s thermal protection system (TPS) and an electromagnet positioned beneath the craft’s TPS. The system operates based on the principles of magnetohydrodynamics (MHD) and uses energy harvested from the ionized flow occurring during flight at hypersonic speeds to power the electromagnet and generate large Lorentz forces capable of augmenting lift and drag forces to steer and control the craft. The energy harvested can alternatively be stored for later use. This improved design increases electrode separation from the shock layer and decreases thermal loads experienced by the electrodes to mitigate thermal degradation.

The Technology

NASA’s MHD patch technology is composed of two electrodes positioned a prescribed distance apart recessed into angled channels on the surface of the TPS of an aircraft or spacecraft and an electromagnetic coil placed directly below the electrodes with the magnetic field protruding out of the surface. Note that the recessed/angled MHD patch described here is a special version of the original MHD patch described in LAR-TOPS-363. During hypersonic flight, the conductive ionizing atmospheric flow over the surface permits current to flow between the two electrodes. This current is harnessed to power the electromagnet which in turn generates strong Lorentz forces that augment lift and drag forces for guidance, navigation, and control of the craft. Alternatively, the current can be used to charge a battery. Changing the size of the MHD patch (e.g., the length or distance between the electrodes), the strength of the electromagnet, or the direction of the magnetic field enables tuning of generated forces for a given craft design. Multiple MHD patches can be leveraged on a single craft. In-silico evaluation of the non-recessed, non-angled MHD patch technology on select aeroshell designs for mock entry into planetary atmospheres has been performed. A single 1m2 MHD patch exerts forces up to 200 kN under simulated Neptune atmosphere entry that can be used to control a craft.

NASA Image Library: https://www.nasa.gov/offices/oct/images/office-of-the-chief-technologist-history-nasa-is-with-you-when-you-fly/nasa-is-with-you-when-you-fly-supersonic-passenger-air-travel

Elements of MHD patch with recessed angled electrodes integrated with a blunt body aeroshell of a spacecraft

Benefits

Improves performance: Increases electrode separation from the shock layer thereby decreasing thermal loads on the electrodes.
Generates large lift and drag forces: Predecessor technology generates forces up to 200 kN under Neptune atmosphere reentry conditions which are projected to be similar to Earth.
Harvests power: Current generated from skimming of ionizing atmospheres can be stored for later use
Is radar-silent: Non-protruding and projected to have minimal radar signature.
Enables larger payloads to be delivered faster: Facilitates entry of larger, heavier craft into planetary atmospheres (including earth) at higher speeds.

Applications

Aerospace and defense: Guidance, navigation, and control of hypersonic aircraft and spacecraft; power harvesting; aerocapture

Download Fact Sheet as a PDF

Ask a Question

Apply to License

Technology Details

Category Aerospace

Reference Number LAR-TOPS-364

Case Number(s) LAR-20037-1

Patent(s) (pop-up blockers must be disabled)

Papers New Magnetohydrodynamic (MHD) Lift Concept for More Efficient Missions to Mars and Neptune. Conference Paper. December 29, 2021. https://arc.aiaa.org/doi/abs/10.2514/6.2022-0934 New Magnetohydrodynamic (MHD) Lift Concept for More Efficient Missions to Mars and Neptune. Presentation. January, 2022. https://ntrs.nasa.gov/citations/20210025128 Effect of Plasma Sheaths on Earth Re-entry MHD Processes. December 29, 2021. https://arc.aiaa.org/doi/10.2514/6.2022-0980

Tags:

entry descent landing ESL magnetohydrodynamic MHD avionics electronics hypersonic steer control navigate energy harvest aerocapture lift drag

Similar Results

Source NASA Image Library: https://www.nasa.gov/image-feature/jpl/entering-the-martian-atmosphere-with-the-perseverance-rover

System for Flight Control of Extremely Fast (Hypersonic) Aircraft

NASA’s MHD patch technology consists of two electrodes positioned a prescribed distance apart on the surface of the TPS of an aircraft or spacecraft and an electromagnetic coil placed directly below the electrodes with the magnetic field protruding out of the surface. During hypersonic flight, the conductive ionizing atmospheric flow over the surface enables current to flow between the two electrodes. This current is harnessed to power the electromagnet which in turn generates strong Lorentz forces that augment lift and drag forces for guidance, navigation, and control of the craft. Alternatively, the current can be used to charge a battery. Changing the size of the MHD patch (e.g., the length or distance between the electrodes), the strength of the electromagnet, or the direction of the magnetic field enables tuning of generated forces for a given craft design. Multiple MHD patches can be leveraged on a single craft. In-silico evaluation of the MHD patch technology on select aeroshell designs for mock entry into planetary atmospheres has been performed. A 1m2 MHD patch exerts forces up to 200 kN under simulated Neptune atmosphere entry, significantly increasing the lift/drag (L/D) ratio for the aeroshell investigated. This value is the same order of magnitude as the “whole body” drag and lift forces computed for the aeroshell suggesting the generated forces can be used to control a craft.

Annular Ion Engine

The advantages displayed by Glenn's AIE stem from a number of novel design concepts, centered on an annular discharge chamber with a set of annular ion optics. The annular discharge chamber increases the effective anode surface area for electron collection as compared to a conventional cylindrically shaped ion thruster of equivalent beam area. With this increased surface area, the AIE can operate at higher discharge currents and therefore high beam currents, thereby yielding a significantly increased (3x) thrust density. An annular-geometry flat electrode can be added to enable higher-perveance designs with even higher thrust densities, with improved F/P and efficiencies compared to more conventional, spherically domed electrodes. In addition, Glenn's design allows the neutralizer cathode assembly (NCA) to be placed in a central position within the annulus, which not only eliminates the cantilevered-outboard NCA used in most conventional ion thrusters but also enables a shared gimbal platform. These benefits make manufacturing the AIE simpler as well as allowing more compact engine designs. All of these advantages add up to an electric propulsion machine that yields superior performance over the entire Isp range, making the AIE attractive for next-generation SEP vehicles. Glenn's technological advance enables spacecraft to travel farther, faster, and more cheaply than with any other propulsion technology - with clear benefits for NASA and commercial space applications.

Magnetic Shield Using Proximity Coupled Spatially Varying Superconducting Order Parameters

The invention uses the superconducting "proximity effect" and/or the "inverse proximity effect" to form a spatially varying order parameter. When designed to expel magnetic flux from a region of space, the proximity effect(s) are used in concert to make the superconducting order parameter strongly superconducting in the center and more weakly superconducting toward the perimeter. The shield is then passively cooled through the superconducting transition temperature. The superconductivity first nucleates in the center of the shielding body and expels the field from that small central region by the Meissner effect. As the sample is further cooled the region of superconducting order grows, and as it grows it sweeps the magnetic flux lines outward.

Low Frequency Portable Acoustic Measurement System

Langley has developed various technologies to enable the portable detection system, including: - 3-inch electret condenser microphone - unprecedented sensitivity of -45 dB/Hz - compact nonporous windscreen - suitable for replacing spatially demanding soaker hoses in current use - infrasonic calibrator for field use - piston phone with a test signal of 110 dB at 14Hz. - laboratory calibration apparatus - to very low frequencies - vacuum isolation vessel - sufficiently anechoic to permit measurement of background noise in microphones at frequencies down to a few Hz - mobile source for reference - a Helmholtz resonator that provides pure tone at 19 Hz The NASA system uses a three-element array in the field to locate sources of infrasound and their direction. This information has been correlated with PIREPs available in real time via the Internet, with 10 examples of good correlation.

Adaptive Thermal Management System

Efficient thermal management has long been an issue in both commercial systems and in the extreme environments of space. In space exploration and habitation, significant challenges are experienced in providing fluid support systems such as cryogenic storage, life support, and habitats; or thermal control systems for launch vehicle protection, environmental heat management, or electronic instruments. Furthermore, these systems operate in dynamic, transient modes and often under extremes of temperature or pressure. The current technical requirements associated with the thermal management of these systems result in control issues as well as significant life-cycle costs. To combat these issues, the Adaptive Thermal Management System (ATMS) was developed to help provide the capability for tanks, structural walls, or composite substrate materials to switch functionality (conductive or insulative) depending on environmental conditions or applied stimuli. As a result, the ATMS provides the ability to adapt between both heating and cooling modes within a single system. For example, shape memory alloy (SMA) elements are used to actuate at certain design temperatures to create a conductive bridge between two metal plates allowing broad-area heat rejection from the hotter surface. Upon cooling to the lower design set-point, the SMA elements return to their original shapes, thereby breaking the conductive path and returning the system to its overall insulative state. This technology has the potential to be applied to any system that would have the need for a self-regulating thermal management system that allows for heat transfer from one side to another.