System for Flight Control of Extremely Fast (Hypersonic) Aircraft

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.

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.

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.

The typical remedy for space radiation hazards has been to harden the space vehicle's electronics and software from these high-speed particles and placing heavy shielding in these manned or sensitive areas. This adds considerable weight and cost to the launch vehicle, reduces payload capacity, and is passive in nature. SEPs and CMEs can be deflected by a magnetic field to pass around the spacecraft and not be absorbed by it. This deflection of solar wind and radiation is due to the Lorentz force. However, a magnetic field that is attached to the spacecraft and enclosing it would cause other shielding issues with equipment and would require much more electrical power to operate due to the need to enclose the entire spacecraft within that attached magnetic field. This would also perturb the data collection and transmissions of the spacecraft. Additionally, the generated magnetic field can capture some of the solar radiation as a plasma within the magnetic torus further impeding scientific data collection due to its close position to the spacecraft. DERDS is deployed in space away from the protected spacecraft to remain between the radiation source and the spacecraft. It utilizes on board cosmic ray sensors to note the need for the strength of the magnetic field, and on-board sensors to position itself directly in line between the radiation source and the protected spacecraft or station. Onboard computers and thrusters maintain the required position, so that the magnetic field is positioned for the best deflection angle based on incoming radiation. The DERDS magnetic field can be varied in both direction, intensity, and time by use of both AC and DC electrical power inputs and varied as needed to optimize the deflection angle and power requirements. The magnetic field can also be perturbed in irregular or set patterns by onboard computers and sensors as needed to maintain the proper deflection of SEPs, CMEs, and other cosmic rays. DERDS creates a magnetic field that will not need to be so large (with a much larger power requirement) as to encompass the entire protected spacecraft, and the magnetic field will not interfere with the spacecraft.

This technology is a flexible, lighter weight radiation shield made from hybrid carbon/metal fabric and based on the Z-grading method of layering metal materials of differing atomic numbers to provide radiation protection for protons, electrons, and x-rays. To create this material, a high density metal is plasma spray-coated to carbon fiber. Another metal with less density is then plasma spray-coated, followed by another, and so on, until the material with the appropriate shielding properties is formed. Resins can be added to the material to provide structural adhesion, reducing the need for mechanical bonding. This material is amenable to molding and could be used to build custom radiation shielding to protect cabling and electronics in situations where traditional metal shielding is difficult to place.