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USNTPS FTM-NO U.S. Naval Test Pilot School Flight Test Manual (Preliminary) Systems Testing [Loose Leaf Publication] [Naval Air Warfare Center, NAWC.
Table of contents

• Agency Micro-sites
• Us Navy Flight Test Manual
• Full text of "DTIC ADA Fixed Wing Stability and Control, Theory and Flight Test Techniques,"

We are not interested in energy harvesting, since there are little to no opportunities for scavenging energy in a storage environment as described in Bradford [1]; 2 the power source output voltage shall be a fixed voltage between 1. For reference, current technology, ultra-low power microcontrollers require 50 microamps to microamps per MHz clock frequency over the voltage range of 0. Contractor shall provide a final phase I report.

For a nuclear power source system, contractor shall include a preliminary plan for obtaining a NRC license and a life-cycle management plan. Contractor shall develop test method s to verify power source meets the requirements described in the description section. Contractor shall provide the government with a report describing the test method s and test results. Contractor shall have an independence source, with government concurrence, test and evaluate prototype power source. Contractor shall provide a copy of the test and evaluation report to the Government.

Contractor shall deliver 2 prototype power sources to the government point of contact for test and evaluation. Contractor shall provide midterm and final reports. For a nuclear power source, contractor shall include in the final report a plan for obtaining a NRC license and a life-cycle management plan.

Current batteries do not have more that 5 to 10 years of shelf life over the industrial temperature range. Low power consumer electronics, industrial control, oil and gas monitoring systems, and harsh environment monitoring systems would all benefit from long life battery technology.

Medical electronics pacemakers, and insulin pumps would also benefit from improved battery technology. Current electronic health monitoring systems spend most of their time in an ultra-low power sleep mode. We are interested in an electronic health monitoring system that can run continuously on less than microamps current. A typical health monitoring system consists of a sensor, analog signal processing, an analog-to-digital converter, microcontroller and digital signal processing.

We are interested in an electronic health monitoring system with less than microwatts continuous power consumption. A low power sensor by itself does not meet the low power system requirement for this topic.

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Due to the low current requirement, this topic is for a wired health monitoring system. Offeror may propose a wireless system; however, the offeror still must meet the microamp average current requirement. For example, a typical pressure sensor may output a voltage, current or frequency proportional to the applied pressure. Analog signal processing may be required to appropriately scale the sensor's output signal for an analog-to-digital converter. Digital signal processing may be required to linearize the pressure transfer function.

For example, a typical industrial pressure sensor outputs a current. A gain stage is required to convert the sensor output current to a 0 to 3 volt range for a 12 bit analog-to-digital converter. A digital signal processing step is required to convert the 12 bit digital code number 0 through 0x through 0x0fff to a 0. The entire sensor system is required to be ultra-low power.

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Missiles may be placed in long term storage for 10 to 20 years or longer. Health monitoring systems require, extremely low power sensors and extremely low power analog and digital signal processing to achieve more than 10 years of operation.

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Batteries to power health monitoring systems are a separate concern. This SBIR topic is not seeking any battery research or development. This SBIR topic is not seeking any chemical sensor development. PHASE I: Contractor shall research the feasibility of developing an ultra-low power electronic health monitoring system with less than microwatts continuous power consumption. We are interested in sensors for humidity, temperature, rate of temperature change, pressure, and battery charge level e. Contractor shall select 4 of 5 sensors for the health monitoring system.

Phase I proposals are required to address the three criteria above. The contractor shall provide midterm and final reports. The final report shall describe health monitor system 1 operation, 2 estimated system performance, 3 estimated power consumption for each individual element, and the total system power, 4 estimated operating temperature range, 5 estimated operational vibration limits, 6 estimated operational lifetime, and 7 estimated non-powered lifetime shelf lifetime. The electronic health monitoring system without battery shall have a volume smaller than 1 x 1 x 0.

Contractor shall have an independent source, with government concurrence, test and evaluate the performance of the electronic health monitoring system. Contractor shall provide a copy of the test and evaluation report to the government. Contractor shall provide 2 electronic health monitoring systems to the government point of contact for test and evaluation. Contractor shall provide a preliminary datasheet for electronic health monitoring system. Contractor shall provide a final report describing the electronic health monitoring system. Contractor shall provide the government a 2 day on site training for the electronic health monitoring system.

Full text of "DTIC ADA Fixed Wing Stability and Control, Theory and Flight Test Techniques,"

Automotive applications require rugged, low power electronic health monitoring systems for diagnostics and prognostics. Military systems missiles, aircraft, ships, and vehicles are interested in ultra-low power electronic health monitoring systems for system monitoring, diagnostics and prognostics. For the medical industry, battery powered systems like heart pacemakers, blood glucose monitors, etc. These same advantages have been applied to internal gas turbine combustor walls[3] and should equally apply to airbreathing missiles ducted rockets, ramjets, and particularly scramjet powered air vehicles.

Transpiration refers to the transport of fluid through a porous wall at near zero momentum; i. This transpiration cooling process provides for a layer of fluid to insulate and convect heat away from the porous wall and, additionally, reduce the viscous drag of the cross flow. The application of transpiration cooling to missile systems has been inhibited, at least in part, to the added complexity plus the high cost and time required to fabricate porous transpiration walls from heat resistant metals.

Even for scramjet engine applications where the internal viscous drag may well exceed the external form or pressure drag, the advantages of the technology have largely been deferred while addressing the fundamental problems of engine design and operation. Ceramic matrix composites CMC [4], however, may well provide an alternative to the tedious and expensive production process for metal transpiration surfaces.

Ceramic matrix composites offer unique properties for high temperature applications. Most commonly proposed as a structural material for rocket nozzles, motor cases, and airframes, they should provide adequate strength over the required range of operating temperatures with the potential for weight savings and increased propellant loading since insulation materials may be reduced or eliminated. Indeed, those strength and temperature characteristics are now being exploited for uncooled turbine shrouds and high pressure turbine static seals for advanced turbojet engine designs[5,6].

More uniquely, in an unfilled form, these porous ceramic matrix composites could prove ideal as transpiration materials for combustor walls or external air vehicle surfaces. In subsequent steps they are filled and processed so as to reduce the porosity. The reduction in porosity improves both structural and high temperature properties which are beneficial for the applications mentioned above.

CMCs with porosity may have applications for transpiration cooling but their properties need further investigation to determine the optimum combination of porosity, strength, and temperature capabilities. Hence, the technology for ceramic matrix composite production is now well established but innovation will be required for transpiration boundaries in terms of fabrication and properties to include thermo-structural properties, containment fixtures, porosity, and fluid flow characteristics.

What is needed then is a clear demonstration of porous CMCs for missile transpiration cooling applications, specifically for scramjet engine internal combustor walls and for hypersonic air-vehicle external walls.

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Success in those applications should assure equal success in many commercial applications as well. Metrics for success would be an area weight of half that for a fabricated steel transpiration surface at one-fifth the cost. Additionally, the unfilled CMC material should show a degradation of no more than fifty percent for any time period at elevated temperatures. PHASE I: Innovative technical approaches will be formulated leading to the development of ceramic matrix composite materials for transpiration cooling as a marketable product.

Preliminary analysis of test article concepts will be performed for structural and thermal requirements. The second test will be of a CMC transpiration cooled external wall section in an exiting conical body at hypersonic velocities[2]. Additionally, prototype ceramic matrix composite coupons for these tests will be delivered to the Government for high temperature strength testing and fluid flow characterization. These two tests will require both planar and conical CMC transpiration surfaces. The combustion duct will employ two planar transpiration walls of approximately 0.

The Additional geometric details are given in references 1,2, and 8. The two ground based tests will be run to validate the use of ceramic matrix composite materials for transpiration cooled combustor and air vehicle walls. Testing will require detailed analysis for thermal and structural requirements, fabrication of the required composite transpiration wall materials, installation in the existing combustor and conical tunnel model, and completion of the ground testing.

Deliverables will consist of the resultant test data to demonstrate structural integrity and aerothermal characteristics of the transpiration cooled installations.

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Metrics for success in these ground based tests will be 1 structural integrity for a test time of 50 ms with and without transpiration, 2 a reduction of viscous surface drag by a factor of ten with active transpiration, and 3 a reduction in surface heat flux by a factor of ten with active transpiration. PHASE III: The end result of this research effort will be a validated approach for the production of composite materials for transpiration cooling as a marketable product. For military applications, this technology is directly applicable to all rocket propulsion missile systems as an advanced material for nozzles, motor cases, and airframes with the additional application to combustors for airbreathing missiles.

Gas turbine applications, both military and commercial, to include both turbo shaft and turbojet variants have already employed CMC materials for combustor walls and variants of transpiration cooling for combustor walls and turbine blades[9,3]. This advancement for transpiration with porous CMC materials will have direct application to this large commercial arena. For strictly commercial applications, this technology is directly applicable to all commercial launch systems such as the NASA Aries, and the Delta and Atlas families.

Additionally many industries utilizing high temperature combustors petroleum, cement, power generation, and food processing to name but a few could employ this technology. OBJECTIVE: Develop, investigate, and validate a novel optical primary optic for a wide field of view semi-active laser spot-tracking missile seeker based on a biologically-inspired compound eye for use in the near-infrared spectrum.

Provide effective rejection of solar interference, and allow tracking of a target by a missile in flight without the need for a gimbaled sensor. The Army now places a strong emphasis on low-cost missile seekers for use on relatively small missile platforms.