Empower 2208 Solid State Pulse Amplifier | 8 kW, 1 – 2 GHz

RTCA/DO-160 Section 20 provides test procedures to determine if equipment will operate when the EUT and its interconnecting cables are exposed to Radio Frequency interference. Continuous Wave (CW), Square Wave AM (SW), and Pulse Modulated (PM) RF signals are required. A Line Impedance Stabilization Network (LISN) must be inserted in series with each power lead and ungrounded power return lead, with a 10 uF capacitor connected between the power input of the LISN and the ground plane. RTCA/DO-160 Section 20 has been updated to reflect the requirements of the new FAA rule for High Intensity Radiated Fields testing, also known as HIRF Testing, which is a form of EMC testing applicable to equipment that is subject to extreme electromagnetic environments and/or mission-critical equipment whose failure would be hazardous to human safety. HIRF requirements are applied to ensure that the aircraft electrical and electronic systems can continue safe operation without interruption, failure or malfunction.   Conducted Susceptibility Similar to MIL-STD-461F test method CS114, the RF conducted susceptibility test has the RF interference coupled into the EUT interconnecting cables and power leads using an injection probe calibrated (in a 50 ohm fixture) to the required test level before performing the test. During testing, the RF current induced into the cable or lead under test is monitored with a calibrated RF current probe, and the RF power applied to the injection probe is increased until the appropriate current level (as defined by the applicable Equipment Category used) is reached.   Radiated Susceptibility Similar to MIL-STD-461F test method RS103, the EUT and its interconnecting cables and power leads are exposed to RF radiated fields in the frequency range of 100 MHz to 18 GHz. There two RF radiated susceptibility test methods specified in RTCA/DO-160 Section 20. The first method uses a standard semi-anechoic chamber as in MIL-STD-461F test

LV 148 Standards are written for electric and electronic components for vehicles with a 48V Electrical System. This standard details a series of procedures for a test involving electrical normative bases and addressing the practical challenges for vehicle components and systems. LV 148 covers electric and electronic components for vehicles within a 48V electrical system's test conditions. Topics and tests covered include tolerances, operating voltage ranges, and other standard values and specifications. With an increasing amount of completely electric vehicles manufactured every year, the LV 148 will remain relevant in the coming decades to ensure standards. There are two main test setups LV 148 applies for voltage simulations and voltage dropouts. Test setup for voltage simulation DC source Signal generator Auxiliary equipment Measuring devices Test setup for voltage dropouts DC source Electronic switch Signal generator Auxiliary equipment Measuring devices In addition, the LV 148 standards apply to ground offset, short circuit signal and power line, standby current, the ground lost, internal dielectric strength, operations with/without functional limitation, over-voltage range, and under-voltage range tests.   Tolerances & Standard Values Frequencies ±1% Temperatures ±2 °C Humidity ±5% Times/durations +5%; 0% Voltages ±0.5% Currents ±2% Room Temperature TRT = 23 °C ± 5 °C Humidity 25 % (+ 5 % bis 0 %) to 75 % (- 5 % bis 0 %) Test Temperature Ttest = TRT Operating Voltage U48max Source Impedance 10 mOhm ≤ Ri ≤ 100 mOhm   Terms A, B, C, D in Diagrams Functional status A, B, C,

EUROCAE is an international non-profit making organization in Europe. Membership is open to manufacturers and users of equipment for aeronautics, trade associations, national civil aviation administrations, and, under certain conditions, non-European organizations. Its work program is principally directed to the preparation of performance specifications and guidance documents for civil aviation equipment, for adoption and use at European and world-wide levels.  EUROCAE ED-14 defines a series of minimum standard environmental test conditions (categories) and applicable test procedures for airborne equipment. The purpose of these tests is to provide a laboratory means of determining the performance characteristics of airborne equipment in environmental conditions representative of those which may be encountered in airborne operation of the equipment.  The standard environmental test conditions and test procedures contained herein may be used in conjunction with applicable equipment performance standards as a minimum specification under environmental conditions, which can ensure a sufficient degree of confidence in performance during operations. The document includes 26 Sections and three Appendices. Examples of tests covered include vibration, power input, radio frequency susceptibility, lightning and electrostatic discharge. Coordinated with RTCA, EUROCAE/ED-14G and RTCA/DO-160G are identically worded.

IEC 61326 (EN 61326) is an international EMC standard developed to regulate the electromagnetic compatibility (EMC) of electrical devices, specifically laboratory equipment. IEC 61326 applies to equipment developed for test and measurement and used in control or laboratory applications. The standard lists requirements for EMC testing, which include radiated susceptibility, conducted susceptibility, radiated emissions and conducted emissions tests. EN 61326 is an equivalent standard that applies to the European Union. IEC 61326 is divided into several parts: IEC 61326-1 | General testing requirements IEC 61326-2-1 | Requirements specific to sensitive test equipment in EMC unprotected testing IEC 61326-2-2 | Requirements for monitoring equipment utilized in low-voltage distribution systems IEC 61326-2-3 | Requirements for transducers with remote or integrated signal conditioning IEC 61326-2-4 | Requirements for insulation monitoring devices per IEC 61557-8 and insulation fault location per IEC 61557-9 IEC 61326-2-5 | Requirements for field devices with IEC 61784-1, CP 3/2 compliant field devices IEC 61326-3-1 | Immunity requirements for functional safety; limited to equipment designed for safety functions in industrial applications as specified by IEC 61508 with SIL 1-3 Buy Standard

Boeing D6-16050-4 contains the electromagnetic compatibility (EMC) requirements of electrical/electronic equipment selected for installation on Boeing commercial transport airplanes. Transient, audio frequency, and radio frequency limits of emissions and susceptibility are specified for the equipment. Typical test set-ups, test procedures, approved measuring equipment and test provisions are included along with designer’s notes to assist in proper interpretation of design and test requirements. In addition, EMC Test Procedure and Test Report data requirements are specified in Boeing D6-16050-4. Many test procedures have been updated and clarified, with additional attention given to requirements for supporting documentation. Electromagnetic compatibility requires that each system in an airplane performs its intended function in the airplane electromagnetic environment, and that the operation of such system does not interfere or degrade the performance of other airplane systems. Airplane electromagnetic compatibility requires appropriate airplane structural design, equipment installation, wiring installation, and equipment qualification. The limits of emissions and susceptibility thresholds contained in this document are a means of assuring that the design objectives will be achieved when compliant equipment is installed on an airplane. Each supplier has full responsibility for the EMC design, construction and testing of furnished equipment. This effort shall be in accordance with the applicable procurement specification and Boeing D6-16050-4. This shall include the responsibility to design into all circuitry and associated packaging proven and effective techniques for control of emissions and susceptibilities. Although the test procedures and methods detailed herein are standardized, each supplier has the responsibility of demonstrating that the performance of each unit is tested and exercised with the hardware, interfaces, software, and modes

Boeing D6-16050-5 contains the electromagnetic compatibility (EMC) requirements of electrical and electronic equipment selected for installation on Boeing commercial transport airplanes that are primarily constructed of composite material. Transient, audio frequency, and radio frequency limits of emissions and susceptibility are specified for the equipment. Test procedures, typical test set-ups, approved measuring equipment and test provisions are included along with designer’s notes to assist in the proper interpretation of design and test requirements. EMC Test Procedure and Test Report data requirements are also specified. Electromagnetic compatibility requires that each airplane system perform its intended function in the airplane electromagnetic environment and that the operation of a given system does not degrade the performance of other airplane systems. Airplane electromagnetic compatibility requires appropriate airplane structural design, equipment installation, wiring installation, and equipment qualification. The emission limits and susceptibility thresholds contained in Boeing D6-16050-5 are a means of assuring that the design objectives will be achieved when compliant equipment is installed on an airplane. Each supplier has full responsibility for the EMC design, construction, and testing of furnished equipment. This effort shall be in accordance with the applicable system requirements documentation and this document. This shall include the responsibility to design into all circuitry and associated packaging proven and effective techniques for control of emissions and susceptibilities. Although the test procedures and methods detailed in Boeing D6-16050-5 are standardized, each supplier has the responsibility of demonstrating that the performance of each unit is tested and exercised with the hardware, interfaces, software, and modes of operation representative of the actual in-service installation. Test equipment and load simulation