AE Techron 7228 Linear Power Amplifier | 1000 W, 100kHz - 1MHz

RTCA/DO-160 Section 18 provides test procedures to determine if the EUT will operate as specified when audio frequency interference is applied to the AC and/or DC power input. RTCA/DO-160 Section 18 is similar MIL-STD 461F test method CS101 with the only difference being test level and frequency range. The EUT must be tested while operating at both minimum and maximum current draw (if applicable), and at the AC power frequency extremes if designated for use with Variable Frequency systems when testing to RTCA/DO-160 Section 18 requirements. Equipment Categories There are three DC power Equipment Categories (R, B, and Z) that indicate the type of power used by the equipment and the type of DC power source with which the equipment is compatible. AC Power Equipment Categories are specified as R and K. Category R is used with an additional designation (a two-character code), placed in parenthesis following the Category designator, indicates that the equipment has been tested for use with Constant Frequency (CF), Narrow Variable Frequency (NF), or Wide Variable Frequency (WF). Category K designates that the EUT has been tested for use with any type of AC power input, and tested to a higher level of voltage distortion than category R. RTCA/DO-160 provides standard procedures and environmental test criteria for testing airborne equipment for the entire spectrum of aircraft from light, general aviation aircraft and helicopters through the "jumbo jets" and SST categories of aircraft. The tests outlined in this standard are performed to meet FAA and international regulations for electrical and electronic equipment installed on commercial aircraft. RTCA/DO-160 G is the current version of this standard. Coordinated with EUROCAE, RTCA/DO-160G and EUROCAE/ED-14G are identically worded. DO-160G is recognized by the International Organization for Standardization (ISO) as de facto international standard ISO-7137.  

RTCA/DO-160 Section 19 provides test procedures to determine whether the EUT can operate as required when the equipment and interconnecting cables are subjected to audio frequency electric fields, magnetic fields, and transient voltage spikes. In RTCA/DO-160 Section 19, the test levels for interconnecting cable tests are determined by the length of wire exposed to the radiating wire. RTCA/DO-160 Section 19 states that magnetic and electric fields induced into cables, the test level is defined as the product of the length of interconnecting cable exposed to the radiating wire and the rms voltage or current applied to the wire. Equipment RTCA/DO-160 provides standard procedures and environmental test criteria for testing airborne equipment for the entire spectrum of aircraft from light, general aviation aircraft and helicopters through the "jumbo jets" and SST categories of aircraft. The tests outlined in this standard are performed to meet FAA and international regulations for electrical and electronic equipment installed on commercial aircraft. RTCA/DO-160 G is the current version of this standard. Coordinated with EUROCAE, RTCA/DO-160G and EUROCAE/ED-14G are identically worded. DO-160G is recognized by the International Organization for Standardization (ISO) as de facto international standard ISO-7137. The Equipment Categories are comprised of two characters. The first character (A, B, C, or Z) indicates the tests performed and severity level of the tests. The second character (C, N, or W) indicates the AC power system operating frequency (Constant, Narrow Variable, or Wide Variable) which the EUT is compatible with. User Guide Buy Standard View DO-160 Sec. 19 Setup (spikes) calibration setup (spikes) test setup  

MIL-STD-461G CS101 applies from 30 Hz to 150 kHz for equipment and subsystem AC, limited to current draws ≤ 30 amperes per phase, and DC input power leads, not including returns. MIL-STD-461G CS101 is also applicable to systems that draw more than 30 amps if the system has an operating frequency of 150 kHz or less and an operating sensitivity of 1 μV or better (such as 0.5 μV). If the EUT is DC operated, MIL-STD-461G CS101 requirement applies over the frequency range of 30 Hz to 150 kHz. If the EUT is AC operated, this requirement applies to start from the second harmonic of the EUT power frequency and extending to 150 kHz.  This test procedure is used to verify the ability of the EUT to withstand signals coupled onto input power leads. There are two methods provided for making measurements of the applied signal. The first uses an oscilloscope with a power input isolation transformer. The second uses a measurement receiver together with a transducer. The transducer electrically isolates the receiver from the EUT power and reduces the levels to protect the receiver.   Test Equipment The test equipment shall be as follows: Signal generator Power amplifier Oscilloscope or measurement receiver Coupling transformer Capacitor, 10 μF Isolation transformer for oscilloscope use or transducer for measurement receiver use Resistor, 0.5 ohm LISNs   Procedures The test procedures shall be as follows: a. Turn on the measurement equipment and allow sufficient time for stabilization. b. Calibration. (1) Set the signal generator to the lowest test frequency. (2) Increase the applied signal until the oscilloscope or measurement receiver indicates the voltage level corresponding to the maximum required power level specified for the limit on Figure CS101-2. Verify the output waveform is sinusoidal for oscilloscope measurements. (3) Record the setting of the signal source. (4) Scan the required frequency

MIL-STD-461G CS109 applies from 60 Hz to 100 kHz for equipment and subsystems that have an operating frequency of 100 kHz or less and an operating sensitivity of 1 μV or better (such as 0.5 μV). Handheld equipment is exempt from MIL-STD-461G CS109.  According to MIL-STD-461G CS109, the EUT shall not exhibit any malfunction, degradation of performance, or deviation from specified indications, beyond the tolerances indicated in the individual equipment or subsystem specification.   Test Equipment The test equipment shall be as follows: Signal generator Amplifier (if required) Isolation transformers Current probe Measurement receiver Resistor, 0.5 ohm Coupling transformer   Procedures The test procedures shall be as follows: a. Turn on the EUT and measurement equipment and allow sufficient time for stabilization. b. Set the signal generator to the lowest required frequency. Adjust the signal generator to the required level as a minimum. Monitor the current with the current probe and measurement receiver. c. Scan the signal generator over the required frequency range in accordance with Table III while maintaining the current level at least to the level specified in the applicable limit. Monitor the EUT for susceptibility. d. If susceptibility is noted, determine the threshold level in accordance with 4.3.10.4.3. e. Repeat 5.11.3.4b through 5.11.3.4d for each diagonal set of test points on each surface of the EUT to be tested.   Test Setup The test setup shall be as follows: a. It is not necessary to maintain the basic test setup for the EUT as shown and described in Figures 2 through 5 and in 4.3.8. b. Calibration. No special calibration is required. c. EUT testing. (1) As shown in Figure CS109-2, configure the EUT and the test equipment (including the test signal source, the test current measurement equipment, and the equipment required for operating the EUT or measuring

MIL-STD-704 defines the requirements outlined by the Department of Defense for the characteristics of aircraft electric power generated at the input terminals of electric utilization equipment. MIL-STD-704 is intended to detail electric power quality requirements for DoD aircraft, but may also be used with commercial planes or other vehicle types. Standards like ISO 1540 and SAE-AS1212 also dictate aircraft electric power requirements, but are not generally relevant for military aircraft, as they do not address the areas of concern for military aircraft electric power quality and need wider limits compared to MIL-STD-704. MIL-STD-704 also takes into account legacy DoD equipment and aircraft electrical systems.   General Requirements 4.1 Aircraft Electric Power System Requirements   Aircraft electrical power systems should offer electric power with the characteristics specified in this standard at the utilization equipment terminals during all powerations of the power system. Airframe manufacturers or modifiers are responsible for offering the distribution and protection network to the terminals of the utilization equipment while maintaining power characteristics specified in MIL-STD-704; characteristics of the power measured at the output terminal of an unregulated power source or the POR of a regulated power source should be within the limits specified in the detail specification applicable to the power source. Protective devices should operate independently of control/regulation equipment. 4.2 Aircraft Utilization Equipment Requirements   Utilization equipment should be compatible with the power characteristics specified in MIL-STD-704. Aircraft should operate at the performance level specified in its detail specification in all of the following modes of operation: Normal Abnormal Transfer Emergency Starting Loss of power or the loss of one or more phases of AC should not result in

The purpose of ISO 7637-2 is to ensure electromagnetic compatibility of passenger and commercial vehicles operating on 12V or 24V electrical systems. ISO 7637-2 requires multiple conducted transients to be coupled onto DC lines to test the compatibility of vehicles. This standard is applicable to both internal combustion engine and electric motor vehicles.   Equipment Required: Transient Generator - HILO CAR TEST 14 Oscilloscope - Tektronix MDO4104C Differential Probe - Probe Master 4234 ISO 7637-2 Test Pulses The following tables show data that highlights Pulse 1, Pulse 2a, Pulse 2b, Pulse 3a, and Pulse 3b. Pulse 1 ISO 7637-2 Pulse 1 is used to simulate the transients created in the case that a motor, or inductive load, is disconnected from the circuit.    Parameters of this pulse can be verified using an oscilloscope and differential probe to meet the specifications below. Pulse 2a ISO 7637-2 Pulse 2a is used to simulate transients that occur when there is a current interruption on a device in parallel with the DUT and caused by the wiring harness inductance. Pulse 2b ISO 7637-2 Pulse 2b is used to simulate transients when a vehicle is turned off, but electric DC motors remain active and serve as a generator. Pulse 3a The pulse 3a is similar to an EFT pulse as seen in IEC 61000-4-4 (HYPERLINK THIS), this transient waveform is simulating switching occuring in a system connected by a wiring harness, in which the load is capacitive or inductive. Pulse 3b Similar to pulse 3a, except opposite polarity. Pulse 3b is another EFT waveform representing switching within a wire harness. These pulses also simulate the scenario in which a fuse is blown.   Pulse 4, 5a, & 5b ISO 7637 Pulse 4, Pulse 5a/5b were removed from the most recent revision of ISO 7637-2 and can be found now in ISO 16750-2.   ISO 7637-2 Test Equipment ATEC recommends the following products for testing