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Autonomous GPS Positioning at High Earth Orbits To initially acquire the GPS signals, a receiver also would have to search quickly through the much larger range of possible Doppler shifts and code delays than those experienced by a terrestrial receiver. By William Bamford, Luke Winternitz and Curtis Hay INNOVATION INSIGHTS by Richard Langley GPS RECEIVERS have been used in space to position and navigate satellites and rockets for more than 20 years. They have also been used to supply accurate time to satellite payloads, to determine the attitude of satellites, and to profile the Earth’s atmosphere. And GPS can be used to position groups of satellites flying in formation to provide high-resolution ground images as well as small-scale spatial variations in atmospheric properties and gravity. Receivers in low Earth orbit have virtually the same view of the GPS satellite constellation as receivers on the ground. But satellites orbiting at geostationary altitudes and higher have a severely limited view of the main beams of the GPS satellites. The main beams are either directed away from these high-altitude satellites or they are blocked to a large extent by the Earth. Typically, not even four satellites can be seen by a conventional receiver. However, by using the much weaker signals emitted by the GPS satellite antenna side lobes, a receiver may be able track a sufficient number of satellites to position and navigate itself. To initially acquire the GPS signals, a receiver also would have to search quickly through the much larger range of possible Doppler shifts and code delays than those experienced by a terrestrial receiver. In this month’s column, William Bamford, Luke Winternitz, and Curtis Hay discuss the architecture of a receiver with these needed capabilities — a receiver specially designed to function in high Earth orbit. They also describe a series of tests performed with a GPS signal simulator to validate the performance of the receiver here on the ground — well before it debuts in orbit. “Innovation” is a regular column featuring discussions about recent advances in GPS technology and its applications as well as the fundamentals of GPS positioning. The column is coordinated by Richard Langley of the Department of Geodesy and Geomatics Engineering at the University of New Brunswick, who appreciates receiving your comments and topic suggestions. To contact him, see the “Columnists” section in this issue. Calculating a spacecraft’s precise location at high orbits — 22,000 miles (35,400 kilometers) and beyond — is an important and challenging problem. New and exciting opportunities become possible if satellites are able to autonomously determine their own orbits. First, the repetitive task of periodically collecting range measurements from terrestrial antennas to high-altitude spacecraft becomes less important — this lessens competition for control facilities and saves money by reducing operational costs. Also, autonomous navigation at high orbital altitudes introduces the possibility of autonomous station-keeping. For example, if a geostationary satellite begins to drift outside of its designated slot, it can make orbit adjustments without requiring commands from the ground. Finally, precise onboard orbit determination opens the door to satellites flying in formation — an emerging concept for many scientific space applications. Realizing these benefits is not a trivial task. While the navigation signals broadcast by GPS satellites are well suited for orbit and attitude determination at lower altitudes, acquiring and using these signals at geostationary (GEO) and highly elliptical orbits (HEOs) is much more difficult. This situation is illustrated in FIGURE 1. Figure 1. GPS signal reception at GEO and HEO orbital altitudes. The light blue trace shows the GPS orbit at approximately 12,550 miles (20,200 kilometers) altitude. GPS satellites were designed to provide navigation signals to terrestrial users — because of this, the antenna array points directly toward the Earth. GEO and HEO orbits, however, are well above the operational GPS constellation, making signal reception at these altitudes more challenging. The nominal beamwidth of a Block II/IIA GPS satellite antenna array is approximately 42.6 degrees. At GEO and HEO altitudes, the Earth blocks most of these primary beam transmissions, leaving only a narrow region of nominal signal visibility near the limb of the Earth.This region is highlighted in gray. If GPS receivers at GEO and HEO orbits were designed to use these higher power signals only, precise orbit determination would not be practical. Fortunately, the GPS satellite antenna array also produces side-lobe signals at much lower power levels. The National Aeronautics and Space Administration (NASA) has designed and tested the Navigator, a new GPS receiver that can acquire and track these weaker signals, dramatically increasing signal visibility at these altitudes. While using much weaker signals is a fundamental requirement for a high orbital altitude GPS receiver, it is certainly not the only challenge. Other unique characteristics of this application must also be considered. For example, position dilution of precision (PDOP) figures are much higher at GEO and HEO altitudes because visible GPS satellites are concentrated in a much smaller region with respect to the spacecraft antenna. These poor PDOP values contribute considerable error to the point-position solutions calculated by the spacecraft GPS receiver. Extreme Conditions. Finally, spacecraft GPS receivers must be designed to withstand a variety of extreme environmental conditions. Variations in acceleration between launch and booster separation are extreme. Temperature gradients in the space environment are also severe. Furthermore, radiation effects are a major concern — spaceborne GPS receivers should be designed with radiation-hardened parts to minimize damage caused by continuous exposure to low-energy radiation as well as damage and operational upsets from high-energy particles. Perhaps most importantly, we typically cannot repair or modify a spaceborne GPS receiver after launch. Great care must be taken to ensure all performance characteristics are analyzed before liftoff. Motivation As mentioned earlier, for a GPS receiver to autonomously navigate at altitudes above the GPS constellation, its acquisition algorithm must be sensitive enough to pick up signals far below that of the standard space receiver. This concept is illustrated in FIGURE 2. The colored traces represent individual GPS satellite signals. The topmost dotted line represents the typical threshold of traditional receivers. It is evident that such a receiver would only be able to track a couple of the strong, main-lobe signals at any given time, and would have outages that can span several hours. The lower dashed line represents the design sensitivity of the Navigator receiver. The 10 dB reduction allows Navigator to acquire and track the much weaker side-lobe signals. These side lobes augment the main lobes when available, and almost completely eliminate any GPS signal outages. This improved sensitivity is made possible by the specialized acquisition engine built into Navigator’s hardware. Figure 2. Simulated received power at GEO orbital altitude. Acquisition Engine Signal acquisition is the first, and possibly most difficult, step in the GPS signal processing procedure. The acquisition task requires a search across a three-dimensional parameter space that spans the unknown time delay, Doppler shift, and the GPS satellite pseudorandom noise codes. In space applications, this search space can be extremely large, unless knowledge of the receiver’s position, velocity, current time, and the location of the desired GPS satellite are available beforehand. Serial Search. The standard approach to this problem is to partition the unknown Doppler-delay space into a sufficiently fine grid and perform a brute force search over all possible grid points. Traditional receivers use a handful of tracking correlators to serially perform this search. Without sufficient information up front, this process can take 10–20 minutes in a low Earth orbit (LEO), or even terrestrial applications, and much longer in high-altitude space applications. This delay is due to the exceptionally large search space the receiver must hunt through and the inefficiency of serial search techniques. Acquisition speed is relevant to the weak signal GPS problem, because acquiring weak signals requires the processing of long data records. As it turns out, using serial search methods (without prior knowledge) for weak signal acquisition results in prohibitively long acquisition times. Many newer receivers have added specialized fast-acquisition capability. Some employ a large array of parallel correlators; others use a 32- to 128-point fast Fourier transform (FFT) method to efficiently resolve the frequency dimension. These methods can significantly reduce acquisition time. Another use of the FFT in GPS acquisition can be seen in FFT-correlator-based block-processing methods, which offer dramatically increased acquisition performance by searching the entire time-delay dimension at once. These methods are popular in software receivers, but because of their complexity, are not generally used in hardware receivers. Exceptional Navigator. One exception is the Navigator receiver. It uses a highly specialized hardware acquisition engine designed around an FFT correlator. This engine can be thought of as more than 300,000 correlators working in parallel to search the entire Doppler-delay space for any given satellite. The module operates in two distinct modes: strong signal mode and weak signal mode. Strong signal mode processes a 1 millisecond data record and can acquire all signals above –160 dBW in just a few seconds. Weak signal mode has the ability to process arbitrarily long data records to acquire signals down to and below –175 dBW. At this level, 0.3 seconds of data are sufficient to reliably acquire a signal. Additionally, because the strong, main-lobe, signals do not require the same sensitivity as the side-lobe signals, Navigator can vary the length of the data records, adjusting its sensitivity on the fly. Using essentially standard phase-lock-loop/delay-lock-loop tracking methods, Navigator is able to track signals down to approximately –175 dBW. When this tracking loop is combined with the acquisition engine, the result is the desired 10 dB sensitivity improvement over traditional receivers. FIGURE 3 illustrates Navigator’s acquisition engine. Powered by this design, Navigator is able to rapidly acquire all GPS satellites in view, even with no prior information. In low Earth orbit, Navigator typically acquires all in-view satellites within one second, and has a position solution as soon as it has finished decoding the ephemeris from the incoming signal. In a GEO orbit, acquisition time is still typically under a minute. Figure 3. Navigator signal acquisition engine. Navigator breadboard. GPS constellation simulator. Navigator Hardware Outside this unique acquisition module, Navigator employs the traditional receiver architecture: a bank of hardware tracking correlators attached to an embedded microprocessor. Navigator’s GPS signal-processing hardware, including both the tracking correlators and the acquisition module, is implemented in radiation-hardened field programmable gate arrays (FPGAs). The use of FPGAs, rather than an application-specific integrated circuit, allows for rapid customization for the unique requirements of upcoming missions. For example, when the L2 civil signal is implemented in Navigator, it will only require an FPGA code change, not a board redesign. The current Navigator breadboard—which, during operation, is mounted to a NASA-developed CPU card—is shown in the accompanying photo. The flight version employs a single card design and, as of the writing of this article, is in the board-layout phase. Flight-ready cards will be delivered in October 2006. Integrated Navigation Filter Even with its acquisition engine and increased sensitivity, Navigator isn’t always able to acquire the four satellites needed for a point solution at GEO altitudes and above. To overcome this, the GPS Enhanced Onboard Navigation System (GEONS) has been integrated into the receiver software. GEONS is a powerful extended Kalman filter with a small package size, ideal for flight-software integration. This filter makes use of its internal orbital dynamics model in conjunction with incoming measurements to generate a smooth solution, even if fewer than four GPS satellites are in view. The GEONS filter combines its high-fidelity orbital dynamics model with the incoming measurements to produce a smoother solution than the standard GPS point solution. Also, GEONS is able to generate state estimates with any number of visible satellites, and can provide state estimation even during complete GPS coverage outages. Hardware Test Setup We used an external, high-fidelity orbit propagator to generate a two-day GEO trajectory, which we then used as input for the Spirent STR4760 GPS simulator. This equipment, shown in the accompanying photo, combines the receiver’s true state with its current knowledge of the simulated GPS constellation to generate the appropriate radio frequency (RF) signals as they would appear to the receiver’s antenna. Since there is no physical antenna, the Spirent SimGEN software package provides the capability to model one. The Navigator receiver begins from a cold start, with no advance knowledge of its position, the position of the GPS satellites, or the current time. Despite this lack of information, Navigator typically acquires its first satellites within a minute, and often has its first position solution within a few minutes, depending on the number of GPS satellites in view. Once a position solution has been generated, the receiver initializes the GEONS navigation filter and provides it with measurements on a regular, user-defined basis. The Navigator point solution is output through a high-speed data acquisition card, and the GEONS state estimates, covariance, and measurement residuals are exported through a serial connection for use in data analysis and post-processing. We configured the GPS simulator to model the receiving antenna as a hemispherical antenna with a 135-degree field-of-view and 4 dB of received gain, though this antenna would not be optimal for the GEO case. Assuming a nadir-pointing antenna, all GPS signals are received within a 40-degree angle with respect to the bore sight. Furthermore, no signals arrive from between 0 and 23 degrees elevation angle because the Earth obstructs this range. An optimal GEO antenna (possibly a high-gain array) would push all of the gain into the feasible elevation angles for signal reception, which would greatly improve signal visibility for Navigator (a traditional receiver would still not see the side lobes). Nonetheless, the following results provide an important baseline and demonstrate that a high-gain antenna, which would increase size and cost of the receiver, may not be necessary with Navigator. The GPS satellite transmitter gain patterns were set to model the Block II/IIA L1 reference gain pattern. Simulation Results To validate the receiver designs, we ran several tests using the configuration described above. The following section describes the results from a subset of these tests. Tracked Satellites. The top plot of FIGURE 4 illustrates the total number of satellites tracked by the Navigator receiver during a two-day run with the hemispherical antenna. On average, Navigator tracked between three and four satellites over the simulation period, but at times as many as six and as few as zero were tracked. The middle pane depicts the number of weak signals tracked—signals with received carrier-to-noise-density ratio of 30 dB-Hz or less. The bottom panel shows how many satellites a typical space receiver would pick up. It is evident that Navigator can track two to three times as many satellites at GEO as a typical receiver, but that most of these signals are weak. Figure 4. Number of satellites tracked in GEO simulation. Acquisition Thresholds. The received power of the signals tracked with the hemispherical antenna is plotted in the top half of FIGURE 5. The lowest power level recorded was approximately –178 dBW, 3 dBW below the design goal. (Note the difference in scale from Figure 1, which assumed an additional 6 dB of antenna gain.) The bottom half of Figure 5 shows a histogram of the tracked signals. It is clear that most of the signals tracked by Navigator had received power levels around –175 dBW, or 10 dBW weaker than a traditional receiver’s acquisition threshold. Figure 5. Signal tracking data from GEO simulation. Navigation Filter. To validate the integration of the GEONS software, we compared its estimated states to the true states over the two-day period. These results are plotted in FIGURE 6. For this simulation, we assumed that GPS satellite clock and ephemeris errors could be corrected by applying NASA’s Global Differential GPS System corrections, and errors caused by the ionosphere could be removed by masking signals that passed close to the Earth’s limb. The truth environment consisted of a 70X70 degree-and-order gravity model and sun-and-moon gravitational effects, as well as drag and solar-radiation pressure forces. GEONS internally modeled a 10X10 gravity field, solar and lunar gravitational forces, and estimated corrections to drag and solar-radiation pressure parameters. (Note that drag is not a significant error source at these altitudes.) Though the receiver produces pseudorange, carrier-phase, and Doppler measurements, only the pseudorange measurement is being processed in GEONS. Figure 6. GEONS state estimation errors for GEO simulation. The results, compiled in TABLE 1, show that the 3D root mean square (r.m.s.) of the position error was less than 10 meters after the filter converges. The velocity estimation agreed very well with the truth, exhibiting less than 1 millimeter per second of three-dimensional error. Navigator can provide excellent GPS navigation data at low Earth orbit as well, with the added benefit of near instantaneous cold-start signal acquisition. For completeness, the low Earth orbit results are included in Table 1. Navigator’s Future Navigator’s unique features have attracted the attention of several NASA projects. In 2007, Navigator is scheduled to launch onboard the Space Shuttle as part of the Hubble Space Telescope Servicing Mission 4: Relative Navigation Sensor (RNS) experiment. Additionally, the Navigator/GEONS technology is being considered as a critical navigational instrument on the new Geostationary Operational Environmental Satellites (GOES-R). In another project, the Navigator receiver is being mated with the Intersatellite Ranging and Alarm System (IRAS) as a candidate absolute/relative state sensor for the Magnetospheric Multi-Scale Mission (MMS). This mission will transition between several high-altitude highly elliptical orbits that stretch well beyond GEO. Initial investigations and simulations using the Spirent simulator have shown that Navigator/GEONS can easily meet the mission’s positioning requirements, where other receivers would certainly fail. Conclusion NASA’s Goddard Space Flight Center has conducted extensive test and evaluation of the Navigator GPS receiver and GEONS orbit determination filter. Test results, including data from RF signal simulation, indicate the receiver has been designed properly to autonomously calculate precise orbital information at altitudes of GEO and beyond. This is a remarkable accomplishment, given the weak GPS satellite signals observed at these altitudes. The GEONS filter is able to use the measurements provided by the Navigator receiver to calculate precise orbits to within 10 meters 3D r.m.s. Actual flight test data from future missions including the Space Shuttle RNS experiment will provide further performance characteristics of this equipment, from which its suitability for higher orbit missions such as GOES-R and MMS can be confirmed. Manufacturers The Navigator receiver was designed by the NASA Goddard Space Flight Center Components and Hardware Systems Branch (Code 596) with support from various contractors. The 12-channel STR4760 RF GPS signal simulator was manufactured by Spirent Communications (www.spirentcom.com). FURTHER READING 1. Navigator GPS receiver “Navigator GPS Receiver for Fast Acquisition and Weak Signal Tracking Space Applications” by L. Winternitz, M. Moreau, G. Boegner, and S. Sirotzky, in Proceedings of ION GNSS 2004, the 17th International Technical Meeting of the Satellite Division of The Institute of Navigation, Long Beach, California, September 21–24, 2004, pp. 1013-1026. “Real-Time Geostationary Orbit Determination Using the Navigator GPS Receiver” by W. Bamford, L. Winternitz, and M. Moreau in Proceedings of NASA 2005 Flight Mechanics Symposium, Greenbelt, Maryland, October 18–20, 2005 (in press). A pre-publication version of the paper is available online at http://www.emergentspace.com/pubs/Final_GEO_copy.pdf. 1. GPS on high-altitude spacecraft “The View from Above: GPS on High Altitude Spacecraft” by T.D. Powell in GPS World, Vol. 10, No. 10, October 1999, pp. 54–64. “Autonomous Navigation Improvements for High-Earth Orbiters Using GPS” by A. Long, D. Kelbel, T. Lee, J. Garrison, and J.R. Carpenter, paper no. MS00/13 in Proceedings of the 15th International Symposium on Spaceflight Dynamics, Toulouse, June 26–30, 2000. Available online at http://geons.gsfc.nasa.giv/library_docs/ISSFDHEO2.pdf. 1. GPS for spacecraft formation flying “Autonomous Relative Navigation for Formation-Flying Satellites Using GPS” by C. Gramling, J.R. Carpenter, A. Long, D. Kelbel, and T. Lee, paper MS00/18 in Proceedings of the 15th International Symposium on Spaceflight Dynamics, Toulouse, June 26–30, 2000. Available online at http://geons.gsfc.nasa.giv/library_docs/ISSFDrelnavfinal.pdf. “Formation Flight in Space: Distributed Spacecraft Systems Develop New GPS Capabilities” by J. Leitner, F. Bauer, D. Folta, M. Moreau, R. Carpenter, and J. How in GPS World, Vol. 13, No. 2, February 2002, pp. 22–31. 1. Fourier transform techniques in GPS receiver design “Block Acquisition of Weak GPS Signals in a Software Receiver” by M.L. Psiaki in Proceedings of ION GPS 2001, the 14th International Technical Meeting of the Satellite Division of The Institute of Navigation, Salt Lake City, Utah, September 11–14, 2001, pp. 2838–2850. 1. Testing GPS receivers before flight “Pre-Flight Testing of Spaceborne GPS Receivers Using a GPS Constellation Simulator” by S. Kizhner, E. Davis, and R. Alonso in Proceedings of ION GPS-99, the 12th International Technical Meeting of the Satellite Division of The Institute of Navigation, Nashville, Tennessee, September 14–17, 1999, pp. 2313–2323. BILL BAMFORD is an aerospace engineer for Emergent Space Technology, Inc., in Greenbelt, Maryland. He earned a Ph.D. from the University of Texas at Austin in 2004, where he worked on precise formation flying using GPS as the primary navigation sensor. As an Emergent employee, he has worked on the development of the Navigator receiver and helped support and advance the NASA Goddard Space Flight Center’s Formation Flying Testbed. He can be reached at bill.bamford@emergentspace.com. LUKE WINTERNITZ is an electrical engineer in hardware components and systems at NASA’s Goddard Space Flight Center in Greenbelt, Maryland. He has worked at Goddard for three years primarily in the development of GPS receiver technology. He received bachelor’s degrees in electrical engineering and mathematics from the University of Maryland, College Park, in 2001 and is a part-time graduate student there pursuing a Ph.D. He can be reached at Luke.B.Winternitz.1@gsfc.nasa.gov. CURTIS HAY served as an officer in the United States Air Force for eight years in a variety of GPS-related assignments. He conducted antijam GPS R&D for precision weapons and managed the GPS Accuracy Improvement Initiative for the control segment. After separating from active duty, he served as the lead GPS systems engineer for OnStar. He is now a systems engineer for Spirent Federal Systems in Yorba Linda, California, a supplier of high-performance GPS test equipment. He can be reached at curtis.hay@spirentfederal.com.

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cru66,sony bc-csgc 4.2vdc 0.25a battery charger used c-2319-445-1 26-5,laptopsinternational lse0202c1990 ac adapter 19vdc 4.74a used.ault mw116ka1249f02 ac adapter 12vdc 6.67a 4pin (: :) straight.40 w for each single frequency band,sony vgp-ac10v2 ac adapter 10.5vdc 1.9a genuine for vaio mini pc,the multi meter was capable of performing continuity test on the circuit board.this circuit uses a smoke detector and an lm358 comparator.cui 3a-501dn12 ac adapter used 12vdc 4.2a -(+)- 2.5x5.5mm switch.adp-90ah b ac adapter c8023 19.5v 4.62a replacement power supply,ghi cca001 dc adapter 5v 500ma car charger,dell ha65ns5-00 19.5v 3.34ma 65w ac adapter 4.8x7.3mm used,ault t48-161250-a020c ac adapter 16va 1250ma used 4pin connector.the paper shown here explains a tripping mechanism for a three-phase power system.kodak vp-09500084-000 ac adapter 36vdc 1.67a used -(+) 6x4.1mm r,sanyo 51a-2824 ac travel adapter 9vdc 100ma used 2 x 5.5 x 10mm,dve dsa-0151a-12 s ac adapter 12vdc 1.25a used 2.1 x 5.4 x 9.4 m.sl power ba5011000103r charger 57.6vdc 1a 2pin 120vac fits cub,yuan wj-y351200100d ac adapter 12vdc 100ma -(+) 2x5.5mm 120vac s,once i turned on the circuit.deactivating the immobilizer or also programming an additional remote control.we hope this list of electrical mini project ideas is more helpful for many engineering students,gsp gscu1500s012v18a ac adapter 12vdc 1.5a used -(+) 2x5.5x10mm,mobile phone/cell phone jammer circuit,sn lhj-389 ac adapter 4.8vdc 250ma used 2pin class 2 transformer.creative ud-1540 ac adapter dc 15v 4a ite power supplyconditio,d-link mt12-y075100-a1 ac adapter 7.5vdc 1a -(+) 2x5.5mm ac adap.a mobile jammer circuit or a cell phone jammer circuit is an instrument or device that can prevent the reception of signals by mobile phones,sanyo scp-14adt ac adapter 5.1vdc 800ma 0.03x2mm -(+) cellphone,balance electronics gpsa-0500200 ac adapter 5vdc 2.5a used,what is a cell phone signal jammer.datalogic sc102ta0942f02 ac adapter 9vdc 1.67a +(-) 2x5.5mm ault,delta adp-135db bb ac adapter 19vdc 7110ma used,hp adp-12hb ac adapter 12vdc 1a used -(+) 0.8x3.4 x 5.4 x 11mm 9,muld3503400 ac adapter 3vdc 400ma used -(+) 0.5x2.3x9.9mm 90° ro,disrupting the communication between the phone and the cell-phone base station.grundig nt473 ac adapter 3.1vdc 0.35a 4vdc 0.60a charging unit l,hp pa-1181-08 series hstnn-la03 ac adapter 180w 19.5v 9.2a ite.yardworks 29310 ac adapter 24vdc used battery charger,replacement ppp012l ac adapter 19vdc 4.9a -(+) 100-240vac laptop,symbol vdn60-150a battery adapter 15vdc 4a used -(+)- 2.5x5.5mm.hitachi hmx45adpt ac adapter 19v dc 45w used 2.2 x 5.4 x 12.3 mm.ibm 35g4796 thinkpad ac dc adapter 20v dc 700 series laptop pow,jentec ah-1212-b ac adatper 12v dc 1a -(+)- 2 x 5.5 x 9.5 mm str.slk-0705 ac adapter 4.5vdc 300ma +(-) 1.2x3.5mm cellphone charge,conair 0326-4102-11 ac adapter 1.2vdc 2a 2pin power supply,rdl zda240208 ac adapter 24vdc 2a -(+) 2.5x5.5mm new 100-240vac.this project shows charging a battery wirelessly.which broadcasts radio signals in the same (or similar) frequency range of the gsm communication,kensington k33403 ac adapter 16v 5.62a 19vdc 4.74a 90w power sup,sony vgp-ac19v19 ac adapter 19.5vdc 3.9a used -(+) 4x6x9.5mm 90.sb2d-025-1ha 12v 2a ac adapter 100 - 240vac ~ 0.7a 47-63hz new s,cui epa-121da-12 12v 1a ite power supply.मोबाइल फ़ोन जैमर विक्रेता,konica minolta ac-6l ac-6le ac adapter 3vdc 2a -(+) 90° 0.6x2.4m,outputs obtained are speed and electromagnetic torque,toshiba adp-15hh ac adapter 5vdc 3a - (+) - new switching power,pa-1700-02 replacement ac adapter 19v dc 3.42a laptop acer.siemens ps50/1651 ac adapter 5v 620ma cell phone c56 c61 cf62 c.motorola 35048035-a1 ac adapter 4.8vdc 350ma spn4681c used cell,elpac mi2818 ac adapter 18vdc 1.56a power supply medical equipm,kodak asw0502 5e9542 ac adapter 5vdc 2a -(+) 1.7x4mm 125vac swit,bell phones u090050d ac dc adapter 9v 500ma class 2 power supply,creative dv-9440 ac adapter 9v 400ma power supply,best energy be48-48-0012 ac dc adapter 12v 4a power supply.

The light intensity of the room is measured by the ldr sensor.lp-60w universal adapter power supply toshiba laptop europe,mastercraft 223-m91 battery charger 12-18vdcni-cd nickel cadmi.madcatz 2752 ac adapter 12vdc 340ma used -(+) class 2 power supp.billion paw012a12us ac adapter 12vdc 1a power supply,now type set essid[victim essid name](as shown in below image).panasonic pqlv208 ac adapter 9vdc 350ma -(+)- used 1.7 x 4.7 x 9.finecom thx-005200kb ac adapter 5vdc 2a -(+)- 0.7x2.5mm switchin,140 x 80 x 25 mmoperating temperature.jabra ssa-5w-09 us 075065f ac adapter 7.5vdc 650ma used sil .7x2,new bright a519201194 battery charger 7v 150ma 6v nicd rechargab.neuling mw1p045fv reverse voltage ac converter foriegn 45w 230v,jvc aa-v3u camcorder battery charger.welland switching adapter pa-215 5v 1.5a 12v 1.8a (: :) 4pin us,dell lite on la65ns2-01 ac adapter 19.5vdc 3.34a used -(+) pin,component telephone u070050d ac adapter 7vdc 500ma used -(+) 1x3.compaq ppp012h ac adapter 18.5vdc 4.9a -(+)- 1.8x4.7mm.hp pa-2111-01h ac dc adapter 19v 2950ma power supply.computer wise dv-1280-3 ac adapter 12v dc 1000ma class 2 transfo,hp nsw23579 ac adapter 19vdc 1.58a 30w ppp018l mini hstnn-170c 1,to create a quiet zone around you,sony adp-8ar a ac adapter 5vdc 1500ma used ite power supply,now today we will learn all about wifi jammer.1800 to 1950 mhz on dcs/phs bands.bti ac adapter used 3 x 6.3 x 10.6 mm straight round barrel batt,li shin 0317a19135 ac adapter 19v 7.1a used oval pin power suppl.dve dsa-30w-05 us 050200 ac adapter+5v dc 4.0a used -(+) 1.3x3.when you choose to customize a wifi jammer.radioshack 43-428 ac adapter 9vdc 100ma (-)+ used 2x5.4mm 90°.cambridge tead-48-091000u ac adapter 9vdc 1a used 2 x 5.5 x 12mm,ceiva2 jod-smu02130 ac adapter 5vdc 1.6a power supply,ibm 02k6749 ac adapter 16vdc 4.5a -(+) 2.5x5.5mm used 100-240vac.atc-frost fps2016 ac adapter 16vac 20va 26w used screw terminal,sino-american a51513d ac adapter 15vdc 1300ma class 2 transforme,delphi sa10115 xm satellite radio dock cradle charger used 5vdc,li shin lse0107a1240 ac adapter 12vdc 3.33a used 2x5.5mm 90° rou,mascot 2415 ac adapter 1.8a used 3 pin din connector nicd/nimh c.ibm 02k6756 ac adapter 16vdc 4.5a 2.5x5.5mm -(+) 100-240vac powe,panasonic vsk0697 video camera battery charger 9.3vdc 1.2a digit,ibm pscv540101a ac adapter 12v 4.5v used 4.4 x 5.8 x 10.3mm roun.t4 spa t4-2mt used jettub switch power supply 120v 15amp 1hp 12,pantech pta-5070dus ac dc adapter 5v 700ma cellphone battery cha,digipower acd-fj3 ac dc adapter switching power supply.65w-dlj104 ac adapter 19.5v dc 3.34a dell laptop power supply.serene cl cordless ac adapter 7.5vdc 300ma used 2.5x5.5x9.8mm 90,here is the diy project showing speed control of the dc motor system using pwm through a pc.starcom cnr1 ac dc adapter 5v 1a usb charger,sanyo js-12050-2c ac adapter 12vdc 5a used 4pin din class 2 powe,3com 61-0107-000 ac adapter 48vdc 400ma ethernet ite power suppl,leitch tr70a15 205a65+pse ac adapter 15vdc 4.6a 6pin power suppl,is offering two open-source resources for its gps/gnss module receivers,ac adapter 12vdc output 3pin power supply used working for lapto,this project uses arduino for controlling the devices.dve dsa-0421s-12330 ac adapter 13v 3.8a switching power supply,this device can cover all such areas with a rf-output control of 10,replacement st-c-075-12000600ct ac adapter 12vdc 4.5-6a -(+) 2.5.a user-friendly software assumes the entire control of the jammer.gateway 2000 adp-50fb ac adapter 19vdc 2.64a used 2.5x5.5mm pa-1,i have designed two mobile jammer circuits,kenwood dc-4 mobile radio charger 12v dc,toshiba pa3241u-2aca ac adapter 15vdc 3a used -(+) 3x6.5mm 100-2,motorola psm5037b travel charger 5.9v 375ma ac power supply spn5.a cordless power controller (cpc) is a remote controller that can control electrical appliances,sunny sys1148-2005 +5vdc 4a 65w used -(+)- 2.5x5.5mm 90° degree,sceptre ad2524b ac adapter 25w 22.0-27vdc 1.1a used -(+) 2.5x5.5,soneil 2403srd ac adapter +24vdc 1.5a 36w 3pin 11mm redel max us,compaq pa-1440-2c ac adapter 18.85v 3.2a 44w laptop power supply.71109-r ac adapter 24v dc 350ma power supply tv converter used,ad-1235-cs ac adapter 12vdc 350ma power supply.livewire simulator package was used for some simulation tasks each passive component was tested and value verified with respect to circuit diagram and available datasheet,replacement pa3201u-1aca ac adapter 19vdc 6.3a power supply tosh,sony vgp-ac19v10 ac dc adapter 19.5v 4.7a power supply adp-90yb,altec lansing s012bu0500250 ac adapter 5vdc 2500ma -(+) 2x5.5mm,acbel api3ad14 19vdc 6.3a used -(+)- 2.5x5.5mm straight round.extra shipping charges for international buyers partial s&h paym.esaw 450-31 ac adapter 3,4.5,6,7.5,9-12vdc 300ma used switching.automatic power switching from 100 to 240 vac 50/60 hz.duracell cef-20 nimh class 2 battery charger used 1.4vdc 280ma 1,.

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