MIL-STD-1553B, which superseded the earlier 1975 specification MIL-STD-1553A, was published in 1978. The basic difference between the 1553A and 1553B revisions is that in the latter, the options are defined rather than being left for the user to define as required. It was found that when the standard did not define an item, there was no coordination in its use. Hardware and software had to be redesigned for each new application. The primary goal of the 1553B was to provide flexibility without creating new designs for each new user. This was accomplished by specifying the electrical interfaces explicitly so that electrical compatibility between designs by different manufacturers could be assured.
Six change notices to the standard have been published since 1978.[7] For example, change notice 2 in 1986 changed the title of the document from "Aircraft internal time division command/response multiplex data bus" to "Digital time division command/response multiplex data bus".
MIL-STD-1553C is the last revision made in February 2018. Revision C is functionally equivalent to Revision B but contains updated graphics and tables to ease readability of the standard.[8]
A single bus consists of a wire pair with 70–85 Ω impedance at 1MHz. Where a circular connector is used, its center pin is used for the high (positive) Manchester bi-phase signal. Transmitters and receivers couple to the bus via isolation transformers, and stub connections branch off using a pair of isolation resistors and, optionally, a coupling transformer. This reduces the impact of a short circuit and ensures that the bus does not conduct current through the aircraft. A Manchester code is used to present both clock and data on the same wire pair and to eliminate any DC component in the signal (which cannot pass the transformers). The bit rate is 1.0 megabit per second (1-bit per μs). The combined accuracy and long-term stability of the bit rate is only specified to be within ±0.1%; the short-term clock stability must be within ±0.01%. The peak-to-peak output voltage of a transmitter is 18–27 V.
The bus can be made dual or triply redundant by using several independent wire pairs, and then all devices are connected to all buses. There is provision to designate a new bus control computer in the event of a failure by the current master controller. Usually, the auxiliary flight control computer(s) monitor the master computer and aircraft sensors via the main data bus. A different version of the bus uses optical fiber, which weighs less and has better resistance to electromagnetic interference, including EMP. This is known as MIL-STD-1773.[9] NASA's "AS 1773" experiment has a dual rate of 1Mbit/s or 20Mbit/s – probably a predecessor of STANAG 3910.[10]
Bus protocol
A MIL-STD-1553 multiplex data bus system consists of a Bus Controller (BC) controlling multiple Remote Terminals (RT) all connected together by a data bus providing a single data path between the Bus Controller and all the associated Remote Terminals. There may also be one or more Bus Monitors (BM); however, Bus Monitors are specifically not allowed to take part in data transfers, and are only used to capture or record data for analysis, etc. In redundant bus implementations, several data buses are used to provide more than one data path, i.e. dual redundant data bus, tri-redundant data bus, etc. All transmissions onto the data bus are accessible to the BC and all connected RTs. Messages consist of one or more 16-bit words (command, data, or status). The 16 bits comprising each word are transmitted using Manchester code, where each bit is transmitted as a 0.5 μs high and 0.5 μs low for a logical 1 or a low-high sequence for a logical 0. Each word is preceded by a 3 μs sync pulse (1.5 μs low plus 1.5 μs high for data words and the opposite for command and status words, which cannot occur in the Manchester code) and followed by an odd parity bit. Practically each word could be considered as a 20-bit word: 3-bit for sync, 16-bit for payload and 1-bit for odd parity control. The words within a message are transmitted contiguously and there has to be a minimum of a 4 μs gap between messages. However, this inter-message gap can be, and often is, much larger than 4 μs, even up to 1 ms with some older Bus Controllers. Devices have to start transmitting their response to a valid command within 4–12 μs and are considered to not have received a command or message if no response has started within 14 μs.
All communication on the bus is under the control of the Bus Controller using commands from the BC to the RTs to receive or transmit. The sequence of words, (the form of the notation is <originator>.<word_type(destination)> and is a notation similar to CSP), for transfer of data from the BC to a terminal is
This means that during a transfer, all communication is started by the Bus Controller, and a terminal device cannot start a data transfer on its own. In the case of an RT to RT transfer the sequence is as follows: An application or function in the subsystem behind the RT interface (e.g. RT1) writes the data that is to be transmitted into a specific (transmit) sub-address (data buffer). The time at which this data is written to the sub-address is not necessarily linked to the time of the transaction, though the interfaces ensure that partially updated data is not transmitted. The Bus controller commands the RT that is the destination of the data (e.g. RT2) to receive the data at a specified (receive) data sub-address and then commands RT1 to transmit from the transmit sub-address specified in the command. RT1 transmits a Status word, indicating its current status, and the data. The Bus Controller receives RT1's status word, and sees that the transmit command has been received and actioned without a problem. RT2 receives the data on the shared data bus and writes it into the designated receive sub-address and transmits its Status word. An application or function on the subsystem behind the receiving RT interface may then access the data. Again the timing of this read is not necessarily linked to that of the transfer. The Bus Controller receives RT2's status word and sees that the receive command and data have been received and actioned without a problem.
If, however, either RT fails to send its status or the expected data or indicates a problem through the setting of error bits in the status word, the Bus Controller may retry the transmission. Several options are available for such retries including an immediate retry (on the other data bus of a redundant pair of data buses) and a retry later (on the same bus) in the sequence of transfers.
The sequences ensure that the terminal is functioning and able to receive data. The status word at the end of a data transfer sequence ensures that the data has been received and that the result of the data transfer is acceptable. It is this sequence that gives MIL-STD-1553 its high integrity.
However, the standard does not specify any particular timing for any particular transfer — that's up to the system designers. Generally (the way it is done on most military aircraft), the Bus Controller has a schedule of transfers that covers the majority of transfers, often organized into a major frame or major cycle, which is often subdivided into minor cycles. In such a cyclic executive schedule structure, transfers that occur in every minor cycle (rate group 1) happen at the highest rate, typically 50Hz, transfers that occur in every other minor cycle, of which there are two groups (rate group 2.1 and 2.2) happen at the next highest rate, e.g. 25Hz. Similarly, there are four groups (3.1, 3.2, 3.3, and 3.4) at, e.g., 12.5Hz and so on. Hence, where this scheduling structure is used, the transfers are all at harmonically related frequencies, e.g. 50, 25, 12.5, 6.25, 3.125, and 1.5625Hz (for a major frame comprising 32 minor cycles at 50Hz). Whilst RTs cannot start a transfer directly on their own, the standard does include a method for when an RT needs to transmit data that is not automatically scheduled by the Bus Controller. These transfers are often called acyclic transfers as they are outside the structure used by the cyclic executive. In this sequence, an RT requests transmission through a bit in the status word, the Service Request bit. Generally, this causes the Bus Controller to transmit a Transmit Vector Word Mode Code command. However, where an RT only has one possible acyclic transfer, the Bus Controller can skip this part. The vector word is transmitted by the RT as a single 16-bit data word. The format of this vector word is not defined in the standard, so the system designers must specify what values from what RTs mean what action the Bus Controller is to take. This may be to schedule an acyclic transfer either immediately or at the end of the current minor cycle. This means that the Bus Controller has to poll all the Remote Terminals connected to the data bus, generally at least once in a major cycle. RTs with higher-priority functions (for example, those operating the aircraft control surfaces) are polled more frequently. Lower-priority functions are polled less frequently.
Six types of transactions are allowed between the BC and a specific RT or between the Bus Controller and a pair of RTs:
Figure 6: Information transfer formats. Note: "TRANSMIT COMMAND" equals "command word"
Controller to RT Transfer. The Bus Controller sends one 16-bit receive command word, immediately followed by 1 to 32 16-bit data words. The selected Remote Terminal then sends a single 16-bit Status word.
RT to Controller Transfer. The Bus Controller sends one transmit command word to a Remote Terminal. The Remote Terminal then sends a single Status word, immediately followed by 1 to 32 words.
RT to RT Transfers. The Bus Controller sends out one receive command word immediately followed by one transmit command word. The transmitting Remote Terminal sends a Status word immediately followed by 1 to 32 data words. The receiving Terminal then sends its Status word.
Mode Command Without Data Word. The Bus Controller sends one command word with a Sub-address of 0 or 31 signifying a Mode Code type command. The Remote Terminal responds with a Status word.
Mode Command With Data Word (Transmit). The Bus Controller sends one command word with a Sub-address of 0 or 31 signifying a Mode Code type command. The Remote Terminal responds with a Status word immediately followed by a single Data word.
Mode Command With Data Word (Receive). The Bus Controller sends one command word with a Sub-address of 0 or 31 signifying a Mode Code type command immediately followed by a single data word. The Remote Terminal responds with a Status word.
MIL-STD-1553B also introduced the concept of optional broadcast transfers, in which data is sent to all RTs that implement the option, but to which no RTs respond, as this would cause conflicts on the bus. These can be used where the same data is sent to multiple RTs, to reduce the number of transactions and thus reduce the loading on the data bus. However, the lack of explicit responses by the RTs receiving these broadcasts means that these transfers cannot be automatically re-tried in the event of an error in the transaction.
Four types of broadcast transactions are allowed between the BC and all capable RTs:
Figure 7: Broadcast information transfer formats
Controller to RT(s) Transfer. The Bus Controller sends one receive command word with a Terminal address of 31 signifying a broadcast type command, immediately followed by 0 to 32 data words. All Remote Terminals that implement broadcasts will accept the data but no Remote Terminals will respond.
RT to RT(s) Transfers. The Bus Controller sends out one receive command word with a Terminal address of 31 signifying a broadcast type command, immediately followed by one transmit command. The transmitting Remote Terminal sends a Status word immediately followed by 1 to 32 data words. All Remote Terminals that implement broadcasts will accept the data but no Remote Terminals will respond.
Mode Command Without Data Word (Broadcast). The Bus Controller sends one command word with a Terminal address of 31 signifying a broadcast type command and a sub-address of 0 or 31 signifying a Mode Code type command. No Remote Terminals will respond.
Mode Command With Data Word (Broadcast). The Bus Controller sends one command word with a Terminal address of 31 signifying a broadcast type command and a sub-address of 0 or 31 signifying a Mode Code type command, immediately followed by one Data word. No Remote Terminals will respond.
The Command Word is built as follows. The first 5 bits are the Remote Terminal address (0–31). The sixth bit is 0 for Receive or 1 for Transmit. The next 5 bits indicate the location (sub-address) to hold or get data on the Terminal (1–30). Note that sub-addresses 0 and 31 are reserved for Mode Codes. The last 5 bits indicate the number of words to expect (1–32). All zero bits indicate 32 words. In the case of a Mode Code, these bits indicate the Mode Code number (e.g., Initiate Self Test and Transmit BIT Word).
Command Word Bit Usage
Remote Terminal address (0 - 31)
Receive or Transmit
Location (sub-address) of data (1 - 30)
Number of words to expect (1 - 32)
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
The Status Word decodes as follows. The first 5 bits are the address of the Remote Terminal that is responding. The rest of the word is single bit condition codes, with some bits reserved. A 'one' state indicates condition is true. More than one condition may be true at the same time.
Status Word Bit Usage
Remote Terminal address
Message Error
Instrumentation
Service Request
Reserved
Broadcast Cmd Received
Busy
Subsystem Flag
Dynamic Bus Acceptance
Terminal Flag
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
The image below exemplifies many of the protocol and physical layer concepts explained above. For example, the RT address contained in the Command Word has a value of 0x3 (in range of 0 to 31). The sixth bit is 1, indicating a Transmit from the RT. The sub-address is 0x01. The last 5 bits indicate the number of words to expect, which has a value of 1, which is matched by the single Data Word (value 0x2) after the Status Word.
Also as explained above, devices have to start transmitting their response to a valid command within 4–12 microseconds. In the example, the Response Time is 8.97 μs, therefore within specifications. This means that the Remote Terminal (RT) number 3 has responded to the Bus Controller query after 8.97 μs. The amplitude of the query is lower than the amplitude of the response because the signal is probed at a location closer to the Remote Terminal.
In the Status Word, the first 5 bits are the address of the Remote Terminal that is responding, in this case 0x3. A correct Transfer exhibits the same RT address in the Command Word as in the Status Word.
A RT to BC Transfer, with 1 Data Word
Conceptual description
Figure 1: Sample MIL-STD-1553B Multiplex Data Bus Architecture
Figure 1 shows a sample MIL-STD-1553B system that consists of:
redundant MIL-STD-1553B buses
a Bus Controller
a Backup Bus Controller
a Bus Monitor
a standalone Remote Terminal with one or more subsystems communicating with it
a subsystem with an embedded Remote Terminal
The Bus Controller
There is only one Bus Controller at a time on any MIL-STD-1553 bus. It initiates all message communication over the bus.
Figure 1 shows 1553 data bus details:
operates according to a command list stored in its local memory
commands the various Remote Terminals to send or receive messages
services any requests that it receives from the Remote Terminals
detects and recovers from errors
keeps a history of errors
The 1553B spec dictates that all devices in the system be connected to a redundant pair of buses to provide an alternate data path in the event of damage or failure of the primary bus. Bus messages only travel on one bus at a time, determined by the Bus Controller.
Backup Bus Controller
While there may be only one BC on the bus at any one time, the standard provides a mechanism for handover to a Backup Bus Controller (BBC) or (BUBC), using flags in the status word and Mode Codes. This may be used in normal operation where handover occurs because of some specific function, e.g. handover to or from a BC that is external to the aircraft, but connected to the bus. Procedures for handover in fault and failure conditions generally involve discrete connections between the main and backup BCs, and the backup monitoring the actions of the main BC during operation. For example, if there is a prolonged quiescence on the bus indicating that the active BC has failed, the next highest priority backup BC, indicated by the discrete connections, will take over and begin operating as the active BC.
The Bus Monitor
A Bus Monitor (BM) cannot transmit messages over the data bus. Its primary role is to monitor and record bus transactions, without interfering with the operation of the Bus Controller or the RTs. These recorded bus transactions can then be stored, for later off-line analysis.
Ideally, a BM captures and records all messages sent over the 1553 data bus. However, recording all of the transactions on a busy data bus might be impractical, so a BM is often configured to record a subset of the transactions, based on some criteria provided by the application program.
Alternatively, a BM is used in conjunction with a Backup Bus Controller. This allows the Backup Bus Controller to "hit the ground running", if it is called upon to become the active Bus Controller.
The Remote Terminal
A Remote Terminal can be used to provide:
an interface between the MIL-STD-1553B data bus and an attached subsystem
a bridge between a MIL-STD-1553B bus and another MIL-STD-1553B bus.
For example, in a tracked vehicle, a Remote Terminal might acquire data from an inertial navigational subsystem, and send that data over a 1553 data bus to another Remote Terminal, for display on a crew instrument. Simpler examples of Remote Terminals might be interfaces that switch on the headlights, the landing lights, or the annunciators in an aircraft.
Test Plans for Remote Terminals:
The RT Validation Test Plan is intended for design verification of Remote Terminals designed to meet the requirements of AS 15531 and MIL-STD-1553B with Notice 2. This test plan was initially defined in MIL-HDBK-1553, Appendix A. It was updated in MIL-HDBK-1553A, Section 100. The test plan is maintained by the SAE AS-1A Avionic Networks Subcommittee as AS4111.
The RT Production Test Plan is a simplified subset of the validation test plan and is intended for production testing of Remote Terminals. This test plan is maintained by the SAE AS-1A Avionic Networks Subcommittee as AS4112.
Bus hardware characteristics
The bus hardware encompasses (1) cabling, (2) bus couplers, (3) terminators and (4) connectors.
Cabling
The industry has standardized the cable type as a twinax cable with a characteristic impedance of 78 ohms, which is almost the midpoint of the specification range of 70 to 85 ohms.
MIL-STD-1553B does not specify the length of the cable. However, the maximum length of cable is directly related to the gauge of the cable conductor and time delay of the transmitted signal. A smaller conductor attenuates the signal more than a larger conductor. Typical propagation delay for a 1553B cable is 1.6 nanoseconds per foot. Thus, the end-to-end 100-foot bus (30m) would have a 160 nanosecond propagation delay, which is equal to the average rise time of a 1553B signal. According to MIL-HDBK-1553A, when a signal's propagation delay time is more than 50% of the rise or fall time, it is necessary to consider transmission line effects. This delay time is proportional to the distance propagated. Also, consideration must be given to the actual distance between the transmitter and receiver, and the individual waveform characteristics of the transmitters and receivers.
MIL-STD-1553B specifies that the longest stub length is 20 feet (6.1m) for transformer coupled stubs, but can be exceeded. With no stubs attached, the main bus looks like an infinite length transmission line with no disturbing reflections. When a stub is added, the bus is loaded and a mismatch occurs with resulting reflections. The degree of mismatch and signal distortion due to reflections are a function of the impedance presented by the stub and terminal input impedance. To minimize signal distortion, it is desirable that the stub maintain high impedance. This impedance is reflected back to the bus. At the same time, however, the impedance must be kept low so that adequate signal power will be delivered to the receiving end. Therefore, a tradeoff between these conflicting requirements is necessary to achieve the specified signal-to-noise ratio and system error rate performance (for more information, refer to MIL-HDBK-1553A).
Stubbing
Figure 9: Data bus interface using transformer coupling
Each terminal, RT, BC, or BM, is connected to the bus through a stub, formed of a length of cable of the same type as the bus itself. MIL-STD-1553B defines two ways of coupling these stubs to the bus: transformer coupled stubs and direct coupled stubs. Transformer coupled stubs are preferred for their fault tolerance and better matching to the impedance of the bus, and consequent reduction in reflections, etc. The appendix to MIL-STD-1553B (in section 10.5, Stubbing) states "The preferred method of stubbing is to use transformer coupled stubs… This method provides the benefits of DC isolation, increased common mode rejection, a doubling of effective stub impedance, and fault isolation for the entire stub and terminal. Direct coupled stubs… should be avoided if at all possible. Direct coupled stubs provide no DC isolation or common mode rejection for the terminal external to its subsystem. Further, any shorting fault between the subsystems [sic] internal isolation resistors (usually on a circuit board) and the main bus junction will cause failure of that entire bus. It can be expected that when the direct coupled stub length exceeds 1.6 feet (0.49 meters)], that it will begin to distort the main bus waveforms."
The use of transformer coupled stubs also provides improved protection for 1553 terminals against lightning strikes. Isolation is even more critical in new composite aircraft where the skin of the aircraft no longer provides an inherent Faraday shield as was the case with aluminum skinned aircraft.[11]
In a transformer coupled stub, the length of the stub cable should not exceed 20 feet (6.1m), but this may be exceeded "if installation requirements dictate." The coupling transformer has to have a turns ratio of 1:1.41 ± 3.0 percent. The resistors R both have to have a value of 0.75 Zo ± 2.0 percent, where Zo is the characteristic impedance of the bus at 1MHz.
Figure 10: Data bus interface using direct coupling
In a direct coupled stub, the length of stub cable should not exceed 1-foot, but again this may be exceeded if installation requirements dictate. The isolation resistors R have to have a fixed value of 55 ohms ± 2.0 percent.
Bus couplers
Stubs for RTs, the BC, or BMs, are generally connected to the bus through coupling boxes, which may provide a single or multiple stub connections. These provide the required shielding (≥ 75 percent) and, for transformer coupled stubs, contain the coupling transformers and isolation resistors. They have two external connectors through which the bus feeds, and one or more external connectors to which the stub or stubs connect. These stub connectors should not be terminated with matching resistors, but left open circuit when not used, with blanking caps where necessary. One of the bus connectors may be terminated where the bus coupler is physically at the end of the bus cable, i.e. it is not normally considered essential to have a length of bus cable between the last bus coupler and the termination resistor.
Cable termination
Both ends of the bus, whether it includes one coupler or a series of couplers connected together, must be terminated (in accordance with MIL-STD-1553B) with "a resistance, equal to the selected cable nominal characteristic impedance (Zo) ± 2.0 percent." This is typically 78ohms. The purpose of electrical termination is to minimize the effects of signal reflections that can cause waveform distortion. If terminations are not used, the communications signal can be compromised causing disruption or intermittent communications failures.
Connectors
The standard does not specify the connector types or how they should be wired, other than shielding requirements, etc. In lab environments concentric twinax bayonet style connectors are commonly used. These connectors are available in standard (BNC size), miniature and sub-miniature sizes. In military aircraft implementations, MIL-DTL-5015 and MIL-DTL-38999 circular connectors are generally used.
Evolution
STANAG 3910 (EFABus) mates a 1553 or 1773 link with additional high-speed 20Mbps buses, either optical or electrical. In the STANAG form, the 1553/1773 low-speed link serves as the control channel for the high speed link. In the EFABus Express (EfEx) form, the high-speed link acts as its own control channel. Either way, high and low-speed buses share the same addressing model and can communicate with each other.[12]
STANAG 7221 (E1553) expands a 1553 link with the capability to carry a 100Mbps signal on the same wire without interfering with old signaling.[13] The concept is similar to how ADSL avoids voice frequencies, but done at higher bandwidths.[14] In addition to 1553B, it also runs over coax, twisted pair, Power-Line Carrier, and existing ARINC 429 links.[15]
Similar systems
DIGIBUS (or Digibus, GAM-T-101) is the French counterpart to MIL-STD-1553. It is similar to MIL-STD-1553 in the same notion of Bus Controller, Remote Terminal, monitor, same transmission speed, but the difference is that DIGIBUS uses separate links for data and commands.[16]
GOST 26765.52-87 and its descendant GOST R 52070-2003 are the Soviet and Russian, respectively, equivalents of MIL-STD-1553B. The encoding, data rate, word structure, and control commands are fully identical.
GJV289A is the Chinese equivalent of MIL-STD-1553. Aircraft utilizing this system can reportedly use both Soviet (GOST bus)[17] and western (MIL-STD-1553 bus) weapons.[18]
H009 (also called MacAir H009), introduced by McDonnell in 1967, was one of the first avionics data buses. It is a dual redundant bus controlled by a Central Control Complex (CCC), with up to 16 Peripheral Units (PUs), synchronously communicating using a 1MHz clock. H009 was used in early F-15 fighter jets, but due its noise sensitivity and other reliability issues was replaced by MIL-STD-1553.
Development tools
When developing or troubleshooting for MIL-STD-1553, examination of the electronic signals is useful. A logic analyzer with protocol-decoding capability, also a bus analyzer or protocol analyzer, are useful tools to collect, analyze, decode and store the waveforms of the high-speed electronic signals.
Hardware
Intel M82553 Protocol Management Unit (PMU) using the CHMOS III technology. This device meets full bus interface protocol standard.[19]
In computer architecture, a bus is a communication system that transfers data between components inside a computer, or between computers. This expression covers all related hardware components and software, including communication protocols.
I2C (Inter-Integrated Circuit; pronounced as “eye-squared-see” or “eye-two-see”), alternatively known as I2C or IIC, is a synchronous, multi-controller/multi-target (historically termed as multi-master/multi-slave), single-ended, serial communication bus invented in 1982 by Philips Semiconductors. It is widely used for attaching lower-speed peripheral integrated circuits (ICs) to processors and microcontrollers in short-distance, intra-board communication.
Serial Peripheral Interface (SPI) is a de facto standard for synchronous serial communication, used primarily in embedded systems for short-distance wired communication between integrated circuits.
In electronics, electrical termination is the practice of ending a transmission line with a device that matches the characteristic impedance of the line. Termination prevents signals from reflecting off the end of the transmission line. Reflections at the ends of unterminated transmission lines cause distortion, which can produce ambiguous digital signal levels and misoperation of digital systems. Reflections in analog signal systems cause such effects as video ghosting, or power loss in radio transmitter transmission lines.
Secondary surveillance radar (SSR) is a radar system used in air traffic control (ATC), that unlike primary radar systems that measure the bearing and distance of targets using the detected reflections of radio signals, relies on targets equipped with a radar transponder, that reply to each interrogation signal by transmitting encoded data such as an identity code, the aircraft's altitude and further information depending on its chosen mode. SSR is based on the military identification friend or foe (IFF) technology originally developed during World War II; therefore, the two systems are still compatible. Monopulse secondary surveillance radar (MSSR), Mode S, TCAS and ADS-B are similar modern methods of secondary surveillance.
The air traffic control radar beacon system (ATCRBS) is a system used in air traffic control (ATC) to enhance surveillance radar monitoring and separation of air traffic. It consists of a rotating ground antenna and transponders in aircraft. The ground antenna sweeps a narrow vertical beam of microwaves around the airspace. When the beam strikes an aircraft, the transponder transmits a return signal back giving information such as altitude and the Squawk Code, a four digit code assigned to each aircraft that enters a region. Information about this aircraft is then entered into the system and subsequently added to the controller's screen to display this information when queried. This information can include flight number designation and altitude of the aircraft. ATCRBS assists air traffic control (ATC) surveillance radars by acquiring information about the aircraft being monitored, and providing this information to the radar controllers. The controllers can use the information to identify radar returns from aircraft and to distinguish those returns from ground clutter.
In computer networking, a reliable protocol is a communication protocol that notifies the sender whether or not the delivery of data to intended recipients was successful. Reliability is a synonym for assurance, which is the term used by the ITU and ATM Forum.
ARINC 429, the "Mark 33 Digital Information Transfer System (DITS)," is the ARINC technical standard for the predominant avionics data bus used on most higher-end commercial and transport aircraft. It defines the physical and electrical interfaces of a two-wire data bus and a data protocol to support an aircraft's avionics local area network.
Twinaxial cabling, or twinax, is a type of cable similar to coaxial cable, but with two inner conductors in a twisted pair instead of one. Due to cost efficiency it is becoming common in modern (2013) very-short-range high-speed differential signaling applications.
MIL-STD-1760 Aircraft/Store Electrical Interconnection System defines a standardized electrical interface between a military aircraft and its carriage stores. Carriage stores range from weapons, such as GBU-31 JDAM, to pods, such as AN/AAQ-14 LANTIRN, to drop tanks. Prior to adoption and widespread use of MIL-STD-1760, new store types were added to aircraft using dissimilar, proprietary interfaces. This greatly complicated the aircraft equipment used to control and monitor the store while it was attached to the aircraft: the stores management system, or SMS.
ARINC 708 is a specification for airborne pulse Doppler weather radar systems primarily found on commercial aircraft.
A bus coupler is a device which is used to couple one bus to the other without any interruption in power supply and without creating hazardous arcs. A bus coupler is a breaker used to couple two busbars to perform maintenance on other circuit breakers associated with that busbar.
MIL-STD-1397 standard was issued by the United States Department of Defense (DoD) to define "the requirements for the physical, functional and electrical characteristics of a standard I/O data interface for digital data." The MIL-STD-1397 classification types A, B and D apply specifically to the Naval Tactical Data System (NTDS).
The UNI/O bus is an asynchronous serial bus created by Microchip Technology for low speed communication in embedded systems. The bus uses a master/slave configuration, requiring one signal to pass data between devices. The first devices supporting the UNI/O bus were released in May 2008.
Bus monitoring is a term used in flight testing when capturing data from avionics buses and networks in data acquisition telemetry systems.
STANAG 3910High Speed Data Transmission Under STANAG 3838 or Fibre Optic Equivalent Control is a protocol defined in a NATO Standardization Agreement for the transfer of data, principally intended for use in avionic systems. STANAG 3910 allows a 1 Mb/s STANAG 3838 / MIL-STD-1553B / MoD Def Stan 00-18 Pt 2 (3838/1553B) data bus to be augmented with a 20 Mb/s high-speed (HS) bus, which is referred to in the standard as the HS channel: the 3838/1553B bus in an implementation of STANAG 3910 is then referred to as the low-speed (LS) channel. Either or both channels may be multiply redundant, and may use either electrical or optical media. Where the channels use redundant media, these are individually referred to as buses by the standard.
The ARC-210 is a family of radios for military aircraft that provides two-way, multi-mode voice and data communications over a 30 to 512+ MHz frequency range. It covers both Ultra High Frequency (UHF) and Very High Frequency (VHF) bands with AM, FM and SATCOM capabilities. The ARC-210 radio also includes embedded anti-jam waveforms, including Havequick and SINCGARS, and other data link and secure communications features, providing total battlefield interoperability and high-performance capabilities in the transfer of data, voice and imagery. It features a separate guard receiver for monitoring 121.5 and 243 MHz while simultaneously monitoring the active channel selected. Transmitter power ranges from 5 to 23 watts, depending on frequency and mode. The radios communicates with other avionics over a MIL-STD-1553 data bus.
The AN/AYK-14(V) is a family of computers for use in military weapons systems. It is a general-purpose 16-bit microprogrammed computer, intended for airborne vehicles and missions. Its modular design provides for common firmware and support software. It is still in use on Navy fleet aircraft including the F/A-18, and the AV-8B. The AN/AYK-14(V) family of systems is designed to meet MIL-E-5400 (airborne) requirements.
I3C, also known as SenseWire, is a specification to enable communication between computer chips by defining the electrical connection between the chips and signaling patterns to be used. Short for "Improved Inter Integrated Circuit", the standard defines the electrical connection between the chips to be a two wire, shared (multidrop), serial data bus, one wire (SCL) being used as a clock to define the sampling times, the other wire (SDA) being used as a data line whose voltage can be sampled. The standard defines a signalling protocol in which multiple chips can control communication and thereby act as the bus controller.
The ARINC 629 computer bus was introduced in May 1995 and is used on aircraft such as the Boeing 777, Airbus A330 and Airbus A340 as well as the Airbus A320 series.
↑ Avionic Systems Standardisation Committee, Avionic Data Transmission Interface Systems Part 2: Serial, Time Division Command/Response Multiplex Data Bus Standard, Def Stan 00-18, Issue 2, 28 September 1990
↑ George Marsh, Typhoon: Europe’s Finest, Avionics Today, June 1st 2003.
↑ AECMA Working Group C2-GT9, High Speed Data Transmission Under STANAG 3838 or Fibre Optic Equivalent Control, prEN3910-001, Ed P1, ASD-STAN, 1/31/1996.
↑ Ormsby, John, Editor, "New Product Focus: Components: The M82553 Protocol Management Unit Offers Military Designers A Single Device For All Modes Of Operation", Intel Corporation, Microcomputer Solutions, January/February 1988, page 12
External links
MIL-STD-1553, Digital Time Division Command/Response Multiplex Data Bus. United States Department of Defense, February 2018.
MIL-STD-1773, Fiber Optics Mechanization of an Aircraft Internal Time Division Command/Response Multiplex Data Bus. United States Department of Defense, October 1989.
MIL-STD-1553 Tutorial from AIM, Avionics Databus Solutions, Interface Boards for MIL-STD-1553/1760
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