CN109115263B - Spacecraft measurement system - Google Patents
Spacecraft measurement system Download PDFInfo
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- CN109115263B CN109115263B CN201810521376.5A CN201810521376A CN109115263B CN 109115263 B CN109115263 B CN 109115263B CN 201810521376 A CN201810521376 A CN 201810521376A CN 109115263 B CN109115263 B CN 109115263B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Abstract
The invention discloses a spacecraft measurement system which comprises a processor and a plurality of detection devices. Wherein the processor and the plurality of detection devices are connected in series with each other through a cable to form a ring network structure, so that signals transmitted by the processor and any one of the plurality of detection devices can be received by the rest of the devices configured in the ring network structure. The processor is used for acquiring signals of a flight stage where the vehicle is located and sending signal acquisition instructions to the plurality of detection devices according to the flight stage, wherein the signal acquisition instructions comprise address information corresponding to at least one of the plurality of detection devices. The plurality of detection devices receive the signal acquisition instruction, and the detection devices matched with the address information return detected state parameter signals to the processor. The spacecraft measurement system provided by the invention can conveniently expand the measurement points and replace the fault cable, and greatly improves the universality of the measurement system.
Description
Technical Field
The invention relates to the technical field of measurement of a carrier, in particular to a spacecraft measurement system.
Background
To ensure that a vehicle (which may be a launch vehicle or a missile, for example) is working properly, various parameters of its flight need to be detected. For example, the parameters may include a charge parameter and a non-charge parameter. The non-electric parameters include temperature, pressure, vibration, noise and the like. In the detection of the non-electricity quantity parameter, an electric measuring sensor is generally adopted to sense the non-electricity quantity parameter and convert the non-electricity quantity parameter into a standard voltage signal of 0-5V. The carrier generally adopts a hierarchical and nearby mining and editing system architecture for collecting non-electric parameters. Namely, each sub-stage is provided with a converter and an encoder for respectively supplying power and encoding parameters for each sensor of the stage. And the acquired and compiled non-electric parameters are wirelessly downloaded through the telemetering equipment.
To simplify wiring, sensors typically use an unbalanced single-ended signal output mode, i.e., the secondary power supply and the non-charge signal are common ground. For example, the converter mining and editing device can simultaneously have secondary power output and signal mining and editing functions, and all the sensors are electrically connected with the converter through a cable network.
However, the existing vehicle measurement system is not flexible in architecture, and for different rockets, the cable network of the measurement system often needs to be redesigned and arranged, so that the development period is prolonged, and the production cost is increased.
In addition, when the existing measurement system samples in the takeoff phase and the acceleration phase of the vehicle, the sampling frequency and the signal type are not distinguished according to the flight phase of the vehicle, so that the sampling signal is too much or too complicated, the accurate measurement of the state of the vehicle is not facilitated, and even the interference of the sampling parameter signal may be caused.
Disclosure of Invention
In view of the above technical problems in the related art, the present invention provides a measurement system for an aerospace vehicle. The measurement system is flexible in structure and convenient to maintain, and can conveniently expand measurement points and replace fault cables.
The invention provides a spacecraft measurement system. The space vehicle measurement system comprises a processor and a plurality of detection devices; wherein the processor and the plurality of detection devices are connected in series with each other through a cable to form a ring-shaped mesh structure, so that when the communication of the ring-shaped mesh structure is normal, the signals transmitted by the processor and any one of the plurality of detection devices can be received by the rest of the equipment configured in the ring-shaped mesh structure; the system comprises a plurality of detection devices, a processor and a control unit, wherein the detection devices are used for detecting state parameter signals of a carrier, the processor is used for selecting at least one of the type and the frequency of a signal acquisition instruction sent to the detection devices according to the flight phase of the carrier, and the signal acquisition instruction comprises address information corresponding to at least one of the detection devices; the plurality of detection devices receive the signal acquisition instruction, and the detection device matched with the address information returns the detected state parameter signal to the processor.
In one embodiment, the flight phases include a takeoff phase and an acceleration phase; wherein the signal acquisition instructions comprise signals for acquiring parameter signals for engine temperature and pressure of the vehicle, signals for acquiring acceleration and overload parameters of the vehicle when the vehicle is in a takeoff phase; the frequency of the signal acquisition instruction sent by the processor is reduced along with the time in the takeoff stage after the ignition of the carrier; and when the vehicle is in an acceleration phase, the signal acquisition instructions comprise parameters for acquiring speed, vibration and noise for the vehicle.
In one embodiment, when the carrier is in a takeoff phase, the relation between the sampling frequency f of the processor sending the signal acquisition instruction and the time t satisfies the following conditions: a (1/t)n+ b, where f is positive number, a is 0-1, n is 0-1, t is 0-1, and b is 100.
In one embodiment, the sampling frequency of the signal acquisition instructions sent by the processor increases and then decreases over time while the vehicle is in the acceleration phase.
In one embodiment, the detection device comprises a sensor and an analog-to-digital converter; wherein the sensor is used for detecting a state parameter signal of the aircraft, and the analog-to-digital converter is used for converting the state parameter signal into a digital quantity.
In some embodiments, the processor includes a primary transceiver and a secondary transceiver disposed at two connection ports thereof; the other end of the main transceiver and the other end of the auxiliary transceiver are respectively connected to the ring network structure; whereby the signal transmission direction of the ring network structure comprises a first direction from the primary transceiver to the auxiliary transceiver and a second direction from the auxiliary transceiver to the primary transceiver; the master transceiver is used for sending a signal acquisition instruction to the plurality of detection devices along the first direction; and the auxiliary transceiver sends a signal acquisition instruction to the plurality of detection devices along the second direction when the auxiliary transceiver cannot receive the signal acquisition instruction sent by the main transceiver.
In one embodiment, the plurality of detection devices includes at least a first detection device and a second detection device, the cable includes a first length of cable, a second length of cable, and a third length of cable; one interface of the first detection device is connected to one interface of the second detection device through a first cable, the other interface of the second detection device is connected to one interface of the processor through a second cable, and the other interface of the processor is connected to the other interface of the first detection device through a third cable.
In one embodiment, the interfaces of the first detection device, the second detection device and the processor are provided by three hubs, respectively.
In one embodiment, the three hubs are integrated with the first detection device, the second detection device, and the processor, respectively.
In one embodiment, the processor is a commutation editor.
In one embodiment, the state parameter signal comprises a non-electrical quantity signal comprising at least one of temperature, pressure, vibration and noise.
The measuring system of the space vehicle has at least one of the following technical effects:
(1) according to the spacecraft measurement system, different parameter signals are sampled at different flight stages of the spacecraft, and the sampling frequency of parameters in the flight of the spacecraft is changed, so that the sampling pertinence of the measurement system is increased, and the sampling speed and the sampling effectiveness of the parameters are improved.
(2) According to the spacecraft measurement system, the annular mesh structure is formed between the detection device and the processor, so that a signal sent by any equipment can be received by other equipment, and the reliability of the spacecraft measurement system is improved.
(3) In the space vehicle measuring system, the transceivers are respectively arranged at the two connecting ports of the processor, so that on one hand, when the annular mesh structure is broken, the detecting signals of all (or most) detecting devices can still be acquired; on the other hand, the communication condition of the measuring system can be detected in real time, and fault maintenance can be carried out more conveniently when the annular mesh structure is broken.
(4) According to the space vehicle measuring system, the signals sent by the transceiver comprise the address information of the corresponding sensor, and the sensor sends the state parameters to the transceiver under the condition that the address information is matched with the sensor, so that data resources can be saved, and cross interference among the signals can be avoided.
(5) According to the space carrier measuring system, the processor and each detection device are respectively integrated with the concentrator, so that all devices can be conveniently connected, and the maintenance efficiency of the system is improved.
Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic diagram of a measurement system according to an embodiment of the invention.
Fig. 2 is a schematic structural diagram of a detection apparatus according to an embodiment of the invention.
FIG. 3a is a schematic diagram of a processor, a detection device structure, and electrical connections to cables in a measurement system according to an embodiment of the present invention.
FIG. 3b is a schematic diagram of a measurement system with multiple processors and detection devices spaced apart according to an embodiment of the invention.
Fig. 4 is a schematic diagram of a network node type connection structure of the measurement system of the present invention.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there are additional elements between the two elements. Furthermore, terms such as "first", "second", and the like are also used to describe various elements, regions, sections, and the like, and should not be taken as limiting. Like terms refer to like elements throughout the description.
Typical vehicle measurement systems typically employ a tree-like connection structure. For example, each sensor or sensor assembly is separately connected to a main cable that is connected to a connection port of the converter codec. Namely, one end of the main cable is respectively connected with one end of each sensor or sensor component through a plurality of branch cables, and the other end of each sensor or sensor component is connected with a part to be detected of the carrier.
However, such a tree-shaped vehicle measurement system may have the following drawbacks, for example:
one is that the electrical performance of the system is poor. For example, a conventional vehicle non-electrical measurement system belongs to an analog signal system, and only a signal acquired and coded by an encoder belongs to a digital transmission signal. The vehicle inevitably faces a complex electromagnetic environment during flight. Therefore, if the signal before entering the converter adopt-editor is an analog signal, the signal is likely to be distorted by receiving the interference of the electromagnetic environment. That is, in a complex electromagnetic loop, the reliability of an analog signal is slightly higher than that of a digital signal.
Secondly, the system has inflexible structure and low modularization degree. For example, in the development of a carrier such as a launch vehicle, the non-electrical parameters of almost every launch vehicle may be different, particularly at the early stages of development. If a conventional non-electricity measuring system is used, the cable network needs to be rearranged and designed for each generation. For example, recalculating the length of each drop cable and also requiring the re-production, re-production of the final assembly process file may result in excessive cost and lead time for the initial stages of carrier development.
And thirdly, when the vehicle measuring system has problems, the maintenance is difficult. Often, a failure of the carrier electrical system occurs mostly in the cable. If the fault occurs in the final assembly factory and the testing link after the final assembly, the model development progress is delayed due to the difficulty in assembling and disassembling the carrier and the fact that tools such as soldering irons are not allowed to be used.
Aiming at the problem of the existing vehicle measuring system, the invention provides a system architecture which is similar to the internet and adopts a network as a wire, thereby enhancing the electrical performance of the system. And measuring points can be increased or decreased at any position in the system framework, and meanwhile, when the measuring system breaks down, the broken cable can be conveniently replaced, so that the maintainability of the non-electric quantity measuring system is improved. In addition, due to the measuring system, the sampling data and the sampling frequency are distinguished according to the stage of the carrier, so that the operating efficiency of the measuring system is improved.
The invention provides a spacecraft measurement system. Referring to fig. 1, the measurement system comprises a processor 1 and a plurality of detection devices 2. Wherein the processor 1 and the plurality of detection devices 2 are connected in series with each other through cables a, b, c, d, e to form a ring-shaped mesh structure, so that when the communication of the ring-shaped mesh structure is normal, the signals transmitted by the processor 1 and any one of the plurality of detection devices 2 can be received by the rest of the devices configured in the ring-shaped mesh structure. Wherein, the plurality of detection devices 2 are used for detecting the state parameter signals of the aircraft, and the processor 1 is used for acquiring the flight phase of the vehicle, and selecting at least one of the type and the frequency of sending the signal acquisition instructions to the plurality of detection devices 2 according to the flight phase of the vehicle. Wherein the signal acquisition command includes address information corresponding to at least one of the plurality of detection devices 2. The plurality of detection means 2 receive the signal acquisition instruction, and the detection means 2 matching the address information returns the detected state parameter signal to the processor 1. According to the vehicle measuring system, on one hand, the processor and the plurality of detecting devices are connected in an annular net shape, so that the increase of measuring points and the replacement of fault cables are simple and easy, the reliability and the maintainability of the measuring system are improved, and the production cost of the vehicle measuring system is also reduced; on the other hand, the efficiency of the measuring system is improved by pertinently selecting the type and the frequency of the signal acquisition command according to the flight stage of the carrier.
For example, the flight phase in which the vehicle is located may include a takeoff phase and an acceleration phase. Wherein the takeoff phase may be within 1 second from the time of rocket firing. At this time, for example, the rocket has flown about several kilometers. The acceleration phase may be, for example, from 1 second to several minutes (e.g., 5 minutes), at which time the rocket has flown approximately several hundred kilometers. Typically, the short time during which the rocket fires is the most dangerous phase of the rocket launch. At this time, the flying speed of the carrier rocket is not great, but the inside and the attached part of the engineNear-field devices experience severe changes from low to very high temperatures, and many components are subject to large accelerations and overloads. The success of the launch depends largely on the challenge of the engine and other components to withstand the temperatures, pressures, or accelerations and overloads at this stage. Therefore, detection of temperature, pressure, acceleration, overload, etc. of the engine and associated equipment during takeoff is critical. For example, the frequency of the signals obtained by the processor to obtain the parameters of the temperature, the pressure, the acceleration and the overload of the engine and the related equipment can be more than 1000, namely, the processor can obtain the parameter signals of the temperature, the pressure, the acceleration and the overload of the vehicle of the engine and the related equipment for more than 1000 times in 1 second of the takeoff period. For example, the frequency at which the processor obtains engine temperature, pressure, acceleration, and overload parameters may decrease over time from the time of ignition. For example, the processor sends a signal acquisition command to acquire the frequency f of the engine temperature, pressure and vehicle acceleration and overload parameters in relation to the time t satisfying: a (1/t)n+ b, where f is positive number, a is not less than 0 and not more than 1, n is not less than 0 and not more than 1, t is not less than 0 and not more than 1, and b is not less than 103. For example, 0.4 ≦ a ≦ 0.8,0.2 ≦ n ≦ 0.6, so that the suitability of the acquisition of the parameter signal for the acceleration phase of the vehicle and the pertinence of the state estimation can be further improved.
The rocket has certain reliability in the later accelerating propulsion section because the engine and peripheral equipment are tested in the initial ignition takeoff stage. Therefore, the speed and flight stability of the launch vehicle over time are more important factors in ensuring launch success. At this time, it is possible to detect the temperature, pressure, acceleration, and overload parameters of the engine and nearby equipment at a relatively low frequency, and to detect the flying speed, vibration, noise, and the like of the vehicle at a higher frequency. In addition, when the vehicle is in the early stage of the acceleration phase, the sampling frequency of the parameters (namely, the frequency of the processor sending the signal acquisition command to the detection device) can be gradually increased; and the sampling frequency reaches the maximum value in the middle period of the acceleration stage; when the carrier is in the terminal stage of the acceleration stage, the probability of successful flight of the rocket continuously rises along with the continuous depletion of the liquid or solid fuel, and the sampling frequency of parameters such as the flight speed, the vibration, the noise and the like of the carrier can be linearly or nonlinearly reduced. For example, at the end of the acceleration phase of the vehicle, the sampling frequency of the parameters of the vehicle flight speed, vibration and noise may be accelerated down.
In this embodiment, when the rocket is in the takeoff phase, the processor may also send a first type of signal acquisition instruction at intervals, which is intended to acquire parameters such as engine temperature, pressure, and vehicle acceleration and overload, and a second type of signal acquisition instruction, which is intended to acquire parameters such as speed, vibration, and noise of the rocket. For example, at the time of rocket firing takeoff, the ratio of the frequency of the first type of signal to the transmission frequency of the second type of signal may be between 10: 1 to 5: 1. For example, from the moment of rocket firing to the last moment of the takeoff phase referred to in the present invention, the above-mentioned transmission frequency ratio may be from 10: 1 to 5: 1 is gradually reduced to 1: about 1. During the acceleration phase of the rocket, the ratio of the transmission frequency of the first type of signal to the transmission frequency of the second type of signal may be from 1: 1 is gradually reduced to 1: 4, and after that, gradually again up to 1: about 1. The processor of the embodiment of the invention can improve the efficiency of the measuring system and avoid unnecessary signal transmission in the measuring system by sending two types of signal acquisition instructions at intervals and adjusting the sending frequency ratio of the two types of signal acquisition instructions according to the change of the time after ignition of the rocket and the like, thereby better judging the working state of the rocket.
For example, the measurement system may include a timer. For example, the timer may be provided within the processor. The timer can thus acquire the firing signal, for example, when the rocket is fired, and calculate the time from the firing moment of the rocket. Since the rocket can be accelerated to a high speed shortly after ignition, the timer should have sufficient accuracy so that the transceiver can adjust the type and frequency of the signal acquisition commands sent to the detection means when the spacecraft is in different phases of flight. It is understood that the different types of signal acquisition instructions referred to in the present invention refer to signal acquisition instructions containing different address information, so that when a plurality of detection devices acquire signal acquisition instructions having different address information, the detection device matching the address information returns a measured parameter signal to the processor.
In addition, the processor of the measurement system may also determine the flight phase of the spacecraft according to the speed, acceleration, overload, or other signals detected by the detection device, so as to select the type of the transmission signal acquisition instruction and the frequency of the transmission signal acquisition instruction according to the type of the transmission signal acquisition instruction. In particular, if, for example, the rocket is in the takeoff phase, the transmitted signal acquisition commands are mainly directed to the temperature and pressure, acceleration and overload, etc. of the engine and the nearby equipment. For example, if the rocket is in an acceleration phase, the transmitted signal acquisition command is mainly used for acquiring parameters such as speed, vibration and noise of the engine. And when the rocket is in an acceleration stage, the processor can enable the frequency of sending the signal to acquire the instruction to be continuously increased firstly and then be continuously reduced according to the size of the parameter. As mentioned above, the processor may send the signal acquisition commands for various types of parameters at intervals during the takeoff phase and the accelerated flight phase of the vehicle, but the sending frequency of the signal acquisition commands of different types may be different, and the processor may also change the sending frequency ratio of the signal acquisition commands of different types according to the time lapse from the ignition time.
With continued reference to fig. 1, for example, the processor 1 may have at least two connection ports a1, a2, and each detection device also has at least two connection ports a1, a2, such that the ports are connected in series by cables a-e, forming a circular mesh connection of the devices. For example, as shown in fig. 1, when a plurality of detection apparatuses 2 and processors 1 are connected to each other, a port a1 of one of the apparatuses is connected to a port a2 of the other apparatus through a cable, so that the plurality of detection apparatuses and processors form the above-described ring network structure.
For example, when the vehicle measurement system includes two detection devices and one processor, three cables may be used to connect the three devices. In particular, one of the connection ports of the processor is connected to one of the connection ports of one of the detection devices by a cable, the other connection port of the detection device is connected to one of the ports of the other detection device by a second cable, and the other port of the other detection device is connected to the other port of the processor by a third cable. So that the three cables and the three devices together form an annular network. For example, a node on a cable network connected to each device in a ring network structure forming a ring connection, so that additional detection devices can be targeted into the ring network when additional measurement nodes are needed for the measurement system. For example, as previously described, each additional device may include at least ports a1 and a2, such that the additional devices may be connected to other devices by cables. For example, as shown in fig. 1, a1 of one of the devices is connected to a2 of the other device, so that these additional devices also constitute nodes in the ring connection network.
It is understood that if the number of processors and the number of detection devices are further increased, the connection modes according to the above embodiments may be connected to each other, so as to form a ring network measurement system (e.g., a measurement system as shown in fig. 1) with more devices (nodes) and larger scale. For example, in some embodiments, a ring network architecture may support more than 30 sensor nodes, with an intra-ring data transfer rate of, for example, not less than 10 Mbps. For example, the length of the loop formed by the cable may be no less than 500 meters to meet the distance requirement of the measuring device from the engine when the engine is in test run.
For example, the processor 1 and each detection apparatus 2 may be connected to each other using a HUB (HUB) so that signals transmitted by any one device may be received by other devices in the ring mesh. For example, the processor 1 and the plurality of detection devices 2 may be connected by other connecting elements, but the connection between the processor 1 and the plurality of detection devices 2 is based on the principle that the signal transmitted by each node device in the ring-shaped mesh structure can be received by the other devices.
As described above, when the communication of the ring mesh is normal, the signal transmitted by any node device in the ring mesh can be received by other devices. However, the signal acquisition instruction sent by the processor 1 includes address information corresponding to at least one of the detection devices 2, so that although the plurality of detection devices 2 all receive the signal acquisition instruction, only the detection device 2 matched with the address information in the signal acquisition instruction returns a corresponding parameter signal, thereby not only improving the efficiency of signal transmission, but also avoiding mutual interference between signals.
Referring to fig. 2, in one embodiment, for example, the detection means comprises a sensor 21 and an analog-to-digital converter 22. Wherein the sensor 21 is adapted to detect a state parameter signal of the aircraft and the analog-to-digital converter 22 is adapted to convert the state parameter signal into a digital quantity. The embodiment of the invention further improves the reliability of signal transmission in a complex electromagnetic environment by converting the detection signal of the sensor into a digital quantity.
It should be noted that the sensors of different models detect different signals, and for the sensor whose detected value is a digital value, it is not necessary to provide an analog-to-digital converter.
For example, the plurality of detection devices may be sensors or sensor assemblies. These sensors may include temperature sensors, pressure sensors, noise sensors, overload sensors, acceleration sensors, and the like. For example, the sensors may be provided at positions to be measured of the respective cabin.
Referring to fig. 3a, for example, in one embodiment, the processor 1 includes a primary transceiver 11 and a secondary transceiver 12, which are respectively provided at two connection ports thereof. The other end of the main transceiver 11 and the other end of the auxiliary transceiver 12 are respectively connected to the ring-shaped mesh structure. Two ports of the processor 1 are respectively accessed to the ring network structure through a main transceiver 11 and an auxiliary transceiver 12; so that the signal transmission direction of the ring network structure includes a first direction from the main transceiver 11 to the auxiliary transceiver 12 and a second direction from the auxiliary transceiver 12 to the main transceiver 11. The master transceiver 11 is configured to send a signal acquisition command to the plurality of detection devices 2 along the first direction. The auxiliary transceiver 12 sends a signal acquisition command to the plurality of detection devices 2 along the second direction when the signal acquisition command sent by the main transceiver 11 cannot be received. According to the embodiment of the invention, the main transceiver and the auxiliary transceiver are respectively arranged at the two ports of the processor, so that the communication state of the annular network can be better confirmed, and when the auxiliary transceiver cannot receive the signal of the main transceiver, the signal acquisition instruction is sent from the opposite direction, so that when the annular network is disconnected, most of equipment in the annular mesh structure can still be subjected to parameter acquisition, and the reliability of the detection system is improved.
In this embodiment, if the signal transmitted in the first direction by the primary transceiver 11 cannot be received by the secondary transceiver 12, it is roughly determined that there is a communication failure in the first direction. The failure may be caused by the cables in the looped mesh structure or by a failure of the auxiliary transceiver itself. If the fault is caused by a broken cable, by transmitting a signal acquisition command in the second direction from the auxiliary transceiver 12 when the auxiliary transceiver 12 cannot receive the signal acquisition command of the main transceiver, it is possible to ensure that the signal acquisition command reaches the detection means provided between the auxiliary transceiver and the broken point of the faulty cable in the second direction. Furthermore, a signal acquisition command sent in a first direction by the primary transceiver can reach a detection device arranged between the primary transceiver and the broken cable point. Therefore, the annular network structure can realize that the parameters of all detection devices can be obtained even in the case of a fault cable in the annular mesh structure. In addition, if the auxiliary transceiver 12 fails, for example, the transmission and reception of the auxiliary transceiver 12 are abnormal, the auxiliary transceiver 12 cannot receive the signal of the main transceiver 11 and cannot transmit the signal, so that the main transceiver 11 cannot receive the signal of the auxiliary transceiver 12. The signal acquisition command sent in the first direction by the master transceiver 11 can still reach all the detection devices in the ring network structure. Therefore, when one of the main transceiver and the auxiliary transceiver has abnormal transceiving signals, the signal acquisition command transmitted in the first direction by the main transceiver or the signal acquisition command transmitted in the second direction by the auxiliary transceiver can still be ensured to reach each detection device between the main transceiver and the auxiliary transceiver by transmitting the signal acquisition command in the two directions, so that the redundancy capability of the vehicle measuring system is remarkably improved.
With continued reference to fig. 3a, the detection device may receive a signal acquisition command from either the primary transceiver 11 or the auxiliary transceiver 12 via the transceiver 23, and the detection device is powered via the power connection 24. The power line at the upper end of fig. 3 and the signal line at the lower end of fig. 3 are separated from each other only for functional illustration. For example, the power line and the signal line may be located within the same cable.
Referring to fig. 3b, in this embodiment, a plurality of processors 1 may be arranged at intervals in a ring network structure, for example. That is, the plurality of processors 1 and the plurality of detection devices 2 are disposed at intervals from each other. Wherein, at least two connection ports of any processor are respectively provided with a main transceiver and an auxiliary transceiver. The primary transceivers of these processors may be numbered in sequence as SN1-SN4, and likewise, the secondary transceivers may be numbered correspondingly in sequence as SN1 '-SN 4'. In order to make the location of the primary and secondary transceivers in the ring network clear, the primary and secondary transceivers of the same processor may be numbered correspondingly, such as primary transceiver SN1 and secondary transceiver SN 1', and both belong to the same processor. The numbering of the other primary and secondary transceivers relative to each other may be analogized.
A primary transceiver (e.g., SN1) in the ring network may send a signal acquisition command in the first direction S1, and if the corresponding secondary transceiver SN1 'does not receive the signal acquisition command, the location of the failure point may be determined according to whether the transceiver SN 4' that is numbered away from the primary transceiver receives the signal acquisition command. For example, in the first direction S1, the signal transmitted by the main transceiver SN1 cannot be received by the auxiliary transceiver SN1 ', but can be received by the auxiliary transceiver SN 4', and it can be judged that a communication failure of the ring network structure occurs in a portion between the auxiliary transceiver SN1 'and the transceiver SN 4' adjacent thereto. By sequentially checking the signal acquisition command sent by the master transceiver SN1 and the numbers of the transceivers that received and did not receive the command (e.g., sequentially checking SN4 ', SN3 ' SN2 '), it is possible to quickly determine where the fault point is located, and accordingly, operations such as cable replacement or other fault point repair can be performed.
For example, when the master transceiver SN1 transmits a signal acquisition command in the first direction S1, if none of SN1 ', SN 4', SN3 'receives the signal acquisition command transmitted by the master transceiver SN1 and SN 2' acquires the command, a communication failure point of the ring network structure may occur at a portion thereof located at SN1 '- -SN 4' - -SN3 '- -SN 2'. Thereafter, the communication condition of the ring-shaped mesh structure can be further judged by sending a signal acquisition command in the S2 direction from the SN 1'. For example, if the SN3 acquires the signal and the SN2 does not, a point of failure may occur with a cable having a ring network between the SNs 3-SN 2. Likewise, if the SN4 acquires the signal and the SN3 does not acquire the signal, it is considered that the signal reception of the SN3 master transceiver fails, considering that there is less possibility that the cable between the SN 2-SN 3 and the cable between the SN 3-SN 4 are disconnected at the same time. According to the embodiment of the invention, the fault point can be quickly positioned by configuring the plurality of processors in the electric quantity measuring system, so that the quick maintenance of the ring network structure is completed.
It should be noted that the acquisition of the signal may be performed by the primary and secondary transceivers of the multiple processors in the ring network structure in turn, so that the fault point of the ring network structure may be more accurately located, and the related signal sending and fault locating methods all belong to the protection scope of the present application. Furthermore, multiple processors may be redundant to each other, further improving the adaptability of the vehicle measurement system.
In one embodiment, for example, an aerospace vehicle measurement system includes a first detection device, a second detection device, and a processor. For example, the interfaces of the first detection device, the second detection device and the processor are provided by three hubs, respectively. Also, if the detection system includes a plurality of detection devices and processors, the number of hubs may be equal to and in one-to-one correspondence with the sum of the number of detection devices and processors. These hubs may be provided as separate connectors or may be integrated with the corresponding detection device or processor. And preferably, the concentrator is respectively integrated with the corresponding detection device and the processor, so that the detection system is more compact and has better mechanical property.
In one embodiment, the processor is configured to perform isochronous control on the detection apparatus.
For example, in the vehicle measurement system of the invention, the physical layer of the network bus formed by the cable is IEEE 802.3 Ethernet 100BASE-TX, the MAC layer conforms to GB/T15629.3, and the layers above the MAC layer adopt the Ethernet POWER RLINK protocol conforming to GB/T27960. The network formed by the cable network adopts a shared channel based on a 2-type hub and uses a half-duplex isochronous transmission mode.
Referring to fig. 4, for example, in some of the above embodiments, the processor is a commutation sampler. The commutation editor can be used as a MN (management node) of a cable network, and each sensor is used as a CN (controlled node). In a ring cable network architecture, all devices (including the flow mining editor and sensors) are connected to each other through a HUB. The MN adopts isochronous synchronous control to the CN. For isochronous synchronization control, see GB/T27960 for more detail.
In the schematic diagram of the measurement system shown in fig. 4, the MN sends an access command, which is propagated in the network and can be received by all CNs. Similarly, the send command sent by any CN may also be received by all the other devices. That is, the access command (PReq) of the MN and the return order (PRes) of each CN are broadcast in the network, and the access command transmitted from the MN distinguishes each CN by the MAC address. Each CN monitors the network status in real time, and sends a number return command (for example, the number return command may be a parameter value measured by a sensor) after receiving a command matching the MAC address. The embodiment of the invention adopts the network mode of MN and CN to ensure that the flexibility of the measuring system architecture is high, thereby improving the adaptability of the measuring system.
The above-described embodiments of the present invention may be combined with each other with corresponding technical effects.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (9)
1. An aerospace vehicle measurement system, comprising a processor and a plurality of detection devices; wherein the processor and the plurality of detection devices are connected in series with each other through a cable to form a ring network structure, so that when the communication of the ring network structure is normal, the signals transmitted by the processor and any one of the plurality of detection devices can be received by the rest of the equipment configured in the ring network structure;
the system comprises a plurality of detection devices, a processor and a control unit, wherein the detection devices are used for detecting state parameter signals of a vehicle, the processor is used for acquiring signals related to a flight phase of the vehicle, and selecting at least one of the type and the frequency of a signal acquisition command sent to the detection devices according to the flight phase of the vehicle, and the signal acquisition command comprises address information corresponding to at least one of the detection devices;
the plurality of detection devices receive the signal acquisition instruction, and the detection device matched with the address information returns a detected state parameter signal to the processor;
the processor comprises a main transceiver and an auxiliary transceiver which are respectively arranged at two connecting ports of the processor; the other end of the main transceiver and the other end of the auxiliary transceiver are respectively connected with the annular network structure; whereby the signal transmission direction of the ring network structure comprises a first direction from the primary transceiver to the auxiliary transceiver and a second direction from the auxiliary transceiver to the primary transceiver;
the master transceiver is used for sending signal acquisition instructions to the plurality of detection devices along the first direction;
the auxiliary transceiver sends a signal acquisition instruction to the plurality of detection devices along the second direction when the auxiliary transceiver cannot receive the signal acquisition instruction sent by the main transceiver;
when one of the main transceiver and the auxiliary transceiver has abnormal transceiving signals, the signal acquisition command transmitted by the main transceiver in the first direction or the signal acquisition command transmitted by the auxiliary transceiver in the second direction can still be ensured to reach each detection device between the main transceiver and the auxiliary transceiver by transmitting the signal acquisition command in two directions.
2. An aerospace vehicle measurement system according to claim 1, wherein the flight phases include a takeoff phase and an acceleration phase;
wherein the signal acquisition instructions comprise signals for acquiring vehicle engine temperature and pressure parameters, signals for acquiring vehicle acceleration and overload parameters when the vehicle is in a takeoff phase; the frequency of the signal acquisition instruction sent by the processor is reduced along with the time in the takeoff stage after the ignition of the carrier; and
the signal acquisition instructions include signals for acquiring speed, vibration and noise parameters for the vehicle when the vehicle is in an acceleration phase.
3. An aerospace vehicle measurement system according to claim 2, wherein the sampling frequency/at which the processor sends signal acquisition instructions during the takeoff phase of the vehicle is related to time t by: a (1/t)n+ b, where f is positive number, a is greater than or equal to 0 and less than or equal to 1, n is greater than or equal to 0 and less than or equal to 1, t is greater than or equal to 0 and less than or equal to 1, and b is greater than or equal to 100.
4. An aerospace vehicle measurement system according to claim 2, wherein the frequency of signal acquisition instructions sent by the processor increases and then decreases over time while the vehicle is in the acceleration phase.
5. An aerospace vehicle measurement system according to claim 1, wherein the detection means comprises a sensor and an analog to digital converter;
wherein the sensor is adapted to detect a status parameter signal of the vehicle and the analog-to-digital converter is adapted to convert the status parameter signal into a digital quantity.
6. An airborne vehicle measurement system according to claim 1 wherein the plurality of detection devices includes a first detection device and a second detection device, the cable including a first length of cable, a second length of cable and a third length of cable;
one interface of the first detection device is connected to one interface of the second detection device through a first cable, the other interface of the second detection device is connected to one interface of the processor through a second cable, and the other interface of the processor is connected to the other interface of the first detection device through a third cable.
7. An airborne vehicle measurement system according to claim 6 wherein the interfaces of the first detection device, the second detection device and the processor are provided by three hubs respectively.
8. An airborne vehicle measurement system according to claim 7 wherein the three hubs are of unitary construction with the first detection device, the second detection device and the processor respectively.
9. An aerospace vehicle measurement system according to any one of claims 1-5, wherein the processor is a commutating editor.
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| CN202010835082.7A CN112286087B (en) | 2018-05-28 | 2018-05-28 | Carrier rocket measurement system |
| CN201810521376.5A CN109115263B (en) | 2018-05-28 | 2018-05-28 | Spacecraft measurement system |
| CN202010835063.4A CN112033458B (en) | 2018-05-28 | 2018-05-28 | Rocket measurement system and fault detection method |
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| CN201810521376.5A CN109115263B (en) | 2018-05-28 | 2018-05-28 | Spacecraft measurement system |
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| CN112033458B (en) | 2022-06-17 |
| CN112033458A (en) | 2020-12-04 |
| CN112286087A (en) | 2021-01-29 |
| CN109115263A (en) | 2019-01-01 |
| CN112286087B (en) | 2021-09-14 |
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