CN109115263A - Space launch vehicle measuring system - Google Patents
Space launch vehicle measuring system Download PDFInfo
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- CN109115263A CN109115263A CN201810521376.5A CN201810521376A CN109115263A CN 109115263 A CN109115263 A CN 109115263A CN 201810521376 A CN201810521376 A CN 201810521376A CN 109115263 A CN109115263 A CN 109115263A
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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
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Abstract
The invention discloses a kind of space launch vehicle measuring systems, including processor and multiple detection devices.It is wherein one another in series between processor and multiple detection devices by cable to form ring mesh structure, so that remaining equipment that the signal that either one or two of processor and multiple detection devices are sent can be configured in ring-like network structure is received.Multiple detection devices are used to detect the state parameter signal of vehicle, processor is used to obtain the signal of mission phase locating for vehicle, and signal acquisition instruction is sent to the multiple detection device according to mission phase, it wherein include the address information of at least one corresponding multiple detection devices in signal acquisition instruction.Multiple detection devices receive signal acquisition instruction, and return to state parameter signal detected to processor with the matched detection device of address information.Space launch vehicle measuring system proposed by the present invention, it may be convenient to measure expansion a little and the replacement of failure cable, greatly improve the versatility of measuring system.
Description
Technical field
The present invention relates to vehicle field of measuring technique, and in particular to a kind of space launch vehicle measuring system.
Background technique
In order to ensure vehicle (for example, vehicle can be carrier rocket or guided missile) is working properly, need to fly to it
All kinds of parameters in the process are detected.For example, these parameters may include electrical parameter and non-electrical parameter.Wherein, non-electrical
Measuring parameter includes temperature, pressure, vibration and noise etc..In the detection of non-electrical parameter, electrometric sensor is generallyd use to non-
Electrical parameter carries out sensitivity, and transforms it into the standard voltage signal of 0-5V.Acquisition one of the vehicle to non-electrical parameter
As using the system architecture gathered and edited nearby of classification.I.e. each sub- gradation sets inverter and sampler and coder, to be respectively used to each of the same level
Sensor is powered gathers and edits with parameter.Non-electrical parameter after gathering and editing wirelessly is passed down by remote-measuring equipment.
In order to simplify route, sensor generally uses unbalanced single-ended signal output mode, i.e. secondary power supply and non-electrical
Measure signal altogether.For example, change of current sampler and coder can have the function of that secondary power supply output and signal are gathered and edited simultaneously, and each sensor
It is electrically connected between inverter by cable system.
However, existing vehicle measuring system framework is not flexible, and for different rockets, it is often necessary to be to measurement
The cable system of system is redesigned and is arranged, to extend the lead time, increases production cost.
In addition, existing measuring system is when sampling the takeoff phase of vehicle and boost phase, there is no according to delivery
Mission phase locating for device is distinguish the frequency and signal classification of sampling, to will lead to, sampled signal is excessive or mistake
It is miscellaneous, to be unfavorable for the precise measurement to vehicle state, in some instances it may even be possible to will cause the interference of sampling parameter signal.
Summary of the invention
For above-mentioned technical problem in the related technology, the present invention proposes a kind of measuring system of space launch vehicle.The survey
It is flexible, easy to maintenance to measure system architecture, it may be convenient to measure expansion a little and the replacement of failure cable.
The present invention provides a kind of space launch vehicle measuring systems.The space launch vehicle measuring system include processor and
Multiple detection devices；Wherein it is one another in series between the processor and the multiple detection device by cable to form annular
Reticular structure, thus when the communication of the ring mesh structure is normal, times of the processor and the multiple detection device
Remaining equipment that the signal of one transmission can be configured in the ring-like network structure is received；Wherein, the multiple
Detection device is used to detect the state parameter signal of vehicle, and the processor is used for the mission phase according to locating for vehicle
It selects to send at least one of type and the frequency that signal acquisition instructs to the multiple detection device, wherein the signal obtains
Address information comprising at least one corresponding the multiple detection device in instruction fetch；Described in the multiple detection device receives
Signal acquisition instruction, and return to state detected to the processor with the matched detection device of the address information and join
Number signal.
In one embodiment, the mission phase includes takeoff phase and boost phase；Wherein, it is in vehicle
When takeoff phase, the signal acquisition instruction includes being directed to the engine temperature of vehicle and the parameter letter of pressure for obtaining
Number, for obtain be directed to vehicle acceleration and overload parameters signal；And the processor sends the frequency of signal acquisition instruction
Rate within the takeoff phase after vehicle igniting passage at any time and reduce；And when vehicle is in boost phase,
The signal acquisition instruction includes the parameter signal for obtaining the speed for being directed to vehicle, vibration and noise.
In one embodiment, when vehicle is in takeoff phase, the processor sends adopting for signal acquisition instruction
The relationship of sample frequency f and time t meets: f=a (1/t)n+ b, wherein f is positive number, 0≤a≤1,0≤n≤1,0≤t≤1, b
≥100。
In one embodiment, when vehicle is in boost phase, what the signal acquisition that the processor is sent instructed
The passage of sample frequency at any time first increases to be reduced afterwards.
In one embodiment, the detection device includes sensor and analog-digital converter；Wherein the sensor is used for
The state parameter signal of sense aircraft, the analog-digital converter are used to convert digital quantity for the state parameter signal.
In some embodiments, the processor includes that the main transceiver for being divided into two connectivity port and auxiliary are received
Send out device；The other end of the other end of the main transceiver and the accessory transceiver is respectively connected to the ring-like network structure；
To which the signal transmission direction of the ring-like network structure includes the first party from the main transceiver to the accessory transceiver
To and from second direction from the accessory transceiver to the main transceiver；The main transceiver is used for along the first party
Signal acquisition instruction is sent to the multiple detection device upwards；The accessory transceiver can not receive the main transmitting-receiving
When the signal acquisition instruction that device is sent, signal acquisition instruction is sent to the multiple detection device in the second direction.
In one embodiment, the multiple detection device includes at least the first detection device and second detection device, institute
Stating cable includes first segment cable, second segment cable and third section cable；Wherein an interface of first detection device is logical
An interface of first segment cable connection to the second detection device is crossed, another interface of the second detection device passes through
For the second segment cable connection to an interface of the processor, another interface of the processor passes through the third section
Cable connection to first detection device another interface.
In one embodiment, the interface of first detection device, the second detection device and the processor point
It is not provided by three hubs.
In one embodiment, three hubs respectively with first detection device, the second detection device
It is structure as a whole with the processor.
In one embodiment, the processor is change of current sampler and coder.
In one embodiment, the state parameter signal includes non-electric charge quantity signalling, and the non-electric charge quantity signalling includes temperature
At least one of degree, pressure, vibration and noise.
Space launch vehicle measuring system of the invention at least has one of following technical effect:
(1) space launch vehicle measuring system of the invention, by the different mission phases locating for vehicle, sampling is not
With parameter signal, and change the sample frequency of vehicle in-flight parameter, increase the specific aim of measuring system sampling,
Improve the sample rate and sampling validity of parameter.
(2) space launch vehicle measuring system of the invention forms ring mesh by making between detection device and processor
Structure, it can be ensured that can be received by remaining equipment in the signal of the transmission of any appliance, improve vehicle measuring system
Reliability.
(3) transceiver is respectively set in two connectivity ports of space launch vehicle measuring system of the invention, processor,
To on the one hand may insure when open circuit occurs for ring mesh structure, still available all (or most of) detection dresses
The detection signal set；On the other hand, can also be with the communication conditions of real-time detection measuring system, and occur in ring mesh structure
When breaking, development breakdown maintenance that can be more convenient.
(4) space launch vehicle measuring system of the invention includes respective sensor by the signal for sending transceiver
Address information, and sensor sends state parameter to transceiver, can save number in the matched situation of the address information
According to resource, and it can be avoided the cross jamming between signal.
(5) space launch vehicle measuring system of the invention, by make processor and each detection device respectively with hub
It is wholely set, can make easily to connect between each equipment, to improve the maintenance efficiency of system.
In reading specific embodiment and after checking attached drawing, those skilled in the art will recognize that other
Feature and advantage.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be in embodiment
Required attached drawing is briefly described, it should be apparent that, the accompanying drawings in the following description is only some realities of the invention
Example is applied, it for those of ordinary skill in the art, without creative efforts, can also be attached according to these
Figure obtains other attached drawings.
Fig. 1 is the schematic diagram of measuring system according to an embodiment of the present invention.
Fig. 2 is the structural schematic diagram according to the detection device of the embodiment of the present invention.
Fig. 3 a is processor, structure of the detecting device in measuring system according to an embodiment of the present invention, and the electricity with cable
Connection schematic diagram.
Fig. 3 b is that multiple processors are arranged in middle interval according to embodiments of the present invention and the measuring system structure of detection device is shown
It is intended to.
Fig. 4 is the schematic diagram of the network node formula connection structure of measuring system of the invention.
Specific embodiment
To further illustrate the technical scheme of the present invention below with reference to the accompanying drawings and specific embodiments.Such as " under
Face ", " lower section ", " ... under ", " low ", " top ", " ... on ", the spatial relation term of "high" etc. for keeping description convenient,
To explain positioning of the element relative to second element, indicate in addition to from shown in figure those be orientated different orientations with
Outside, these terms are intended to cover the different orientation of device." element on the other element/under " can be with table in addition, for example
Show that two elements directly contact, can also indicate that also there are other elements between two elements.In addition, such as " first ", " the
Two " etc. term is also used for describing each element, area, part etc., and should not be regarded as limiting.Similar term is describing
Similar element is indicated in the whole text.
Typical vehicle measuring system generallys use tree-like connection structure.For example, each sensor or sensor group
Part is respectively connected to leader cable, and leader cable is connected to the connectivity port of change of current sampler and coder.I.e. one end of leader cable passes through multiple points
Cable is separately connected one end of each sensor or sensor module, the other end and vehicle of sensor or sensor module
Position to be detected connection.
However, for example there may be as following drawbacks for this tree-like vehicle measuring system:
First is that the electrical property of system is poor.For example, traditional vehicle Non-Electricity Measurement system belongs to analog signal system
System, only the signal after sampler and coder is gathered and edited just belongs to digital transmission signal.Vehicle, can be inevitable during flight
Face complicated electromagnetic environment.Therefore, if into the signal before change of current sampler and coder be analog signal, probably
It receives the interference of electromagnetic environment and is distorted.That is, the reliability outline of analog signal is in number under complicated electromagnetism annular
Word signal.
Second is that the framework of system is not flexible, the degree of modularity is low.For example, in the development process of the vehicles such as carrier rocket
In, especially at the initial stage of development, almost the non-electrical parameter of each ignition arrow all may not be identical.If using traditional non-
Power measurement system then needs section to carry out rearranging design to each hair all cable systems.For example, recalculating each branch's electricity
The length of cable, and it also requires producing again, going out total coating process file again, so as to cause vehicle to develop initial stage
Cost is excessively high, the lead time increases.
Third is that vehicle measuring system when something goes wrong, maintenance difficult.Under normal conditions, vehicle electrical system
Failure mostly occurs in cable.If the testing process after general assembly factory and general assembly occurs for failure, can tearing open because of vehicle
It fills difficulty and does not allow the factor using tools such as soldering irons, and lead to the postponement of Project R&D progress.
Aiming at the problem that existing vehicle measuring system, the invention proposes " change net are line " of a kind of similar internet
System architecture, so that making the electrical property of system enhances.And can any position in the system architecture is described increase and decrease measuring point, meanwhile,
When measuring system breaks down, it may be convenient to failure cable is replaced, to improve the maintenance of Non-Electricity Measurement system
Property.Further, since measuring system of the invention, the stage according to locating for vehicle has carried out area to sampled data and sample frequency
Point, to improve the operational efficiency of measuring system.
The present invention provides a kind of space launch vehicle measuring systems.Referring to Fig. 1, which includes processor 1 and more
A detection device 2.Wherein it is one another in series between the processor 1 and the multiple detection device 2 by cable a, b, c, d, e
To form ring mesh structure, thus when the communication of the ring mesh structure is normal, the processor 1 and the multiple
Remaining equipment that the signal that either one or two of detection device 2 is sent can be configured in the ring-like network structure is received.
Wherein, the multiple detection device 2 is used for the state parameter signal of sense aircraft, and the processor 1 is for obtaining vehicle
Locating mission phase, and the mission phase according to locating for vehicle device selects to send signal acquisition to the multiple detection device 2
At least one of type and frequency of instruction.Wherein include corresponding the multiple detection device 2 in the signal acquisition instruction
At least one address information.The multiple detection device 2 receives signal acquisition instruction, and with the address information
Matched detection device 2 returns to state parameter signal detected to the processor 1.Vehicle measuring system of the invention,
On the one hand, it is connected by making processor form ring mesh with multiple detection devices, so that increase and the failure cable of measuring point
Replacement become simple and easy, improve the reliability and maintainability of measuring system, also reduce the life of vehicle measuring system
Produce cost；On the other hand, pass through the type and frequency of the targeted selection signal acquisition instruction of mission phase according to vehicle
Rate improves the efficiency of measuring system.
For example, mission phase locating for vehicle may include takeoff phase and boost phase.Wherein takeoff phase can be with
For within the rocket firing moment to 1 second.At this point, several kms for example, rocket has about flown.Boost phase is for example
It can be (for example, 5 minutes), the hundreds of kilometer at this point, rocket has about flown from 1 second to several minutes.Usual situation
Under, it is the most distress phase of rocket launching within the short time of rocket firing.At this point, the flying speed of carrier rocket is little,
But engine interior and nearby each equipment experienced the acute variation from low temperature to excessive temperature, and multiple components bear compared with
Big acceleration and overload.Whether transmitting succeeds, and being largely dependent on engine and other components can pay and withstand the stage
The test of temperature, pressure or acceleration and overload.Therefore, temperature, the pressure in takeoff phase to engine and relevant device
The detection of power, acceleration and overload etc. is most important.For example, processor sends signal acquisition instruction to obtain engine and phase
The frequency for closing the parameters such as temperature, pressure, acceleration and the overload of equipment can be greater than 1000, i.e., in 1 second of section of taking off,
Processor available 1000 times or more temperature and pressures and vehicle acceleration and overload in relation to engine and relevant device
Parameter signal.For example, processor obtains the parameter frequency of engine temperature, pressure, acceleration and overload from time of ignition
Rate can passage at any time and reduce.For example, processor send signal acquisition instruction with obtain engine temperature, pressure and
The relationship of the frequency f and time t of vehicle acceleration and overload parameters meet: f=a (1/t)n+ b, wherein f is positive number, 0
≤ a≤1,0≤n≤1,0≤t≤1, b >=103.For example, 0.4≤a≤0.8,0.2≤n≤0.6, so as to further change
The specific aim of suitability and state estimations that kind vehicle boost phase parameter signal obtains.
Rocket promotes section in acceleration later, since engine and peripheral equipment experienced initial blast off the stage
Test has certain reliability.Therefore, carrier rocket speed over time and flight stability become and ensure to emit
The higher factor of successful importance.At this point it is possible to the temperature of relatively low frequency detecting engine and neighbouring equipment, pressure
Power, acceleration and overload parameters, and with flying speed, vibration and the noise etc. of higher frequency detecting vehicle.In addition,
When vehicle is in boost phase initial stage, to the sample frequencys of these parameters, (i.e. processor sends signal acquisition to detection device
The frequency of instruction) it can gradually increase；And sample frequency reaches maximum value in the mid-term of boost phase；It is in and adds in vehicle
When fast latter stage in stage, with constantly exhausting for liquid or solid fuel, the probability of rocket successful flight constantly rises, to delivery
The sample frequency of the parameters such as device flying speed, vibration and noise can linear or non-linear decline.For example, at vehicle
In the latter stage of boost phase, the sample frequency of the parameters such as vehicle flying speed, vibration and noise can be accelerated to decline.
In this embodiment, when rocket is in takeoff phase, the transmission that processor can also be spaced, which is intended to obtain, starts
The first kind signal acquisition of machine temperature, pressure and the parameters such as vehicle acceleration and overload instructs and is intended to obtain rocket
The parameters such as speed, vibration and noise the instruction of the second class signal acquisition.For example, in rocket firing departure time, first kind letter
Number frequency and the transmission frequency ratio of the second class signal can be between 10:1 to 5:1.For example, from the rocket firing moment to
The last moment of signified takeoff phase of the invention, above-mentioned transmission frequency ratio can be gradually decreased as 1 between 10:1 to 5:1:
1 or so.In the acceleration mission phase of rocket, the ratio of the transmission frequency of the transmission frequency of first kind signal and the second class signal can
To be gradually decrease to 1:4 from 1:1, and after this, 1:1 or so is gradually risen to again.The processing of the embodiment of the present invention
Device is instructed by the two class signal acquisition of transmission at interval, and adjusts two classes letter according to the variation of time after the igniting of rocket etc.
The transmission frequency ratio for number obtaining instruction, can be improved the efficiency of measuring system, avoid unnecessary signal transmission in measuring system,
To preferably judge the working condition of rocket.
For example, measuring system may include timer.For example, the timer can be set in processor.To timing
Device can obtain ignition signal in such as rocket firing, and the time is calculated from the rocket firing moment.Since rocket is in point
Very high speed can be increased to after fire in very short time, therefore, timer there should be enough precision, to receive and dispatch
Device can be in different mission phases in space launch vehicle, adjust to detection device send signal acquisition instruct type and
Frequency.It is appreciated that the different types of signal acquisition instruction of present invention meaning refers to that the signal comprising different address information obtains
Instruction fetch, so that multiple detection devices are matched when obtaining the instruction of the signal acquisition with different address information with address information
Detection device measured parameter signal is returned to processor.
In addition, the processor of measuring system can also be according to letters such as the speed, accelerations or overload that detection device detects
Number, mission phase locating for spacecraft is judged, so that selection sends the type of signal acquisition instruction accordingly and transmission signal obtains
The frequency of instruction fetch.Specifically, if for example rocket is in takeoff phase, the instruction of the signal acquisition that sends primarily directed to
The temperature and pressure and acceleration of engine and neighbouring equipment and overload etc..For example, if rocket is in boost phase,
The signal acquisition instruction of transmission is predominantly obtained for parameters such as speed, vibration and the noises of engine.And it is in and adds in rocket
Fast stage, processor can be such that the frequency for sending signal acquisition instruction is continuously increased first, later not according to the size of parameter
It is disconnected to reduce.As previously mentioned, takeoff phase and acceleration mission phase in vehicle, it includes needle that processor can be sent with compartment of terrain
Signal acquisition instruction to all kinds of parameters, but the transmission frequency of inhomogeneous signal acquisition instruction can be different, and processor
The transmission frequency ratio of inhomogeneity signal acquisition instruction can also be changed according to the passage for playing the time with time of ignition.
With continued reference to Fig. 1, for example, processor 1 can at least have, there are two connectivity port A1, A2, and each detection device
Also connectivity port A1, A2 make these equipment shapes to be sequentially connected these ports by cable a-e there are two all at least having
Circularize netted connection.For example, as shown in Figure 1, when multiple detection devices 2 and processor 1 are connected to each other, one of equipment
Port A1 by the port A2 of another equipment of cable connection, so that multiple detection devices and processor form above-mentioned ring network
Network structure.
For example, three cables can be used when vehicle measuring system includes two detection devices and a processor
Three equipment are connected.Specifically, one of connectivity port of processor passes through a cable connection to one of detection
Another connectivity port of one connectivity port of equipment, the detection device passes through second cable connection to another detection
The a port of equipment, another port of another detection device by third root cable connection to processor another
Port.To which ring mesh structure is collectively formed in three cables and three equipment.For example, being connected in ring-like network structure every
A equipment constitutes a node on the cable system of annular connection, thus when measuring system needs additional measuring node, it can
In detection device access loop network that be directed to will be additional.For example, as previously mentioned, each additional equipment can be at least
Including port A1 and A2, so that these additional equipment can be connect by cable with other equipment.For example, as shown in Figure 1,
The A1 of one of equipment connects the A2 of another equipment, so that the equipment for keeping these additional is also constituted in annular connection network
Node.
It is understood that if the quantity of processor and the quantity of detection device further increase, it can be according to above-mentioned
The connection type of embodiment is connected to each other, thus form equipment (node) more, larger loop network measuring system
(for example, measuring system as shown in Figure 1).For example, in some embodiments, ring-like network structure can support 30 with
Upper sensor node, message transmission rate is for example not less than 10Mbps in ring.For example, the length for the ring being made of cable can be with
Not less than 500 meters, the required distance of measuring device and engine when meeting transmitter test run.
For example, processor 1 and each detection device 2 can be connected to each other using hub (HUB), thus any appliance
The signal of transmission can be received by other equipment in ring mesh structure.For example, processor 1 and multiple detection devices 2
Can also be using other connector connections, but the connection between processor 1 and multiple detection devices 2 is with ring mesh structure
In each node device send signal principle can be received as by remaining equipment.
As described above, any node equipment in ring mesh structure is sent when the communication of ring mesh structure is normal
Signal can be received by other equipment.But comprising corresponding wherein at least one in the signal acquisition instruction sent by processor 1
The address information of a detection device 2, thereby while multiple detection devices 2 receive the signal acquisition instruction, but only and signal
The matched detection device 2 of address information in acquisition instruction just returns to corresponding parameter signal, and then not only increases signal
The effective percentage of transmission, while being also avoided that interfering with each other between signal.
Referring to fig. 2, in one embodiment, for example, the detection device includes sensor 21 and analog-digital converter 22.
Wherein the sensor 21 is used for the state parameter signal of sense aircraft, and the analog-digital converter 22 is used for the state
Parameter signal is converted into digital quantity.The embodiment of the present invention by making the detection signal of sensor be changed into digital quantity, thus into
One step improves the reliability that signal transmits under complex electromagnetic environment.
It may be noted that the signal of the sensor detection of different model is different, the value that detected for itself is exactly number
The sensor of amount, without setting analog-digital converter.
For example, multiple detection devices can be sensor or sensor module.These sensors may include temperature sensing
Device, pressure sensor, noise transducer, g sensor and acceleration transducer etc..For example, these sensors can be set
In the position to be measured of each cabin.
Referring to Fig. 3 a, for example, in one embodiment, the processor 1 includes the master for being divided into two connectivity port
Transceiver 11 and accessory transceiver 12.The other end of main transceiver 11 and the other end of accessory transceiver 12 are respectively connected to annular
Reticular structure.Two ports of the processor 1 pass through main transceiver 11 respectively and accessory transceiver 12 accesses to the annular
Network structure；To which the signal transmission direction of the ring-like network structure includes receiving from the main transceiver 11 to the auxiliary
Send out the first direction of device 12 and from the accessory transceiver 12 to the second direction of the main transceiver 11.The main transmitting-receiving
Device 11 is used to along the first direction send signal acquisition instruction to the multiple detection device 2.The accessory transceiver 12
When the signal acquisition instruction that the main transceiver 11 is sent can not be received, to the multiple inspection in the second direction
It surveys device 2 and sends signal acquisition instruction.Main transceiver is respectively set by two ports in processor in the embodiment of the present invention
And accessory transceiver, it can preferably confirm the communications status of loop network, and main receipts can not be received in accessory transceiver
When sending out the signal of device, signal acquisition instruction is sent the other way around, when so as to occur open circuit in loop network, still
It may be implemented to carry out parameter acquisition to equipment most of in ring mesh structure, to improve the reliability of detection system.
In this embodiment, if the signal that main transceiver 11 is sent in a first direction can not be connect by accessory transceiver 12
It receives, then substantially judges there is communication failure in the first direction.The failure both may be by the cable in ring mesh structure
Cause, it is also possible to by the induced fault of accessory transceiver itself.If caused by the failure is the open circuit by cable,
Accessory transceiver 12 can not receive main transceiver signal acquisition instruction when, by from accessory transceiver 12 in a second direction
Send signal acquisition instruction, it can be ensured that signal acquisition instruction reaches in a second direction to be arranged in accessory transceiver and failure
Detection device between the breakpoint of cable.In addition, can be arrived by main transceiver along the signal acquisition instruction that first direction is sent
Up to the detection device being arranged between main transceiver and failure cable breakpoint.Therefore, this ring-like network structure may be implemented
Even if in ring mesh structure in the case where failure cable, the parameter of still available all detection devices.Separately
Outside, if accessory transceiver 12 breaks down, for example, the receiving and transmitting signal of accessory transceiver 12 is abnormal, then 12 nothing of accessory transceiver
Method receives the signal of main transceiver 11, signal can not be also sent, so that main transceiver 11 can not also receive accessory transceiver 12
Signal.But main transceiver 11 still can reach in ring-like network structure along the signal acquisition instruction that first direction is sent
All detection devices.Therefore, when one of main transceiver and accessory transceiver receiving and transmitting signal occur abnormal, by bi-directionally sent
Signal acquisition instruction still can guarantee the signal acquisition sent in a first direction by main transceiver instruction or be received by auxiliary
The signal acquisition instruction that hair device is sent in a second direction reaches each detection dress between main transceiver and accessory transceiver
It sets, to improve the redundant ability of vehicle measuring system significantly.
With continued reference to Fig. 3 a, detection device can receive main transceiver 11 or accessory transceiver 12 by transceiver 23
Signal acquisition instruction, and detection device is powered by mains connection 24.Positioned at the power supply line of the upper end Fig. 3 and under Fig. 3
The signal wire at end is separated from each other, it is only for function signal.For example, power supply line and signal wire can be located at same root cable
It is interior.
Referring to Fig. 3 b, in this embodiment, for example, can be in ring-like network structure, the multiple processors of the setting at interval
1.That is, multiple processors 1 are intervally installed with multiple detection devices 2.Wherein, at least two connections of any processor
Main transceiver and accessory transceiver is respectively set in port.It is SN1- that the main transceiver of these processors, which can be numbered sequentially,
SN4, equally, accessory transceiver can also accordingly sequentially number SN1 '-SN4 '.In order to make major-minor transceiver in annular in figure
Position in network understands that the main transceiver and accessory transceiver of same processor can be with reference numerals, such as main transceiver
SN1, corresponding accessory transceiver SN1 ', and both belong to same processor.Other main transceivers to correspond to each other and auxiliary
The numbering of transceiver can with and so on.
A main transceiver (for example, SN1) in loop network can send signal acquisition along above-mentioned first direction S1 and refer to
It enables, it, can be according to number far from the main transceiver if corresponding accessory transceiver SN1 ' does not receive signal acquisition instruction
Transceiver SN4 ' whether receive signal acquisition instruction, judge the position of fault point.For example, in a first direction on S1, main transmitting-receiving
The signal that device SN1 is sent can not be by accessory transceiver SN1 ' reception, but can be by accessory transceiver SN4 ' reception, it can be determined that
Part between accessory transceiver SN1 ' and transceiver SN4 ' adjacent thereto occurs for the communication failure of ring-like network structure.
By the signal acquisition instruction for successively examining main transceiver SN1 to send, with the transceiver for receiving and not receiving the instruction
Number (such as successively examining SN4 ', SN3 ' SN2 '), where can judging fault point rapidly, so as to correspondingly execute electricity
The operation such as cable replacement or the maintenance of other fault points.
For example, when main transceiver SN1 sends signal acquisition instruction along first direction S1, if SN1 ', SN4 ', SN3 '
The signal acquisition instruction of main transceiver SN1 transmission and SN2 ' are all not received by when getting the instruction, then ring-like network structure
Communication failure point be likely to occur in it and be located at -- the part of SN4 ' -- SN3 ' -- SN2 ' SN1 '.Later, can further lead to
It crosses and sends the signal intelligence that signal acquisition instruction judges ring mesh structure along the direction S2 by SN1 '.For example, if SN3 is obtained
To the signal, SN2 does not obtain the signal, then fault point is likely to occur in cable of the loop network between SN3--SN2.
Similarly, if SN4 gets the signal, the signal is had not been obtained in SN3, it is contemplated that cable and SN3-between SN2-SN3
It is smaller to there is a possibility that open circuit simultaneously for the cable of part between SN4, it may be considered that the signal of SN3 main transceiver, which receives, to be occurred
Failure.Ground embodiment of the invention, by power measurement system, configuring multiple processors, can rapid fault point,
To complete the rapid-maintenance of ring-like network structure.
It should be pointed out that the acquisition of signal can be by the major-minor transceiver of multiple processors in ring-like network structure
It carries out, is positioned so as to the fault point more accurately to ring mesh structure in turn, relevant signal is sent and failure
Localization method belongs to the protection scope of the application.In addition, multiple processors can redundancy each other, to further improve
The adaptability of vehicle measuring system.
In one embodiment, for example, space launch vehicle measuring system includes the first detection device, second detection device
With a processor.For example, the interface of first detection device, the second detection device and the processor respectively by
Three hubs provide.Equally, if detection system includes multiple detection devices and processor, the quantity of hub can be with
And one-to-one correspondence equal with the sum of these detection devices and the quantity of processor.These hubs can not only be used for independent connection
Part can also be structure as a whole with corresponding detection device or processor.And preferably, hub respectively with corresponding detection
Device and the processor are structure as a whole, to keep detection system more compact, mechanical property is more preferable.
In one embodiment, the processor is used to carry out isochronous control to the detection device.
For example, the physical layer for the network-bus being made of cable is IEEE in vehicle measuring system of the invention
802.3 Ethernet 100BASE-TX, MAC layer meet GB/T 15629.3, and each layer on MAC layer, which uses, meets GB/T
27960 Ethernet POWERLINK agreements.The network that cable system is constituted uses the shared channel based on 2 class hubs, uses half
Duplexing isochronous transfer mode.
Referring to fig. 4, for example, in some embodiments above, the processor is change of current sampler and coder.The change of current sampler and coder
It can be used as the MN (management node) of cable system, each sensor is respectively as CN (controlled node).In loop cable network knot
In structure, all devices (including change of current sampler and coder and sensor) are connected to each other by HUB (hub).MN is to CN use etc.
When synchronously control.It is controlled about isochronous, GB/T 27960 can be detailed in.
In measuring system schematic diagram as shown in Figure 4, MN sends retrieval command, which propagates in a network, owns
CN can receive the retrieval command.Similarly, what any CN was sent send several orders, can also be connect by remaining all equipment
It receives.That is, the retrieval command (PReq) of MN and sending several times for each CN enable (PRes) all to broadcast in the network, sent out by MN
The retrieval command sent distinguishes each CN by MAC Address.Each CN monitors network state in real time, receives and the matched life of this MAC Address
It is just sent after order several times and enables and (enable the parameter value that can be sensor measurement for example, sending several times).The embodiment of the present invention leads to
The network mode using MN and CN is crossed, keeps the flexibility of measuring system framework high, to improve the adaptability of measuring system.
The above embodiment of the present invention can be combined with each other, and have corresponding technical effect.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of space launch vehicle measuring system, which is characterized in that including processor and multiple detection devices；The wherein processing
It is one another in series between device and the multiple detection device by cable to form ring mesh structure, thus in the ring mesh
When the communication of structure is normal, the signal that either one or two of the processor and the multiple detection device are sent can be configured in institute
Remaining equipment stated in ring-like network structure is received；
Wherein, the multiple detection device is used to detect the state parameter signal of vehicle, and the processor is related for obtaining
The signal of mission phase locating for vehicle, and the mission phase according to locating for vehicle selects to send to the multiple detection device
At least one of type and frequency of signal acquisition instruction, wherein including corresponding the multiple detection in signal acquisition instruction
The address information of at least one device；
The multiple detection device receives the signal acquisition instruction, and with the matched detection device of the address information to institute
It states processor and returns to state parameter signal detected.
2. space launch vehicle measuring system according to claim 1, which is characterized in that the mission phase includes rank of taking off
Section and boost phase；
Wherein, when vehicle is in takeoff phase, the signal acquisition instruction includes being directed to vehicle engine for obtaining
The signal of temperature and pressure parameter, the signal for obtaining vehicle acceleration and overload parameters；And the processor sends letter
Passage of the frequency of number acquisition instruction within the takeoff phase after vehicle igniting at any time and reduce；And
When vehicle is in boost phase, the signal acquisition instruction includes for obtaining the speed for being directed to vehicle, vibration
With the signal of noise parameter.
3. space launch vehicle measuring system according to claim 2, which is characterized in that be in phase takeoff phase in vehicle
Between, the relationship that the processor sends the sample frequency f and time t of signal acquisition instruction meets: f=a (1/t)n+ b, wherein f
For positive number, 0≤a≤1,0≤n≤1,0≤t≤1, b >=100.
4. space launch vehicle measuring system according to claim 2, which is characterized in that be in boost phase in vehicle
When, the frequency for the signal acquisition instruction that the processor is sent first increases at any time to be reduced afterwards.
5. space launch vehicle measuring system according to claim 1, which is characterized in that the detection device includes sensor
And analog-digital converter；
Wherein the sensor is used to detect the state parameter signal of vehicle, and the analog-digital converter is for joining the state
Number signal is converted into digital quantity.
6. space launch vehicle measuring system according to claim 1-5, which is characterized in that the processor includes
It is divided into the main transceiver and accessory transceiver of two connectivity port；The other end of the main transceiver and auxiliary transmitting-receiving
The other end of device is separately connected the ring-like network structure；To which the signal transmission direction of the ring-like network structure includes from institute
State second of main transceiver to the first direction of the accessory transceiver and from the accessory transceiver to the main transceiver
Direction；
The main transceiver is used to along the first direction send signal acquisition instruction to the multiple detection device；
The accessory transceiver is when that can not receive the signal acquisition instruction that the main transceiver is sent, along the second direction
Signal acquisition instruction is sent to the multiple detection device.
7. described in any item space launch vehicle measuring systems according to claim 1, which is characterized in that the multiple detection device
Including at least the first detection device and second detection device, the cable includes first segment cable, second segment cable and third section
Cable；
Wherein an interface of first detection device is by first segment cable connection to one of the second detection device
Interface, another interface of the second detection device by an interface of the second segment cable connection to the processor,
Another interface of the processor passes through the third section cable connection to another interface of first detection device.
8. space launch vehicle measuring system according to claim 7, which is characterized in that first detection device, described
The interface of second detection device and the processor is provided by three hubs respectively.
9. space launch vehicle measuring system according to claim 8, which is characterized in that three hubs respectively with institute
The first detection device, the second detection device and the processor is stated to be structure as a whole.
10. space launch vehicle measuring system according to claim 1-5, which is characterized in that the processor is
Change of current sampler and coder.
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| CN202010835063.4A CN112033458B (en) | 2018-05-28 | 2018-05-28 | Rocket measurement system and fault detection method |
| CN201810521376.5A CN109115263B (en) | 2018-05-28 | 2018-05-28 | Spacecraft measurement system |
| CN202010835082.7A CN112286087B (en) | 2018-05-28 | 2018-05-28 | Carrier rocket measurement system |
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| CN114363381A (en) * | 2022-03-21 | 2022-04-15 | 北京凌空天行科技有限责任公司 | Rocket data acquisition and transmission system and rocket data acquisition and transmission method |
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| CN112033458A (en) | 2020-12-04 |
| CN112286087A (en) | 2021-01-29 |
| CN112286087B (en) | 2021-09-14 |
| CN109115263B (en) | 2021-03-19 |
| CN112033458B (en) | 2022-06-17 |
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