CN110297481A - It unites when a kind of stage separation flight control system high-precision method - Google Patents
It unites when a kind of stage separation flight control system high-precision method Download PDFInfo
- Publication number
- CN110297481A CN110297481A CN201910585923.0A CN201910585923A CN110297481A CN 110297481 A CN110297481 A CN 110297481A CN 201910585923 A CN201910585923 A CN 201910585923A CN 110297481 A CN110297481 A CN 110297481A
- Authority
- CN
- China
- Prior art keywords
- flight control
- separation
- short
- control computer
- conducting sleeve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 168
- 238000000926 separation method Methods 0.000 title claims abstract description 149
- 238000000034 method Methods 0.000 title claims abstract description 35
- 238000004891 communication Methods 0.000 claims abstract description 16
- 238000002955 isolation Methods 0.000 claims description 47
- 238000010304 firing Methods 0.000 claims description 13
- 238000005474 detonation Methods 0.000 claims description 6
- 230000002159 abnormal effect Effects 0.000 claims description 5
- 230000008878 coupling Effects 0.000 claims description 4
- 238000010168 coupling process Methods 0.000 claims description 4
- 238000005859 coupling reaction Methods 0.000 claims description 4
- 230000005611 electricity Effects 0.000 claims description 4
- 239000003990 capacitor Substances 0.000 claims description 3
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 230000008569 process Effects 0.000 description 9
- 230000005540 biological transmission Effects 0.000 description 8
- 230000033001 locomotion Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 239000004020 conductor Substances 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010494 dissociation reaction Methods 0.000 description 1
- 230000005593 dissociations Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- 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
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0259—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the response to fault detection
- G05B23/0283—Predictive maintenance, e.g. involving the monitoring of a system and, based on the monitoring results, taking decisions on the maintenance schedule of the monitored system; Estimating remaining useful life [RUL]
-
- 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
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24065—Real time diagnostics
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
It unites when a kind of stage separation flight control system high-precision method, in separation process, providing the when system mark of redundancy to aircraft between aircraft and launch-vehicle stage, starts to control time range for what aircraft determined autonomous flight.The RS-422 interface communication " separation command " that system mark is sent based on rocket to aircraft when wherein main, to avoid communications errors and frame losing from leading to the time lag started to control, setting " the starting to control delay mark " in every frame " separation command " starts to control delay foundation as what aircraft received effective " separation command "；Mark of uniting when spare is based upon rocket and aircraft provides the on state of short-circuited conducting sleeve in the separate connector of electrical connection.System marks when this method can provide accurate and reliable during stage separation for aircraft.
Description
Technical field
The content of present invention is related to a kind of method of uniting when stage separation flight control system high-precision.
Background technique
In the flight course of aircraft and carrier rocket assembly, when meeting stage separation condition, generally by rocket
It initiates to detect the timing of separation process separation process between controlled stage, aircraft, determination is started to control the time, and defined after isolation
It is started to control in time range.The time relationship that aircraft starts to control to task execution success or failure, if starting to control in advance, flying vehicles control rudder face
Without departing from the interference range in rocket flow field, there are the reversed risks of steerage, will lead to attitude of flight vehicle unstability；If aircraft has been delayed
Control, there are longer without control free moving time, equally causes attitude instability.
Aircraft start to control the time usually with after rocket is electrical and mechanical interface disconnects, therefore before electric interfaces disconnection
System mark when rocket needs to send to aircraft, mark of uniting when aircraft receives start to control after delay.
Conventional when system method is to drive aircraft flight control computer by the output switch parameter of rocket flight control computer
System when On-off signal carries out.Precision of uniting when advantage is is higher.The disadvantage is that only providing single when system mark, serious forgiveness is lower；
It is related to the matching of 2 flight control computer interface circuits, it is understood that there may be drive level and the inconsistent problem of benchmark；It needs to occupy
Output switch parameter resource more than 2 tunnel of rocket flight control computer carries out Redundancy Design.
Another conventional when system method is separate connector plug and socket electricity between setting monitoring aircraft and rocket
The collected short-circuited conducting sleeve of aircraft flight control computer is disconnected system when being used as and indicated by the short-circuited conducting sleeve of gas connection status.Advantage is nothing
Need the switching value resource of rocket flight control computer.The disadvantage is that separate connector short-circuited conducting sleeve in disconnection process there are mechanical movement, because
This from separate connector solution be locked to the time that short-circuited conducting sleeve is fully disconnected spread it is larger, when system mark be transmitted to time of aircraft and become
Change range it is larger, when system precision it is lower.
Summary of the invention
Technical problem solved by the present invention is overcome the deficiencies in the prior art, proposes a kind of stage separation flight control system
It unites method when high-precision of uniting, the serious forgiveness of system mark, is eliminated to rocket flight control computer switching value resource when improving stage separation
Demand and Circuit Matching problem, solution, which is used only to unite when separate connector short-circuited conducting sleeve is used as, indicates that precision is relatively low asks
Topic.
The technical solution of the invention is as follows:
It unites when a kind of stage separation flight control system high-precision method, steps are as follows:
(1) after rocket enters separation process, at the T0 moment, rocket flight control computer is sent to aircraft flight control computer to be divided
From director data frame；
(2) at the T1 moment, rocket flight control computer issues electromagnetism unlock to separate connector plug end by unlock cable
Instruction；
(3) aircraft flight control computer after the power-up, persistently judges separation command data frame, effective when receiving for the first time
When separation command data frame, (4) are entered step；When not receiving separation command data frame or separation command data frame is invalid,
Enter step (5)；
(4) aircraft flight control computer is determined according to the delay mark that starts to control received in separation command data frame for the first time
When controlling delay time, and starting to start to control delay meter, (9) are entered step later；
(5) aircraft flight control computer after the power-up, persistently judges whether electromagnetic unlocking device work is normal, if normal,
(6) are then entered step, (10) are entered step if abnormal；
(6) aircraft flight control computer after the power-up, persistently judges the off-state of short-circuited conducting sleeve, if two-way short-circuited conducting sleeve is disconnected
It opens, then enters step (7), otherwise return step (3)；
(7) aircraft flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects, if reliable disconnect, enters step
(8), otherwise return step (3)；
(8) Timer_2 when aircraft flight control computer starts to start to control delay meter；
(9) at the T2 moment, rocket flight control computer issues fuze to separation bolt by firing cable, separates bolt
It disconnects, enters step (13) later；
(10) at the T2 moment, rocket flight control computer issues fuze to separation bolt by firing cable, separates spiral shell
Bolt disconnects, and aircraft flight control computer after the power-up, persistently judges the off-state of short-circuited conducting sleeve, if two-way short-circuited conducting sleeve disconnects,
(11) are then entered step, otherwise return step (3)；
(11) aircraft flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects, if reliable disconnect, enters step
(12), otherwise return step (3)；
(12) Timer_3 when aircraft flight control computer starts to start to control delay meter enters step (13) later；
(13) terminate and start to control when aircraft flight control computer starts to control delay meter.
Delay time is started to control according to the delay mark determination of starting to control received in separation command data frame for the first time, under
Table:
Wherein Timer_1 is that aircraft flight control computer receives first frame separation command to the delay started to control, and T_422 is
Rocket flight control computer issues the sending cycle of separation command data frame, and n is received for aircraft flight control computer and efficiently separated
The serial number of instruction.
T0 indicates 0 moment of separation timing determined by rocket flight control computer, enters separation process in this time.
T1 indicate rocket flight control computer to separate connector plug end issue electromagnetism unlock instruction at the time of, this time by
The setting of rocket flight control computer, T1 is after T0；T2 indicate rocket flight control computer to separation bolt issue fuze when
It carves, this time is set by rocket flight control computer, and T2 is after tl.
Aircraft flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects specifically: flight control computer collects short circuit
The time that ring disconnects is greater than preset time threshold Timer_DIO.
When Timer_2 is that electromagnetic unlocking device is working properly when starting to control delay meter, two-way short-circuited conducting sleeve is reliably disconnected to flight
The delay that device starts to control is set by aircraft flight control computer；Timer_3 is that electromagnetic unlocking device works not just when starting to control delay meter
Chang Shi, two-way short-circuited conducting sleeve are reliably disconnected to the delay that aircraft starts to control, and are set by aircraft flight control computer；Timer_2 >
Timer_3。
System method is based on uniting when stage separation flight control system when high-precision of uniting when the stage separation flight control system
Device realizes that it includes: separate connector plug end, separate connector socket that bulk cargo, which is set, when the stage separation flight control system
End, separation bolt, unlock cable, the first short-circuited conducting sleeve, the second short-circuited conducting sleeve, is divided rocket flight control computer, aircraft flight control computer
From connector drawstring and firing cable；Electromagnetic unlocking device and unlock pull rod are provided in separate connector plug end；
It is bolted together between rocket and aircraft by separating, rocket flight control computer is by firing cable and divides
From being bolted, the communication between rocket flight control computer and aircraft flight control computer passes through the separation being plugged in together and connects
Device plug end and separate connector socket end are realized；Rocket flight control computer passes through unlock cable connection separate connector plug end
The electromagnetic unlocking device of middle setting, driving unlock pull rod carry out between separate connector plug end and separate connector socket end
Separation unlock；One end of separate connector drawstring is fixed on rocket rocket body, and the other end is fixed on unlock pull rod；
It include short-circuited conducting sleeve power supply circuit and short-circuited conducting sleeve Acquisition Circuit, the first short-circuited conducting sleeve and second in aircraft flight control computer
Short-circuited conducting sleeve is drawn from short-circuited conducting sleeve power supply circuit, into separate connector plug end after separate connector socket end, and
Separate connector plug end is turned back, and is again passed through separate connector socket end and is connected into short-circuited conducting sleeve Acquisition Circuit later.
When electromagnetic unlocking device is effective, before separation bolt detonation, unlock pull rod is driven by electromagnetic unlocking device
Realize the separation unlock between separate connector plug end and separate connector socket end；
When electromagnetic unlocking device failure, after separation bolt detonation, relative displacement is generated between rocket and aircraft,
Unlock pull rod is driven to realize point between separate connector plug end and separate connector socket end by separate connector drawstring
Dissociation lock；
After separate connector plug end and the separation of separate connector socket end, the first short-circuited conducting sleeve and the second short-circuited conducting sleeve are drawn
It is disconnected, open-circuit condition is become from state between short-circuited conducting sleeve Acquisition Circuit and short-circuited conducting sleeve power supply circuit.
Electromagnetic unlocking device is electromagnet, and after being powered by unlock cable, electromagnet generates magnetic force and pulls unlock pull rod；The
One short-circuited conducting sleeve and the second short-circuited conducting sleeve are mutually redundant.
Short-circuited conducting sleeve power supply circuit includes primary power source and current-limiting circuit, and primary power source is the first short-circuited conducting sleeve and the second short-circuited conducting sleeve
Power supply, is arranged current limit circuit, is also equipped between primary power source and the second short-circuited conducting sleeve between primary power source and the first short-circuited conducting sleeve
Current-limiting circuit；
Short-circuited conducting sleeve Acquisition Circuit includes resistance R1~R6, capacitor C1, C2 and light-coupled isolation chip G1, and circuit collection terminal is
IN1 and IN2, output end are OUT1 and OUT2；
First short-circuited conducting sleeve is connected to the first light-coupled isolation of light-coupled isolation chip G1 from the first collection terminal IN1 by resistance R1
Input anode；Flying capcitor C1 between the first light-coupled isolation input anode and negative terminal of light-coupled isolation chip G1, while the first light
Coupling isolation input negative terminal with primary power source is connect by resistance R2, and the first light-coupled isolation exports negative terminal and passes through resistance R3 connection the
One output end OUT1；
Second short-circuited conducting sleeve is connected to the second light-coupled isolation of light-coupled isolation chip G1 from the second collection terminal IN2 by resistance R4
Input anode；Flying capcitor C2 between the second light-coupled isolation input anode and negative terminal of light-coupled isolation chip G1, while the second light
Coupling isolation input negative terminal with primary power source is connect by resistance R5, and the second light-coupled isolation output negative terminal is connected by resistance R6
The end OUT2；
The the first light-coupled isolation output plus terminal and the second light-coupled isolation output plus terminal and secondary power supply of light-coupled isolation chip G1
3.3V+ connection.
The beneficial effect of the content of present invention is:
(1) it unites when of the invention method, definite principle, RS-422 interface is the common communication interface of carrier rocket, using wide
It is general, technology maturation, high reliablity, as when unite flag transmission channel, when increasing cost without additional, and being capable of providing higher
System precision.RS-422 interface data transmission process issues " separation command " to aircraft from rocket and receives finger without mechanical movement
The time of order spreads smaller.
(2) use RS-422 interface RS-422 interface communication " separation command " as it is main when system mark, rocket and flight
Short-circuited conducting sleeve disconnects system mark when being used as spare in device separate connector, is mutually redundant, when RS-422 interface electricity in flight control computer
When road or short-circuited conducting sleeve Acquisition Circuit individually break down, system indicates when can still be acquired by another circuit, therefore improves and be
The reliability of system.
It can be started to control delay time for the different when different aircraft of system traffic sign placement, system mark when guaranteeing to pass through any
It determines after starting to control delay time, aircraft starts to control in defined time range, improves aircraft autonomous flight and starts to control the stage
Safety.
When through RS-422 interface communication transmission " separation command ", setting " start to control delay mark ", can resist due to
It starts to control the time caused by communication frame losing to delay, it is ensured that aircraft starts to control in defined time range, improves serious forgiveness.
(3) system mark, respectively flight control computer serial communication when providing 2 kinds of stage separation for aircraft flight control computer
When system mark with separate connector short-circuited conducting sleeve off-state detect when system indicate, be mutually redundant.The off-state of short-circuited conducting sleeve uses
The output switch parameter and On-off signal of aircraft flight control computer are detected from closed loop, and interface circuit flies control using aircraft and calculates
Machine primary power source ensure that the good compatibility of circuit as reference power supply.Short-circuited conducting sleeve passes through separation connection using continuous conductors
The socket end and plug end of device avoid the core wire hit of socket end and plug end grafting during airborne vibration, generate wrong
When system mark accidentally.Separate connector plug end separates the side separated using electromagnetism with mechanically decoupled redundancy with outlet section unlock
Formula improves and unlocks isolated reliability.
Detailed description of the invention
Bulk cargo sets electric interfaces and mechanical interface annexation figure when Fig. 1 is stage separation；
Fig. 2 is method flow diagram of uniting when stage separation；
Fig. 3 is short-circuited conducting sleeve Acquisition Circuit schematic diagram；
System method separates timing diagram when Fig. 4 is stage separation.
Specific embodiment
As shown in Figure 1, it includes: separate connector plug end 1, separation connection that bulk cargo, which is set, when stage separation flight control system
Device socket end 2, rocket flight control computer 3, aircraft flight control computer 4, separation bolt 5, unlock cable 8, the first short-circuited conducting sleeve 9,
Second short-circuited conducting sleeve 10, separate connector drawstring 11 and firing cable 12；Electromagnetism unlock is provided in separate connector plug end 1
Device and unlock pull rod.
It is linked together between rocket and aircraft by separating bolt 5, rocket flight control computer 3 passes through firing cable 12
It is connected with bolt 5 is separated, separation bolt 5 can be driven to detonate.After separating the detonation of bolt 5, rocket is separated with aircraft mechanical, fire
Arrow falls, aircraft freedom of entry motion state, and starts to control in defined time range.
It will be drawn outside the unlock pull rod being arranged in separate connector plug end 1, separate connector plug end 1 and separate connector
Socket end 2 becomes discrete state from inserting state.The electromagnetism unlock dress that unlock pull rod can be arranged in separate connector plug end 1
It is outer under the magneticaction set to draw, it can also be by being applied to outer under the external broach effect of unlock pull rod draw.
Rocket flight control computer 3 connects electromagnetic unlocking device by unlock cable 8.One end of separate connector drawstring 11 is solid
It being scheduled on rocket rocket body, the other end is fixed on unlock pull rod:
When electromagnetic unlocking device is effective, before separation bolt 5 detonates, rocket flight control computer 3 is unlocked by electromagnetism
It is drawn outside device driving unlock pull rod, realizes the unlock separation between separate connector plug end 1 and separate connector socket end 2；
When electromagnetic unlocking device failure, opposite position is generated after separation bolt 5 detonates, between rocket and aircraft
It moves, is driven by separate connector drawstring 11 and drawn outside unlock pull rod, realize separate connector plug end 1 and separate connector socket
Unlock separation between end 2；
Such mode can guarantee that separate connector plug end 1 and separate connector socket end 2 have the separation side of redundancy
Formula is avoided when electromagnetic unlocking device or drawstring individually break down, and separate connector can not separate.
The present apparatus can provide the when system mark of 2 kinds of redundancies to aircraft, and making aircraft, reliably the time is started to control in determination:
Communication between rocket flight control computer 3 and aircraft flight control computer 4 passes through the separation being plugged in together and connects
Device plug end 1 and separate connector socket end 2 realize, in separation as it is main when system mark；
After separate connector plug end 1 and the unlock separation of separate connector socket end 2, the first short-circuited conducting sleeve 9 and second is short
Road ring 10 is pulled off, and becomes open-circuit condition from state between short-circuited conducting sleeve Acquisition Circuit and short-circuited conducting sleeve power supply circuit, as standby
Used time system label.
It include short-circuited conducting sleeve power supply circuit and short-circuited conducting sleeve Acquisition Circuit, the first short-circuited conducting sleeve 9 and the in aircraft flight control computer 4
Two short-circuited conducting sleeves 10 are drawn from short-circuited conducting sleeve power supply circuit, enter separate connector plug end after passing through separate connector socket end 2
1, and turn back in separate connector plug end 1, it again passes through separate connector socket end 2 and is connected into short-circuited conducting sleeve Acquisition Circuit later.
Short-circuited conducting sleeve passes through the socket end and plug end of separate connector using continuous conductors, avoids the socket end in vibration processes and inserts
The hit of head end grafting core wire generates the when system mark of mistake.
Short-circuited conducting sleeve power supply is all made of aircraft flight control computer primary power source as reference power supply with Acquisition Circuit, ensure that
Short-circuited conducting sleeve input and the good compatibility of output circuit.Short-circuited conducting sleeve power supply circuit includes primary power source and current-limiting circuit, primary electricity
Source is that the first short-circuited conducting sleeve 9 and the second short-circuited conducting sleeve 10 are powered, and is arranged current limit circuit between primary power source and the first short-circuited conducting sleeve 9, one
Current-limiting circuit is also equipped between secondary source and the second short-circuited conducting sleeve 10.
As shown in figure 3, short-circuited conducting sleeve Acquisition Circuit includes resistance R1~R6, capacitor C1, C2 and light-coupled isolation chip G1, circuit
Collection terminal is IN1 and IN2, and output end is OUT1 and OUT2.
First short-circuited conducting sleeve 9 from the first collection terminal IN1 by resistance R1 be connected to the first optocoupler of light-coupled isolation chip G1 every
From input anode；Flying capcitor C1 between the first light-coupled isolation input anode and negative terminal of light-coupled isolation chip G1, while first
Light-coupled isolation input negative terminal with primary power source is connect by resistance R2, and the first light-coupled isolation output negative terminal is connected by resistance R3
First output end OUT1.
Second short-circuited conducting sleeve 10 from the second collection terminal IN2 by resistance R4 be connected to the second optocoupler of light-coupled isolation chip G1 every
From input anode；Flying capcitor C2 between the second light-coupled isolation input anode and negative terminal of light-coupled isolation chip G1, while second
Light-coupled isolation input negative terminal with primary power source is connect by resistance R5, and the second light-coupled isolation output negative terminal is connected by resistance R6
The end OUT2.
The the first light-coupled isolation output plus terminal and the second light-coupled isolation output plus terminal and secondary power supply of light-coupled isolation chip G1
3.3V+ connection.
The working principle of device:
Before stage separation, rocket realizes firm mechanical connection by separating bolt 5 with aircraft.Separate connector is inserted
Head end 1 and separate connector socket end 2 are in connection status, provide for rocket flight control computer 3 with aircraft flight control computer 4
Serial communication access.First short-circuited conducting sleeve 9 and the second short-circuited conducting sleeve 10 are in connection on state.
Stage separation starts, and rocket flight control computer 3 is mentioned by the separate connector of connection to aircraft flight control computer 4
For it is main when system mark；
Then, rocket flight control computer 3 drives electromagnetic unlocking device by unlock cable 8:
When electromagnetic unlocking device is effective, electromagnetic unlocking device, which generates magnetic force, will unlock drawing outside pull rod, make separate connector
Plug end 1 and the unlock separation of separate connector socket end 2, the first short-circuited conducting sleeve 9 are pulled off with the second short-circuited conducting sleeve 10, and short-circuited conducting sleeve is by leading
Logical state becomes open-circuit condition, and flight control computer 4 acquires the open-circuit condition of short-circuited conducting sleeve by short-circuited conducting sleeve Acquisition Circuit, as spare
When system mark；
When electromagnetic unlocking device is invalid, separate connector plug end 1 and separate connector socket end 2 are not unlocked.
Next, rocket flight control computer 3 by the driving separation bolt 5 of firing cable 12, makes to separate the detonation of bolt 5, it is real
Existing rocket and aircraft it is mechanically decoupled:
When electromagnetic unlocking device is effective, rocket flight control computer 3 is completed point before rocket is separated with aircraft mechanical
Unlock separation from connector plug end 1 and separate connector socket end 2；
When electromagnetic unlocking device is invalid, due to generating relative displacement between rocket and aircraft, separation connection is being tensed
Pulling force is generated after device drawstring 11 will unlock drawing outside pull rod, unlocks separate connector plug end 1 and separate connector socket end 2 and divides
From the first short-circuited conducting sleeve 9 is pulled off with the second short-circuited conducting sleeve 10, becomes open-circuit condition from state, flight control computer 4 passes through short circuit
Ring Acquisition Circuit acquire short-circuited conducting sleeve open-circuit condition, as it is spare when system mark.
After rocket is separated with aircraft mechanical, rocket falls, aircraft freedom of entry motion state, and according to when system indicate
It is started to control in defined time range.
As shown in Fig. 2, bulk cargo is set when being based on above-mentioned stage separation flight control system, the present invention proposes a kind of stage separation
It unites method, comprises the following steps that when flight control system high-precision
(1) after rocket enters separation process, at the T0 moment, rocket flight control computer is sent to aircraft flight control computer to be divided
From director data frame；T0 indicates 0 moment of separation timing determined by rocket flight control computer, enters separation process in this time.
(2) at the T1 moment, rocket flight control computer issues electromagnetism unlock to separate connector plug end by unlock cable
Instruction；At the time of T1 indicates that rocket flight control computer issues electromagnetism unlock instruction to separate connector plug end, this time is by fire
The setting of arrow flight control computer, T1 is after T0；
(3) aircraft flight control computer after the power-up, persistently judges separation command data frame, effective when receiving for the first time
When separation command data frame, (4) are entered step；When not receiving separation command data frame or separation command data frame is invalid,
Enter step (5)；
Delay time is started to control according to the delay mark determination of starting to control received in separation command data frame for the first time, under
Table:
Wherein Timer_1 is that aircraft flight control computer receives first frame separation command to the delay started to control, and T_422 is
Rocket flight control computer issues the sending cycle of separation command data frame, and n is received for aircraft flight control computer and efficiently separated
The serial number of instruction.
(4) aircraft flight control computer is determined according to the delay mark that starts to control received in separation command data frame for the first time
When controlling delay time, and starting to start to control delay meter, (9) are entered step later；
(5) aircraft flight control computer after the power-up, persistently judges whether electromagnetic unlocking device work is normal, if normal,
(6) are then entered step, (10) are entered step if abnormal；
(6) aircraft flight control computer after the power-up, persistently judges the off-state of short-circuited conducting sleeve, if two-way short-circuited conducting sleeve is disconnected
It opens, then enters step (7), otherwise return step (3)；
(7) aircraft flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects, if reliable disconnect, enters step
(8), otherwise return step (3)；
(8) Timer_2 when aircraft flight control computer starts to start to control delay meter；
When Timer_2 is that electromagnetic unlocking device is working properly when starting to control delay meter, two-way short-circuited conducting sleeve is reliably disconnected to flight
The delay that device starts to control is set by aircraft flight control computer；
(9) at the T2 moment, rocket flight control computer issues fuze to separation bolt by firing cable, separates bolt
It disconnects, enters step (13) later；
At the time of T2 indicates that rocket flight control computer issues fuze to separation bolt, this time flies control by rocket and calculates
Machine setting, T2 is after tl.
(10) at the T2 moment, rocket flight control computer issues fuze to separation bolt by firing cable, separates spiral shell
Bolt disconnects, and aircraft flight control computer after the power-up, persistently judges the off-state of short-circuited conducting sleeve, if two-way short-circuited conducting sleeve disconnects,
(11) are then entered step, otherwise return step (3)；
(11) aircraft flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects, if reliable disconnect, enters step
(12), otherwise return step (3)；
Aircraft flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects specifically: flight control computer collects short circuit
The time that ring disconnects is greater than preset time threshold Timer_DIO.
(12) Timer_3 when aircraft flight control computer starts to start to control delay meter enters step (13) later；
When Timer_3 is that electromagnetic unlocking device work is abnormal when starting to control delay meter, two-way short-circuited conducting sleeve is reliably disconnected to winged
The delay that row device starts to control is set by aircraft flight control computer；Timer_2 > Timer_3.
(13) terminate and start to control when aircraft flight control computer starts to control delay meter.
Below with reference to Fig. 4, above-mentioned steps are described in detail.
Code name meaning in figure is as follows:
1) process code name
A) A1: system mark (RS-422 interface separation command) carries out starting to control delay when using main；
B) A2_1: when electromagnetic unlocking device is effective in separate connector plug end 1, system mark (short circuit when backup is used
Ring ON OFF state) it carries out starting to control delay；
C) A2_1: when electromagnetic unlocking device fails in separate connector plug end 1, system mark (short circuit when backup is used
Ring ON OFF state) it carries out starting to control delay.
2) intrinsic electrical equipment communications or mechanical action delay
A) the communications delay of Delay_422:RS-422 interface " separation command " data frame, in the same flow of task
In, the delay of each data frame is equal；
B) Delay_DIO: rocket flight control computer 3 sends " electromagnetism unlock instruction ", until the first short-circuited conducting sleeve 9 and the second short circuit
The delay that ring 10 is fully disconnected；
C) Delay_WK: rocket flight control computer 3 send " electromagnetism unlock instruction ", until separate connector plug end 1 with
The delay that 2 shell of separate connector socket end is kept completely separate；
D) Delay_Bomb: rocket flight control computer 3 sends " fuze ", until the delay that separation bolt 5 disconnects.
In conjunction with Fig. 2 and Fig. 4, the execution step correspondence of process A1 is as follows in figure:
1) step 1: at the T0 moment, rocket flight control computer 3 enters separation process, sends RS-422 interface " separation command "
Data frame, sending cycle T_422, with " separation command state " and " starting to control delay to indicate " two in every frame " separation command "
Partial content, see above in table；
2) step 2: at the T1 moment, to the sending of separate connector plug end 1, " electromagnetism unlock refers to rocket flight control computer 3
It enables "；
3) step 3: at the S0 moment, aircraft flight control computer 4 collects effective RS-422 interface " separation finger for the first time
Enable ", it is discrete state by " the separation command state " in decision instruction, " start to control delay mark " normally, enters step 4, and
Ignoring subsequent " separation command ", (since RS-422 interface communication is there are the possibility of frame losing and error code, aircraft flies control meter
The time that calculation machine 4 receives effective " separation command " is S0=Delay_422+ (n-1) × T_422, indicates entry into separation process
Afterwards, preceding n-1 " separation command " Pending The Entry Into Forces that rocket flight control computer 3 issues)；
4) step 4: for aircraft flight control computer 4 according to " starting to control delay mark ", delay time Timer_1- is started to control in determination
(n-1) × T_422, and when starting to start to control delay meter, see above in table, subsequently enter step 9；
5) step 9: at the T2 moment, rocket flight control computer 3 issues " fuze " to separation bolt 5, at the S2 moment, divides
It is disconnected from bolt 5, aircraft freedom of entry motion state, S2=T2+Delay_Bomb；
6) step 13: at the S3 moment, aircraft is started to control, S3=Delay_422+Timer_1.
In conjunction with Fig. 2 and Fig. 4, the execution step correspondence of process A2_1 is as follows in figure:
1) steps 1 and 2 are identical as process A1；
2) step 3: aircraft flight control computer 4 does not collect effective RS-422 interface " separation command ", enters step
5；
3) step 5: electromagnetic unlocking device is effective, enters step 6；
4) step 6: at the S1_A moment, aircraft flight control computer 4 collects the first short-circuited conducting sleeve 9 and the second short-circuited conducting sleeve 10 is complete
Portion disconnects, and S1_A=T1+Delay_DIO enters step 7；
5) step 7: at the S1_B moment, aircraft flight control computer 4 confirms that the first short-circuited conducting sleeve 9 and the second short-circuited conducting sleeve 10 are reliable
It disconnects, S1_B=T1+Delay_DIO+Timer_DIO, starts to start to control delay timing Timer_2；At the S1_C moment, separation connection
Device plug (1) is kept completely separate with socket (2) structural housing, S1_C=T1+Delay_WK；Subsequently enter step 9；
6) step 9 is identical as process A1；Before entering step 13, separate connector plug end 1 and separate connector socket
End 2 complete electrically with it is mechanically decoupled；
7) step 13: at the S3 moment, aircraft (14) is started to control, S3=T1+Delay_DIO+Timer_DIO+Timer_2.
In conjunction with Fig. 2 and Fig. 4, the execution step correspondence of process A2_2 is as follows in figure:
1) step 1~3 are identical as process A1；
2) step 5: electromagnetic unlocking device failure enters step 10；
3) step 10: at the T2 moment, rocket flight control computer 3 issues " fuze " to separation bolt 5；At the S2 moment,
It separates bolt 5 to disconnect, aircraft freedom of entry motion state, S2=T2+Delay_Bomb；At the S2_A moment, aircraft flies control
Computer 4 collects the first short-circuited conducting sleeve 9 and the second short-circuited conducting sleeve 10 is all off, S2_A=T2+Delay_Bomb+Delay_DIO,
Enter step 11；
4) step 11: at the S2_B moment, aircraft flight control computer 4 confirms that the first short-circuited conducting sleeve 9 and the second short-circuited conducting sleeve 10 can
By disconnecting, S2_B=T2+Delay_Bomb+Delay_DIO+Timer_DIO starts to start to control delay timing Timer_3；In S2_C
Moment, separate connector plug end 1 are kept completely separate with 2 structural housing of separate connector plug end socket, S2_C=S2+Delay_
WK；Subsequently enter step 13；
5) step 13: at the S3 moment, aircraft 14 is started to control, S3=T2+Delay_Bomb+Delay_DIO+Timer_DIO+
Timer_3。
In the design process of separation timing, to guarantee that separation process is safe and reliable, need to consider following constraint condition:
1) rocket flight control computer 3 sends the time T0 of RS-422 interface " separation command ", sends separate connector " electromagnetism
The time T1 of unlock instruction ", the time T2 for sending " fuze ", there is T0≤T1 < T2；
2) separation bolt 5 disconnect time started to control the time earlier than aircraft, i.e. S2 < S3, wherein S3-S2 be aircraft with
After Separation, aircraft in a free state without control the time, design separate timing when, with aircraft be detached from rocket flow field
The unstability time of time and aircraft without control state of interference range as input condition, determines the time range without control.
3) receive do not unite simultaneously indicate when, aircraft flight control computer 4 starts to control the time of delay, there is Timer1 >
Timer2 > Timer3.
Embodiment:
When using RS-422 interface " separation command " as time tag, the delay of transmission is instructed to be made of 3 parts:
1) delay 1: rocket flight control computer enters separation process, until starting to send RS-422 interface " separation command " data
Frame, " delay 1 " most short 0, up to the rocket flying-controlled box cycle of operation of leveling off to；
2) delay 2: rocket flight control computer starts to send RS-422 interface " separation command " data frame first byte, until flight
By data frame, all deposit serial ports receives buffer area to device flight control computer, and " delay 2 " is fixed value, and the time is " separation command " number
According to frame total bit divided by RS-422 interface Transmission bit rate；
3) delay 3: aircraft flight control computer starts to read the data that serial ports receives buffer area, until verification, extraction " separate
Instruction ", and start to start to control delay, " delay 3 " most short 0, up to the aircraft flying-controlled box cycle of operation of leveling off to；
By RS-422 interface communication principle it is found that " delay 1 ", " delay 2 ", " delay 3 " are mutually indepedent.
Assuming that the rocket flying-controlled box cycle of operation is 10ms, then the range of " delay 1 " is 0~10ms.
Assuming that " separation command " data frame total bytes are 64 bytes (704), RS-422 interface Transmission bit rate is
115200bps, then " delay 2 " is 6.2ms.
Assuming that the aircraft flying-controlled box cycle of operation is 10ms, then the range of " delay 3 " is 0~10ms.
Aircraft receive the communication delay of rocket " separation command " be " delay 1 ", the sum of " delay 2 " and " delay 3 ", it is most short
Level off to 6.2ms, up to 26.2ms.Therefore the scattered band of " separation command " transmission time be less than 20ms, i.e., rocket and fly
The sum of row device flying-controlled box cycle of operation, precision of uniting when having very high.Under conditions of flight control computer hardware performance meets,
By reducing the cycle of operation of flying-controlled box, the time that can reduce instruction transmission is spread, precision of uniting when obtaining higher.
The present invention is not described in detail content and is known to the skilled person technology.
Claims (10)
1. a kind of method of uniting when stage separation flight control system high-precision, it is characterised in that steps are as follows:
(1) after rocket enters separation process, at the T0 moment, rocket flight control computer sends separation finger to aircraft flight control computer
Enable data frame；
(2) at the T1 moment, rocket flight control computer issues electromagnetism unlock instruction to separate connector plug end by unlock cable；
(3) aircraft flight control computer after the power-up, persistently judges separation command data frame, efficiently separates when receiving for the first time
When director data frame, (4) are entered step；When not receiving separation command data frame or separation command data frame is invalid, enter
Step (5)；
(4) aircraft flight control computer prolongs according to determining start to control of delay mark of starting to control received in separation command data frame for the first time
The slow time, and when starting to start to control delay meter, (9) are entered step later；
(5) aircraft flight control computer after the power-up, persistently judge electromagnetic unlocking device work it is whether normal, if normal, then into
Enter step (6), (10) are entered step if abnormal；
(6) aircraft flight control computer after the power-up, persistently judges the off-state of short-circuited conducting sleeve, if two-way short-circuited conducting sleeve disconnects,
(7) are then entered step, otherwise return step (3)；
(7) aircraft flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects, if reliable disconnect, enters step (8), no
Then return step (3)；
(8) Timer_2 when aircraft flight control computer starts to start to control delay meter；
(9) at the T2 moment, rocket flight control computer issues fuze to separation bolt by firing cable, and separation bolt is disconnected
It opens, enters step (13) later；
(10) at the T2 moment, rocket flight control computer issues fuze to separation bolt by firing cable, and separation bolt is disconnected
It opens, aircraft flight control computer after the power-up, persistently judges the off-state of short-circuited conducting sleeve, if two-way short-circuited conducting sleeve disconnects, into
Enter step (11), otherwise return step (3)；
(11) aircraft flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects, if reliable disconnect, enters step (12),
Otherwise return step (3)；
(12) Timer_3 when aircraft flight control computer starts to start to control delay meter enters step (13) later；
(13) terminate and start to control when aircraft flight control computer starts to control delay meter.
2. method of uniting when a kind of stage separation flight control system high-precision according to claim 1, it is characterised in that: root
Delay time is started to control according to the delay mark determination of starting to control received in separation command data frame for the first time, referring to following table:
Wherein Timer_1 is that aircraft flight control computer receives first frame separation command to the delay started to control, and T_422 is rocket
Flight control computer issues the sending cycle of separation command data frame, and n is received for aircraft flight control computer and efficiently separated instruction
Serial number.
3. method of uniting when a kind of stage separation flight control system high-precision according to claim 1, it is characterised in that: T0
It indicates 0 moment of separation timing determined by rocket flight control computer, enters separation process in this time.
4. method of uniting when a kind of stage separation flight control system high-precision according to claim 1, it is characterised in that: T1
At the time of indicating that rocket flight control computer issues electromagnetism unlock instruction to separate connector plug end, this time flies control meter by rocket
The setting of calculation machine, T1 is after T0；T2 indicate rocket flight control computer to separation bolt issue fuze at the time of, this time by
The setting of rocket flight control computer, T2 is after tl.
5. method of uniting when a kind of stage separation flight control system high-precision according to claim 1, it is characterised in that: fly
Row device flight control computer judges whether two-way short-circuited conducting sleeve reliably disconnects specifically: flight control computer collect short-circuited conducting sleeve disconnection when
Between be greater than preset time threshold Timer_DIO.
6. method of uniting when a kind of stage separation flight control system high-precision according to claim 1, it is characterised in that: rise
When Timer_2 is that electromagnetic unlocking device is working properly when controlling delay meter, what two-way short-circuited conducting sleeve was reliably disconnected to that aircraft starts to control prolongs
When, it is set by aircraft flight control computer；When Timer_3 is that electromagnetic unlocking device work is abnormal when starting to control delay meter, two-way
Short-circuited conducting sleeve is reliably disconnected to the delay that aircraft starts to control, and is set by aircraft flight control computer；Timer_2 > Timer_3.
7. method of uniting when a kind of stage separation flight control system high-precision according to claim 1, it is characterised in that: should
Bulk cargo sets realization when system method is based on stage separation flight control system when high-precision of uniting when stage separation flight control system, should
It includes: separate connector plug end (1), separate connector socket end (2), rocket that bulk cargo, which is set, when stage separation flight control system
Flight control computer (3), aircraft flight control computer (4), separation bolt (5), unlock cable (8), the first short-circuited conducting sleeve (9), second
Short-circuited conducting sleeve (10), separate connector drawstring (11) and firing cable (12)；Separate connector plug end is provided with electromagnetism in (1)
Tripper and unlock pull rod；
It is linked together between rocket and aircraft by separating bolt (5), rocket flight control computer (3) passes through firing cable
(12) with separate bolt (5) connection, communication between rocket flight control computer (3) and aircraft flight control computer (4) passes through slotting
The separate connector plug end (1) being connected together and separate connector socket end (2) are realized；Rocket flight control computer (3) passes through
The electromagnetic unlocking device being arranged in cable (8) connection separate connector plug end (1) is unlocked, driving unlock pull rod carries out separation company
Connect the separation unlock between device plug end (1) and separate connector socket end (2)；One end of separate connector drawstring (11) is fixed
On rocket rocket body, the other end is fixed on unlock pull rod；
It include short-circuited conducting sleeve power supply circuit and short-circuited conducting sleeve Acquisition Circuit, the first short-circuited conducting sleeve (9) and the in aircraft flight control computer (4)
Two short-circuited conducting sleeves (10) are drawn from short-circuited conducting sleeve power supply circuit, are passed through separate connector socket end (2) and are inserted afterwards into separate connector
Head end (1), and turn back in separate connector plug end (1), it again passes through separate connector socket end (2) and is connected into short-circuited conducting sleeve later
Acquisition Circuit.
8. method of uniting when a kind of stage separation flight control system high-precision according to claim 7, it is characterised in that: when
When electromagnetic unlocking device is effective, before separation bolt (5) detonation, unlock pull rod is driven to realize separation by electromagnetic unlocking device
Separation unlock between connector plug end (1) and separate connector socket end (2)；
When electromagnetic unlocking device failure, after separation bolt (5) detonation, relative displacement is generated between rocket and aircraft,
Unlock pull rod is driven to realize separate connector plug end (1) and separate connector socket end by separate connector drawstring (11)
(2) the separation unlock between；
After separate connector plug end (1) and separate connector socket end (2) separation, the first short-circuited conducting sleeve (9) and the second short-circuited conducting sleeve
(10) it is pulled off, open-circuit condition is become from state between short-circuited conducting sleeve Acquisition Circuit and short-circuited conducting sleeve power supply circuit.
9. method of uniting when a kind of stage separation flight control system high-precision according to claim 7, it is characterised in that: electricity
Magnetic tripper is electromagnet, and after being powered by unlock cable (8), electromagnet generates magnetic force and pulls unlock pull rod；First short circuit
Ring (9) and the second short-circuited conducting sleeve (10) are mutually redundant.
10. method of uniting when a kind of stage separation flight control system high-precision according to claim 7, it is characterised in that:
Short-circuited conducting sleeve power supply circuit includes primary power source and current-limiting circuit, and primary power source is the first short-circuited conducting sleeve (9) and the second short-circuited conducting sleeve (10)
Power supply, is arranged current limit circuit, between primary power source and the second short-circuited conducting sleeve (10) between primary power source and the first short-circuited conducting sleeve (9)
Current limit circuit is set；
Short-circuited conducting sleeve Acquisition Circuit includes resistance R1~R6, capacitor C1, C2 and light-coupled isolation chip G1, circuit collection terminal be IN1 with
IN2, output end are OUT1 and OUT2；
First short-circuited conducting sleeve (9) is connected to the first light-coupled isolation of light-coupled isolation chip G1 from the first collection terminal IN1 by resistance R1
Input anode；Flying capcitor C1 between the first light-coupled isolation input anode and negative terminal of light-coupled isolation chip G1, while the first light
Coupling isolation input negative terminal with primary power source is connect by resistance R2, and the first light-coupled isolation exports negative terminal and passes through resistance R3 connection the
One output end OUT1；
Second short-circuited conducting sleeve (10) is connected to the second light-coupled isolation of light-coupled isolation chip G1 from the second collection terminal IN2 by resistance R4
Input anode；Flying capcitor C2 between the second light-coupled isolation input anode and negative terminal of light-coupled isolation chip G1, while the second light
Coupling isolation input negative terminal with primary power source is connect by resistance R5, and the second light-coupled isolation output negative terminal is connected by resistance R6
The end OUT2；
The the first light-coupled isolation output plus terminal and the second light-coupled isolation output plus terminal and secondary power supply 3.3V+ of light-coupled isolation chip G1
Connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910585923.0A CN110297481B (en) | 2019-07-01 | 2019-07-01 | High-precision time system method of interstage separation flight control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910585923.0A CN110297481B (en) | 2019-07-01 | 2019-07-01 | High-precision time system method of interstage separation flight control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110297481A true CN110297481A (en) | 2019-10-01 |
| CN110297481B CN110297481B (en) | 2024-03-15 |
Family
ID=68029728
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910585923.0A Active CN110297481B (en) | 2019-07-01 | 2019-07-01 | High-precision time system method of interstage separation flight control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110297481B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979753A (en) * | 2019-11-01 | 2020-04-10 | 中国科学院光电研究院 | Aerostat carries on planet sampling reentry module and retrieves experimental electrical system |
| CN111089516A (en) * | 2019-12-03 | 2020-05-01 | 北京星际荣耀空间科技有限公司 | Solid carrier rocket interstage separation method, device and equipment |
| CN111756361A (en) * | 2020-07-06 | 2020-10-09 | 北京星际荣耀空间科技有限公司 | Time scale generating circuit and time scale distributing system of multistage carrier rocket |
| CN113324445A (en) * | 2020-02-28 | 2021-08-31 | 星河动力(北京)空间科技有限公司 | Rocket rapid separation time sequence design method |
| CN113682499A (en) * | 2021-08-10 | 2021-11-23 | 北京空间飞行器总体设计部 | Spacecraft multi-space separation method |
| CN114727165A (en) * | 2022-06-09 | 2022-07-08 | 北京航天驭星科技有限公司 | Method and device for determining takeoff time of rocket based on telemetering data |
| CN116499321A (en) * | 2023-02-03 | 2023-07-28 | 彭昆雅 | Separation control method, device and equipment for solid binding carrier rocket booster |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6622971B1 (en) * | 2001-05-22 | 2003-09-23 | Lockheed Martin Corporation | Adapter for connecting rocket stages |
| KR101528903B1 (en) * | 2015-01-12 | 2015-06-12 | 엘아이지넥스원 주식회사 | Apparatus for controlling separating flight vehicle using time delay |
| CN104895700A (en) * | 2015-04-15 | 2015-09-09 | 北京航天自动控制研究所 | Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion |
| CN106557022A (en) * | 2015-09-29 | 2017-04-05 | 上海宇航系统工程研究所 | A kind of carrier rocket redundancy sequential control system |
| CN109556871A (en) * | 2018-12-13 | 2019-04-02 | 西安航天动力研究所 | A kind of liquid-propellant rocket engine Timing Signal detection system and method |
-
2019
- 2019-07-01 CN CN201910585923.0A patent/CN110297481B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6622971B1 (en) * | 2001-05-22 | 2003-09-23 | Lockheed Martin Corporation | Adapter for connecting rocket stages |
| KR101528903B1 (en) * | 2015-01-12 | 2015-06-12 | 엘아이지넥스원 주식회사 | Apparatus for controlling separating flight vehicle using time delay |
| CN104895700A (en) * | 2015-04-15 | 2015-09-09 | 北京航天自动控制研究所 | Low delay ignition confirmation system and confirmation method applied to rocket ground information fusion |
| CN106557022A (en) * | 2015-09-29 | 2017-04-05 | 上海宇航系统工程研究所 | A kind of carrier rocket redundancy sequential control system |
| CN109556871A (en) * | 2018-12-13 | 2019-04-02 | 西安航天动力研究所 | A kind of liquid-propellant rocket engine Timing Signal detection system and method |
Non-Patent Citations (2)
| Title |
|---|
| PHILIP C. CALHOUN: "《Spacecraft alignment determination and control for dual spacecraft precision formation flying》", 《ACTA ASTRONAUTICA》, 31 December 2018 (2018-12-31), pages 349 * |
| 李慧通: "《新型级间分离方案设计与仿真》", 《固体火箭技术》, no. 4, 15 August 2016 (2016-08-15), pages 580 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979753A (en) * | 2019-11-01 | 2020-04-10 | 中国科学院光电研究院 | Aerostat carries on planet sampling reentry module and retrieves experimental electrical system |
| CN111089516A (en) * | 2019-12-03 | 2020-05-01 | 北京星际荣耀空间科技有限公司 | Solid carrier rocket interstage separation method, device and equipment |
| CN113324445A (en) * | 2020-02-28 | 2021-08-31 | 星河动力(北京)空间科技有限公司 | Rocket rapid separation time sequence design method |
| CN111756361A (en) * | 2020-07-06 | 2020-10-09 | 北京星际荣耀空间科技有限公司 | Time scale generating circuit and time scale distributing system of multistage carrier rocket |
| CN113682499A (en) * | 2021-08-10 | 2021-11-23 | 北京空间飞行器总体设计部 | Spacecraft multi-space separation method |
| CN114727165A (en) * | 2022-06-09 | 2022-07-08 | 北京航天驭星科技有限公司 | Method and device for determining takeoff time of rocket based on telemetering data |
| CN116499321A (en) * | 2023-02-03 | 2023-07-28 | 彭昆雅 | Separation control method, device and equipment for solid binding carrier rocket booster |
| CN116499321B (en) * | 2023-02-03 | 2024-01-23 | 彭昆雅 | Separation control method, device and equipment for solid binding carrier rocket booster |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110297481B (en) | 2024-03-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110297481A (en) | It unites when a kind of stage separation flight control system high-precision method | |
| CN104895700B (en) | A kind of low time delay ignition confirming system and confirmation method of arrow ground information fusion | |
| EP1119693B1 (en) | Exciter controlled by full authority digital electronic control (fadec) system | |
| CN105487093B (en) | For recovering the device and method for the unmanned plane that falls | |
| CN109795720B (en) | Detonation control design method of initiating explosive device for spacecraft cabin separation | |
| CN109204893B (en) | Design method of high-reliability spacecraft and carrier rocket electrical interface | |
| CN108945530A (en) | A kind of satellite and the rocket separation Design of Signal and its analogy method | |
| CN204215176U (en) | A kind of aircraft security self-destruction control circuit | |
| CN109683532A (en) | A kind of steering engine and more steering engine controllers and unmanned aerial vehicle control system | |
| CN103926854A (en) | Contactor control method and contactor combination circuit control method | |
| CN107112779B (en) | Battery, battery management system, mobile platform and electrical equipment | |
| CN116222323A (en) | Time sequence signal self-test system on carrier rocket | |
| CN112393653A (en) | Electronic detonator blasting control system for improving anti-interference performance | |
| CN107994669A (en) | A kind of missile-borne microsatellite energy control system | |
| CN106681302A (en) | Solid state relay self-holding device for missile-borne power distribution and test control method thereof | |
| CN112414236A (en) | Electronic detonator for improving communication reliability | |
| CN109855488B (en) | MOEMS fuse safety system | |
| CN210072407U (en) | Interstage separation flight control system time system device | |
| CN104583077B (en) | It is suitable for cutting off the circuit of the supply of electric power of electrical equipment and including the system of this circuit | |
| CN110287050B (en) | Grid rudder autonomous power distribution time sequence control device | |
| CN104155889B (en) | high-precision switch controller | |
| CN110442057A (en) | A kind of the delayed exploding control system and control method of fire extinguishing bomb | |
| CN207884608U (en) | A kind of missile-borne controller takes off signal receiving circuit | |
| CN112556521A (en) | Electronic detonator for improving communication anti-interference performance | |
| CN206180638U (en) | Mobile platform |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |