CN110515296A - A kind of inexpensive electrical system suitable for reurnable booster - Google Patents
A kind of inexpensive electrical system suitable for reurnable booster Download PDFInfo
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- CN110515296A CN110515296A CN201910786612.0A CN201910786612A CN110515296A CN 110515296 A CN110515296 A CN 110515296A CN 201910786612 A CN201910786612 A CN 201910786612A CN 110515296 A CN110515296 A CN 110515296A
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- G—PHYSICS
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
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Abstract
Present disclose provides a kind of reurnable booster electrical system, including multilevel system, every grade of system includes the first bus, the second bus, several nodes, and each node is connect with the first bus, the second bus simultaneously；First bus of adjacent two-stage system is connected with each other via separate connector；Second bus of adjacent two-stage system is connected with each other via separate connector；Data exchange is synchronized with Fixed Time Interval between each node.Each node can connect independent main website, and spare main website detects that main website is lost, and can start to take over control, and after realizing separation, each section can still be worked with complete independently, so that the recycling for rocket after separation provides condition.The disclosure additionally provides a kind of carrier rocket using the electrical system.The system architecture not only has the advantages that high bandwidth, high real-time, highly reliable, easy extension, but also bus supports main website to switch online, and transplanting is convenient, configures simple and flexible, is very suitable to recycling system Rocket Electrical System.
Description
Technical field
This disclosure relates to carrier rocket field more particularly to a kind of electrical system of low cost suitable for reurnable booster
System.
Background technique
Carrier rocket electrical system is the core system of carrier rocket, be responsible for carrier rocket signal acquisition, gesture stability, when
Sequence instruction is outputed, control instruction executes etc., needs to meet the requirement such as high reliablity, strong real-time.The direct shadow of electrical system framework
Ring the comprehensive performance and reliability of carrier rocket.
Currently, domestic active service carrier rocket electrical system is not recyclable framework, electrical system is mostly used without total wire body
System or dual redundant 1553B bus system, computer is installed in Upper Stage on navigation device, arrow, using primary silver zinc battery
Or thermal cell power supply, electric control system and Electrical Measurement System are mutually indepedent, after rocket lower stage engine cutoff and above
Grade separation is fallen after lower stage separation without control state.
By taking certain domestic active service carrier rocket electrical system as an example, electrical system includes control system and measuring system.Control
System processed uses 1553B bus system, and computer completes navigation, guidance and Attitude control equation fortune as control core on arrow
It calculates and 1553B bus management, configuration distributors and servo controller at different levels is controlled for power supply and distribution and servo mechanism.Measuring system
By RS422 interface control system digital quantity telemetry intelligence (TELINT), pass through at different levels non-of the module collection of gathering and editing of standardized designs
Digital information and total environment parameter.
Since domestic active service mainstream carrier rocket not can be recycled, electrical system framework does not also support recyclable repetition
It uses.Although New Launch use 1553B bus system, electrical system reliability enhancing, quality mitigate, arrow interface subtract
It is few, but since domestic carrier rocket design of electrical system payes attention to reliability, ignorance economy, cost is still higher.
Foreign Launch Vehicles type is more, and the framework that electrical system uses is with their own characteristics.Mitsubishi Corporation of Japan H-2A delivery
Rocket is cluster two-stage rocket, and 53 meters of overall length, diameter 4m, electrical system uses Integration Design, and electrical system uses two
1553B bus is realized wherein arrow of the 1553B bus for the arrow of level-one to carry computer and second level carries computer communication
The communication such as test data, control instruction and timing, arrow of another 1553B bus for second level carry computer and inertia measurement list
Member communication, is transmitted for inertia test data.H-2A carrier rocket improves system reliability using 1553B bus mode, has
There are the characteristics of simplified strong real-time, structure, light weight, but 1553B bus higher cost, the economy of electrical system is insufficient, and
Do not have recyclable function.
SpaceX company, the U.S. starts to walk relatively early on reurnable booster, is the most well-known public affairs of our times commercial launch
Department and our times uniquely realize the company of rocket utilization and recycle, and 9 heavy rocket of falcon repeatedly recycles level-one,
But the electrical system framework related data announced is less, is found out according to limited data, and falcon rocket has used triple redundance rrow machine,
Bus uses switch type redundant network communication structure, and rocket mainly passes through two computers and controlled, and one is flight control
Computer, in the instrument room on second level top, another is engine control computer, is mounted on level-one.Flight control meter
Calculation machine is connect with ground control system by standard ethernet, hardware and software needed for simplifying rocket.9 heavy rocket of falcon
With preferable economy, utilization and recycle is can be achieved in booster, core grade, and less due to announcing data, electrical system is specific
Bus architecture and the composition still inaccurate understanding in the situation external world.
Currently, the generally existing following technical problem of the prior art:
1) framework bus system can be recycled: electrical system 1553B bus is one master and multiple slaves formula, lower stage separation on traditional arrow
Afterwards due to can not achieve bus control right adapter tube, cause to cannot achieve autonomous control from bus system, furthermore 1553B bus is logical
News rate is 1Mbps/s, and the application scenarios big for equipment complicated composition, communication data amount on arrow, bus bandwidth cannot expire
Foot.
2) framework forms: the flight controller and combined navigation device of electrical system are respectively positioned on Upper Stage instrument on traditional arrow
Cabin is the control core of entire rocket, and lower stage is not equipped with flight controller and combined navigation device, and battery is downward from Upper Stage
Face grade power supply, this framework composition are unable to satisfy reurnable booster lower stage recovery flight control, power demand.
Summary of the invention
At least one of in order to solve the above-mentioned technical problem, present disclose provides a kind of inexpensive electrical systems to support
After Separation, rockets at different levels still are able to effectively control, and reach the technical effect of rocket recycling, and the technical effect of the disclosure is adopted
It is realized with following technical scheme:
A kind of low cost electrical system, including multilevel system, every grade of system includes the first bus, the second bus, several
Node, each node are connect with first bus and second bus simultaneously；
First bus of adjacent two-stage system is connected with each other by separate connector；Second bus of adjacent two-stage system is borrowed
It is connected with each other by separate connector；
Data exchange is synchronized with Fixed Time Interval between each node.
Further, each node is connected with each other by the first bus and the first exchanger；Each node is logical simultaneously
It crosses the second bus and the second exchanger is connected with each other.
Further, each node is connect by interface selector with the first bus and the second bus.
A kind of inexpensive electrical system suitable for carrier rocket, the electrical system including any of the above-described；Every grade of system
Flight controller, combined navigation device, servo mechanism and distributor are connected with by each node；Have and only any level-one
Flight controller is in running order；The flight controller of off working state detects that the flight controller of previous priority sequence is logical
When news truncation or failure, start flight controller according to sequence.
Further, the multilevel system includes primary system and level two, and the servo mechanism of primary system includes 4
Actuator, the servo mechanism of level two include 2 actuator.
Further, the multilevel system includes primary system and level two, and the level two is connected by node
There is attitude control power device.
Further, the systems at different levels also have telemetering equipment, and the telemetering equipment includes gather and edit module and transmitting mould
Block.
A kind of inexpensive electrical system suitable for carrier rocket includes load device and above-mentioned Rocket Electrical System, goes back
Including connect the load device with the second separate connector of the level two, connect the connection that falls off of the primary system
Device.
Meanwhile present disclose provides a kind of courses of work applied to above-mentioned carrier rocket comprising the steps of:
Level-one flight step: after aircraft first class engine blasts off, second level flight controller is as bus master pair
Bus is scheduled control level-one inflight phase flight；Level-one telemetering equipment is acquired sensor information；When meeting I and II
After separation condition, the second level flight controller issues order, the igniting of level-one retro-rocket and I and II stage separation, terminates
Level-one flight；
Level-one recycling step: level-one flight controller monitors that main website is lost in bus, automatically switches to main website, and adapter tube is total
Line traffic control, and execute exhausting section Row control；
Second level flight step: second level flight controller outputs second level engine ignition, and second level flight controller continues to receive
Second level combines navigation data；Aircraft flight is to predetermined position, and after meeting second level engine cutoff condition, primary flight controls are opened
Second level shutdown command out；
Load separating step: after second level engine cutoff, second level flight controller control attitude control engine, which accurately adjusts, to fly
Row device posture outputs payload separation command after reaching condition of entering the orbit；
Secondary recovery step: after load separation, second level flight controller controls attitude control power device and carries out pose adjustment, so
Control second level engine ignition again afterwards；Implement reclaimer.
Compared with prior art, the beneficial effect of the disclosure is:
The technical solution of the disclosure includes multilevel system, and each node of every grade of system can connect independent main website,
Spare main website detects that its preferential main website is fed back without information, can start to take over control, after realizing separation, each section
It can still be worked with complete independently.To provide condition for the recycling of the aircraft after separation.
Dual redundant industry ethernet system, supporting bus principal and subordinate are online in real time using high speed for the electrical system bus of the disclosure
Switching can independently switch bus master controller after lower stage separation, adapter tube bus marco, and communication speed maximum is reachable
1000Mbps/s, have the characteristics that with a large bandwidth and at a high rate, highly reliable, Yi Yizhi, low cost, recyclable fortune can be met very well
Carry the bussing technique demand of rocket.
The electrical system of the disclosure is equipped with flight controller and navigation device rocket is at different levels, and systems at different levels independently supply
Electricity controls rocket flight by Upper Stage flight controller before not separating, and Upper Stage is continued to fly by flight controller control after separation
Row, lower stage, which switchs to be controlled by the same level flight controller, completes recycling, to solve traditional Rocket Electrical System framework composition not
The problem of adapting to reurnable booster demand.
Detailed description of the invention
Attached drawing shows the illustrative embodiments of the disclosure, and it is bright together for explaining the principles of this disclosure,
Which includes these attached drawings to provide further understanding of the disclosure, and attached drawing is included in the description and constitutes this
Part of specification.
Fig. 1 is the redundant system schematic diagram of the disclosure；
Fig. 2 is the aircraft redundant system schematic diagram of the disclosure.
Specific embodiment
The disclosure is described in further detail with embodiment with reference to the accompanying drawing.It is understood that this place
The specific embodiment of description is only used for explaining related content, rather than the restriction to the disclosure.It also should be noted that being
Convenient for description, part relevant to the disclosure is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the disclosure can
To be combined with each other.The disclosure is described in detail below with reference to the accompanying drawings and in conjunction with embodiment.
Embodiment one:
Referring to attached drawing 1, present disclose provides a kind of inexpensive electrical system suitable for reurnable booster, including it is more
Grade system, every grade of system includes the first bus, the second bus, several nodes, each node simultaneously with first bus
And the second bus connection；First bus of adjacent two-stage system is connected with each other by separate connector；Adjacent two-stage system
The second bus be connected with each other by separate connector；Synchrodata exchange cycle between each node occurs, i.e., each described
Data exchange is synchronized with Fixed Time Interval between node.
In the present embodiment, first network is constituted between the first bus and each node, is constituted between the second bus and each node
Second network, when first network breaks down, each node will automatically select the second network and work on；It together should the second network
When failure, each node will automatically select first network and work on；First network and the second network are mutually redundant.Similarly,
In the present embodiment, multilevel system is mutually redundant by the first bus and the second bus.
Redundant system is that double-network redundant industry ethernet system, double-network redundant refer in system high speed in real time in the present embodiment
There are two independent networks, and when a network breaks down, another network can still work.Double-network redundant is a kind of physics
The redundancy of medium, for each node, all there are two network interfaces.
Referring to Fig.1, each node is connected with each other by the first bus and the first exchanger (HUB1)；Each section simultaneously
Point is connected with each other by the second bus and the second exchanger (HUB2).In the present embodiment, each node can be separately connected independent
Main website；Bus can at most connect 240 nodes, can configure multiple main websites, one of them is in active state, and other main websites are in
Stand-by state is then immediately switched to spare communication port when main website master communication interface failure.
Using the inexpensive electrical system of the present embodiment, the second bus of adjacent two-stage system is mutual by separate connector
Connection；In practical applications, after separate connector classifies primary system and level two, since two-stage system all at least wraps
Containing a main website (flight controller, combined navigation device etc.), spare main website detects its preferential main website without information
Feedback, it can starting is rapidly to take over control, and after realizing separation, each section still can be with the technology of complete independently work
Effect, the recycling for the aircraft after separation provide condition.
Embodiment two:
A kind of inexpensive electrical system suitable for reurnable booster, including above-mentioned redundant system；Every grade of system is equal
Flight controller, combined navigation device, servo mechanism and distributor are connected with by each node；Have and only any level-one flies
Line control unit is in running order；The flight controller of off working state detects the flight controller communication of previous priority sequence
When truncation or failure, start flight controller according to sequence.
The priority sequence of the disclosure refers to has multiple identical components in redundant system, and component starting is with sequence
Coding, such as the first addressable part, the second addressable part, third addressable part ... third addressable part only detect the
One addressable part, the second addressable part just will start when being in communication truncation or failure.
A kind of inexpensive electrical system suitable for reurnable booster, including above-mentioned redundant system；In the present embodiment,
By taking the application in booster-missile combination as an example.
The multilevel system includes primary system and level two；
The primary system is connected with level-one flight controller, level-one telemetering equipment, level-one integrated navigation by each node
Device, level-one servo mechanism and level-one distributor；
The level two is connected with second level flight controller, second level telemetering equipment, second level integrated navigation by each node
Device, two stage servomechanism, second level switchgear house and attitude control power device.
Primary system and the equal self-contained independent completion system of level two, only have differences on concrete function.Flight controller
The functions such as integrated navigation calculation, gesture stability, timing control, engine control, are the control cores of entire rocket.Integrated navigation
Device uses satellite navigation and positioning and inertial navigation complex method, provides high-precision integrated navigation information, leads for flight controller
Boat, which calculates, to be used.
In the present embodiment, using above-mentioned redundant system, the flight controller and group of primary system and level two may make
Navigation device is closed to be mutually backups；
When the level-one flight controller or the second level flight controller are in running order；The second level flight control
Device or the level-one flight controller detect the level-one flight controller or the second level flight controller communication truncation or
When failure, start the second level flight controller or the level-one flight controller.
Similarly, when the level-one combined navigation device device or the second level combined navigation device are in running order；It is described
Second level combined navigation device or the level-one combined navigation device detect the level-one combined navigation device or the secondary groups
When closing navigation device communication truncation or failure, start the second level combined navigation device or the level-one combined navigation device.
In preferred embodiments, the level-one servo mechanism includes 4 actuator.Level-one servo mechanism is electronic watches
System is taken, using " one drags four " form, the pitching for realizing whole rocket, yaw and rolling three are swung by the single-degree-of-freedom of four jet pipes
Channel control.
The two stage servomechanism includes 2 actuator and the attitude control power connecting with first bus and the second bus
Device.Second level uses " one drag two " form, realizes that the triple channel of whole rocket controls jointly with second-level attitude control power device.
The multilevel system includes N grades of systems, N >=3 altogether.The disclosure can be applied in multistep rocket, for example, when being applied to
When three-stage rocket, the N=3；
Guarantee to realize recyclable requirement in aircraft design of electrical system at different levels, it is at different levels to be equipped with for matching
Electricity, flight controller, navigation device etc., so that the system that the equal self-contained of electrical system after isolation at different levels is independently closed, can control
The same level processed is flown according to scheduled track.
In the present embodiment, high speed dual redundant industry ethernet constitution in real time is used using above-mentioned redundant system, there is height
The advantages that bandwidth, high real-time, highly reliable, inexpensive, easy extension.Before separation at different levels, Upper Stage flight controller is as bus master
Controller, other send control instruction from equipment in bus, control the flight of entire rocket.After separation at different levels, lower stage flies
Line control unit is independently switched to master controller, controls and itself continues to fly, and control the same level aircraft completes recycling.
Embodiment three:
This implementation aircraft includes above-mentioned aircraft redundant system, and in addition the aircraft should also include carrying
Lotus device connects the load device and the second separate connector of the level two, connect falling off for the primary system
Connector.Umbilical connector realizes the connection of primary system and ground surface platform.
It is worth noting that, including satellite navigation module, inertia in level-one combined navigation device and secondary navigation device
Navigation module and rate gyroscope module, and external sensible is realized by defending lead antenna.It ensures after each grade of separation, can utilize
The combined navigation device of the same level carries out location navigation, to realize recycling.And combined navigation device uses satellite navigation and positioning
With inertial navigation complex method, high-precision integrated navigation information is provided, navigating to calculate for flight controller uses.
Level-one distributor and second level distributor contain Power entry module and ignition module, and distributor is mainly provided by battery
Electric power.And batteries at different levels and distributor complete independently-powered, the distribution of the same level aircraft, and battery is using mature chargeable height
Density lithium battery scheme, can adapt to rocket high temperature, low temperature and mechanical environment, convenient for reusing after recycling.
Level-one telemetering equipment and second level telemetering equipment include gather and edit module and transmitting module, and module of gathering and editing mainly passes through biography
Sensor and converter obtain data, and transmitting module can exchange data with outside by telemetering antenna.Two-stage configures telemetering
Device can acquire telemetry parameter on the same level aircraft, be issued after coding by telemetering antenna.It is set using control and measurement fusion
Meter, shared bus effectively reduce battery, connector, number of cables, reduce electrical system weight, increase rocket payload.
Level-one flight controller and second level flight controller include navigation calculation module, gesture stability module, timing
Control module, engine control module, engine control module are connect with engine.Level-one flight controller and second level flight control
Different control methods is stored in device processed, to realize the predetermined function of aircraft at different levels and realize recycling.Flight controller
The functions such as integrated navigation calculation, gesture stability, timing control, engine control, are the control cores of entire rocket.
It is worth noting that aircraft is including but not limited to rocket, such as aircraft, guided missile etc..The disclosure preferably uses rocket
Load the redundant system.It supports to recycle using the rocket two-stage of the framework, which can also be conveniently used for parallel connection binding, multistage
The reusable rocket of cascade.
Now the working method of rocket is described as follows:
Electrical system work includes level-one inflight phase, level-one recovery flight section, second level inflight phase, star during rocket flight
Arrow segregation section and secondary recovery inflight phase, to emit main enable as flight zero point.
Level-one inflight phase: after rocket first class engine blasts off, all batteries are via distributors at different levels on arrow on arrow
Equipment power supply；Second level flight controller is scheduled bus as bus master, real-time reception integrated navigation data, calculates one
Grade SERVO CONTROL instruction, servo mechanism drive rocket tube, control thrust vectoring and rocket posture, control one
Grade inflight phase flight；Level-one telemetering equipment is acquired sensor information, is issued after coding by transmitter, telemetering antenna；
After meeting I and II separation condition, primary flight controls output the igniting of level-one retro-rocket and I and II stage separation, knot
The flight of beam level-one.
Level-one recovery flight section: after the separation of rocket I and II, level-one is transferred to exhausting section flight, the control of level-one flight at this time
Device monitors that main website is lost in bus, automatically switches to main website, adapter tube bus marco, and execute exhausting section Row control；Level-one
Flight controller real-time reception level-one integrated navigation data calculate SERVO CONTROL instruction and rocket thrust instruction etc., to rocket
Posture, position, thrust etc. are controlled, and are controlled level-one according to scheduled track and are dropped to recovery point；Level-one landing rear stage flies
Line control unit controls the shutdown of rocket first class engine, disconnects power supply, completes level-one recycling.
Second level inflight phase: after the separation of rocket I and II, second level flight controller outputs second level engine ignition, rocket into
Enter second level inflight phase, starts second level flight control；Second level flight controller continues to receive second level combination navigation data, output control
Instruct the thrust vectoring and gesture stability that rocket is realized to two stage servomechanism and attitude control power device；Rocket flight is to predetermined
Position, after meeting second level engine cutoff condition, primary flight controls output second level shutdown command, terminate the dynamic flight of second level
Section.
The satellite and the rocket separate inflight phase: after second level engine cutoff, rocket enters satellite and the rocket separation inflight phase；Second level flight controller
Control attitude control engine accurately adjusts rocket posture, outputs payload separation command after reaching condition of entering the orbit, payload enters
Rail.
Secondary recovery inflight phase: after satellite and the rocket separation, second level flight controller controls attitude control power device and carries out pose adjustment,
Re-orbit control is completed, then controls second level engine ignition again；Second level flight controller continues to receive second level integrated navigation number
According to controlling the thrust vectoring and posture of rocket, implement reclaimer；Second level flight controller controls rocket second level after second level is landed
Engine cutoff disconnects power supply, completes secondary recovery.
In the description of this specification, reference term " one embodiment/mode ", " some embodiment/modes ", " show
The description of example ", " specific example " or " some examples " etc. mean to combine the specific features of the embodiment/mode or example description,
Structure, material or feature are contained at least one embodiment/mode or example of the application.In the present specification, to upper
The schematic representation for stating term is necessarily directed to identical embodiment/mode or example.Moreover, the specific features of description,
Structure, material or feature can be combined in any suitable manner in any one or more embodiment/modes or example.In addition,
Without conflicting with each other, those skilled in the art can by different embodiment/modes described in this specification or
Example and different embodiment/modes or exemplary feature are combined.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include at least one this feature.In the description of the present application, the meaning of " plurality " is at least two, such as two, three
It is a etc., unless otherwise specifically defined.
It will be understood by those of skill in the art that above embodiment is used for the purpose of clearly demonstrating the disclosure, and simultaneously
Non- be defined to the scope of the present disclosure.For those skilled in the art, may be used also on the basis of disclosed above
To make other variations or modification, and these variations or modification are still in the scope of the present disclosure.
Claims (9)
1. a kind of electrical system suitable for reurnable booster, it is characterised in that: including multilevel system, every grade of system is wrapped
The first bus, the second bus, several nodes are included, each node is connect with first bus and second bus simultaneously；
First bus of adjacent two-stage system is connected with each other via separate connector；Second bus of adjacent two-stage system via point
It is connected with each other from connector；
Data exchange is synchronized with Fixed Time Interval between each node.
2. a kind of electrical system suitable for reurnable booster as described in claim 1, it is characterised in that: each section
Point is connected with each other by the first bus and the first exchanger；Each node is mutual by the second bus and the second exchanger simultaneously
Connection.
3. a kind of electrical system suitable for reurnable booster as claimed in claim 2, it is characterised in that: each section
Point is connect via interface selector with the first bus and the second bus.
4. a kind of electrical system suitable for reurnable booster, it is characterised in that: including described in claim any one of 1-3
Electrical system；Every grade of electrical system by each node be connected with flight controller, combined navigation device, servo mechanism and
Distributor；
Have and only any level-one flight controller is in bus master working condition；The flight controller of slave station working condition is examined
When measuring current master station communication truncation or failure, bus master working condition is automatically switched to.
5. a kind of electrical system suitable for reurnable booster according to claim 4, it is characterised in that: described more
Grade system includes primary system and level two, and the servo mechanism of primary system includes 4 actuator, the servo of level two
Structure includes 2 actuator.
6. a kind of electrical system suitable for reurnable booster according to claim 4, it is characterised in that: described more
Grade system includes primary system and level two, and the level two is connected with attitude control power device by node.
7. a kind of electrical system suitable for reurnable booster, feature according to claim 4-6 any one
Be: the systems at different levels also have telemetering equipment, and the telemetering equipment includes gather and edit module and transmitting module.
8. a kind of reurnable booster using the electrical system includes the feature as described in claim 5-7 any one
It is: further includes connecting the load device and the separate connector of the level two, connecting falling off for the primary system
Connector.
9. one kind is applied to carrier rocket as claimed in claim 8, it is characterised in that comprise the steps of:
Level-one flight step: after rocket first class engine blasts off, second level flight controller as bus master to bus into
The flight of row scheduling controlling level-one inflight phase；Level-one telemetering equipment is acquired sensor information；When meeting I and II lightning strip
After part, second level flight controller issues order, the igniting of level-one retro-rocket and I and II stage separation, terminates level-one flight；
Level-one recycling step: level-one flight controller monitors that main website is lost in bus, automatically switches to main website, takes over total line traffic control
System, and execute exhausting section Row control；
Second level flight step: second level flight controller outputs second level engine ignition, and second level flight controller continues to receive second level
Integrated navigation data；Aircraft flight is to predetermined position, and after meeting second level engine cutoff condition, primary flight controls output two
Grade shutdown command；
Load separating step: after second level engine cutoff, second level flight controller control attitude control engine accurately adjusts aircraft
Posture outputs payload separation command after reaching condition of entering the orbit；
Secondary recovery step: after load separation, second level flight controller controls attitude control power device and carries out pose adjustment, then again
Secondary control second level engine ignition；Implement reclaimer.
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Cited By (7)
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| CN110988564A (en) * | 2019-12-24 | 2020-04-10 | 北京中科宇航探索技术有限公司 | Subsection rocket electrical system and test method thereof |
| CN111301716A (en) * | 2020-03-23 | 2020-06-19 | 北京中科宇航技术有限公司 | Power supply and distribution system of multistage carrier rocket |
| CN111306997A (en) * | 2020-03-23 | 2020-06-19 | 北京中科宇航技术有限公司 | Electric system and electric control method of carrier rocket |
| 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 |
| CN114815901A (en) * | 2022-06-24 | 2022-07-29 | 东方空间技术(北京)有限公司 | Rocket-mounted electrical system of carrier rocket |
| CN115729154A (en) * | 2022-11-24 | 2023-03-03 | 航天科工火箭技术有限公司 | Low-cost carrier rocket separation body falling area control electrical system |
| CN117054136A (en) * | 2023-08-15 | 2023-11-14 | 东方空间技术(山东)有限公司 | Measurement system and method for recyclable carrier rocket |
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| CN110988564A (en) * | 2019-12-24 | 2020-04-10 | 北京中科宇航探索技术有限公司 | Subsection rocket electrical system and test method thereof |
| CN111301716A (en) * | 2020-03-23 | 2020-06-19 | 北京中科宇航技术有限公司 | Power supply and distribution system of multistage carrier rocket |
| CN111306997A (en) * | 2020-03-23 | 2020-06-19 | 北京中科宇航技术有限公司 | Electric system and electric control method of carrier rocket |
| CN111301716B (en) * | 2020-03-23 | 2021-09-14 | 北京中科宇航技术有限公司 | Power supply and distribution system of multistage carrier rocket |
| 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 |
| CN114815901A (en) * | 2022-06-24 | 2022-07-29 | 东方空间技术(北京)有限公司 | Rocket-mounted electrical system of carrier rocket |
| CN114815901B (en) * | 2022-06-24 | 2022-09-20 | 东方空间技术(北京)有限公司 | Rocket-mounted electrical system of carrier rocket |
| CN115729154A (en) * | 2022-11-24 | 2023-03-03 | 航天科工火箭技术有限公司 | Low-cost carrier rocket separation body falling area control electrical system |
| CN115729154B (en) * | 2022-11-24 | 2024-04-30 | 航天科工火箭技术有限公司 | Low-cost carrier rocket separation landing zone control electrical system |
| CN117054136A (en) * | 2023-08-15 | 2023-11-14 | 东方空间技术(山东)有限公司 | Measurement system and method for recyclable carrier rocket |
| CN117054136B (en) * | 2023-08-15 | 2024-06-11 | 东方空间技术(山东)有限公司 | Measurement system and method for recyclable carrier rocket |
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