CN108419153B - Instruction transmission method between spacecraft and carrier - Google Patents
Instruction transmission method between spacecraft and carrier Download PDFInfo
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- CN108419153B CN108419153B CN201810146690.XA CN201810146690A CN108419153B CN 108419153 B CN108419153 B CN 108419153B CN 201810146690 A CN201810146690 A CN 201810146690A CN 108419153 B CN108419153 B CN 108419153B
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- instruction
- subsystem
- triggering subsystem
- electrical
- triggering
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Classifications
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04Q—SELECTING
- H04Q9/00—Arrangements in telecontrol or telemetry systems for selectively calling a substation from a main station, in which substation desired apparatus is selected for applying a control signal thereto or for obtaining measured values therefrom
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L67/00—Network arrangements or protocols for supporting network services or applications
- H04L67/01—Protocols
- H04L67/12—Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
Abstract
The present invention relates to the instruction transmission methods between a kind of spacecraft and carrier, Transmission system is realized based on instruction, described instruction Transmission system includes mechanical triggering subsystem and electrical triggering subsystem, it include: that S1. triggers mechanical first instruction triggered in subsystem, and is respectively sent to carrier and electrical triggering subsystem；S2. the electrical triggering subsystem receives first instruction, and second triggered in the electrical triggering subsystem instructs and be sent to the subsystem in spacecraft.The highly reliable instruction of spacecraft and carrier when the upward flight stage is normal or escape is realized in such a way that mechanical triggering subsystem and electrical triggering subsystem combine to transmit.The present invention uses binary channels, the Redundancy Design of multiconductor, multiple instructions maincenter, has prevented the mistake hair of instruction transmission, the hidden danger of leakage hair.
Description
Technical field
The present invention relates to the instruction transmission methods between a kind of instruction transmission method more particularly to a kind of spacecraft and carrier.
Background technique
Electric interfaces between spacecraft and carrier are as the information interaction passage between two equipments, for synchronizing carrier and boat
The time reference of its device, and collaboration carrier and spacecraft upward flight section various movements, generally include delivery take off, device
The movement of the series of instructions such as radome fairing is thrown in arrow separation.
Different from general spacecraft task, manned space flight task is commonly designed during escape system guarantee upward flight section
The safety of spacefarer.The task of escape system, if occurring jeopardizing the significant trouble of spacefarer's safety, can be pressed before throwing radome fairing
It requires according to lifesaving by spacecraft return capsule escape unharmed Failure risk area.Escape system needs highly to match between spacecraft and carrier
It closes, wherein the command transmission system between spacecraft and carrier is the key of spacecraft and carrier interaction, and instruction transmission leakage hair is accidentally sent out
Influence the safety of the success or failure of space travel task and spacefarer.
Summary of the invention
The purpose of the present invention is to provide the instruction transmission methods between a kind of spacecraft and carrier, and it is reliable to solve instruction transmission
The low problem of property.
For achieving the above object, the present invention provides the instruction transmission method between a kind of spacecraft and carrier, based on referring to
Transmission system is enabled to realize, described instruction Transmission system includes mechanical triggering subsystem and electrical triggering subsystem, comprising:
S1. the first instruction in the mechanical triggering subsystem is triggered, and is respectively sent to carrier and electrical triggering subsystem
System；
S2. the electrical triggering subsystem receives first instruction, triggers second in the electrical triggering subsystem
It instructs and is sent to the subsystem in spacecraft.
According to an aspect of the present invention, second triggered in the electrical triggering subsystem instructs and is sent to spacecraft
In subsystem the step of in, it is synchronous to send second instruction to carrier.
According to an aspect of the present invention, first instruction is transmitted by two instruction paths；
Second instruction is transmitted by an instruction path.
According to an aspect of the present invention, first instruction is no sourse instruction comprising separation command, mechanism action refer to
It enables.
According to an aspect of the present invention, the mechanical triggering subsystem characterizes institute using the on off operating mode of electric conductor access
State the effective and invalid of the first instruction, and the mechanical triggering subsystem is by being mechanically connected or disconnecting described in action triggers the
One instruction.
According to an aspect of the present invention, the electrical triggering subsystem includes at least two instruction maincenters；
Described instruction maincenter includes instruction control unit sum number pipe unit.
According to an aspect of the present invention, the electrical triggering subsystem controls intermediate relay by described instruction maincenter
Closing or opening characterize it is described second instruction it is effective and invalid, and the electrical triggering subsystem using multi signal lock join
Mode triggers second instruction when multiple signals are effective.
According to an aspect of the present invention, the electrical triggering subsystem includes normal and two kinds of instructions of failure send mould
Formula；
The electrical triggering subsystem default uses normal instructions sending mode, if triggering the faulting instruction sending mode
Fault mode condition, then the electrical triggering subsystem is converted to faulting instruction sending mode.
According to an aspect of the present invention, the fault mode condition at least two；
When meeting all fault mode conditions simultaneously, the faulting instruction of the electrical triggering subsystem is sent
Mode starting.
According to an aspect of the present invention, mechanical isolation, the electrical triggering subsystem are set in mechanical triggering subsystem
Middle setting electromagnetic isolation.
A kind of scheme according to the present invention, it is real in such a way that machinery triggering subsystem and electrical triggering subsystem combine
The highly reliable instruction transmission of spacecraft and carrier when the upward flight stage is normal or escape is showed.The present invention uses bilateral
The Redundancy Design in road, multiconductor, multiple instructions maincenter has prevented the mistake hair of instruction transmission, the hidden danger of leakage hair.The present invention is using mechanical
Isolation and electromagnetic isolation technology, solve spacecraft and carrier assembly in the electromagnetic environment problem of ascent stage complexity, ensure that
Instruction is transmitted timely and effective, and the delay or loss of instruction transmission are further avoided.Mechanical triggering subsystem through the invention
System and electrical triggering subsystem ensure escape system dependent instruction normal transmission during aerial mission, effectively improve space flight
The reliability and safety of device and carrier provide a strong guarantee for the life security of spacefarer.
A kind of scheme according to the present invention by the mechanical mechanical connection for triggering subsystem or disconnects the finger of action triggers first
It enables, ensure that mechanical triggering subsystem can trigger the first instruction in time during connecting or disconnecting, avoid delay, into
One step ensure that the timely sending of the first instruction.In the present embodiment, the first instruction is triggered by the on-off of electric conductor,
Therefore the first instruction is no sourse instruction.By being mechanically connected or disconnecting the first instruction triggers of action drives, the first instruction is avoided
The electric fault of trigger process, and influence of the complicated electromagnetic force thermal environment to the first instruction in flight course is avoided, it ensure that
What is instructed is timely and effective, further improves the safety of spacecraft and carrier in flight course.Pass through double instruction paths
Setting ensure that the reliable of the first instruction transmission, further ensured first to play the role of the backup of instruction transmission
What is instructed is timely and effective.Machinery triggering subsystem is synchronous to send the first instruction to carrier and electrical triggering subsystem to ensure that
The time reference for the second instruction that electrical triggering subsystem issues is synchronous with carrier.
A kind of scheme according to the present invention, by the setting of multiple instruction maincenter, to play the backup of instruction transmission
Effect ensure that the reliable of the second instruction transmission, further ensure the timely and effective of the second instruction.Meanwhile passing through multiple fingers
It enables maincenter not only ensure backup and meets high density and issue an order demand.
Detailed description of the invention
Fig. 1 schematically shows a kind of structure chart of the command transmission system of embodiment according to the present invention；
Fig. 2 schematically shows a kind of flow diagram of the instruction transmission method of embodiment according to the present invention；
Fig. 3 a schematically shows a kind of mechanical communication state of the mechanical triggering subsystem of embodiment according to the present invention
Structure chart；
Fig. 3 b schematically shows a kind of mechanical off-state of the mechanical triggering subsystem of embodiment according to the present invention
Structure chart；
Fig. 4 schematically shows a kind of knot of double instruction paths of the mechanical triggering subsystem of embodiment according to the present invention
Composition；
Fig. 5 schematically shows a kind of connection figure of the mechanical triggering subsystem of embodiment according to the present invention；
Fig. 6 a schematically shows a kind of knot of the off-state of the electrical triggering subsystem of embodiment according to the present invention
Composition；
Fig. 6 b schematically shows a kind of knot of the connected state of the electrical triggering subsystem of embodiment according to the present invention
Composition；
Fig. 7 schematically shows a kind of connection figure of the electrical triggering subsystem of embodiment according to the present invention；
Fig. 8 schematically shows a kind of electrical triggering subsystem instruction sending mode conversion of embodiment according to the present invention
Flow chart.
Specific embodiment
It, below will be to embodiment in order to illustrate more clearly of embodiment of the present invention or technical solution in the prior art
Needed in attached drawing be briefly described.It should be evident that the accompanying drawings in the following description is only of the invention some
Embodiment for those of ordinary skills without creative efforts, can also be according to these
Attached drawing obtains other attached drawings.
When being described for embodiments of the present invention, term " longitudinal direction ", " transverse direction ", "upper", "lower", " preceding ",
" rear ", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", orientation or positional relationship expressed by "outside" are based on phase
Orientation or positional relationship shown in the drawings is closed, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore above-mentioned term cannot
It is interpreted as limitation of the present invention.
The present invention is described in detail with reference to the accompanying drawings and detailed description, embodiment cannot go to live in the household of one's in-laws on getting married one by one herein
It states, but therefore embodiments of the present invention are not defined in following implementation.
As shown in Figure 1, a kind of embodiment according to the present invention, the instruction transmission side between spacecraft and carrier of the invention
Method based on instruction realize by Transmission system 1, and wherein command transmission system 1 includes mechanical triggering subsystem 11 and electrical triggering subsystem
12.Machinery triggering subsystem 11 can send instruction to carrier 3 and electrical triggering subsystem 12 respectively.Electrical triggering subsystem 12 can
The subsystem 2 into carrier 3 and spacecraft sends instruction respectively, and electrically triggering subsystem 12 also can receive carrier 3 and boat
The telemetry that subsystem 2 in its device issues.
As shown in Fig. 2, a kind of embodiment according to the present invention, the instruction transmission side between spacecraft and carrier of the invention
Method includes:
S1. the first instruction in Crush trigger triggering subsystem, and it is respectively sent to carrier and electrical triggering subsystem；
S2. electrically triggering subsystem receives the first instruction, and second triggered in electrical triggering subsystem instructs and be sent to
Subsystem in spacecraft.
In conjunction with shown in Fig. 3 a and Fig. 3 b, a kind of embodiment party according to the present invention, machinery triggering subsystem 11 passes through spacecraft
Basic machine performance directly triggers and generates the first instruction.In the present embodiment, mechanical triggering subsystem 11 uses electric conductor
111 pass through different bay sections or mechanical component, are instructed by the on-off two states characterization first of 111 access of electric conductor effective
With it is invalid.It is described in detail by taking two bay sections as an example, as shown in Figure 3a, the first joint face A and the second cabin in the first bay section
The second joint face B in section is mutually mechanically connected.Electric conductor 111 passes through the first joint face A interconnected and the second joint face
B, in the present embodiment, it is assumed that when electric conductor 111 is in connected state, the first instruction in 111 access of electric conductor is invalid
State.Referring to shown in Fig. 3 b, the first bay section and the second bay section are separated from each other, therefore the first joint face A and the second joint face B are mutual
It is separate, across the electric conductor 111 of the first bay section and the second bay section when disconnecting the mechanical connection of the first bay section and the second bay section, phase
It is in an off state with answering, then the first instruction in 111 access of electric conductor becomes effective status.It is, of course, also possible to pass through conductance
When body 111 disconnects, the invalid state of the first instruction of characterization, the trigger process of the first instruction is same as described above, and details are not described herein.
By the mechanical mechanical connection for triggering subsystem 11 or the instruction of action triggers first is disconnected, ensure that mechanical triggering subsystem 11 exists
The first instruction can be triggered during connecting or disconnecting in time, avoids delay, further ensures the timely of the first instruction
It issues.In the present embodiment, the first instruction is triggered by the on-off of electric conductor 111, therefore the first instruction is passive finger
It enables.By being mechanically connected or disconnect the first instruction triggers of action drives, the electric fault of the first instruction triggers process is avoided, with
And influence of the complicated electromagnetic force thermal environment to the first instruction in flight course is avoided, it ensure that the timely and effective of instruction, further
Improve the safety of spacecraft and carrier in flight course.In the present embodiment, the first instruction includes separation command, machine
Structure action command.
As shown in figure 4, a kind of embodiment according to the present invention, machinery triggering subsystem 11 is set using double instruction paths
Meter.In the present embodiment, double instruction paths of mechanical triggering subsystem 11 are mutually independent.It is shown in Figure 4, two groups of electricity
Conductor 111 is mutually independent to pass through different bay sections or mechanical component, to constitute double instruction paths.In conjunction with Fig. 3 a and Fig. 4 institute
Show in the present embodiment, there is the first instruction path C and the second instruction path D.Wherein the first instruction path C is spacecraft
Propelling module instruction path, the second instruction path D are spacecraft orbit cabin transmission channel.As the first joint face A and the second joint face B
Between when passing through mechanical action, the first instruction path C and the second instruction path D set out the first instruction simultaneously, and independently
Outflow.By the setting of double instruction paths, thus play the role of instruction transmission backup, ensure that the first instruction transmit can
It leans on, has further ensured the timely and effective of the first instruction.Certainly, more the also settable instructions of mechanical triggering subsystem 11 are logical
Road, such as three, four or more, details are not described herein.
Referring to figure 1 and figure 5, a kind of embodiment according to the present invention in step S1, passes through mechanical linkage position
The first instruction of separating action triggering.In the present embodiment, when disconnected by machinery between the first joint face A and the second joint face B
It starts when making, the first instruction is characterized as being effectively in machinery triggering subsystem 11.Machinery triggering subsystem 11 is instructed first
It is sent in carrier 3 and electrical triggering subsystem 12 simultaneously.In the present embodiment, the mechanical subsystem 11 that triggers is to 3 He of carrier
The instruction path that electrical triggering subsystem 12 sends the first instruction is double instruction paths.By the setting of double instruction paths, from
And play the role of the backup of instruction transmission, ensure that the first instruction is transmitted reliable, further ensure the first instruction and
Shi Youxiao.Machinery triggering subsystem 11 is synchronous to send the first instruction to carrier 3 and electrical triggering subsystem 12 to ensure that electricity
The time reference that gas triggers the second instruction that subsystem 12 issues is synchronous with carrier.
In conjunction with shown in Fig. 6 a and Fig. 6 b, a kind of embodiment according to the present invention, electrical triggering subsystem 12 of the invention
Including instruction maincenter 121 and intermediate relay 122.In the present embodiment, by instructing maincenter 121 to intermediate relay 122
Control signal is sent, intermediate relay 122 carries out the electrical triggering subsystem 12 of open and close contact characterization according to control signal
In second instruction it is effective and invalid.In the present embodiment, referring to Fig. 6 a, it is assumed that when 122 break contact of intermediate relay,
The second instruction in electrical triggering 12 access of subsystem is invalid state.Referring to shown in Fig. 6 b, intermediate relay 122 is closed contact
When, the second instruction electrically triggered in the access of subsystem 12 becomes effective status.It is, of course, also possible to pass through intermediate relay
When 122 break contact, the effective status of the second instruction of characterization, details are not described herein.In conjunction with shown in Fig. 6 a and Fig. 6 b, in this implementation
It is electrical to trigger subsystem 12 connection mode is locked using multi signal in mode, when multiple (two, three or more) signals are
The second instruction of triggering when effectively.Connection mode is locked by using multi signal, needs multiple signals that could effectively trigger the second instruction, from
And avoid the second instruction in electrical triggering 12 access of subsystem mistakes or leaks hair.
As shown in fig. 7, a kind of embodiment according to the present invention, in step S2, the electrical subsystem 12 that triggers receives first
Instruction triggers in electrical the second instruction triggered in subsystem 12 and the subsystem 2 being sent in spacecraft.In present embodiment
In, instruction maincenter 121 includes 1211 sum number pipe unit 1212 of instruction control unit.In the present embodiment, referring to Fig. 6 a and figure
6b, the electrical subsystem 12 that triggers receive the first instruction and are issued by 1211 sum number pipe unit 1212 of instruction control unit multiple
Signal connects the contact of intermediate relay 122, so that the second instruction for making electrically to trigger in subsystem 12 is effective, it is further real
Now to the control of the subsystem 2 in spacecraft.In the present embodiment, as needed, intermediate relay 122 can be multiple
(two, three or more).In the present embodiment, the second instruction electrically in triggering subsystem 12 is synchronized to be sent to load
In tool 3, to realize the control to carrier 3.In the present embodiment, the second instruction is transmitted by an instruction path.
Shown in Figure 4, the second instruction by the first instruction path C by being transmitted.
As shown in fig. 7, a kind of embodiment according to the present invention, the subsystem 2 in spacecraft include GNC subsystem 21,
Recovery subsystem 22, overall circuit subsystem 23, tracking-telemetry and command subsystem 24, propulsion subsystem 25 and structural mechanism subsystem 26.It is logical
The co- controlling for crossing 1211 sum number pipe unit 1212 of instruction control unit guarantees that above-mentioned subsystem is accurate and timely completes work
The conversion of state is further ensured that the rapid effective of the second instruction execution.In the present embodiment, electrically triggering subsystem 12 wraps
Include at least two instruction maincenters 121.By the setting of multiple instruction maincenter 121, thus play the role of the backup of instruction transmission,
It ensure that the reliable of the second instruction transmission, further ensure the timely and effective of the second instruction.Meanwhile passing through multiple instruction maincenter
121 not only ensure backup and meet high density and issue an order demand.
A kind of embodiment according to the present invention, electrical triggering subsystem 12 of the invention include normal and two kinds of failure fingers
Enable sending mode.In the present embodiment, electrically triggering subsystem 12 default is referred to using normal instructions sending mode progress second
The transmission of order.If the electrical subsystem that triggers is converted to failure when triggering the fault mode condition of faulting instruction sending mode
Instruct sending mode.
As shown in figure 8, a kind of embodiment according to the present invention, fault mode condition at least two.In this embodiment party
In formula, fault mode condition is three.When electrically triggering subsystem 12 meets whole fault mode conditions simultaneously, faulting instruction
Sending mode starting.Certainly, electrical to touch as long as electrically the triggering one of fault mode condition of subsystem 12 is not satisfied
It sends out subsystem 12 and still uses normal instructions sending mode.As shown in figure 8, electrically triggering subsystem 12 passes through the side successively judged
Formula verifies whether to meet all fault mode conditions, and normal instructions sending mode is returned if being unsatisfactory for.
A kind of embodiment according to the present invention is provided with mechanical isolation and electromagnetic isolation in command transmission system 1.At this
In embodiment, mechanical isolation is set in machinery triggering subsystem 11, electromagnetic isolation is arranged in electrical trigger in subsystem 12.It is mechanical
Trigger the electric conductor 111 in subsystem 11 and between the electrical system of spacecraft by mechanical isolation (or physical isolation), and
Only it is connected with carrier 3.In the present embodiment, the intermediate relay 122 electrically in triggering subsystem 12 uses electromagnetism relay
Device, the coil in intermediate relay 122 and is connected between the electrical system in spacecraft, the contact in intermediate relay 122
It is connected with carrier 3.Electromagnetic isolation between coil and contact in intermediate relay 122.By being set in command transmission system 1
It is equipped with mechanical isolation and electromagnetic isolation, to ensure that being isolated between spacecraft and carrier 3, it is ensured that instruct transmission can
It leans on.
Above content is only enumerating for concrete scheme of the invention, for the equipment and structure of wherein not detailed description, is answered
When being interpreted as that the existing common apparatus in this field and universal method is taken to be practiced.
The foregoing is merely a schemes of the invention, are not intended to restrict the invention, for the technology of this field
For personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (9)
1. the instruction transmission method between spacecraft and carrier, which is characterized in that Transmission system is realized based on instruction, and described instruction passes
Defeated system includes mechanical triggering subsystem and electrical triggering subsystem, comprising:
S1. the first instruction in the mechanical triggering subsystem is triggered, and is respectively sent to carrier and electrical triggering subsystem, institute
It states mechanical triggering subsystem and the effective and invalid and described of first instruction is characterized using the on off operating mode of electric conductor access
Machinery triggering subsystem is by being mechanically connected or disconnecting the first instruction described in action triggers；
S2. the electrical triggering subsystem receives first instruction, triggers the second instruction in the electrical triggering subsystem
And it is sent to the subsystem in spacecraft.
2. instruction transmission method according to claim 1, which is characterized in that the in the triggering electrical triggering subsystem
Two instruct and the step of be sent to the subsystem in spacecraft in, it is synchronous to send second instruction to carrier.
3. instruction transmission method according to claim 1 or 2, which is characterized in that first instruction passes through two instructions
It is transmitted in channel；
Second instruction is transmitted by an instruction path.
4. instruction transmission method according to claim 3, which is characterized in that first instruction is no sourse instruction, packet
Include separation command, mechanism action instruction.
5. instruction transmission method according to claim 3, which is characterized in that the electrical triggering subsystem includes at least two
A instruction maincenter；
Described instruction maincenter includes instruction control unit sum number pipe unit.
6. instruction transmission method according to claim 5, which is characterized in that the electrical triggering subsystem passes through the finger
The closing or opening of maincenter control intermediate relay is enabled to characterize the effective and invalid of second instruction, and the electrical triggering
Subsystem locks connection mode using multi signal, and second instruction is triggered when multiple signals are effective.
7. instructing transmission method according to claim 1 or 5, which is characterized in that the electrical triggering subsystem includes just
Normal and two kinds of instruction sending modes of failure；
The electrical triggering subsystem default uses normal instructions sending mode, if triggering the event of the faulting instruction sending mode
Hinder mode condition, then the electrical triggering subsystem is converted to faulting instruction sending mode.
8. instruction transmission method according to claim 7, which is characterized in that the fault mode condition at least two；
When meeting all fault mode conditions simultaneously, the faulting instruction sending mode of the electrical triggering subsystem
Starting.
9. instruction transmission method according to claim 1, which is characterized in that in machinery triggering subsystem setting it is mechanical every
From electromagnetic isolation is arranged in the electrical triggering subsystem.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810146690.XA CN108419153B (en) | 2018-02-12 | 2018-02-12 | Instruction transmission method between spacecraft and carrier |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810146690.XA CN108419153B (en) | 2018-02-12 | 2018-02-12 | Instruction transmission method between spacecraft and carrier |
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| CN108419153A CN108419153A (en) | 2018-08-17 |
| CN108419153B true CN108419153B (en) | 2019-03-08 |
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| CN109204893B (en) * | 2018-09-07 | 2021-01-05 | 北京空间技术研制试验中心 | Design method of high-reliability spacecraft and carrier rocket electrical interface |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103022774A (en) * | 2012-12-28 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Satellite-rocket separation connector |
| CN105841556A (en) * | 2016-02-25 | 2016-08-10 | 湖北航天技术研究院总体设计所 | General advanced upper stage of solid launch vehicle |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103543752B (en) * | 2013-10-09 | 2017-03-15 | 深圳市大疆创新科技有限公司 | A kind of remote control thereof and remote control systems |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103022774A (en) * | 2012-12-28 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Satellite-rocket separation connector |
| CN105841556A (en) * | 2016-02-25 | 2016-08-10 | 湖北航天技术研究院总体设计所 | General advanced upper stage of solid launch vehicle |
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