CN107346359A - Safe separating envelope design method between spacecraft - Google Patents
Safe separating envelope design method between spacecraft Download PDFInfo
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- CN107346359A CN107346359A CN201710541700.5A CN201710541700A CN107346359A CN 107346359 A CN107346359 A CN 107346359A CN 201710541700 A CN201710541700 A CN 201710541700A CN 107346359 A CN107346359 A CN 107346359A
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- G06F30/15—Vehicle, aircraft or watercraft design
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Abstract
Safe separating envelope design method includes between the spacecraft of the present invention：It is safe separating envelope design basis body to choose the relative less person of change of configuration layouts in two choristas；On the basis of the outline envelope of reference body, minimum dynamic security distance is given, separation envelope is formed from benchmark to minimum dynamic security distance is extended out；All projecting points on search separation envelope, to each projecting point, using the projecting point as starting point, do the ray for α with reference body disengaging movement angular separation；If all rays are all fallen within separation envelope, the separation envelope is safe separating envelope；If thering is ray to fall separating outside envelope, using fall separate outside envelope and can surround other rays ray and the figure that surrounds of separation envelope as safe separating envelope.The present invention just considers separation dynamic process at the beginning of design to be influenceed, and reliability is high, can quickly provide the safe separating envelope between spacecraft, time saving and energy saving without separating dynamics simulation analysis.
Description
Technical field
The present invention relates to spacecraft piece-rate system safety Design and aircraft configurations layout designs technical field, specifically relate to
A kind of and safe separating envelope design method between spacecraft.
Background technology
With the development of spacecraft technology, some are needed by multiple bay sections or more to complete the spacecraft of complex task
Individual aircraft composition.Body is formed when one to be needed to complete just to need when particular task or task are completed and need to abandon point
From.
The design of safe separating envelope mainly uses empirical method between spacecraft at present.Typically using the external envelope of active chorista as
Benchmark, to a given distance X is extended out, form a safe separating envelope；Configuration layouts designer is with the safe separating bag
Whether network is boundary, carries out configuration layouts' design, then carry out separating dynamics simulation analysis, sent out when being separated between confirmation spacecraft
Raw collision, it can not receive if analysis result is that somewhere collides or dynamic spacing is smaller, X values local at this are adjusted
Greatly, new safe separating envelope is formed, and carries out the Iterative Design of configuration layouts；It is dynamic to carry out separation again for new configuration layouts
Whether Mechanics Simulation is analyzed, collided when being separated between confirmation spacecraft.And so on, until two choristas on all devices,
Structure member does not collide through simulation analysis, just forms the safe envelope of formal separation.Divide safely between existing spacecraft
From envelope design method, each configuration layouts' adjustment will re-establish emulation kinetic model, carry out separating dynamics emulation
Analysis, wastes time and energy.
The content of the invention
It is an object of the invention to provide safe separating envelope design method between a kind of spacecraft, set in safe separating envelope
Separation dynamic process is just considered at the beginning of meter to be influenceed, and can quickly provide the safe separating envelope between spacecraft.
To achieve the above object, safe separating envelope design method between a kind of spacecraft of present invention offer, including with
Lower step：1) it is safe separating envelope design basis body to choose the relative less person of change of configuration layouts in two choristas；2) with base
On the basis of the outline envelope of quasi- body, minimum dynamic security distance is given, is formed from benchmark to minimum dynamic security distance is extended out
Separate envelope；3) all projecting points on search separation envelope, to each projecting point, using the projecting point as starting point, do and benchmark
Body disengaging movement angular separation is α ray；4) if all rays are all fallen within separation envelope, the separation envelope is
Safe separating envelope；If thering is ray to fall separating outside envelope, separating outside envelope to fall and other rays can be surrounded
The figure that ray and separation envelope surround is safe separating envelope.
Safe separating envelope design method between above-mentioned spacecraft, wherein, in the step 3), α >=14 °.
Safe separating envelope design method between above-mentioned spacecraft, wherein, the projecting point includes the starting point of separation envelope.
Safe separating envelope design method between above-mentioned spacecraft, wherein, minimum dynamic security distance is according to task by experience
It is determined that.
Compared with prior art, the method have the benefit that：
Safe separating envelope design method just considers separation dynamic process shadow at the beginning of design between the spacecraft of the present invention
To ring, reliability is high, as long as the outline envelope of non-referenced body does not invade safe separating envelope, then two separation (reference body and non-
Reference body) it would not collide, it is time saving and energy saving without separating dynamics simulation analysis；Divide safely between the spacecraft of the present invention
It is simple from envelope design method, quickly carry out spacecraft piece-rate system and totality suitable for spacecraft scheme, first sample development stage
The Iterative Design of configuration layouts, reduce unnecessary separating dynamics simulation calculation.
Brief description of the drawings
Safe separating envelope design method is provided by following embodiment and accompanying drawing between the spacecraft of the present invention.
Fig. 1 show safe separating envelope design method schematic diagram between the spacecraft of present pre-ferred embodiments one.
Fig. 2 show safe separating envelope design method schematic diagram between the spacecraft of present pre-ferred embodiments two.
Embodiment
Below with reference to Fig. 1~Fig. 2 safe separating envelope design method the spacecraft of the present invention, make further detailed
Thin description.
Safe separating envelope design method comprises the following steps between the spacecraft of the present invention：
1) it is safe separating envelope design basis body to choose the relative less person of change of configuration layouts in two choristas；
2) on the basis of the outline envelope of reference body, minimum dynamic security distance is given, (i.e. reference body is outer by benchmark
Profiled envelope) form separation envelope to extending out minimum dynamic security distance；
Minimum dynamic security distance is according to task by empirically determined；
3) all projecting points on search separation envelope, to each projecting point, using the projecting point as starting point, do and reference body
Disengaging movement angular separation is α ray；
The projecting point includes the starting point of separation envelope；
α is relevant with separating rate and separation attitude angular speed that task allows, empirically determined, for example, taking α >=14 °；
4) if all rays are all fallen within separation envelope, the separation envelope is safe separating envelope；If there is ray
Fall and separating outside envelope, then separating outside envelope to fall and the ray and the figure that surrounds of separation envelope of other rays can be surrounded
Shape is safe separating envelope.
The safe separating envelope designed by this method is the safe separating envelope finally determined, due to the safe separating bag
Network just considers separation dynamic process at the beginning of designing influence, and reliability is high, without carrying out separating dynamics simulation analysis, you can
Safe separating between spacecraft under guarantee non-faulting operating mode.
Between two spacecrafts or the body of a spacecraft and its separable bay section/interstructural safe separating envelope it is equal
This method can be used.
The now safe separating envelope design method between the spacecraft of the specific embodiment detailed description present invention.
Example 1：
Fig. 1 show safe separating envelope design method schematic diagram between the spacecraft of present pre-ferred embodiments one.
1) it is active chorista to assume spacecraft A, and spacecraft B is passive chorista, and spacecraft A is used to connect spacecraft B
Bay section configuration layouts determine substantially, select body on the basis of spacecraft A；
2) on the basis of spacecraft A outline envelope, minimum dynamic security distance DX is given, from benchmark to extending out minimum
Dynamic security distance DX forms separation envelope BL1, in Fig. 1 shown in (a)；
3) all projecting points on search separation envelope BL1 (starting point for including separation envelope BL1), it is described through search
Projecting point has a, b, c, d, e, f six, in Fig. 1 shown in (b)；Respectively using a, b, c, d, e, f as starting point, do and divide with spacecraft A
The ray for being α from direction of motion angle, in Fig. 1 shown in (c)；
In the present embodiment, the direction of arrow in Fig. 1 in (c) is spacecraft A disengaging movements direction；α takes 14 °；
4) as shown in (c) in Fig. 1, the ray using b, c, d, f as starting point is all fallen within outside separation envelope BL1, and with b and f
Other rays are surrounded for the radial energy of starting point, then are safety by the ray of starting point and separation envelope the BL1 figure surrounded of b and f
Envelope BL is separated, in Fig. 1 shown in (d).
As long as spacecraft B outline envelope does not invade the safe separating envelope BL that the present invention designs, then spacecraft A is with navigating
Its device B separation will not collide.
In Fig. 1 (d), in the present embodiment, spacecraft B protrusion 2 comes into safe separating envelope BL, it is necessary to right
The configuration layouts of spacecraft B protrusion 2 adjust (Iterative Design for carrying out configuration layouts).After adjusting configuration layouts, only
Spacecraft B outline envelope is wanted not enter safe separating envelope BL, spacecraft A is separated with spacecraft B and would not touched
Hit, it is time saving and energy saving without being judged by separating dynamics simulation analysis to verify.It is pointed out that this method is scheme
The Fast design method of safe separating envelope when demonstration and first sample design, it is contemplated that the influence of dynamic process is separated, to most of
The design of safe separating envelope is applicable between spacecraft.If spacecraft B protrusion 2 needs to establish because task needs to be not easy to adjust
Kinetic model, carry out separating dynamics simulation analysis, it is determined whether collide influence safety.
Example 2：
Fig. 2 show safe separating envelope design method schematic diagram between the spacecraft of present pre-ferred embodiments two
1) assume that spacecraft A is active chorista, spacecraft B is passive chorista, and spacecraft B configuration layouts are substantially true
It is fixed, and the bay section that spacecraft A is used to connect spacecraft B selects body on the basis of spacecraft B still in Preliminary design；
2) on the basis of spacecraft B outline envelope, minimum dynamic security distance DX is given, from benchmark to extending out minimum
Dynamic security distance DX forms separation envelope BL2, in Fig. 2 shown in (a)；
3) all projecting points on search separation envelope BL2 (starting point for including separation envelope BL2), it is described through search
Projecting point has a ', b ' two, in Fig. 2 shown in (b)；It is respectively starting point with a ', b ', does and pressed from both sides with spacecraft B disengaging movements direction
Angle is α ray, in Fig. 2 shown in (c)；
In the present embodiment, the direction of arrow in Fig. 2 in (c) is spacecraft B disengaging movements direction；α takes 14 °；
4) as shown in (c) in Fig. 2, the ray with a ', b ' for starting point is all fallen within outside separation envelope BL2, then with a ' and b '
The figure that ray and separation envelope BL2 for starting point surround is safe separating envelope BL ', in Fig. 2 shown in (d).
In Fig. 2 (d), in the present embodiment, spacecraft A protrusion 2 ' come into safe separating envelope BL ', it is necessary to
The configuration layouts of spacecraft A protrusion 2 ' are adjusted.
Although giving detailed description and explanation to the design method of the present invention above, it should be noted that we
The key parameter being related in this method can be changed and modified, effect is still without departing from specification and accompanying drawing caused by it
, all should be within protection scope of the present invention during the spirit covered.
Claims (4)
1. safe separating envelope design method between spacecraft, it is characterised in that comprise the following steps：
1) it is safe separating envelope design basis body to choose the relative less person of change of configuration layouts in two choristas；
2) on the basis of the outline envelope of reference body, minimum dynamic security distance is given, is pacified from benchmark to minimum dynamic is extended out
Full distance forms separation envelope；
3) all projecting points on search separation envelope, to each projecting point, using the projecting point as starting point, do and are separated with reference body
The ray that direction of motion angle is α；
4) if all rays are all fallen within separation envelope, the separation envelope is safe separating envelope；If there is ray to fall
Separate outside envelope, then using fall separate outside envelope and the ray of other rays can be surrounded and separate the figure that surrounds of envelope as
Safe separating envelope.
2. safe separating envelope design method between spacecraft as claimed in claim 2, it is characterised in that in the step 3), α
≥14°。
3. safe separating envelope design method between spacecraft as claimed in claim 2, it is characterised in that in the step 3),
The projecting point includes the starting point of separation envelope.
4. safe separating envelope design method between spacecraft as claimed in claim 2, it is characterised in that in the step 2),
Minimum dynamic security distance is according to task by empirically determined.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710541700.5A CN107346359B (en) | 2017-07-05 | 2017-07-05 | Method for designing safety separation envelope between spacecrafts |
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| CN201710541700.5A CN107346359B (en) | 2017-07-05 | 2017-07-05 | Method for designing safety separation envelope between spacecrafts |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108418736A (en) * | 2018-02-13 | 2018-08-17 | 北京空间技术研制试验中心 | Support the 1553B bus systems and control method of the in-orbit change of configuration of spacecraft |
| CN110414018A (en) * | 2018-04-27 | 2019-11-05 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | A kind of virtual reality simulation method and system of Flight Vehicle Stage Separation |
| CN115268257A (en) * | 2022-08-09 | 2022-11-01 | 北京航空航天大学 | Method and device for controlling separation of multiple spacecrafts |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2388758A1 (en) * | 2010-05-21 | 2011-11-23 | Thales | Satellite telecommunication system comprising a mechanism for separating messages transmitted by a plurality of transmitters |
| CN105549606A (en) * | 2015-12-21 | 2016-05-04 | 北京理工大学 | Super-close optimized collision-avoidance proximity method for failure satellite |
| CN106054613A (en) * | 2016-06-28 | 2016-10-26 | 西北工业大学 | Trajectory planning method for autonomous and safe approaching to rolling fault satellite |
| CN106081170A (en) * | 2016-07-11 | 2016-11-09 | 上海宇航系统工程研究所 | Satellite and the rocket connection separation mechanism |
| CN106596155A (en) * | 2016-11-18 | 2017-04-26 | 上海宇航系统工程研究所 | Spacecraft separation test system and method |
-
2017
- 2017-07-05 CN CN201710541700.5A patent/CN107346359B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2388758A1 (en) * | 2010-05-21 | 2011-11-23 | Thales | Satellite telecommunication system comprising a mechanism for separating messages transmitted by a plurality of transmitters |
| CN105549606A (en) * | 2015-12-21 | 2016-05-04 | 北京理工大学 | Super-close optimized collision-avoidance proximity method for failure satellite |
| CN106054613A (en) * | 2016-06-28 | 2016-10-26 | 西北工业大学 | Trajectory planning method for autonomous and safe approaching to rolling fault satellite |
| CN106081170A (en) * | 2016-07-11 | 2016-11-09 | 上海宇航系统工程研究所 | Satellite and the rocket connection separation mechanism |
| CN106596155A (en) * | 2016-11-18 | 2017-04-26 | 上海宇航系统工程研究所 | Spacecraft separation test system and method |
Non-Patent Citations (1)
| Title |
|---|
| 宋美茜: "有效载荷分离安全性及包络分析", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108418736A (en) * | 2018-02-13 | 2018-08-17 | 北京空间技术研制试验中心 | Support the 1553B bus systems and control method of the in-orbit change of configuration of spacecraft |
| CN110414018A (en) * | 2018-04-27 | 2019-11-05 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | A kind of virtual reality simulation method and system of Flight Vehicle Stage Separation |
| CN115268257A (en) * | 2022-08-09 | 2022-11-01 | 北京航空航天大学 | Method and device for controlling separation of multiple spacecrafts |
| CN115268257B (en) * | 2022-08-09 | 2024-06-07 | 北京航空航天大学 | Method and device for controlling separation of multiple spacecrafts |
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| CN107346359B (en) | 2020-08-28 |
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