CN103129751A - Design method and system of spacecraft based on split-type configuration - Google Patents
Design method and system of spacecraft based on split-type configuration Download PDFInfo
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- 238000000926 separation method Methods 0.000 claims description 42
- 238000005457 optimization Methods 0.000 claims description 10
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Abstract
The invention discloses a design method of a spacecraft based on a split-type configuration. The method includes the steps of: according to the requirement of a mission, calculating the velocity increment needed by operations including orbital transfer, determining the required fuel carrying volume of the spacecraft, optimizing dry weights of modular systems of all levels if the fuel carrying volume exceeds a threshold value, and performing multi-level expansion to a combination-type spacecraft according to needs. The invention further provides a corresponding system. The design method and the system of the spacecraft based on the split-type configuration are mainly characterized by having a multi-level combination-type configuration design, reduce the on-orbit dry weight of the space craft through multiple splitting, and improve the propellant efficiency after being split. Compared with a configuration design of a traditional integration type space craft, the spacecraft based on the split-type configuration has the advantages of being strong in engine-driven capacity, long in on-orbit life, high in carrying capacity, good in expansibility and easy to form type serialization. The design method of the spacecraft based on the split-type configuration relates to configuration design methods of novel spacecrafts which are capable of performing missions such as deep space exploration and long-life high-orbit large platform.
Description
Technical field
The present invention relates to the space vehicle overall design technique, be specifically related to a kind of space vehicle method of designing and system based on the separation type configuration.
Background technology
Space flight market had proposed the demand of the aspects such as strong motor-driven, long life, flight far away, large carrying in recent years, occurred carrying large-scale optics load 8-10 ton scale satellite, go to Mars to carry out the aircraft of survey of deep space, these new demands require all spacecraft to carry to advance that dosage is more, architecture quality is lighter.How under the situation that total mass and quality of loads are determined, obtains larger velocity increment, being conducive to the life-span and motor-driven, or under total mass and the certain condition of velocity increment, raising load carrying capacity is the important topic that the spacecraft general design faces.
Space vehicle separation type configuration designing method is the space vehicle for the propellant amount of carrying large percentage, when general design, the propulsion system that aircraft power is provided is designed to a kind of method of designing of separable standalone module.
In each subsystem of large space aircraft, propulsion subsystem has taken larger " quality resource " and " volume resource ".When general design, propulsion system is designed by separable standalone module, when propellant exhausts, N/R is partly cast aside, can effectively reduce propulsion system residue dry weight to the impact of follow-up maneuverability, dry weight alleviate the optimization that will be conducive to Aircraft Conceptual Design, the enhancing of function and the raising of overall performance.
Summary of the invention
For the deficiencies in the prior art part, the object of the present invention is to provide a kind of space vehicle method of designing based on the separation type configuration, for space vehicle (as deep space probe, high rail large platform of the long life etc.) design with large velocity increment demand provides a kind of method of designing.
According to an aspect of the present invention, provide a kind of space vehicle method of designing based on the separation type configuration, comprise the steps:
Step 1: according to mission requirements, calculating comprises the required velocity increment of operation that becomes rail, determines the fuel amount of carrying that aircraft is required, if the described fuel amount of carrying surpasses threshold value, enters step 2 and continues to carry out;
Step 2: modular system dry weights at different levels are optimized;
Step 3: as required the compound type space vehicle is carried out multi-tier.
Preferably, described threshold value is 50% of aircraft total mass.
Preferably, described step 2 is specially, according to the required fuel quantities that carry at different levels, carry out the estimation of preliminary structure and propulsion system dry weight, after the mechanical analysis simulation calculation, each level system dry weight that comprises disengagement gear is optimized, is down to system's dry weight minimum.
Preferably, described step 3 is specially, and further carries out interval division to carrying fuel ratio, thereby determines a minute number of stages, and minute number of stages is between 2 grades to 4 grades.
Preferably, if the fuel amount of carrying the aircraft total mass 50% to 70% between, adopt 2 grades of separation designs; If the fuel amount of carrying the aircraft total mass 70% to 80% between, adopt 3 grades of separation designs; If the fuel amount of carrying surpasses 80% of aircraft total mass, consider to adopt 4 grades to separate design.
According to another aspect of the present invention, also provide a kind of space vehicle design system based on the separation type configuration, comprise as lower device:
Analytical equipment is used for according to mission requirements, calculates to comprise the required velocity increment of operation that becomes rail, determines the fuel amount of carrying that aircraft is required, if the described fuel amount of carrying surpasses threshold value, triggers optimization device and continues to carry out;
Optimization device is used for modular system dry weights at different levels are optimized;
Expanding unit is used for as required the compound type space vehicle being carried out the multi-tier setting.
Preferably, described threshold value is 50% of aircraft total mass.
Preferably, described optimization device specifically is used for, according to the required fuel quantities that carry at different levels, carry out the estimation of preliminary structure and propulsion system dry weight, after the mechanical analysis simulation calculation, each level system dry weight that comprises disengagement gear is optimized, is down to system's dry weight minimum.
Preferably, described expanding unit specifically is used for, and further carries out interval division to carrying fuel ratio, thereby determines a minute number of stages, and minute number of stages is between 2 grades to 4 grades.
Preferably, if the fuel amount of carrying the aircraft total mass 50% to 70% between, adopt 2 grades of separation designs; If the fuel amount of carrying the aircraft total mass 70% to 80% between, adopt 3 grades of separation designs; If the fuel amount of carrying surpasses 80% of aircraft total mass, consider to adopt 4 grades to separate design.
The present invention compares with traditional integral type space vehicle Design Mode, and its advantage and beneficial effect comprise:
1) strong at the trailer kinetic force: the advantage of separation type space vehicle maneuverability mainly comes from the increase that propellant exhausts, gives up the velocity increment that brings after unnecessary dry weight, namely under launch mass and the certain prerequisite of the propellant amount of carrying, adopt the space vehicle of separation type thought design that larger velocity increment can be provided, thereby improved maneuverability and the capability of fast response of space vehicle.
2) extend in the rail life-span: because the space vehicle that adopts separation design is carrying under the prerequisite of identical propelling dosage, can provide larger velocity increment to keep for track, thereby can extend the service life of aircraft.
3) improve load-carrying capacity: after each level system dry weight is optimized design, the conservation of fuel amount that the separation type configuration brings will can be used for increasing the load-bearing ability.Usually, the aircraft scale is larger, adopts the load-carrying capacity that obtains after separation design to promote more obvious.
Description of drawings
By reading the detailed description of non-limiting example being done with reference to the following drawings, it is more obvious that other features, objects and advantages of the present invention will become:
Fig. 1 is according to the space vehicle emission state figure based on the separation type configuration provided by the invention;
Fig. 2 is at the rail constitution diagram according to the space vehicle based on the separation type configuration provided by the invention;
Fig. 3 is the schematic diagram of state before and after separating according to the space vehicle based on the separation type configuration provided by the invention.
In figure:
1 is the load cabin;
2 is service module;
3 is propulsion module;
9 is detachable module.
The specific embodiment
The present invention is described in detail below in conjunction with specific embodiment.Following examples will help those skilled in the art further to understand the present invention, but not limit in any form the present invention.Should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement.These all belong to protection scope of the present invention.
In the present embodiment, particularly, described space vehicle method of designing based on the separation type configuration comprises the steps:
Step 1: determine the demand that fuel carries according to mission requirements.
According to the mission requirements of aircraft, calculate the required velocity increments of operation such as becoming rail, thereby obtain the required fuel ratio that carries of aircraft.And then determine whether to adopt the separation type configuration designing method.It is generally acknowledged in a preference of the present embodiment when the fuel amount of carrying surpass total mass 50% the time, should adopt the separation type Configuration Design.
Step 2: modular system dry weights at different levels are optimized.
Typical separation type configuration can be divided into three cabin sections: propulsion module, service module and load cabin.Each cabin section is equipped with the propulsion system of coupling and carries corresponding fuel according to the task needs.Usually, propulsion module mainly is same as the mobile operation that large velocity increment is provided, and needs to load a large amount of fuel; Be mainly each subsystem of satellite in service module, usually load a small amount of fuel; The load cabin is mainly capacity weight working environment is provided, and does not usually possess maneuverability.
Each cabin section is carried out fuel distribute, and make structure and the estimation of propulsion system dry weight.By simulation calculation, each level system dry weight (containing disengagement gear) is optimized, system's dry weight is down to minimum, maximize so that protect the advantage of separation design.
Step 3: as required multi-tier is carried out in compound type spaceflight.
The space vehicle of separation type, each module independent design according to different mission requirements, can the flexible configuration module form, promote the extended capability of aircraft, to satisfy the demand of the different tasks such as survey of deep space, long-term earth observation, Space Attack, different loads.Propelling unit/cabin based on separating thought design standalone module has good scalability: the first, take the basical traditional model module as baseline, under the prerequisite that does not change main structure, rationally enlarge the volume of tank, and improve the fuel amount of carrying.The second, increase independent propulsion die, provide larger velocity increment by the multistage-separation (MSS) mode.
After design parameters, index, technique and the state of propulsion module basical traditional model module is cured, easier normalisation, seriation and type spectrum.Simultaneously between each standalone module, as propulsion module and service module can independently develop, concurrent testing, be conducive to shorten the lead time, realize producing fast, reducing development cost.Can satisfy better the mission requirements that the Future in China polytypic develops simultaneously, high density is launched.
Correspondingly, the present invention also provides a kind of space vehicle design system based on the separation type configuration, comprises as lower device:
Analytical equipment is used for according to mission requirements, calculates to comprise the required velocity increment of operation that becomes rail, determines the fuel amount of carrying that aircraft is required, if the described fuel amount of carrying surpasses threshold value, triggers optimization device and continues to carry out;
Optimization device is used for modular system dry weights at different levels are optimized;
Expanding unit is used for as required the compound type space vehicle being carried out the multi-tier setting.
In a preference of the present embodiment, described threshold value is 50% of aircraft total mass.Described optimization device specifically is used for, according to the required fuel quantities that carry at different levels, carry out the estimation of preliminary structure and propulsion system dry weight, after the mechanical analysis simulation calculation, each level system dry weight that comprises disengagement gear is optimized, is down to system's dry weight minimum.Described expanding unit specifically is used for, and further carries out interval division to carrying fuel ratio, thereby determines a minute number of stages, and minute number of stages is between 2 grades to 4 grades.
Further preferably, if the fuel amount of carrying the aircraft total mass 50% to 70% between, adopt 2 grades of separation designs; If the fuel amount of carrying the aircraft total mass 70% to 80% between, adopt 3 grades of separation designs; If the fuel amount of carrying surpasses 80% of aircraft total mass, consider to adopt 4 grades to separate design.
Above specific embodiments of the invention are described.It will be appreciated that, the present invention is not limited to above-mentioned specific implementations, and those skilled in the art can make various distortion or modification within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. the space vehicle method of designing based on the separation type configuration, is characterized in that, comprises the steps:
Step 1: according to mission requirements, calculating comprises the required velocity increment of operation that becomes rail, determines the fuel amount of carrying that aircraft is required, if the described fuel amount of carrying surpasses threshold value, enters step 2 and continues to carry out;
Step 2: modular system dry weights at different levels are optimized;
Step 3: as required the compound type space vehicle is carried out multi-tier.
2. the space vehicle method of designing based on the separation type configuration according to claim 1, is characterized in that, described threshold value is 50% of aircraft total mass.
3. the space vehicle method of designing based on the separation type configuration according to claim 1, it is characterized in that, described step 2, be specially, according to the required fuel quantities that carry at different levels, carry out the estimation of preliminary structure and propulsion system dry weight, after the mechanical analysis simulation calculation, each level system dry weight that comprises disengagement gear is optimized, is down to system's dry weight minimum.
4. the space vehicle method of designing based on the separation type configuration according to claim 1, is characterized in that, described step 3 is specially, and further carries out interval division to carrying fuel ratio, thereby determine a minute number of stages, and minute number of stages is between 2 grades to 4 grades.
5. the space vehicle method of designing based on the separation type configuration according to claim 4, is characterized in that, if the fuel amount of carrying the aircraft total mass 50% to 70% between, adopt 2 grades of separation designs; If the fuel amount of carrying the aircraft total mass 70% to 80% between, adopt 3 grades of separation designs; If the fuel amount of carrying surpasses 80% of aircraft total mass, consider to adopt 4 grades to separate design.
6. the space vehicle design system based on the separation type configuration, is characterized in that, comprises as lower device:
Analytical equipment is used for according to mission requirements, calculates to comprise the required velocity increment of operation that becomes rail, determines the fuel amount of carrying that aircraft is required, if the described fuel amount of carrying surpasses threshold value, triggers optimization device and continues to carry out;
Optimization device is used for modular system dry weights at different levels are optimized;
Expanding unit is used for as required the compound type space vehicle being carried out the multi-tier setting.
7. the space vehicle design system based on the separation type configuration according to claim 6, is characterized in that, described threshold value is 50% of aircraft total mass.
8. the space vehicle design system based on the separation type configuration according to claim 6, it is characterized in that, described optimization device, specifically be used for, according to the required fuel quantities that carry at different levels, carry out the estimation of preliminary structure and propulsion system dry weight, after the mechanical analysis simulation calculation, each level system dry weight that comprises disengagement gear is optimized, is down to system's dry weight minimum.
9. the space vehicle design system based on the separation type configuration according to claim 6, is characterized in that described expanding unit, specifically be used for, further carry out interval division to carrying fuel ratio, thereby determine a minute number of stages, minute number of stages is between 2 grades to 4 grades.
10. the space vehicle design system based on the separation type configuration according to claim 9, is characterized in that, if the fuel amount of carrying the aircraft total mass 50% to 70% between, adopt 2 grades of separation designs; If the fuel amount of carrying the aircraft total mass 70% to 80% between, adopt 3 grades of separation designs; If the fuel amount of carrying surpasses 80% of aircraft total mass, consider to adopt 4 grades to separate design.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103612774A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Separable micro and nano-satellite configuration |
| CN105005643A (en) * | 2015-06-26 | 2015-10-28 | 北京航空航天大学 | Manned lunar-landing quality scale estimation method and system |
| CN105035360A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Cabin-segmentation type separable platform configuration based on four-point connection |
| CN110356588A (en) * | 2019-07-05 | 2019-10-22 | 中国人民解放军国防科技大学 | Multi-stage stacking co-location launching method of heterogeneous satellite cluster |
| CN111891391A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Satellite propulsion module and its separation method |
Citations (1)
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|---|---|---|---|---|
| CN101687553A (en) * | 2006-12-11 | 2010-03-31 | 迈克尔·D·约翰逊 | modular spacecraft |
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- 2013-01-18 CN CN2013100204663A patent/CN103129751A/en active Pending
Patent Citations (1)
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|---|---|---|---|---|
| CN101687553A (en) * | 2006-12-11 | 2010-03-31 | 迈克尔·D·约翰逊 | modular spacecraft |
Non-Patent Citations (1)
| Title |
|---|
| 张伟: "空间飞行器分离式构型设计思想初探", 《中国宇航学会深空探测技术专业委员会第九届学术年会论文集》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103612774A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Separable micro and nano-satellite configuration |
| CN103612774B (en) * | 2013-11-20 | 2015-12-09 | 西北工业大学 | A detachable micro-nano-satellite configuration |
| CN105005643A (en) * | 2015-06-26 | 2015-10-28 | 北京航空航天大学 | Manned lunar-landing quality scale estimation method and system |
| CN105005643B (en) * | 2015-06-26 | 2018-01-23 | 北京航空航天大学 | A kind of method and system of manned moon landing's mass Quantity customizing |
| CN105035360A (en) * | 2015-07-31 | 2015-11-11 | 上海卫星工程研究所 | Cabin-segmentation type separable platform configuration based on four-point connection |
| CN110356588A (en) * | 2019-07-05 | 2019-10-22 | 中国人民解放军国防科技大学 | Multi-stage stacking co-location launching method of heterogeneous satellite cluster |
| CN111891391A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Satellite propulsion module and its separation method |
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Application publication date: 20130605 |