CN107016153A - Manned spacecraft system weight control method based on matching system - Google Patents
Manned spacecraft system weight control method based on matching system Download PDFInfo
- Publication number
- CN107016153A CN107016153A CN201611181655.9A CN201611181655A CN107016153A CN 107016153 A CN107016153 A CN 107016153A CN 201611181655 A CN201611181655 A CN 201611181655A CN 107016153 A CN107016153 A CN 107016153A
- Authority
- CN
- China
- Prior art keywords
- weight
- design
- manned spacecraft
- supporting
- control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
Abstract
The invention provides a kind of manned spacecraft system weight control method based on matching system, to make system weight controllable, comprehensively, by various product according to supporting management, all supporting formation matching systems, matching system includes coordinative composition of equipments, cable is supporting, it is supporting directly under part, pipeline is supporting, standard component is supporting and heat control material is supporting, so that big to section structure, the part of as low as screw fastener is included into system, by the completeness for ensureing matching system, carry out Weight control to avoid Lou item based on complete matching system, so as to ensure the controllability of system weight state, accuracy.Therefore, pass through the present invention, all parts are included into system, and by ensureing the completeness of matching system, Weight control is carried out based on complete matching system, Lou item can be avoided, ensure controllability, the accuracy of system weight state, in addition, by accurate Weight control, reasonable to system weight can planning as a whole, strictly controlling, accurately realizing.
Description
Technical field
The invention belongs to the state control techniques field in manned spacecraft design and development process, it is related to one kind and is based on matching somebody with somebody
The manned spacecraft system weight control method of set system.
Background technology
System weight control is always the important process of the industry in development process such as Ship Design, airplane design, and is navigated
Weight control in its aircraft development process is particularly important.Aerospace craft has in large scale, system complex, technology close
Collection, comprehensive strong, very risky distinguishing feature, rationally control system weight, then can be real under certain carrying capacity
Now rational functional configuration and payload configuration, realizes larger effective utilization；Conversely, system weight is out of control, gently then can shadow
Acoustic system function, cause design repeatedly, influence designing quality and Development Schedule are heavy then may result in the development of model task
Only.
Manned spacecraft, as the Typical Representative of aerospace craft product, is the complex flight that current China develops
Device, due to its high reliability, the mission requirements of high security, more needs plan as a whole, strictly reasonable to system weight in its development process
Control, accurate realization.
Therefore, it is badly in need of a kind of scheme, can be put into practice according to Project R＆D, based on matching system, to carry out manned spacecraft
System weight control.
The content of the invention
It will be appreciated that manned spacecraft typically has following features：
Bay section is more, is typically made up of 2 or 3 bay sections；
Equipment is more, there is 600~1000 equipment on device；
Species is complicated, and the existing metal material of product has nonmetallic materials again on device.
Therefore, when carrying out Weight control, easily there is leakage item, the pre- timing of weight is not accurate enough carrying out, and carrying out
Entity weigh when side exposure excess weight problems, cause develop repeatedly.
Based on this, the present invention proposes a kind of manned spacecraft system weight control program based on matching system, can
Carry out delicate control.
The invention provides a kind of manned spacecraft system weight control method based on matching system, to make system weight
It is controllable, comprehensive, by various product according to supporting management, all supporting formation matching systems, wherein, matching system is matched somebody with somebody including equipment
Set, cable be supporting, directly under part is supporting, pipeline is supporting, standard component is supporting and heat control material is supporting so that it is big to section structure,
The part of as low as screw fastener is included into system, by ensureing the completeness of matching system, based on complete matching system
Carry out Weight control to avoid Lou item, so as to ensure the controllability of system weight state, accuracy.
Manned spacecraft matching system includes：Manned spacecraft coordinative composition of equipments table, the supporting table of manned spacecraft sensor, load
The supporting table of people's spacecraft priming system, the supporting table of manned spacecraft low-frequency cable net, the supporting table of manned spacecraft high frequency cable net, load
The supporting table of people's spacecraft 1553B bus cables, the supporting table of the bus cable of manned spacecraft 1394, manned spacecraft construction seals
Supporting table, the supporting table of manned spacecraft final assembly parts, the supporting table of manned spacecraft general assembly standard component, the total tubulature of manned spacecraft
Road and the supporting table of pipeline parts, manned spacecraft ventilation and the supporting table of cleaning system pipeline, manned spacecraft heat control material are supporting
Table.
In addition, the development of manned spacecraft is divided into schematic design phase, first sample design phase and positive sample design phase, its
In, Weight control works through whole Course of development, and in Project R＆D, Weight control work is included into system and set
In meter, and the closed loop and iteration designed with system design formation, when weight is unsatisfactory for predetermined index request, carry out scheme
Loss of weight measure is redesigned or takes, to meet weight demands.
The schematic design phase developed in manned spacecraft, perform following operate：Index decomposition is rationally carried out, wherein, it is right
System index is decomposed, while weight indicator after decomposition is allocated to subsystem and each responsible party；It is reserved reasonably to set
Surplus is counted, wherein, in the case where design has certain uncertainty, pass through the perfect of scheme so that system weight progressively increases
It is long, so that the design result according to early stage manned spacecraft, in the design margin of schematic design phase reserved 8%~10%；It is accurate
Weight is really carried out to estimate, wherein, wanted after weight indicator is distributed, carrying out system weight according to predetermined design estimates；
Design is modified in time, wherein, it is modified for the scheme that can not meet system weight index.
The first sample design phase developed in manned spacecraft, perform following operate：Weight control moves forward and closed loop, wherein,
In unit product design aspect, in first sample Design Stage, weight calculating is carried out before production, and in system design layer
Face, before the delivery of first sample product, accurately holds to system weight, and is designed improvement to the design for being unsatisfactory for requiring,
The closed-loop control link of design phase is used as so as to which Weight control be worked；It is accurate to carry out deviation control, wherein, according to product
Maturity, uses for reference the titration data prestored, determines the deviation range of product and carry out design deviation differentiation, by signing first sample
IDS tables, using the upper limit control method of deviation, make the summation of the accessible maximum weight of product as current system weight；Profit
Carry out weight optimizing with result of the test, wherein, carry out unit acceptance test and qualification test, carry out in system slow test,
The validity of vibration test, mechanical analysis checking design, and result of the test is analyzed, so that before design requirement is met
The over-redundancy for cutting down structure design is put, is pursued Weight-optimised；State control of weighing is carried out, wherein, carry out system before weighing
State is cleared up, and is completed weight and is estimated, presence states control is carried out in weighing process, and data analysis is carried out after weighing, and based on weight
Amount factor, designs according to result of calculation check system of weighing and carries out adaptive improvement.
Preferably, weight factor at least includes the difference weight of dress device frock weight, process conditions and true part, does not participate in title
The product weight of weight, gas-liquid working medium weight.
The positive sample design phase developed in manned spacecraft, perform following operate：Solidify design point, wherein, by system
Design point solidifies in time, and signs positive sample IDS tables in strict accordance with the deviation requirement of product, so that the delivery for carrying out product is tested
Receive；Product weight control is carried out, wherein, after system design is state cured, the strict product that carries out is in production, implementation process
Weight control, to it is overproof examination ＆ approval be rigid in checking up and control；Weight calculating is carried out, wherein, calculating essence is improved using measured value
Accuracy, and filling weight is precisely controlled when promoting gas cylinder, repropellenting.
Therefore, compared with prior art, following beneficial effect can be realized using the present invention：
The part greatly to section structure, as low as screw fastener is set to be included into system；
By ensureing the completeness of matching system, Weight control is carried out based on complete matching system, Lou item can be avoided, protected
Demonstrate,prove controllability, the accuracy of system weight state；
By accurate Weight control, it reasonable to system weight can plan as a whole, strictly control, accurately realize.
Brief description of the drawings
The schematic diagram that Fig. 1 is constituted for the basis weight of manned spacecraft；
Fig. 2 is the flow chart of the canonical system Weight control process of manned spacecraft.
Embodiment
It should be noted that in order to carry out delicate control, it is proposed that weight control method and control based on matching system
Flow.
(1) complete matching system is set up
Product category is numerous on manned spacecraft, quantity is more, is that system weight control brings very big difficulty.To make system
Weight is controllable, comprehensive, by various product according to supporting management, all supporting formation systems.Matching system includes coordinative composition of equipments, electricity
Cable is supporting, directly under part is supporting, pipeline is supporting, standard component is supporting, heat control material is supporting etc., makes big to section structure, as low as screw
The part of fastener is included into system.
By ensureing the completeness of matching system, Weight control is carried out based on complete matching system, then can avoid Lou item,
Ensure controllability, the accuracy of system weight state.Specifically, the matching system of manned spacecraft is as shown in the following Table 1.
Table 1
(2) control flow of closed loop is set up
The development of manned spacecraft is divided into schematic design phase, first sample design phase and positive sample design phase, Weight control
Work through whole Course of development.During Project R＆D, Weight control includes system design, and is designed with system design formation
Closed loop and iteration.When weight is unsatisfactory for index request, to carry out scheme redesign or take loss of weight measure, until meeting
Untill weight demands.Manned spacecraft canonical system Weight control flow is as shown in Figure 2.
Referring to Fig. 2, it is related to the control of the manned spacecraft system weight based on matching system of the specific embodiment of the invention
The idiographic flow of method is as follows：
1. the conceptual level
Rationally carry out index decomposition：Conceptual level will decompose to system index, at the same will decompose after weight indicator to
Subsystem and each responsible party are allocated.
Reserve rational design margin：The manned spacecraft schematic design phase can deposit uncertainty certain in design,
And it is perfect with scheme, system weight typically can progressively increase, according to the design result of early stage manned spacecraft, in scheme
The design margin of development stage typically reserved 8%~10%.
The accurate weight that carries out is estimated：System weight is carried out after weight indicator distribution according to design to estimate.
Design is modified in time：To be modified in time for the scheme that can not meet system weight index.
2. the first sample stage
Weight control moves forward and closed loop：, will before first sample Design Stage, production in unit product design aspect
Carry out weight calculating；In system design aspect, require there is a relatively accurate assurance to system weight before first sample product is delivered.
Improvement is designed in time, it is necessary to which the project for adjusting index is needed by Weight control batching for the design for being unsatisfactory for requiring
Standard can be performed.Weight control is worked and is used as the closed-loop control link of design phase.
It is accurate to carry out deviation control：To use for reference titration data before this according to the maturity of product, rationally determine product
Deviation range.The deviation that to be designed of inheriting completely, slightly changing and brand-new design is distinguished, and by this signing first sample
IDS tables.To ensure the feasibility of scheme, the upper limit control method of deviation, i.e., the maximum weight being likely to be breached product can be used
Summation be used as current system weight.
Weight optimizing is carried out using result of the test：The first sample stage will carry out will in unit acceptance test, qualification test, system
Carry out slow test, vibration test, mechanical analysis etc. to verify design validity, result of the test is analyzed, met
Structure design over-redundancy is rationally cut down on the premise of design requirement, is pursued Weight-optimised.
Carry out state control of weighing：System mode cleaning is carried out before weighing, weight is completed and estimates；Carried out in weighing process
Presence states are controlled；Data analysis is carefully carried out after weighing, to consider to fill device frock weight, process conditions and the difference weight of true part
Measure, do not participate in the factors such as the product weight weighed, gas-liquid working medium weight.Design and carry out according to result of calculation check system of weighing
Adaptive improvement.
3. the positive sample stage
Solidify design point in time：Into the positive sample design phase, system design state should solidify in time.In strict accordance with product
Deviation requirement sign positive sample IDS tables, and carry out the delivery of product accordingly and check and accept.
It is strict to carry out product weight control：After system design is state cured, the strict product that carries out is in production, implementation process
Overproof examination ＆ approval are rigid in checking up by Weight control, it then follows the principle of " prevent as far as possible, strictly review " carries out overproof control.
It is accurate to carry out weight calculating：Carry out using measured value in principle during weight calculating, to improve calculating precision.Separately
Outside, it is that before propulsive working medium filling, the accurate weight of emission state is by meter because last time system is weighed before transmission
Obtain, it is therefore desirable to which promoting will be precisely controlled when gas cylinder, repropellenting to filling weight.
Do not specified in the present invention and partly belong to techniques known.
Claims (7)
1. a kind of manned spacecraft system weight control method based on matching system, it is characterised in that to make system weight can
Control, comprehensively, by various product according to supporting management, all supporting formation matching systems,
Wherein, the matching system include coordinative composition of equipments, cable it is supporting, directly under part is supporting, pipeline is supporting, standard component is supporting and heat
Control material is supporting, so that the big part to section structure, as low as screw fastener is included into system,
By ensureing the completeness of the matching system, carry out Weight control to avoid Lou item based on complete matching system, from
And ensure the controllability of system weight state, accuracy.
2. the manned spacecraft system weight control method according to claim 1 based on matching system, it is characterised in that
The manned spacecraft matching system includes：Manned spacecraft coordinative composition of equipments table, the supporting table of manned spacecraft sensor, manned boat
Its supporting table of device priming system, the supporting table of manned spacecraft low-frequency cable net, the supporting table of manned spacecraft high frequency cable net, manned boat
The supporting table of its device 1553B bus cables, the supporting table of the bus cable of manned spacecraft 1394, manned spacecraft construction seals are supporting
Table, the supporting table of manned spacecraft final assembly parts, the supporting table of manned spacecraft general assembly standard component, manned spacecraft general assembly pipeline and
The supporting table of pipeline parts, manned spacecraft ventilation and the supporting table of cleaning system pipeline, the supporting table of manned spacecraft heat control material.
3. the manned spacecraft system weight control method according to claim 1 or 2 based on matching system, its feature exists
In, the development of the manned spacecraft is divided into schematic design phase, first sample design phase and positive sample design phase,
Wherein, Weight control work is through whole Course of development, and in Project R＆D, and the Weight control work is received
Enter into system design, and the closed loop and iteration designed with system design formation,
When weight is unsatisfactory for predetermined index request, carry out scheme redesign or loss of weight measure is taken, to meet weight demands.
4. the manned spacecraft system weight control method according to claim 3 based on matching system, it is characterised in that
The schematic design phase developed in the manned spacecraft, perform following operate：
Index decomposition is rationally carried out, wherein, system index is decomposed, while by weight indicator after decomposition to subsystem and respectively
Responsible party is allocated；
Rational design margin is reserved, wherein, in the case where design has certain uncertainty, by the perfect of scheme, make
System weight is obtained progressively to increase, so that the design result according to early stage manned spacecraft, in the schematic design phase reserved 8%
~10% design margin；
The accurate weight that carries out is estimated, wherein, wanted after the weight indicator is distributed, system is carried out according to predetermined design
Weight is estimated；
Design is modified in time, wherein, it is modified for the scheme that can not meet the system weight index.
5. the manned spacecraft system weight control method according to claim 3 based on matching system, it is characterised in that
The first sample design phase developed in the manned spacecraft, perform following operate：
Weight control moves forward and closed loop, wherein, in unit product design aspect, in first sample Design Stage, in production
Preceding progress weight calculating, and in system design aspect, before the delivery of first sample product, system weight is accurately held, and it is right
The design for being unsatisfactory for requiring is designed improvement, and the closed-loop control link of design phase is used as so that Weight control be worked；
It is accurate to carry out deviation control, wherein, according to the maturity of product, the titration data prestored is used for reference, the inclined of product is determined
Poor scope simultaneously carries out design deviation differentiation, by the IDS tables for signing first sample, using the upper limit control method of deviation, makes product reachable
The summation of the maximum weight arrived is used as current system weight；
Weight optimizing is carried out using result of the test, wherein, carry out unit acceptance test and qualification test, carry out static(al) in system
Experiment, vibration test, the validity of mechanical analysis checking design, and result of the test is analyzed, so that will meeting design
The over-redundancy of structure design is cut down on the premise of asking, is pursued Weight-optimised；
State control of weighing is carried out, wherein, system mode cleaning is carried out before weighing, weight is completed and estimates, carried out in weighing process
Presence states are controlled, and data analysis is carried out after weighing, and based on weight factor, according to weighing, result of calculation check system is designed simultaneously
Carry out adaptive improvement.
6. the manned spacecraft system weight control method according to claim 5 based on matching system, it is characterised in that
The weight factor at least includes the difference weight of dress device frock weight, process conditions and true part, does not participate in the product weight weighed
Amount, gas-liquid working medium weight.
7. the manned spacecraft system weight control method according to claim 3 based on matching system, it is characterised in that
The positive sample design phase developed in the manned spacecraft, perform following operate：
Solidify design point, wherein, system design state is solidified in time, and positive sample is signed in strict accordance with the deviation requirement of product
IDS tables, so that the delivery for carrying out product is checked and accepted；
Product weight control is carried out, wherein, after the system design is state cured, the strict product that carries out is in production, implementation
During Weight control, to it is overproof examination ＆ approval be rigid in checking up and control；
Weight calculating is carried out, wherein, calculating precision is improved using measured value, and when promoting gas cylinder, repropellenting
Filling weight is precisely controlled.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611181655.9A CN107016153A (en) | 2016-12-20 | 2016-12-20 | Manned spacecraft system weight control method based on matching system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611181655.9A CN107016153A (en) | 2016-12-20 | 2016-12-20 | Manned spacecraft system weight control method based on matching system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107016153A true CN107016153A (en) | 2017-08-04 |
Family
ID=59440134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611181655.9A Pending CN107016153A (en) | 2016-12-20 | 2016-12-20 | Manned spacecraft system weight control method based on matching system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107016153A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110194283A (en) * | 2019-06-14 | 2019-09-03 | 北京卫星环境工程研究所 | Spacecraft AIT process layout method with transit hall |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468849A (en) * | 2015-11-26 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft weight control method |
-
2016
- 2016-12-20 CN CN201611181655.9A patent/CN107016153A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468849A (en) * | 2015-11-26 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft weight control method |
Non-Patent Citations (2)
| Title |
|---|
| 李兴乾 等: ""载人航天器系统重量控制方法研究"", 《航天器环境工程》 * |
| 柳宁 等: ""天宫一号技术状态管理方法及工程实践"", 《载人航天》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110194283A (en) * | 2019-06-14 | 2019-09-03 | 北京卫星环境工程研究所 | Spacecraft AIT process layout method with transit hall |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Tuegel | The airframe digital twin: some challenges to realization | |
| CN112380625A (en) | aMBSE method suitable for design of aircraft airborne system architecture | |
| US20130260016A1 (en) | Sealant Analysis System | |
| Dmitriev et al. | Special aspects of quality assurance in the design, manufacture, testing of aerospace engineering products | |
| CN106845925A (en) | Engineering based on the BIM amount of calculating quickly and project high in the clouds collaborative platform soon is to amount method | |
| CN106971051A (en) | A kind of flight ensures service time evaluation method and system | |
| CN107748808A (en) | Reliability index distribution optimization method, system and medium based on Operations of Interva Constraint | |
| Krist et al. | Kestrel Results at Liftoff Conditions for a Space Launch System Configuration in Proximity to the Launch Tower | |
| CN107016153A (en) | Manned spacecraft system weight control method based on matching system | |
| Abdol-Hamid et al. | Ares I Vehicle Computed Turbulent Ascent Aerodynamic Data Development and Analysis | |
| Kobryn et al. | Digital thread and twin for systems engineering: EMD to disposal | |
| Bergeron et al. | Near-body/Cartesian off-body simulations for C-17 and extraction parachute | |
| US8645114B1 (en) | Data point averaging for computational fluid dynamics data | |
| Kryuchkova | Development and testing of non-viscid solver based on UST3D programming code | |
| Feng et al. | Research on the demand distribution of aviation equipment maintenance spare parts | |
| CN109409000B (en) | Test coverage analysis method | |
| Viitanen et al. | A review of aeronautical fatigue investigations in finland april 2019-april 2021 | |
| Dubinskii et al. | Safety provision for composite structures in aviation: today and tomorrow | |
| Demenko et al. | Evaluation of spacecraft composite structure load-carrying capability by shock test | |
| Sinske et al. | HALO flight test with instrumented under-wing stores for aeroelastic and load measurements in the DLR project iLOADS | |
| Cosner | Assessment of vehicle performance predictions using CFD | |
| Sun et al. | Cost-Effectiveness analysis model for civil aircraft flight tests | |
| Munjulury et al. | Knowledge-based aircraft fuel system integration | |
| Bush et al. | Computational and experimental investigation of F/A-18E sting support and afterbody distortion effects | |
| Arif et al. | Attribute control chart for a lognormal distribution under accelerated time-censoring |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170804 |