CN110276107A - It is a kind of consider the more sphere tanks of spacecraft between weak dependence more sphere tank structural parameter determining methods - Google Patents
It is a kind of consider the more sphere tanks of spacecraft between weak dependence more sphere tank structural parameter determining methods Download PDFInfo
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Abstract
It is a kind of consider the more sphere tanks of spacecraft between weak dependence more sphere tank structural parameter determining methods, to more sphere tank structures carry out Preliminary design, primarily determine sphere structure power transmission layout basic design parameters；Establish the finite element model of more sphere tank structures；Autonomous flight section internal pressure design conditions, powered phase internal pressure, axis pressure and shearing co-design operating condition are carried out to finite element model using finite element method and hoisting Design operating condition is analyzed；Extract load at the symmetrical border in operating condition, if load is more than allowable load at symmetrical border, then adjust sphere structure design parameter, if boundary load meets design requirement, then more sphere tank structure designs are completed, the basic design parameters for saving sphere structure power transmission layout, as final more sphere tank structural parameters.
Description
Technical field
The present invention relates to a kind of more sphere tank structural parameters of weak dependence between consideration more sphere tanks of spacecraft
It determines method, belongs to aerospace craft structure-design technique field.
Background technique
In aerospace craft field of structural design, the method for salary distribution of inside configuration load determines the specific side of structure design
Load is reasonably assigned in bearing structure by case by the transfer mode of optimization design load, to making full use of material to hold
It carries potentiality, mitigate Flight Vehicle Structure weight, guarantee that load-carrying properties are of great significance.
The existing more sphere structure design methods of aerospace craft generally face overall structure and carry out design, for overall structure
Each component between interaction concern it is less, influence each other between each component, design relevance it is stronger, to carry out set up grade set
Meter and verification experimental verification have a major impact, and can only carry out the bulk testing verifying of full device structure, cannot achieve the level of infrastructure product
Formula verifying, causes empirical risk uncontrollable, and test failure causes design repeatedly, and waste financial resources material resources.
Summary of the invention
Present invention solves the technical problem that are as follows: it overcomes the shortage of prior art, mentions and locate a kind of more spheres of consideration spacecraft
More sphere tank structural parameter determining methods of weak dependence, problem to be solved by this invention are how to reduce space flight between tank
Influencing each other between each sphere component, meets between the more sphere structures of spacecraft in the more sphere structure designs of aircraft
Weak relevant design demand meets the needs of modularized design, the low cost verifying of spacecraft structure, solves structure development
The problem of necessary overall structure is considered every possible angle in the process, it is only necessary to can meet after succeeding in developing independent single tank structure assembling
Whole device performance requirement, significantly shortens the lead time, reduces development cost.
The technical solution that the present invention solves are as follows: it is a kind of consider the more sphere tanks of spacecraft between weak dependence more spheres
Tank structural parameter determining method, steps are as follows:
Step 1: determine the design parameter of more sphere tanks, the thickness and width including whole frame ring, the radius of inter-tank section
And wall thickness；
Step 2: according to the design parameter for more sphere tanks that step 1 determines, establishing the finite element of more sphere tank structures
Model；
Step 3: the internal pressure performance analysis of autonomous flight section is carried out to the finite element model of step 2, obtain each inter-tank section by
Tank connected to it transmitting come load；
Step 4: the finite element model of step 2 being carried out powered phase internal pressure, axis is pressed and shears combinational acting to analyze, is obtained each
The load that the tank connected to it transmitting that inter-tank section is subject to comes；
Step 5: lifting performance analysis being carried out to the finite element model of step 2, obtain that each inter-tank section is subject to is connected thereto
Tank transmitting come load；
Step 6: the load obtained to step 3,4,5 judges, if having among step 3,4,5 obtained load one or
Above it has been more than the loading demands of setting, then has determined that the design parameter of more sphere tanks is undesirable, change the step setting in 1
Count parameter, return step 1；Otherwise determination step 1 determines that the design parameter of more sphere tanks meets weak correlation between more sphere tanks
Property require.
It is preferred: more sphere tanks, including multiple spherical tanks, inter-tank section, whole frame ring, support；Support is multiple, if
It sets on the episphere and lower semisphere of multiple spherical tanks；
It is preferred: to be connected between the adjacent spherical tank of every two by inter-tank section, multiple spherical shape tanks pass through its episphere
The support of setting is connect with whole frame ring；Inter-tank section spherical tank connected to it does not penetrate through, and multiple spherical shape tanks have independent
Store function；
Preferred: whole frame ring is the annular slab of bandwidth.
Preferred: inter-tank section, is hollow cylinder, and cylindrical body both ends connect spherical tank.
It is preferred: main inflight phase internal pressure design conditions, specifically: in autonomous flight section, each sphere tank boost pressure
The working condition of load difference maximum rating.
It is preferred: powered phase internal pressure, axis pressure and shearing combinational acting, specifically: in powered phase, structure transverse acceleration is most
Internal pressure, axis pressure and the working condition for shearing state at big moment.
It is preferred: lifting operating condition, specifically: the lifting loaded-up condition in lifting, when suspension centre minimum number state.
Preferred: autonomous flight section refers to the utonomous working state period that aircraft is detached from after rocket.
Preferred: powered phase refers to that aircraft is carried the working condition period of the period of rocket carrying.
Preferred: lifting refers to working condition period when lifting of the aircraft at ground.
Preferred: the support of spherical tank bottom connects carrier rocket, and support is overloaded due to flight generates axis pressure and shearing,
Fuel is stored in tank
Preferred: in powered phase, inter-tank section can generate axis pressure and shearing
Preferred: in hoisting process, the support being connect by top with whole frame ring slings more sphere tanks.
The advantages of the present invention over the prior art are that:
(1) present invention has fully considered the carrying and design feature of more sphere tanks, sets for the modularization of practical structures
The development demand that meter, low cost are verified, proposes weak phase between the more sphere tank structures of spacecraft based on finite element method
Close design method.By effectively controlling the load transmitted between tank structure, effect of the inter-tank section in terms of transmitting load is weakened,
The single sphere independent design and verification experimental verification that more sphere structures can be achieved, reduce design complexities and validation difficulty.
(2) present invention is not store by using based on the load scheme transmitted between finite element method tank structure
The constraint of box structure form can carry out weak relevant design between more sphere tank structures towards complicated spherical tank structure.
(3) weak relevant design between the more sphere tank structures of spacecraft proposed by the present invention, reduces between tank and case
Connection load between section simplifies and connects design between tank and inter-tank section.
(4) weak relevant design between the more sphere tank structures of spacecraft proposed by the present invention is carried out using independent tank
Verification experimental verification shortens product production cycle, improves development efficiency.
(5) weak relevant design between the more sphere tank structures of spacecraft proposed by the present invention, it is only necessary to which tackling key problem is developed only
Vertical tank structure, can significantly reduce development cost.
Detailed description of the invention
Fig. 1 is preferred four spheres tank structural schematic diagram.
Fig. 2 more sphere tank structural parameters of weak dependence between more sphere tanks determine implementing procedure.
Specific embodiment
The invention will be described in further detail in the following with reference to the drawings and specific embodiments.
Present invention is mainly used for the more sphere tank field of structural design of spacecraft, aircraft include autonomous flight section and
Powered phase；Autonomous flight section refers to the utonomous working state period that aircraft is detached from after rocket, and powered phase refers to that aircraft is transported
Carry the working condition period for the period that rocket carries.Inter-tank section is in terms of transmitting load between method of the invention can weaken sphere
Effect, solve each interactional critical issue of sphere tank of more sphere tank structures, it can be achieved that more sphere structures
Single sphere independent design and verification experimental verification substitute whole device test for single sphere structure verifying and establish technical foundation, be embodied
It is as follows:
Step 1: determining the design parameter of more sphere tanks, the thickness including whole frame ring (is denoted as Kt) and width (be denoted as
Kb), the radius of inter-tank section (is denoted as Dr) and wall thickness (be denoted as Dt), wherein more sphere tanks, including multiple spherical tanks, inter-tank section,
Whole frame ring, support；Support be it is multiple, the episphere and lower semisphere of multiple spherical tanks, the adjacent spherical storage of every two are set
It is connected between case by the inter-tank section of hollow cylindrical, the support and whole frame ring that multiple spherical shape tanks are arranged by its episphere
Connection；Inter-tank section spherical tank connected to it does not penetrate through, and multiple spherical shape tanks have independent store function；
Step 2: according to the design parameter for more sphere tanks that step 1 determines, establishing the finite element of more sphere tank structures
Model；
Step 3: the tank inner pressuring load of the utonomous working state period after being detached from rocket due to aircraft is mutually larger, and each
Tank pressurization may be different according to needing, and different influences is generated to inter-tank section, therefore need to carry out autonomous flight section internal pressure
Operating condition design, the internal pressure of the utonomous working state period after aircraft disengaging rocket is carried out by the finite element model to step 2
Performance analysis obtains the load that the tank connected to it transmitting that each inter-tank section is subject to comes, and wherein inner pressuring load operating condition is each ball
Body tank boost pressure load difference maximum rating, circular are as follows:
Assuming that aircraft spherical shape tank total n, the internal pressure of each tank is (P1、...、Pi、...、Pj、...、Pn), i
Be 1 integer for arriving n with j, i is less than j, and the utonomous working state total s after being detached from rocket is a, respectively 1,2 ..., s, if t
For utonomous working status number, t is more than or equal to 1 and is less than or equal to s, then design conditions Psj(pressure difference in design conditions, that is, each tank
It is worth maximum working condition) are as follows:
Wherein, PsjFor the maximum working condition of pressure difference in each tank, the value of i and j are that 1~n, t are 1~s；Pi t
For the internal pressure under t-th of state of i-th of tank；For the internal pressure under t-th of state of j-th of tank；
Step 4:, need to be to step since aircraft powered phase lateral load is affected to the structure between each tank
2 finite element model carries out powered phase internal pressure, axis pressure and shearing combinational acting analysis, and obtain that each inter-tank section is subject to is connected thereto
The load come of tank transmitting, wherein internal pressure, axis pressure and shearing combinational acting are in powered phase, when structure transverse acceleration maximum
Internal pressure, axis pressure and the shearing state at quarter；
Step 5: due to being lifted with there may be non-uniform load, slinger being carried out to the finite element model of step 2
Condition analysis obtains the load that the tank connected to it transmitting that each inter-tank section is subject to comes, wherein lifting operating condition is specially to lift
When, the lifting loaded-up condition of (suspension centre quantity is more than or equal to 3) when suspension centre minimum number state；
Step 6: the load obtained to step 3,4,5 judges, if having among step 3,4,5 obtained load one or
Above it has been more than the loading demands of setting, then has determined that the design parameter of more sphere tanks is undesirable, change the step setting in 1
Count parameter, return step 1；Otherwise determination step 1 determines that the design parameter of more sphere tanks meets weak correlation between more sphere tanks
Property require.
Since the combination of pulling force and shearing is the direct factor of inter-tank section Joint failure between tank, autonomous flight section is carried out
Internal pressure performance analysis obtains the load that the tank connected to it transmitting that each inter-tank section is subject to comes, specifically includes: each spherical shape tank
The combination of drawing load and shearing load for inter-tank section.
Since the combination of pulling force and shearing is the direct factor of inter-tank section Joint failure between tank, carry out in powered phase
Pressure, axis pressure and shearing combinational acting analysis obtain the load that the tank connected to it transmitting that each inter-tank section is subject to comes, specific to wrap
It includes: combination of each spherical shape tank for the drawing load and shearing load of inter-tank section.
Since the combination of pulling force and shearing is the direct factor of inter-tank section Joint failure between tank, lifting operating condition point is carried out
Analysis, obtain the load that the tank connected to it transmitting that each inter-tank section is subject to comes, specifically include: each spherical shape tank is for inter-tank section
Drawing load and shearing load combination.
If having one or more among the load that step 3,4,5 obtain has been more than the loading demands of setting, more balls are determined
The design parameter of body tank is undesirable, changes the step the design parameter in 1, and loading demands decision scheme is preferred are as follows: by axis
(i.e. drawing load) is drawn to be denoted as N, shearing (i.e. shearing load) is denoted as Q, it is assumed that the failure limit stress that axis is drawn isThe mistake of shearing
Imitating limit stress isThen
Wherein, related coefficient of the n between tank, n value is smaller, and correlation is lower between tank.
When the axis by inter-tank section draws N, and shearing Q combination is not able to satisfy above-mentioned determination requirement, the preset more balls of step (1)
The relationship of the update of the design parameter of body tank, specifically:
WhenWhen:
Wherein, α, β are the parameter greater than 1；Indicate the thickness of the whole frame ring after changing,It indicates after changing
Whole frame ring width；(thickness and width of the whole frame ring in 1 design parameter is changed the step, it is whole in design parameter
The thickness and width of body frame ring is changed to respectivelyWith)
WhenWhen,
Wherein,γ is the parameter greater than 1；Indicate the radius of the inter-tank section after changing,It indicates after changing
The wall thickness of inter-tank section；(radius and wall thickness of the inter-tank section in 1 design parameter are changed the step, the inter-tank section in design parameter
Radius and wall thickness are changed to respectivelyWith)
As a kind of preferred embodiment of the invention, it will judge that load-up condition is adopted with the process for adjusting sphere structure design parameter
Carried out with business multidisciplinary optimization software, iteration speed can be accelerated, it is preferred to use Isight software executes.
It is as follows as embodiment using preferred four spheres tank structure below:
Step 1: determining the design parameter of four sphere tank structures, four sphere tank structural schematic diagrams are as shown in Figure 1, entirety
Frame ring is the annulus for having thickness, and inter-tank section 2 is cylinder, if whole frame ring 1 is with a thickness of 6mm, width parameter 60mm, inter-tank section
2 radius 160mm, thickness 3mm；
Step 2: the four sphere tank parameter of structure design according to step 1 establish corresponding finite element model；
Step 3: assuming that four sphere tanks are detached from utonomous working state totally 3 of the utonomous working state period after rocket
(utonomous working state total s i.e. after disengaging rocket, s=3), tank pressure state of 4 tanks under 3 working conditions point
Not are as follows:
1st working condition (i.e. when s=1): (1.8MPa, 2.2MPa, 1.8MPa, 2.2MPa), (i.e. hypothesis aircraft ball
When the number n=4, s=1 of shape tank, the internal pressure of each tank is (P1、P2、P3、P4), respectively (1.8MPa, 2.2MPa,
1.8MPa、2.2MPa))
2nd working condition (i.e. when s=2): (1.9MPa, 2.1MPa, 1.9MPa, 2.1MPa) (assumes aircraft ball
The internal pressure of its each tank is (P when the number n=4, s=2 of shape tank1、P2、P3、P4), respectively (1.9MPa, 2.1MPa,
1.9MPa、2.1MPa))
3rd working condition (i.e. when s=3): (2.0MPa, 2.0MPa, 2.0MPa, 2.0MPa) (assumes aircraft ball
The internal pressure of its each tank is (P when the number n=4, s=3 of shape tank1、P2、P3、P4), respectively (2.0MPa, 2.0MPa,
2.0MPa、2.0MPa))
It being calculated by each working condition tank internal pressure maximum difference, the difference of first job state is up to 0.4MPa,
Second difference for making state is up to 0.2MPa, and the difference that third makees state is up to 0MPa, and maximum difference is first
Working condition, therefore design conditions PsjFor first design conditions:
Psj=(1.8MPa, 2.2MPa, 1.8MPa, 2.2MPa)
Four sphere finite element model Static Strength Analysis are carried out using this group of load, the axis for exporting each inter-tank section draws load
With shearing(the load that the tank connected to it transmitting that i.e. each inter-tank section is subject under the operating condition comes, comprising: axis drawing (is drawn
Load), shearing (i.e. shearing load))
Step 4: to the finite element model of step 2 carry out the active segment structure transverse acceleration maximum moment internal pressure 0.3MPa,
Axis presses 5600kN and shearing 5kN combinational acting analysis (i.e. progress powered phase internal pressure, axis pressure and the analysis of shearing combinational acting), obtains
The load that the tank connected to it transmitting that each inter-tank section is subject to comes, the axis for exporting each inter-tank section draw loadWith shearing
(the load that the tank connected to it transmitting that i.e. each inter-tank section is subject under the operating condition comes；)
Step 5: lifting load shape when 4 suspension centres when carrying out suspension centre minimum number state to the finite element model of step 2
State is analyzed and (carries out lifting performance analysis), and the load that the tank connected to it transmitting that each inter-tank section is subject to is obtained,
The axis for exporting each inter-tank section draws loadWith shearing(tank connected to it that i.e. each inter-tank section is subject under the operating condition passes
Pass the load come；)
Step 6: based on Isight establish the radius of whole 1 thickness of frame ring and width, inter-tank section 2 with thickness corresponding step 3-
The inter-tank section load (load that the tank connected to it transmitting that each inter-tank section is subject under i.e. each operating condition comes) of three operating conditions in 5
(iterative model is the iterative model based on building design parameter to iterative model, and formula 1, formula 2 and formula 3 form iteration mould
Type), the failure limit stress that axis is drawn isThe failure limit stress of shearing isPhase
Relationship number n=0.1, α=1.05, β=1.05,γ=1.02 are the parameter greater than 1.
And updated design parameter is calculated after judging using formula 1, using formula 2, formula 3, design parameter changes
For process as shown in Fig. 2, using updated design parameter replacement step 1 four sphere tank parameter of structure design, return step
Rapid 1, by iteration 12 times, meet design requirement, iteration terminates；
Step 7: output meet design requirement four sphere tank structures design parameter, comprising: whole frame ring 1 with a thickness of
7.3mm, width parameter 73mm, 2 radius 173mm of inter-tank section, thickness 3.5mm, inter-tank section maximum axis drawing load areCorresponding shear-type load isMeeting the failure limit stress that axis is drawn isIt cuts
The failure limit stress cut isRequirement.
Weak correlation is set between the more sphere tank structures of spacecraft based on finite element method provided by through the invention
Meter method realizes the design object for the load transmitted between control tank structure.
The present invention has fully considered the carrying and design feature of more sphere tanks, for practical structures modularized design,
The development demand of low cost verifying, weak correlation is set between proposing the more sphere tank structures of the spacecraft based on finite element method
Meter method.By effectively controlling the load transmitted between tank structure, effect of the reduction inter-tank section in terms of transmitting load can be real
The now single sphere independent design and verification experimental verification of more sphere structures, reduces design complexities and validation difficulty.
The present invention is by using based on the load scheme transmitted between finite element method tank structure, not by tank knot
The constraint of configuration formula can carry out weak relevant design between more sphere tank structures towards complicated spherical tank structure, reduce storage
Connection load between case and inter-tank section simplifies and connects design between tank and inter-tank section.
Weak relevant design between the more sphere tank structures of spacecraft proposed by the present invention, is tested using independent tank
Verifying, shortens product production cycle, improves development efficiency, and the more sphere tank structures of spacecraft proposed by the present invention
Between weak relevant design, it is only necessary to independent tank structure is developed in tackling key problem, can significantly reduce development cost.
Claims (10)
1. more sphere tank structural parameter determining methods of weak dependence, special between a kind of consideration more sphere tanks of spacecraft
Sign is that steps are as follows:
Step 1: determine the design parameter of more sphere tanks, the thickness and width including whole frame ring, the radius and wall of inter-tank section
It is thick；
Step 2: according to the design parameter for more sphere tanks that step 1 determines, establishing the finite element model of more sphere tank structures；
Step 3: the internal pressure performance analysis of autonomous flight section is carried out to the finite element model of step 2, obtain that each inter-tank section is subject to
The load that its tank connected transmitting comes；
Step 4: powered phase internal pressure being carried out to the finite element model of step 2, axis is pressed and shearing combinational acting analysis, obtained between each case
The load that the tank connected to it transmitting that section is subject to comes；
Step 5: lifting performance analysis being carried out to the finite element model of step 2, obtains the storage connected to it that each inter-tank section is subject to
The load that case transmitting comes；
Step 6: the load obtained to step 3,4,5 judges, if having one or more among step 3,4,5 obtained load
It has been more than the loading demands of setting, has then determined that the design parameter of more sphere tanks is undesirable, has changed the step the design ginseng in 1
Number, return step 1；Otherwise weak dependence is wanted between the design parameter of the determining more sphere tanks of determination step 1 meets more sphere tanks
It asks.
2. more sphere tank knots of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 1
Structure parameter determination method, it is characterised in that: more sphere tanks, including multiple spherical tanks, inter-tank section, whole frame ring, support；Branch
Seat be it is multiple, the episphere and lower semisphere of multiple spherical tanks are set；
Connected between the adjacent spherical tank of every two by inter-tank section, support that multiple spherical shape tanks are arranged by its episphere and
Whole frame ring connection；Inter-tank section spherical tank connected to it does not penetrate through, and multiple spherical shape tanks have independent store function.
3. more sphere tank knots of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 2
Structure determines method, it is characterised in that: whole frame ring is the annular slab of bandwidth.
4. more sphere tank knots of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 1
Structure parameter determination method, it is characterised in that: inter-tank section, is hollow cylinder, and cylindrical body both ends connect spherical tank.
5. more sphere tank knots of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 1
Structure parameter determination method, it is characterised in that: autonomous flight section internal pressure design conditions, specifically: in autonomous flight section, each sphere
The working condition of tank boost pressure load difference maximum rating.
6. more sphere tank knots of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 1
Structure parameter determination method, it is characterised in that: powered phase internal pressure, axis pressure and shearing combinational acting, specifically: in powered phase, knot
Internal pressure, axis pressure and the working condition for shearing state at structure transverse acceleration maximum moment.
7. more sphere tank knots of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 1
Structure parameter determination method, it is characterised in that: lifting operating condition, specifically: in lifting, lifting when suspension centre minimum number state is carried
Lotus state.
8. more sphere tank knots of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 1
Structure parameter determination method, it is characterised in that: autonomous flight section refers to the utonomous working state period that aircraft is detached from after rocket.
9. more sphere tank knots of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 1
Structure parameter determination method, it is characterised in that: powered phase refers to that aircraft is carried the working condition period of the period of rocket carrying.
10. more sphere tanks of weak dependence between a kind of consideration more sphere tanks of spacecraft according to claim 1
Structural parameter determining method, it is characterised in that: lifting refers to working condition period when lifting of the aircraft at ground.
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| CN113849906A (en) * | 2021-08-31 | 2021-12-28 | 上海宇航系统工程研究所 | Cylindrical storage tank strength design method based on carrier rocket internal pressure effect |
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| CN106650045A (en) * | 2016-12-05 | 2017-05-10 | 大连理工大学 | Optimized design and strength analysis method of secondary box section structure |
| CN106628266A (en) * | 2017-01-13 | 2017-05-10 | 哈尔滨工业大学 | Suspension type composite storage box structure |
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