CN110276107B - Multi-sphere storage box structure parameter determination method considering weak correlation among multi-sphere storage boxes of spacecraft - Google Patents

Multi-sphere storage box structure parameter determination method considering weak correlation among multi-sphere storage boxes of spacecraft Download PDF

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CN110276107B
CN110276107B CN201910457966.0A CN201910457966A CN110276107B CN 110276107 B CN110276107 B CN 110276107B CN 201910457966 A CN201910457966 A CN 201910457966A CN 110276107 B CN110276107 B CN 110276107B
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史立涛
宋林郁
吴春雷
郑华勇
朱景忠
刘涛
李�昊
冀宾
王春林
杨颜志
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Shanghai Aerospace System Engineering Institute
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Abstract

A method for determining structural parameters of a multi-sphere storage box by considering weak correlation among the multi-sphere storage boxes of a spacecraft comprises the steps of initially designing the multi-sphere storage box structure and initially determining basic design parameters of force transmission layout of the sphere structure; establishing a finite element model of a multi-sphere storage tank structure; analyzing the internal pressure design working condition of the autonomous flight section, the internal pressure of the active section, the shaft pressure and the shearing force combined design working condition and the hoisting design working condition of the autonomous flight section by using a finite element method; and extracting the load at the symmetrical boundary in the working condition, if the load at the symmetrical boundary exceeds the allowable load, adjusting the structural design parameters of the sphere, if the load at the boundary meets the design requirement, completing the structural design of the multi-sphere storage tank, and storing the basic design parameters of the force transmission layout of the sphere structure as the final structural parameters of the multi-sphere storage tank.

Description

Multi-sphere storage box structure parameter determination method considering weak correlation among multi-sphere storage boxes of spacecraft
Technical Field
The invention relates to a method for determining structural parameters of a multi-sphere storage box by considering weak correlation among the multi-sphere storage boxes of a spacecraft, and belongs to the technical field of structural design of spacecraft.
Background
In the field of structural design of aerospace craft, the distribution mode of the internal load of the structure determines the concrete scheme of structural design, and the load is reasonably distributed to a bearing structure by optimizing the transmission mode of the design load, so that the method has important significance in fully utilizing the bearing potential of materials, reducing the structural weight of the aircraft and guaranteeing the bearing performance.
The existing design method of the multi-sphere structure of the aerospace craft is generally oriented to the whole structure to develop the design, concerns on interaction among components of the whole structure are small, the components are mutually influenced, the design relevance is strong, the development and construction level design and test verification are important, the whole test verification of the whole structure can only be developed, the hierarchical verification of a structural product can not be realized, the test risk is uncontrollable, the test disfavored causes design repetition, and financial resources and material resources are wasted.
Disclosure of Invention
The technical problems solved by the invention are as follows: the invention provides a method for determining structural parameters of a multi-sphere storage box by considering weak correlation among the multi-sphere storage boxes of a spacecraft, which solves the problems of reducing the mutual influence among sphere components in the multi-sphere structural design of the spacecraft, meeting the weak correlation design requirement among the multi-sphere structures of the spacecraft, meeting the requirements of modularized design and low-cost verification of the spacecraft structure, solving the problem that the whole structure is considered in the whole structure development process, and meeting the performance requirement of the whole structure after the independent single storage box structure is assembled only by successful development, obviously shortening the development period and reducing the development cost.
The technical scheme of the invention is as follows: a method for determining structural parameters of a multi-sphere storage box considering weak correlation among the multi-sphere storage boxes of a spacecraft comprises the following steps:
step 1: determining design parameters of the multi-sphere storage tank, including the thickness and width of the integral frame ring, and the radius and wall thickness of the tank interval;
step 2: establishing a finite element model of the multi-sphere storage box structure according to the design parameters of the multi-sphere storage box determined in the step 1;
step 3: analyzing the internal pressure working condition of the autonomous flight section of the finite element model in the step 2 to obtain the load transmitted by a storage tank connected with each tank interval;
step 4: analyzing the combined working conditions of the internal pressure, the axial pressure and the shearing force of the active section of the finite element model in the step 2 to obtain the load transmitted by the storage tank connected with each tank interval;
step 5: carrying out hoisting working condition analysis on the finite element model in the step 2 to obtain the load transmitted by the storage tank connected with each tank interval;
step 6: judging the loads obtained in the steps 3, 4 and 5, if one or more of the loads obtained in the steps 3, 4 and 5 exceeds the set load requirement, judging that the design parameters of the multi-sphere storage tank are not in accordance with the requirement, changing the design parameters in the step 1, and returning to the step 1; otherwise, the judging step 1 determines that the design parameters of the multi-sphere storage tanks meet the weak correlation requirement among the multi-sphere storage tanks.
Preferably: the multi-sphere storage tank comprises a plurality of spherical storage tanks, tank intervals, an integral frame ring and a support; the plurality of supports are arranged on the upper hemispheres and the lower hemispheres of the plurality of spherical storage tanks;
preferably: every two adjacent spherical storage tanks are connected through a tank interval, and a plurality of spherical storage tanks are connected with the integral frame ring through a support arranged on the upper hemisphere of each spherical storage tank; the tank interval is not communicated with the spherical storage tanks connected with the tank interval, and a plurality of spherical storage tanks have independent storage functions;
preferably: the integral frame ring is an annular plate with a width.
Preferably: the tank interval is a hollow cylinder, and two ends of the cylinder are connected with a spherical storage tank.
Preferably: the internal pressure design working condition of the main flight section is as follows: and in the autonomous flight section, the ball storage tanks are in a working condition of the maximum pressure load difference value.
Preferably: the combined working conditions of the internal pressure, the axial pressure and the shearing force of the driving section are as follows: in the active section, the structure is transversely overloaded with the working conditions of the internal pressure, the shaft pressure and the shearing force state at the maximum moment.
Preferably: the hoisting working condition is specifically as follows: and when the hoisting is performed, the hoisting load state is the state with the least number of hoisting points.
Preferably: the autonomous flight segment refers to an autonomous operating state period of the aircraft after the aircraft is detached from the rocket.
Preferably: the active segment refers to an operational state period of the period in which the aircraft is onboard the launch vehicle.
Preferably: hoisting refers to the period of operating conditions of the aircraft during hoisting while on the ground.
Preferably: the support at the bottom of the spherical storage tank is connected with a carrier rocket, and the support generates axial pressure and shearing force due to flying overload, and the fuel is stored in the storage tank
Preferably: in the driving section, axial compression and shearing force can be generated in the box section
Preferably: in the hoisting process, the multi-sphere storage box is hoisted through the support with the top connected with the integral frame ring.
Compared with the prior art, the invention has the advantages that:
(1) The invention fully considers the bearing and structural characteristics of the multi-sphere storage tank, and provides a weak correlation design method among the multi-sphere storage tank structures of the spacecraft based on a finite element method aiming at the development requirements of modularized design and low-cost verification of an actual structure. The load transmitted between the storage box structures is effectively controlled, the effect of the box interval in the aspect of load transmission is weakened, the independent design and test verification of single spheres of the multi-sphere structure can be realized, and the design complexity and verification difficulty are reduced.
(2) The invention solves the load scheme transmitted between the storage box structures by adopting the finite element-based method, is not constrained by the storage box structure form, and can develop weak correlation design between the multi-sphere storage box structures facing to the complex spherical storage box structure.
(3) The weak correlation design between the multi-sphere storage box structures of the spacecraft reduces the connection load between the storage box and the box interval and simplifies the connection design between the storage box and the box interval.
(4) The weak correlation design among the structures of the multi-sphere storage tanks of the spacecraft provided by the invention adopts the independent storage tanks to carry out test verification, shortens the production period of products and improves the development efficiency.
(5) The weak correlation design among the multi-sphere storage box structures of the spacecraft only needs to develop the independent storage box structure by a tap, so that the development cost can be obviously reduced.
Drawings
FIG. 1 is a schematic diagram of a preferred four-sphere tank configuration.
FIG. 2 is a flow chart of a multi-sphere tank structure parameter determination implementation for weak correlation between multi-sphere tanks.
Detailed Description
The invention is described in further detail below with reference to the drawings and the specific embodiments.
The invention is mainly used in the field of the structural design of a multi-sphere storage tank of a spacecraft, and the spacecraft comprises an autonomous flight section and an active section; the autonomous flight section refers to an autonomous working state period after the aircraft is separated from the rocket, and the active section refers to a working state period of a period when the aircraft is carried by the carrier rocket. The method of the invention can weaken the effect of the inter-sphere box section in the aspect of load transmission, solves the key problem of mutual influence of each sphere storage box of the multi-sphere storage box structure, can realize independent design and test verification of single sphere of the multi-sphere structure, lays a technical foundation for the replacement of the whole test of the single sphere structure verification, and is specifically implemented as follows:
step 1: determining design parameters of the multi-sphere tank, including thickness of the integral frame ring (denoted as K t ) And width (denoted as K) b ) The radius of the box section (denoted as D r ) And wall thickness (denoted as D t ) The multi-sphere storage tank comprises a plurality of spherical storage tanks, tank intervals, an integral frame ring and a support; the plurality of support seats are arranged on the upper hemispheres and the lower hemispheres of the plurality of spherical storage tanks, every two adjacent spherical storage tanks are connected through a hollow cylindrical tank interval, and the plurality of spherical storage tanks are connected with the integral frame ring through the support seats arranged on the upper hemispheres of the plurality of spherical storage tanks; the tank interval is not communicated with the spherical storage tanks connected with the tank interval, and a plurality of spherical storage tanks have independent storage functions;
step 2: establishing a finite element model of the multi-sphere storage box structure according to the design parameters of the multi-sphere storage box determined in the step 1;
step 3: because the internal pressure load of the storage tanks in the autonomous working state period after the aircraft is separated from the rocket is relatively large, and the pressurization of each storage tank possibly has different influences on the tank intervals according to the needs, the internal pressure working condition design of the autonomous flight section needs to be developed, the internal pressure working condition analysis of the autonomous working state period after the aircraft is separated from the rocket is carried out on the finite element model in the step 2, the load transmitted by the storage tank connected with the finite element model in each tank interval is obtained, wherein the internal pressure load working condition is the state with the largest difference value of the pressurization pressure loads of the storage tanks of each sphere, and the specific calculation method is as follows:
assuming that the aircraft has n tanks, the internal pressure of each tank is (P 1 、...、P i 、...、P j 、...、P n ) I and j are integers from 1 to n, i is smaller than j, s autonomous working states after the rocket is separated from the rocket are {1, 2..once, s }, t is set as an autonomous working state number, t is greater than or equal to 1 and less than or equal to s, and the design working condition P is set sj The design working condition (namely the working condition with the largest internal pressure difference value of each storage tank) is as follows:
Figure BDA0002077187900000051
wherein P is sj In the working state of the maximum internal pressure difference of each storage tank, the values of i and j are 1-n, and t is 1-s; p (P) i t An internal pressure in a t-th state of the i-th tank;
Figure BDA0002077187900000052
the internal pressure of the jth tank in the jth state;
step 4: because the side load of the active section of the aircraft has a great influence on the structure among all the storage tanks, the finite element model in the step 2 is required to be subjected to analysis of the combined working conditions of the internal pressure, the axial pressure and the shearing force of the active section, so that the load transmitted by the storage tanks connected with the active section is obtained, wherein the combined working conditions of the internal pressure, the axial pressure and the shearing force are the internal pressure, the axial pressure and the shearing force at the moment of the maximum transverse overload of the structure in the active section;
step 5: the hoisting condition analysis is carried out on the finite element model in the step 2 to obtain the load transmitted by the storage box connected with the finite element model, wherein the hoisting condition is specifically a hoisting load state when the number of hoisting points is the minimum (the number of the hoisting points is more than or equal to 3) during hoisting;
step 6: judging the loads obtained in the steps 3, 4 and 5, if one or more of the loads obtained in the steps 3, 4 and 5 exceeds the set load requirement, judging that the design parameters of the multi-sphere storage tank are not in accordance with the requirement, changing the design parameters in the step 1, and returning to the step 1; otherwise, the judging step 1 determines that the design parameters of the multi-sphere storage tanks meet the weak correlation requirement among the multi-sphere storage tanks.
Because the combination of the tensile force and the shearing force is a direct factor of failure of the connection of the tank intervals among the storage tanks, the analysis of the internal pressure working condition of the autonomous flight section is carried out to obtain the load transmitted by the storage tanks connected with the tank intervals, and the method specifically comprises the following steps: the combination of tensile and shear loads of each spherical tank for the tank compartment.
Because the combination of the tensile force and the shearing force is a direct factor of failure of the connection of the tank intervals among the storage tanks, the analysis of the combined working conditions of the internal pressure, the axial pressure and the shearing force of the active section is carried out to obtain the load transmitted by the storage tank connected with the tank intervals, and the method specifically comprises the following steps: the combination of tensile and shear loads of each spherical tank for the tank compartment.
Because the combination of tensile force and shearing force is the direct factor of the failure of the connection of the tank intervals among the storage tanks, the hoisting working condition analysis is carried out to obtain the load transmitted by the storage tanks connected with the tank intervals, and the method specifically comprises the following steps: the combination of tensile and shear loads of each spherical tank for the tank compartment.
If one or more of the loads obtained in the steps 3, 4 and 5 exceeds the set load requirement, determining that the design parameters of the multi-sphere storage tank are not in accordance with the requirement, changing the design parameters in the step 1, and preferably, determining the load requirement: let the pullout (i.e., pullout load) be N, the shear force (i.e., shear load) be Q, assuming the ultimate failure stress of the pullout is
Figure BDA0002077187900000061
Shear failure limit stress of +.>
Figure BDA0002077187900000062
Then
Figure BDA0002077187900000063
Wherein n is a correlation coefficient between the storage tanks, and the smaller the value of n is, the lower the correlation between the storage tanks is.
When the combination of shearing force Q can not meet the judging requirement through the axial pull N of the box interval, the updating relation of the design parameters of the multi-sphere storage box preset in the step (1) is specifically as follows:
when (when)
Figure BDA0002077187900000064
When (1):
Figure BDA0002077187900000065
wherein alpha and beta are parameters larger than 1;
Figure BDA0002077187900000066
indicating the thickness of the modified integral frame ring, < >>
Figure BDA0002077187900000067
Representing the width of the changed integral frame ring; (i.e., changing the thickness and width of the integral frame ring in the design parameters of step 1. The thickness and width of the integral frame ring in the design parameters are changed to +.>
Figure BDA0002077187900000068
And->
Figure BDA0002077187900000069
)
When (when)
Figure BDA00020771879000000610
When (I)>
Figure BDA00020771879000000611
Wherein, the liquid crystal display device comprises a liquid crystal display device,
Figure BDA0002077187900000071
gamma is a parameter greater than 1; />
Figure BDA0002077187900000072
Indicating the radius of the changed bin section, < >>
Figure BDA0002077187900000073
Representing the wall thickness of the altered box section; (i.e., changing the radius and wall thickness of the tank compartment in the design parameters of step 1. The radius and wall thickness of the tank compartment in the design parameters are changed to +.>
Figure BDA0002077187900000074
And->
Figure BDA0002077187900000075
)
As a preferred mode of the invention, the processes of judging the load condition and adjusting the structural design parameters of the sphere are carried out by adopting commercial multidisciplinary optimization software, so that the iteration speed can be increased, and the process is preferably carried out by adopting Isight software.
The following is given by way of example a preferred four-sphere tank structure:
step 1: determining design parameters of a four-sphere storage box structure, wherein the four-sphere storage box structure is shown in a schematic diagram in FIG. 1, the integral frame ring is a circular ring with thickness, the box interval 2 is cylindrical, the thickness of the integral frame ring 1 is 6mm, the width parameter is 60mm, the radius of the box interval 2 is 160mm, and the thickness is 3mm;
step 2: establishing a corresponding finite element model according to the structural design parameters of the four-sphere storage tank in the step 1;
step 3: assuming that the four-sphere storage tanks have 3 autonomous working states (i.e. s, s=3) in the period of autonomous working states after being separated from the rocket, the storage tank pressure states of the 4 storage tanks in the 3 working states are respectively:
the 1 st working state (i.e. s =1 time): (1.8 MPa, 2.2MPa, 1.8MPa, 2.2 MPa), (i.e. assuming that the number of spherical tanks of the aircraft is n=4, s=1, the internal pressure of each tank is (P) 1 、P 2 、P 3 、P 4 ) (1.8 MPa, 2.2MPa, 1.8MPa, 2.2 MPa) respectively)
2 nd operating state (i.e. s=2): (1.9 MPa, 2.1MPa, 1.9MPa, 2.1 MPa) (i.e., assuming that the number of spherical tanks of the aircraft is n=4, s=2, the internal pressure of each tank is (P) 1 、P 2 、P 3 、P 4 ) (1.9 MPa, 2.1MPa, 1.9MPa, 2.1 MPa) respectively)
3 rd operating state (i.e. s=3): (2.0 MPa ) (i.e., assuming that the number of spherical tanks of the aircraft is n=4, s=3, the internal pressure of each tank is (P) 1 、P 2 、P 3 、P 4 ) (2.0 MPa ) respectively)
The maximum difference value of the internal pressure of the storage tank in each working state is calculated, the maximum difference value of the first working state is 0.4MPa, the maximum difference value of the second working state is 0.2MPa, the maximum difference value of the third working state is 0MPa, and the maximum difference value is the first working state, so that the working condition P is designed sj For the first design condition:
P sj ＝(1.8MPa、2.2MPa、1.8MPa、2.2MPa)
the group of loads are used for carrying out static strength analysis of the four-sphere finite element model, and the axial tension load of each box interval is output
Figure BDA0002077187900000081
And/or shear force->
Figure BDA0002077187900000082
( I.e. the load transmitted by the storage tank connected with each tank interval under the working condition comprises: axial tension (i.e., tension load), shear (i.e., shear load) )
Step 4: and (2) carrying out combined working condition analysis (namely carrying out combined working condition analysis of the internal pressure, the axial pressure and the shearing force of the active section) on the internal pressure of 0.3MPa, the axial pressure of 5600kN and the shearing force of 5kN at the moment of maximum transverse overload of the active section structure on the finite element model in the step (2) to obtain each boxThe load transmitted by the storage tank connected with the compartment receives and outputs the axle pulling load of each compartment
Figure BDA0002077187900000083
And/or shear force->
Figure BDA0002077187900000084
(i.e. the load transmitted from the storage tank to which each tank section is connected under the working condition;)
Step 5: analyzing the hoisting load states (namely hoisting working condition analysis) of 4 hoisting points when the finite element model in the step 2 is in the state of minimum number of hoisting points, obtaining the load transmitted by the storage box connected with each box section, and outputting the axial pulling load of each box section
Figure BDA0002077187900000085
And/or shear force->
Figure BDA0002077187900000086
(i.e. the load transmitted from the storage tank to which each tank section is connected under the working condition;)
Step 6: establishing an iterative model (the iterative model is an iterative model based on construction design parameters, and the formula 1, the formula 2 and the formula 3 form an iterative model) of the thickness and the width of the integral frame ring 1 and the radius and the thickness of the box interval 2 corresponding to the loads of the box intervals in the three working conditions in the steps 3-5 (namely, the loads transmitted by the storage boxes connected with the box intervals under each working condition), wherein the failure limit stress of the axial pull is as follows
Figure BDA0002077187900000087
Shear failure limit stress of +.>
Figure BDA0002077187900000088
The correlation coefficient n=0.1, α=1.05, β=1.05, ++>
Figure BDA0002077187900000089
γ=1.02 is a parameter greater than 1.
After the judgment of the formula 1, the updated design parameters are obtained through calculation of the formula 2 and the formula 3, the iteration flow of the design parameters is shown in the figure 2, the structural design parameters of the four-sphere storage tank in the step 1 are replaced by the updated design parameters, the step 1 is returned, the design requirements are met through 12 iterations, and the iteration is ended;
step 7: outputting design parameters of the four-sphere tank structure meeting design requirements, comprising: the thickness of the integral frame ring 1 is 7.3mm, the width parameter is 73mm, the radius of the box section 2 is 173mm, the thickness is 3.5mm, and the maximum axial pull load of the box section is
Figure BDA0002077187900000091
The corresponding shear load is +.>
Figure BDA0002077187900000092
The failure limit stress satisfying the axial pull is +.>
Figure BDA0002077187900000093
Shear failure limit stress of +.>
Figure BDA0002077187900000094
Is not limited.
The design method for weak correlation between the multi-sphere tank structures of the spacecraft based on the finite element method provided by the invention realizes the design goal of controlling the load transferred between the tank structures.
The invention fully considers the bearing and structural characteristics of the multi-sphere storage tank, and provides a weak correlation design method among the multi-sphere storage tank structures of the spacecraft based on a finite element method aiming at the development requirements of modularized design and low-cost verification of an actual structure. The load transmitted between the storage box structures is effectively controlled, the effect of the box interval in the aspect of load transmission is weakened, the independent design and test verification of single spheres of the multi-sphere structure can be realized, and the design complexity and verification difficulty are reduced.
According to the invention, a load scheme transmitted between the storage box structures is solved based on a finite element method, the constraint of the storage box structure form is avoided, the weak correlation design between the multi-sphere storage box structures can be developed for the complex spherical storage box structure, the connection load between the storage box and the box interval is reduced, and the connection design between the storage box and the box interval is simplified.
The weak correlation design between the multi-sphere storage box structures of the spacecraft provided by the invention adopts the independent storage box to carry out test verification, shortens the product production period and improves the development efficiency, and only needs to attack and develop the independent storage box structure, thereby obviously reducing the development cost.

Claims (9)

1. A method for determining structural parameters of a multi-sphere storage box considering weak correlation among the multi-sphere storage boxes of a spacecraft is characterized by comprising the following steps:
step 1: determining design parameters of the multi-sphere storage tank, including the thickness and width of the integral frame ring, and the radius and wall thickness of the tank interval;
step 2: establishing a finite element model of the multi-sphere storage box structure according to the design parameters of the multi-sphere storage box determined in the step 1;
step 3: analyzing the internal pressure working condition of the autonomous flight section of the finite element model in the step 2 to obtain the load transmitted by a storage tank connected with each tank interval;
step 4: analyzing the combined working conditions of the internal pressure, the axial pressure and the shearing force of the active section of the finite element model in the step 2 to obtain the load transmitted by the storage tank connected with each tank interval;
step 5: carrying out hoisting working condition analysis on the finite element model in the step 2 to obtain the load transmitted by the storage tank connected with each tank interval;
step 6: judging the loads obtained in the steps 3, 4 and 5, if one or more of the loads obtained in the steps 3, 4 and 5 exceeds the set load requirement, judging that the design parameters of the multi-sphere storage tank are not in accordance with the requirement, changing the design parameters in the step 1, and returning to the step 1; otherwise, the judging step 1 determines that the design parameters of the multi-sphere storage tanks meet the weak correlation requirement among the multi-sphere storage tanks;
the multi-sphere storage tank comprises a plurality of spherical storage tanks, tank intervals, an integral frame ring and a support; the plurality of supports are arranged on the upper hemispheres and the lower hemispheres of the plurality of spherical storage tanks;
every two adjacent spherical storage tanks are connected through a tank interval, and a plurality of spherical storage tanks are connected with the integral frame ring through a support arranged on the upper hemisphere of each spherical storage tank; the tank interval is not communicated with the spherical storage tanks connected with the tank interval, and a plurality of spherical storage tanks have independent storage functions.
2. A method of determining a multi-sphere tank structure that accounts for weak correlation between multi-sphere tanks of a spacecraft according to claim 1, wherein: the integral frame ring is an annular plate with a width.
3. A method of determining a multi-sphere tank configuration parameter taking into account weak correlation between multi-sphere tanks of a spacecraft as claimed in claim 1, wherein: the tank interval is a hollow cylinder, and two ends of the cylinder are connected with a spherical storage tank.
4. A method of determining a multi-sphere tank configuration parameter taking into account weak correlation between multi-sphere tanks of a spacecraft as claimed in claim 1, wherein: the internal pressure design working condition of the autonomous flight section is as follows: and in the autonomous flight section, the ball storage tanks are in a working condition of the maximum pressure load difference value.
5. A method of determining a multi-sphere tank configuration parameter taking into account weak correlation between multi-sphere tanks of a spacecraft as claimed in claim 1, wherein: the combined working conditions of the internal pressure, the axial pressure and the shearing force of the driving section are as follows: in the active section, the structure is transversely overloaded with the working conditions of the internal pressure, the shaft pressure and the shearing force state at the maximum moment.
6. A method of determining a multi-sphere tank configuration parameter taking into account weak correlation between multi-sphere tanks of a spacecraft as claimed in claim 1, wherein: the hoisting working condition is specifically as follows: and when the hoisting is performed, the hoisting load state is the state with the least number of hoisting points.
7. A method of determining a multi-sphere tank configuration parameter taking into account weak correlation between multi-sphere tanks of a spacecraft as claimed in claim 1, wherein: the autonomous flight segment refers to an autonomous operating state period of the aircraft after the aircraft is detached from the rocket.
8. A method of determining a multi-sphere tank configuration parameter taking into account weak correlation between multi-sphere tanks of a spacecraft as claimed in claim 1, wherein: the active segment refers to an operational state period of the period in which the aircraft is onboard the launch vehicle.
9. A method of determining a multi-sphere tank configuration parameter taking into account weak correlation between multi-sphere tanks of a spacecraft as claimed in claim 1, wherein: hoisting refers to the period of operating conditions of the aircraft during hoisting while on the ground.
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