CN112966340B - Small deviation quick correction method for carrying capacity of solid binding carrier rocket - Google Patents
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- 230000008859 change Effects 0.000 claims abstract description 32
- 238000004364 calculation method Methods 0.000 abstract description 16
- 238000013461 design Methods 0.000 abstract description 14
- 239000007788 liquid Substances 0.000 description 8
- 239000003814 drug Substances 0.000 description 7
- 229940079593 drug Drugs 0.000 description 7
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 4
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- 239000001257 hydrogen Substances 0.000 description 2
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Natural products C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 239000012088 reference solution Substances 0.000 description 1
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Abstract
The invention discloses a small deviation quick correction method for carrying capacity of a solid binding carrier rocket, which comprises the following steps: giving the mass, thrust, specific impulse and working time length of each module of a reference scheme of the solid binding carrier rocket, and calculating the carrying capacity of the solid binding carrier rocket on a designated target track; calculating the change rate of the carrying capacity relative to the mass of each module; and correcting the carrying capacity by utilizing the change of the mass of each module and the change rate of the carrying capacity relative to the mass of the module. The small deviation quick correction method can quickly correct the rocket carrying capacity deviation under the condition of given mass deviation, and has the characteristics of simplifying the carrying capacity calculation complexity, reducing the calculation amount and improving the rocket design efficiency.
Description
Technical Field
The invention belongs to the technical field of carrier rocket overall design, and particularly relates to a small deviation rapid correction method for carrier capacity of a solid binding carrier rocket.
Background
At present, the propulsion power of the carrier rocket is divided into solid power and liquid power, and the solid engine has the characteristics of simple test and convenient transportation, and is easy to launch and guarantee; the liquid engine has higher propulsion ratio and can be controlled in a refined way, and the large-scale production is easy; the booster adopts solid power and rocket core stage adopts liquid power by means of solid-liquid combination, and the boosting stage adopting solid binding carrier rocket configuration relies on a solid engine to provide most of take-off thrust, and the high-altitude stage relies on a liquid engine to provide track-in thrust, so that on one hand, the difficulty of rocket launching guarantee can be greatly simplified, and on the other hand, the advantages of the solid power and the liquid power can be furthest exerted. Multiple solid binding carrier rockets such as delta 4, universe 5, fire, arian 5/6, H-2A/2B/3, GSLV Mk3 and the like are developed successively in the United states, europe and India, wherein the delta 4 core stage adopts oxyhydrogen propulsion, the universe 5 adopts a liquid oxygen kerosene basic stage matched oxyhydrogen superior stage scheme, the fire adopts a liquid oxygen methane basic stage matched oxyhydrogen superior stage scheme, different numbers of small solid boosters are respectively bound, the Arian 5/6 adopts an oxyhydrogen basic stage matched conventional or oxyhydrogen superior stage scheme, the Arian 5 binds two large solid boosters, the Arian 6 binds 2 or 4 medium solid boosters, the H-2A/2B/3 core stage adopts oxyhydrogen propulsion, 2 or 4 medium solid boosters are bound, the GSLV Mk3 adopts a conventional basic stage oxyhydrogen superior stage scheme, and 2 large solid boosters are bound. The solid-bound carrier rocket configuration is one of the main options of the world aerospace county.
The solid boosting module is generally large in mass, deltase:Sub>A 4 and fire booster are respectively configured with 34 tons of GEM-60 total weight and 30 tons of drug loading, GEM-63XL total weight and 48 tons of drug loading, the booster developed by cosmic 5 configuration Aerojet is 46.7 tons of total weight and 41 tons of drug loading, the total weight of Alinstalled 5 booster P241 is 270 tons, the drug loading is 240 tons, the total weight of Alinstalled 6 booster P120C is 155 tons, the drug loading is 144 tons, the total weight of H-2A/B booster SRB-A is 77 tons, the drug loading is 66 tons, the drug loading of H-3 booster SRB-3 is 67 tons, GSLV MK3 booster S200 tons, the weight ratio of all rocket is high, and the weight of each rocket is relatively large in influence on carrying capacity.
The flight process of the carrier rocket can be modeled as a segmented acceleration problem of the variable mass rocket under the action of aerodynamic resistance in a gravity field, the carrying capacity is the most core technical index of rocket design, and under the condition of determining the power and time sequence of the carrier rocket, the important performance of rocket scheme adjustment is small change of the mass of a rocket module, and the small deviation of the carrying capacity relative to a reference scheme is caused by the mass change. However, in the prior art, as long as the mass of the rocket module changes, the carrying capacity of the rocket needs to be recalculated, which results in high calculating complexity and large calculating amount of carrying capacity in the overall design process. Therefore, even when the mass of the rocket module is changed slightly, the problems of high carrying capacity calculation complexity and large calculation amount exist.
Disclosure of Invention
In view of the above, the invention provides a method for quickly correcting small deviation of carrying capacity of a solid binding carrier rocket, which can quickly correct the deviation of the carrying capacity of the rocket under the condition of given mass deviation, and has the characteristics of simplifying the calculation complexity of the carrying capacity, reducing the calculation amount and improving the design efficiency of the rocket.
The invention is realized by the following technical scheme:
a small deviation quick correction method for carrying capacity of a solid binding carrier rocket comprises the following steps:
giving the mass, thrust, specific impulse and working time length of each module of a reference scheme of the solid binding carrier rocket, and calculating the carrying capacity of the solid binding carrier rocket on a designated target track;
calculating the change rate of the carrying capacity relative to the mass of each module;
and correcting the carrying capacity by utilizing the change of the mass of each module and the change rate of the carrying capacity relative to the mass of the module.
Further, in the step of calculating the carrying capacity of the solid-bound carrier rocket in the designated target orbit, the implicit function of the carrying capacity with respect to each module is:
m E ＝m(M 1 ,I 1 ,t 1 ,F 1 ；M 2 ,I 2 ,t 2 ,F 2 ；...；M i ,I i ,t i ,F i ；...；M n ,I n ,t n ,F n ；E)；
wherein E is a specified target track, m E For carrying capacity i is rocket module i=1, 2, …, n-1, m i For the mass of module I, I i For specific impulse of module i, F i Thrust for module i is t i The working time of the module i is the working time of the module i, and n is the module type.
Still further, in the case of module thrust, timing, and specified target track determination, the implicit function reduces to:
m E ＝m(M 1 ,M 2 ,...M i ...M n )。
further, in the step of calculating the rate of change of the carrying capacity with respect to the mass of each module, the rate of change K may be expressed as:
wherein DeltaM i Is the varying mass of module i.
Further, in the step of correcting the carrying capacity by using the change in mass of each module and the change rate of the carrying capacity relative to the mass of the module, the change value Δm of the carrying capacity E The method comprises the following steps:
further, the core stage of the solid binding carrier rocket is bound with a solid booster.
Further, the number of the solid boosters is 2-4.
The beneficial effects are that:
the small deviation quick correction method of the carrier capacity of the solid binding carrier rocket is used for the overall design of the solid binding carrier rocket, the carrier capacity of the solid binding carrier rocket is expressed as a recessive function of the mass, thrust, specific impulse and working time of each module of the rocket, the change relation of the target carrier capacity relative to the mass of the module is obtained through numerical calculation, and the carrier capacity is corrected according to the change relation, so that the carrier capacity of the solid binding carrier rocket can be quickly calculated when the mass of the rocket module is slightly changed, the working complexity of the carrier capacity calculation in the overall design process of the carrier rocket is simplified, the carrier capacity calculation amount is simplified, the rocket design efficiency is improved, the main contradiction of the design of a convenient positioning scheme is promoted, and the carrier capacity potential is fully excavated, and the method has considerable technical application prospect.
Drawings
FIG. 1 is a flow chart of a method for quickly correcting small deviations in the carrying capacity of a solid-bound carrier rocket in accordance with the present invention;
fig. 2 is a schematic flow chart of the carrying capacity calculation.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
Referring to fig. 1, the embodiment of the invention provides a method for quickly correcting small deviation of carrying capacity of a solid binding carrier rocket, which is mainly applicable to the situation that the mass of a module of the solid binding carrier rocket is adjusted in a small scale, and specifically comprises the following steps:
step S10, given the mass, thrust, specific impulse and working time length of each module of a reference scheme of the solid binding carrier rocket, calculating the carrying capacity of the solid binding carrier rocket on a designated target track; in general, the solid binding carrier rocket can be divided into a solid booster, a core stage and four modules of the upper stage; the core stage of the solid binding carrier rocket is bound with solid boosters, and the number of the solid boosters can be 2-4, such as: 2, 3 or 4; in calculating the carrying capacity of a solid bound carrier rocket at a specified target orbit, the implicit function of the carrying capacity with respect to each module can be expressed as:
m E ＝m(M 1 ,I 1 ,t 1 ,F 1 ；M 2 ,I 2 ,t 2 ,F 2 ；...；M i ,I i ,t i ,F i ；...；M n ,I n ,t n ,F n ；E)；
wherein E is a specified target track, m E For carrying capacity i is rocket module i=1, 2, …, n-1, m i For mass of module I, I i For specific impulse of module i, F i For thrust of module i, t i The working time of the module i is the working time of the module i, and n is the module type;
in the case of module thrust, timing, and specified target track determination, the implicit function can be reduced to:
m E ＝m(M 1 ,M 2 ,...M i ...M n )。
step S20, calculating the change rate of the carrying capacity relative to the mass of each module; in the step of calculating the rate of change of the carrying capacity with respect to the mass of each module, the rate of change may be expressed as:
wherein DeltaM i The quality of the change for module i;
step S30, correcting the carrying capacity by utilizing the change of the mass of each module and the change rate of the carrying capacity relative to the mass of the module, wherein the change value delta M of the carrying capacity E The method comprises the following steps:
the small deviation quick correction method of the carrier capacity of the solid binding carrier rocket is used for the overall design of the solid binding carrier rocket, the carrier capacity of the solid binding carrier rocket is expressed as a recessive function of the mass, thrust, specific impulse and working time of each module of the rocket, the change relation of the target carrier capacity relative to the mass of the module is obtained through numerical calculation, and the carrier capacity is corrected according to the change relation, so that the carrier capacity of the solid binding carrier rocket can be quickly calculated when the mass of the rocket module changes slightly, the working complexity of the carrier capacity calculation in the overall design process of the carrier rocket is simplified, the carrier capacity calculation amount is simplified, the rocket design efficiency is improved, the main contradiction of the design of a convenient positioning scheme is promoted, and the carrier capacity potential is fully excavated, and the method has considerable technical application prospect.
Compared with the existing precise calculation method for the carrying capacity of the solid-bound carrier rocket, the small-deviation rapid correction method for the carrying capacity of the solid-bound carrier rocket is mainly suitable for the situation that the mass of a module of the solid-bound carrier rocket is adjusted in a small way, has the characteristics of simplicity and convenience in calculation method, low complexity and small calculation amount, can be widely applied to the rapid correction process of the carrying capacity, and has great significance for performance estimation in the overall design process of the solid-bound carrier rocket. The method for correcting the carrying capacity can reduce the overall design difficulty of the rocket to the greatest extent, improves the design efficiency of the rocket, facilitates the main contradiction of the positioning scheme design, fully excavates the carrying capacity potential, has considerable technical application prospect, and can be widely applied to the overall design of the solid binding carrier rocket.
As shown in fig. 2, which shows a schematic diagram of the rapid modification of the carrying capacity, the solid bundled carrier rocket is divided into four modules of a solid booster, a core stage and an upper stage in the process of modifying the carrying capacity, wherein 1 represents the solid booster, 2 represents the core stage, 3 represents the core stage, and 4 represents the upper stage, namely Δm 1 As mass deviation of solid booster, deltaM 2 For the first order of the core, ΔM 3 For core-level mass deviation ΔM 4 For the quality deviation of the upper stage, K 1 Correction coefficient K for core first order 2 Correction coefficient K for core first order 3 Correction coefficient of core level, K 4 For the correction factor of the upper level, m E For carrying capacity, m 0 Reference solution carrying capacity for solid-bound carrier rocket ΔM E The method is used for binding the carrier rocket for the solid and adjusting the carrying capacity variation quantity generated by the mass of the module.
The carrying capacity correction method of the invention is adopted to correct the carrying capacity of two specific types of rockets.
Example 1
The H-2B type carrier rocket is in a two-stage half-configuration, a core stage adopts liquid hydrogen and liquid oxygen for propulsion, two LE-7 engines are arranged at one stage, one LE-5B engine is arranged at the second stage, and four solid boosters are bundled; the seed island emits a LEO circular orbit with an inclination angle of 350km and 51 DEG at the field emission, and the correction constant K of the quality of the solid booster to the carrying capacity 1 A correction constant K of the primary mass of the core to the carrying capacity of-0.1 2 A correction constant K of the upper-level mass to carrying capacity of-0.3 3 Is-1, thus, the change value DeltaM of the carrying capacity E The expression of (2) is:
Δm E ＝-0.1ΔM 1 -0.3ΔM 2 -ΔM 3 ；
according to the expression, the carrying capacity is reduced by 100kg every 1t of the mass of the solid booster; the carrying capacity is increased by 100kg every 1t of the mass of the solid booster is reduced; the carrying capacity is reduced by 150kg when the mass of the core primary is increased by 500 kg; the carrying capacity is increased by 150kg every 500kg of the mass of the core primary is reduced; the carrying capacity is increased by 1kg for every 1kg of the mass of the upper stage is reduced; the carrying capacity is reduced by 1kg for every 1kg of the mass of the upper stage.
Example two
The Alian 5ECA type carrier rocket is in a two-stage half-configuration, the core stage adopts liquid hydrogen and liquid oxygen for propulsion, a fire engine is arranged at one stage, a Vinci engine is arranged at the second stage, and two solid boosters are bundled. At the guarana emission field emission of 250km, 5 ° tilt LEO circular orbit, correction constant K of solid booster mass to carrying capacity 1 A correction constant K of core primary mass to carrying capacity of-0.13 2 A correction constant K of the upper-level mass to carrying capacity of-0.113 3 Is-1, thus, the change value DeltaM of the carrying capacity E The expression of (2) is:
Δm E ＝-0.13ΔM 1 -0.113ΔM 2 -ΔM 3 ；
according to the expression, the carrying capacity is reduced by 130kg every 1t of the mass of the solid booster; the carrying capacity is increased by 130kg every 1t of the mass of the solid booster is reduced; the carrying capacity is reduced by 11.3kg when the mass of the core primary is increased by 100kg; the carrying capacity is increased by 11.3kg when the mass of the core primary is reduced by 100kg; the carrying capacity is increased by 1kg for every 1kg of the mass of the upper stage is reduced; the carrying capacity is reduced by 1kg for every 1kg of the mass of the upper stage.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A method for quickly correcting small deviation of carrying capacity of a solid binding carrier rocket is characterized by comprising the following steps:
giving the mass, thrust, specific impulse and working time length of each module of a reference scheme of the solid binding carrier rocket, and calculating the carrying capacity of the solid binding carrier rocket on a designated target track;
calculating the change rate of the carrying capacity relative to the mass of each module;
the rate of change in the step of calculating the rate of change of carrying capacity with respect to mass of each module is expressed as:
correcting the carrying capacity by utilizing the change of the mass of each module and the change rate of the carrying capacity relative to the mass of the module;
in the step of correcting, the change value Δm of the carrying capacity E The method comprises the following steps:
wherein DeltaM i For varying mass of module i, m E For carrying capacity i is rocket module i=1, 2, …, n-1, m i The mass of the module i, and n is the module type.
2. The correction method as set forth in claim 1, wherein in the step of calculating the carrying capacity of the solid-bundled carrier rocket at the specified target orbit, the implicit function of the carrying capacity with respect to each module is:
m E ＝m(M 1 ,I 1 ,t 1 ,F 1 ；M 2 ,I 2 ,t 2 ,F 2 ；...；M i ,I i ,t i ,F i ；...；M n ,I n ,t n ,F n ；E)；
wherein E is a specified target track I i For specific impulse of module i, F i For thrust of module i, t i The working time of the module i.
3. The correction method as claimed in claim 2, wherein in the case of module thrust, timing and determination of a specified target trajectory, the implicit function is reduced to:
m E ＝m(M 1 ,M 2 ,...M i ...M n )。
4. a method of modifying as in any one of claims 1-3 wherein the core stage of the solid bound launch vehicle is bound with a solid booster.
5. The correction method according to claim 4, wherein the number of the solid boosters is 2 to 4.
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