CN115310211A - Overall design method and device for vertical take-off and landing reusable launch vehicle - Google Patents
Overall design method and device for vertical take-off and landing reusable launch vehicle Download PDFInfo
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Abstract
The disclosure relates to a general design method and a device for a vertical take-off and landing reusable carrier rocket, and belongs to the field of general design of carrier rockets. The method comprises the steps that firstly, a plurality of design schemes are generated according to selectable rocket diameters, engine layout schemes and propellant types; then, evaluating each design scheme by using a design scheme evaluation method of a vertical take-off and landing reusable launch vehicle; and finally, outputting a plurality of schemes with feasible evaluation results in all the design schemes together with the design parameters. The general design method disclosed by the invention is simple and efficient, is suitable for automation, enables designers to pay attention to the selection of the rocket body diameter, the selection of the engine layout scheme and the selection of the propellant type in the general design, and releases from heavy work related to different design schemes formed by combining different parameters, greatly improves the general design efficiency of the carrier rocket, and lays a foundation for quickly forming the reuse capacity.
Description
Technical Field
The disclosure relates to a carrier rocket overall design method and device, in particular to a vertical take-off and landing reusable carrier rocket overall design method and device, and belongs to the technical field of carrier rocket overall design.
Background
The reusable carrier rocket is a necessary way for reducing the cost of entering space nowadays, and the reusable carrier rocket for vertical take-off and landing is the most practical and feasible reusable transportation system route in China at present based on historical reasons. A plurality of schemes can be provided for the vertical take-off and landing reusable launch vehicle in the overall design stage, and each scheme needs to be evaluated in multiple dimensions such as carrying capacity, carrying efficiency, engineering implementation and the like so as to screen out a proper scheme for subsequent work such as overall demonstration, key technology attack, demonstration verification and engineering development reference. The screening work is time-consuming and labor-consuming, and a simple and convenient overall design means is lacked.
Disclosure of Invention
The purpose of the present disclosure is to overcome the drawbacks of the prior art and to solve the above technical problems, in part or in whole, to provide a vertical take-off and landing reusable launch vehicle overall design method and apparatus.
The purpose of the present disclosure is achieved by the following technical solutions.
In a first aspect, the present disclosure provides a total design method of a vertical take-off and landing reusable launch vehicle, which is used for a vertical take-off and landing reusable launch vehicle with two stages of single-core stages and an odd number of engines connected in parallel, and comprises the following contents:
selecting and generating a plurality of design schemes according to selectable rocket diameters, engine layout schemes and propellant types; wherein, the diameter of the rocket is selected to be m, the layout scheme of the engine is selected to be n, the type of the propellant is selected to be k, and the number of the design schemes is m x n x k;
evaluating each design scheme by using a vertical take-off and landing reusable launch vehicle design scheme evaluation method;
evaluating m n k of the designs as feasiblelThe individual solutions are output along with their design parameters.
In a second aspect, the present disclosure provides a total design device of a vertical take-off and landing reusable launch vehicle, which is used for a vertical take-off and landing reusable launch vehicle with two stages of single-core stages and an odd number of engines connected in parallel, and comprises a scheme combination module, a scheme evaluation module and a scheme screening module, wherein,
scheme combination module: for generating a plurality of design options based on alternative rocket diameters, engine layout options, and propellant type selections; wherein, the diameter of rocket is chosen to be m, the layout scheme of engine is chosen to be n, the propellant type is chosen to be k, then the number of design schemes is m x n x k;
a scheme evaluation module: for evaluating each of the designs using a VTOL reuse launch vehicle design evaluation method;
a scheme screening module: means for evaluating m x n x k of the designs as feasiblelThe solutions are output along with their design parameters.
In a third aspect, the present disclosure provides an electronic device comprising:
at least one processor; and (c) a second step of,
a memory communicatively coupled to the at least one processor; wherein the memory stores instructions executable by the at least one processor to enable the at least one processor to perform the method of any of the embodiments of the first aspect.
In a fourth aspect, the present disclosure provides a computer-readable storage medium having stored thereon a computer program which, when executed by a processor, causes the processor to perform the method according to any of the embodiments of the first aspect.
Advantageous effects
The invention provides a highly automated overall design method of a vertical take-off and landing reusable carrier rocket, which is simple and efficient; the method ensures that designers only need to pay attention to rocket body diameter type selection, engine layout scheme type selection and propellant type selection in the overall design, and the complex work related to different design schemes under different parameter selection is automatically generated and evaluated by the device, thereby greatly improving the overall design efficiency of the vertical take-off and landing reusable carrier rocket and laying a foundation for the capability of rapidly forming the vertical take-off and landing reusable carrier rocket in China. Furthermore, the screened scheme has practical feasibility in engineering practice by designing an evaluation method under the given scheme. And optimizing the carrying capacity equation to obtain the relevant parameters of the maximized load under the given scheme condition, thereby providing reference basis for subsequent work.
Drawings
FIG. 1 is a schematic flow chart of a general design method of a vertical take-off and landing reusable launch vehicle provided in an embodiment of the present disclosure;
FIG. 2 is a schematic of a two-stage single core stage configuration;
FIG. 3 is a schematic diagram of a layout scheme of 5 engines;
FIG. 4 is a schematic diagram of a layout of 7 engines;
FIG. 5 is a schematic diagram of a 9 engine layout;
fig. 6 is a schematic structural diagram of an electronic device according to an embodiment of the present disclosure.
Detailed Description
The present disclosure will be described in detail below with reference to specific embodiments shown in the drawings. These embodiments are not limited to the disclosure, and structural, methodological, or functional changes made by those of ordinary skill in the art in light of these embodiments are intended to be within the scope of the disclosure.
In the description of the present disclosure, it is to be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the present disclosure and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and therefore should not be considered limiting to the disclosure. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present disclosure, "a plurality" means two or more unless otherwise specified.
In the description of the present disclosure, it should be noted that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present disclosure can be understood by those of ordinary skill in the art through specific situations.
For the purpose of illustrating the objects, technical solutions and advantages of the embodiments of the present disclosure, the technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure.
The method is imperative for meeting the increasingly vigorous satellite exploration requirement of people, reducing the rocket launching cost and improving the reuse capacity of the carrier rocket. The existing carrier rocket in China is designed based on disposable use, and must be redesigned based on reuse capacity. According to the power type, the domestic and foreign repeated use technical route is mainly divided into rocket power repeated use and combined power repeated use. Wherein the rocket power is repeatedly used and is divided into an axisymmetric configuration (a vertical take-off and landing repeatedly used carrier rocket) and a lift type configuration. The rocket power is relatively mature after decades of development technologies, and particularly, the vertical take-off and landing reusable carrier rocket based on the rocket power is broken through first, so that the carrier rocket not only comprehensively surpasses the previous generation carrier rocket in the aspects of carrying capacity, carrying efficiency, launching cost and the like, but also is the reusable carrier rocket which is most hopeful to be applied to large-scale engineering at the present stage. Therefore, the present disclosure makes an overall design with vertical take-off and landing reuse of the launch vehicle as a subject. For the rocket, a plurality of key parameters need to be determined during the overall design, each key parameter can be selected, so that the number of schemes with the order of magnitude can be generated by combining different parameters, researchers need to judge the carrying capacity, carrying efficiency and practical feasibility of the schemes under the condition of combining different parameters one by one, and therefore a proper overall design scheme is screened out to serve as the basis of the next work. These screening tasks are burdensome and inefficient, and thus researchers cannot devote more important efforts to key parameter selection, key technology attack, and the like. To address this problem, the present disclosure provides an overall design method and apparatus for a vertical take-off and landing reuse launch vehicle.
As shown in fig. 1, the present disclosure provides an overall design method of a vertical take-off and landing reusable launch vehicle, which is used for a vertical take-off and landing reusable launch vehicle with two stages of single-core stages and an odd number of engines connected in parallel, and comprises the following contents:
generating a plurality of design solutions according to selectable rocket diameters, engine layout solutions and propellant type selection; wherein, the diameter of rocket is chosen to be m, the layout scheme of engine is chosen to be n, the propellant type is chosen to be k, then the number of design schemes is m x n x k;
evaluating each design scheme by using a vertical take-off and landing reusable launch vehicle design scheme evaluation method;
evaluating m n k of the designs as feasiblelThe individual solutions are output along with their design parameters.
M, n, k andlare all natural numbers greater than or equal to 1.
From the rocket configuration, in order to realize the orbit entering, the conventional carrier rocket configuration mainly adopts a single-core-stage configuration and a binding configuration, wherein the binding configuration is divided into solid boosting, small-sized liquid boosting and general core-stage boosting. Considering that solid boosting and small liquid boosting cannot be recycled or the recycling value is not high, and considering the universalization, serialization and combination, the carrier rocket for vertical take-off and landing is preferably in a single-core-level configuration and then in a core-level binding configuration. Generally, the more the number of stages is, the more interstage separation mechanisms are adopted, the lower the flight reliability is, and from the perspective of recycling and reusing, the two-stage single-core stage configuration is the optimal configuration for repeated use. Fig. 2 is a schematic diagram showing a configuration of two single-core stages of a launch vehicle, and it can be seen that the configuration includes a core stage 1, a core stage 2 and a fairing 3. In power layout, the carrier rocket for vertical take-off and landing repeated use tends to adopt odd engines of the same type, a single engine is arranged in the center, and even engines are symmetrically arranged around the circumference, such as 2, 3, 4 and the like. Referring to fig. 3, fig. 4 and fig. 5, the layout diagrams of odd engines of the same type are respectively shown, the center of the engine is 1 engine, and 4, 6 or 8 engines of the same type are uniformly distributed on the periphery of the center engine. For different types of rocket diameters, such as 3350mm, 3800mm, 4200mm or 5000mm, different layout schemes of engines, such as 5, 7 or 9 engines, different types of propellants, such as liquid oxygen kerosene or liquid oxygen methane, 4 x 3 x 2=24 different design schemes can be combined. By the method, researchers only need to determine the key parameters such as rocket diameter, engine layout scheme, propellant type and the like in the overall design to select types, all schemes can be automatically generated, the schemes are judged one by one, and realistic and feasible schemes in engineering are output to serve as the overall primary design scheme of the researchers for further detailed design and selection.
The evaluation method of the design scheme of the carrier rocket for repeated use in vertical take-off and landing can be realized by adopting the conventional artificial rough estimation method and can also be realized by adopting the following method so as to integrally improve the accuracy and the automation degree of the evaluation of a specific design scheme in the overall design:
1. calculating the maximum thrust F of a base level according to the diameter of an arrow body, an engine layout scheme and the type of a propellant;
in particular, a maximum thrust F = n × F may be set, whereinnThe number of the engines is, f is the thrust of a single engine, and the thrust is calculated by the following formula: f = thrust surface density of the engine corresponding to a typical engine of propellant type.
The nozzle area of the engine can be replaced by the area of a single engine, and the maximum diameter of the single engine can be obtained according to the diameter of the rocket body and the layout scheme of the engine.
Specifically, for layout schemes 5, 7 or 9, the maximum diameter of a single enginedCan be calculated by the following formula:
whereinDIs the arrow body diameter.
And according to the thrust surface density of a typical engine, the thrust of a single engine with the corresponding diameter is obtained in the same proportion. The thrust of a single engine can be obtained by multiplying the thrust surface density of a typical liquid oxygen kerosene or liquid oxygen methane engine by the nozzle area of the engine. By taking the Merlin-1D thrust surface density of the liquid oxygen kerosene engine as 1271 kN/square meter and the Raptor thrust surface density of the liquid oxygen methane engine as 1657 kN/square meter as examples, engines with different layout schemes such as 3350mm, 3800mm, 4200mm or 5000mm, 5, 7 or 9 sets of rocket bodies and the like can be obtained, and the basic-level maximum thrust under the condition that the propellants are respectively liquid oxygen kerosene or liquid oxygen methane is shown in the table.
TABLE 1 estimation of maximum thrust at base level under different power layouts
2. Calculating the total mass from Fm 0 ；
In particular, it can be based on the formulam 0 F/(weighted ratio gravity acceleration) the total mass is calculated. According to statistics, the thrust-weight ratio of the main single-core configuration carrier rocket in the world is mostly 1.2-1.5, and preferably, the thrust-weight ratio of the single-core configuration carrier rocket for vertical take-off and landing repeated use is set to be 1.3, so that the mass of the carrier rocket is 6215kN/1.3/9.8=487t for a 3350mm diameter configuration, a 5-engine layout and a liquid oxygen kerosene power type.
3. Calculating the carrying capacity according to the interstage ratio and the rocket structure coefficient by the formula (1);
wherein, deltavIndicates the speed increment,I sp1 Shows the specific impulse of a first-class engine,I sp2 Shows the specific impulse of the two-stage engine,m 1 Represents the total mass of the first stage,m 2 Represents the total mass of the second stage,m s1 Represents the quality of the primary structure,m s2 Represents the mass of the secondary structure,m p Representing payload mass, σ 1 Representing first order structure coefficient, σ 2 Represents a secondary structure coefficient,εRepresents the interstage ratio;
according to statistics, the primary structure coefficient is approximately between 6% and 12%, and is intensively distributed between 6% and 8%; the secondary structure coefficient is between 4% and 12%, and the secondary structure coefficient is intensively distributed between 8% and 10%. For example, for a two-stage single-core stage rocket with 3350mm diameter configuration, 5 engine layout and liquid oxygen kerosene power, a first-stage structural coefficient is assumed
7.5% of secondary structure coefficient
Is 9% in a secondary-to-secondary ratio
9, it can be derived, primary total mass 438t, structural mass 33t, propellant mass 405t; the secondary total mass is 49t, the structural mass is 4t, and the propellant mass is 45t.
Since the formula (1) ignores the resistance loss and the gravity loss, the theoretical LEO orbital velocity increment of 7.9km/s cannot be adopted for calculation. According to statistics, the speed increment of a typical single-core carrier rocket in the world is approximately 9.2 km/s-10 km/s, and 9.5km/s can be selected as the LEO speed increment in the orbit. According to the prior art capability, a primary engine sea level specific impulse 2900m/s and a secondary engine vacuum specific impulse 3300m/s can be selected, a velocity increment equation is solved by combining the structural mass and the propellant mass of the rocket, and the LEO orbit carrying capacity of the design scheme of the carrier rocket with the diameter of 3350mm, the layout of 5 engines and the liquid oxygen kerosene power type reuse is 10.2t and the carrying efficiency is 2.1.
4. In the formula (1)εAs the optimization variables, the variables of the optimization,m p as optimization target, according to a preset ΔvThe constant maximizes carrying capacity;
the overall optimization of the reusable rocket under the condition of multi-engine parallel connection of a single-core stage and odd engines is actually a single-parameter constraint optimization problem with structural coefficients and specific impulse as constants, inter-stage ratio as design variables and carrying capacity as an optimization target, the definition of the optimization problem is shown as the following formula, and the maximum carrying capacity of the rocket under a certain configuration (overall design scheme) and the corresponding inter-stage ratio can be obtained by solving the optimization problem. Still taking the above case as an example, solving the optimization problem shows that the carrying capacity reaches a maximum of 10.51t at an interstage ratio of 6.26.
Wherein
Is a velocity increment constant, which is taken as an example of the LEO on-track velocity increment of 9.5km/s, and the optimization method is utilized to calculate the parameters under different design schemes in the table 1The maximum carrying capacity of (a) and the corresponding inter-stage ratio, the results are shown in table 2.
TABLE 2 maximum carrying capacity and interstage ratio for different power configurations
5. Calculating the slenderness ratio of the rocket according to the optimization result;
specifically, the process of calculating the rocket slenderness ratio according to the optimization result comprises the following steps:
will be epsilon andm P is substituted by formula (1) to obtainm 1 、m 2 、m s1 Andm s2 ；
according tom 1 、m 2 、m s1 Andm s2 obtaining the quality of each substage propellant;
calculate the full arrow length according to: the full arrow length = mass of propellant per substage/(relative density of propellant per rocket body cross-sectional area) + length of fairing;
calculating the rocket slenderness ratio according to the following formula: slenderness ratio = full arrow length/arrow body diameter.
The relative density of liquid oxygen kerosene under the condition of theoretical mixing ratio of 2.74 is 1.024, the relative density of liquid oxygen methane under the condition of mixing ratio of 3.5 is 0.8276, the length of a propellant storage box (approximately equal to the mass of propellant/(the relative density of propellant) and the cross-sectional area of an arrow body) under different design schemes in the table 2 can be obtained by combining the diameter of the arrow body, the length of a full arrow (neglecting the length of a box section and an instrument cabin) can be obtained by assuming the length of a fairing to be 10m, and the slenderness ratio of the full arrow can be further obtained as shown in the table 3.
TABLE 3 slenderness ratios under different power layouts
6. Whether the slenderness ratio accords with the engineering practice is used as a judgment standard to determine whether the scheme is feasible.
Under the current process conditions, the slenderness ratio is mostly between 10 and 20, for example, the slenderness ratio of Falcon 9 reaches 19.1 world top. According to the principle, the slenderness ratio of the scheme in the part shown in the table 3 is smaller than 20, the existing process conditions are relatively met, the slenderness ratio of the scheme in the part exceeds 20, and engineering is difficult to realize. The data results show that: the 3350mm diameter configuration, 5 engine layout, slenderness ratio of liquid oxygen kerosene power scheme of 17.9, is a relatively feasible overall scheme, can be regarded as the reference of the subsequent preliminary design scheme.
According to the slenderness ratios of the 24 schemes in the table 3, it can be determined that 10 design schemes with slenderness ratios lower than 20 have practical feasibility, and the 10 schemes are output together with relevant design parameters thereof for reference of subsequent design and engineering realization of the launch vehicle. Design parameters related to the solution may include key parameter content reflecting launch vehicle performance and engineering implementation as follows: rocket body diameter, engine layout scheme, propellant type and maximum diameter of single enginedTotal mass ofm 0 Inter-stage ratio ofεPayload massm p First order total massm 1 Is the second order total massm 2 Is the quality of the primary structurem s1 Is the quality of the secondary structurem s2 The mass of the primary propellant, the mass of the secondary propellant, the slenderness ratio, the carrying efficiency and the like, so as to provide reference for general demonstration, key technology attack, demonstration verification and engineering development.
In summary, the overall design method for the vertical take-off and landing reusable launch vehicle provided by the disclosure has the following characteristics:
1. the method is suitable for automatic realization, and is simple and efficient;
2. by adopting a simple analysis method, the overall scheme of the carrier rocket for vertical take-off and landing repeated use under the conditions of different diameter configurations, power layouts and propellant types and the type spectrum scheme under different combinations can be quickly obtained, and references can be provided for overall demonstration, key technology clearance, demonstration verification and engineering development; designers are relieved from the evaluation of a plurality of fussy schemes, and only the arrow diameter model selection, the engine layout scheme model selection and the propellant type model selection per se in the overall design need to be concerned, so that the overall design efficiency of the vertical take-off and landing reusable launch vehicle is greatly improved, and a foundation stone is laid for the capability of quickly forming the vertical take-off and landing reusable launch vehicle in China;
3. the carrier rocket with two-stage single-core-stage and odd-number engine parallel-connection configurations and vertical take-off and landing repeated use is taken as a research object, the maximum diameter of the engine under different rocket body diameter configurations is obtained according to a topological optimization method, further the base-stage maximum thrust is obtained according to the engine thrust surface density parameters, and the take-off scale of the whole rocket is quickly established;
4. the screened scheme has practical feasibility in engineering practice by designing an evaluation method under a given scheme;
5. by optimizing the carrying capacity equation, the related parameters of the maximized load under the given scheme condition are obtained, and the accuracy of the design scheme evaluation is improved.
The present disclosure also provides a vertical take-off and landing reusable carrier rocket overall design device, which is used for a vertical take-off and landing reusable carrier rocket with two stages of single-core stages and odd engines connected in parallel, and comprises:
scheme combination module: for generating a plurality of design scenarios based on selectable rocket diameters, engine layout scenarios, and propellant type selection; wherein, the diameter of rocket is chosen to be m, the layout scheme of engine is chosen to be n, the propellant type is chosen to be k, then the number of design schemes is m x n x k;
a scheme evaluation module: the method is used for evaluating each design scheme by using a vertical take-off and landing reusable launch vehicle design scheme evaluation method;
a scheme screening module: for making the evaluation result of the m x n x k designs feasible according to the evaluation resultlThe individual solutions are output along with their design parameters.
The specific implementation method of each module is referred to the related content of the general design method of the vertical take-off and landing reusable launch vehicle, and is not described herein again.
Fig. 6 is a schematic structural diagram of an electronic device according to an embodiment of the present disclosure, where the device may execute the processing procedure provided in the foregoing method embodiment, and as shown in fig. 6, the electronic device 110 includes: memory 111, processor 112, computer programs, and communications interface 113; wherein the computer program is stored in the memory 111 and is configured to be executed by the processor 112 for performing the method as described above.
In addition, the embodiment of the present disclosure also provides a computer readable storage medium, on which a computer program is stored, where the computer program is executed by a processor to implement the method described in the above embodiment. Those of ordinary skill in the art will understand that: all or a portion of the steps of implementing the above-described method embodiments may be performed by hardware associated with program instructions. The program may be stored in a computer-readable storage medium. When executed, the program performs steps comprising the method embodiments described above; and the aforementioned storage medium includes: various media that can store program codes, such as ROM, RAM, magnetic or optical disks.
Specific examples are given in this specification for the purpose of illustrating the disclosure and implementations. The details introduced in the examples are not intended to limit the scope of the claims but rather to aid in understanding the present disclosure. Those skilled in the art will understand that: although the description is given in terms of embodiments, not every embodiment includes only a single embodiment, and such description is for clarity only, and those skilled in the art will recognize that the embodiments described herein may be combined as a whole to form other embodiments as would be understood by those skilled in the art. And that various modifications, changes, or alterations to the steps of the preferred embodiments are possible without departing from the spirit and scope of this disclosure and the appended claims. Therefore, the disclosure should not be limited to the disclosure of the preferred embodiments and drawings.
Claims (10)
1. A general design method of a vertical take-off and landing reusable launch vehicle is characterized in that: the vertical take-off and landing reusable launch vehicle used for the parallel connection of two stages of single-core-stage engines and odd engines comprises the following contents:
generating a plurality of design solutions according to selectable rocket diameters, engine layout solutions and propellant type selection; wherein, the diameter of rocket is chosen to be m, the layout scheme of engine is chosen to be n, the propellant type is chosen to be k, then the number of design schemes is m x n x k;
evaluating each design scheme by using a vertical take-off and landing reusable launch vehicle design scheme evaluation method;
evaluating m n k of the designs as feasiblelThe individual solutions are output along with their design parameters.
2. The method of claim 1, wherein the method comprises the steps of: the method for evaluating the design scheme of the vertical take-off and landing reusable launch vehicle comprises the following steps:
calculating the maximum thrust F of a base level according to the diameter of an arrow body, an engine layout scheme and the type of a propellant;
calculating the total mass from Fm 0 ：
Calculating the carrying capacity according to the interstage ratio and the rocket structure coefficient by the formula (1);
wherein, deltavIndicates the speed increment,I sp1 Shows the specific impulse of a first-class engine,I sp2 Shows the specific impulse of the two-stage engine,m 1 Represents the total mass of the first stage,m 2 Represents the total mass of the second stage,m s1 Represents the quality of the primary structure,m s2 Represents the quality of the secondary structure,m p Representing payload mass, σ 1 Representing first order structure coefficient, σ 2 Represents a secondary structure coefficient,εRepresents the interstage ratio;
in the formula (1)εAs the optimization variables, the variables of the optimization,m p as optimization target, according to a preset ΔvThe constant maximizes carrying capacity;
calculating the slenderness ratio of the rocket according to the optimization result;
and determining whether the scheme is feasible or not by taking whether the slenderness ratio accords with the engineering practice as a judgment standard.
3. The method of claim 2, wherein the method comprises the steps of: the engine layout scheme is that 1 engine is arranged in the center, and the rest engines are uniformly distributed on the periphery of the center engine.
4. The method of claim 3, wherein the method comprises the steps of: maximum diameter of the enginedComprises the following steps:
whereinDFor the diameter of the rocket in question,nthe number of engines.
5. The method of claim 4, wherein the method comprises the steps of: f = n F, where F is the thrust of the single engine, calculated by: f = thrust surface density of the engine corresponding to a typical engine of said propellant type.
6. The method of claim 2, wherein the method comprises the steps of: the describedm 0 = F/(push-to-weight ratio gravitational acceleration).
7. The method according to any one of claims 2-6, wherein: the process of calculating the rocket slenderness ratio according to the optimization result comprises the following steps:
will be epsilon andm P is substituted by formula (1) to obtainm 1 、m 2 、m s1 Andm s2 ；
according tom 1 、m 2 、m s1 Andm s2 obtaining the quality of each sub-level propellant;
calculate the full arrow length according to: the full arrow length = mass of propellant per substage/(relative density of propellant per rocket body cross-sectional area) + length of fairing;
calculating the rocket slenderness ratio according to the following formula: slenderness ratio = full arrow length/arrow body diameter.
8. The method of claim 7, wherein the method comprises the steps of: the criterion is whether the slenderness ratio is less than 20.
9. The method of claim 7, wherein the method comprises the steps of: the design parameters comprise rocket body diameter, engine layout scheme, propellant type and maximum diameter of single enginedTotal mass ofm 0 Inter-stage ratio ofεPayload massm p First order total massm 1 Is the second order total massm 2 Is the quality of the primary structurem s1 Is the quality of the secondary structurem s2 The mass of the primary propellant, the mass of the secondary propellant, the slenderness ratio and the carrying efficiency.
10. The utility model provides a VTOL reuse carrier rocket overall design device which characterized in that: a vertical take-off and landing reusable launch vehicle for two-stage single-core-stage and odd-number engine parallel connection comprises:
a scheme generation module: for generating a plurality of design scenarios based on selectable rocket diameters, engine layout scenarios, and propellant type selection; wherein, the diameter of rocket is chosen to be m, the layout scheme of engine is chosen to be n, the propellant type is chosen to be k, then the number of design schemes is m x n x k;
a scheme evaluation module: for evaluating each of the designs using a VTOL reuse launch vehicle design evaluation method;
a scheme screening module: means for evaluating m x n x k of the designs as feasiblelThe individual solutions are output along with their design parameters.
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| CN116495198A (en) * | 2023-04-19 | 2023-07-28 | 东方空间技术(山东)有限公司 | Swing control method of rocket and rocket |
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