CN113591214A - Design method for configuration parameters of ultra-low orbit satellite - Google Patents
Design method for configuration parameters of ultra-low orbit satellite Download PDFInfo
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- CN113591214A CN113591214A CN202110807130.6A CN202110807130A CN113591214A CN 113591214 A CN113591214 A CN 113591214A CN 202110807130 A CN202110807130 A CN 202110807130A CN 113591214 A CN113591214 A CN 113591214A
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Abstract
The invention discloses a design method of configuration parameters of an ultra-low orbit satellite, which comprises the steps of initializing and determining the initial satellite length and the diameter of an external tangent circle of a windward surface of the ultra-low orbit satellite; determining the optimal windward shape according to the relationship between the pneumatic resistance and the volume resistance ratio of the ultra-low orbit satellite at the specified orbit height and the windward shape; determining a satellite slenderness ratio which enables the minimum pneumatic resistance of the ultra-low orbit satellite at a specified orbit height; and calculating to obtain the critical angle of each side face of the ultra-low orbit satellite for designing the diffuse scattering coefficient according to the relationship between the aerodynamic resistance and the diffuse scattering coefficient of the ultra-low orbit satellite at the specified orbit height. The design of the invention realizes three parameters of windward surface shape, satellite slenderness ratio and diffuse scattering coefficient and aims at reducing aerodynamic resistance, can effectively reduce the aerodynamic resistance of the ultra-low orbit satellite, reduces the interference influence on the orbit and the attitude of the satellite caused by the aerodynamic resistance, improves the stability of the ultra-low orbit satellite, and prolongs the on-orbit time of the ultra-low orbit satellite.
Description
Technical Field
The invention relates to a satellite configuration design technology, in particular to a design method of ultra-low orbit satellite configuration parameters.
Background
The design of the satellite configuration needs to meet the mutual restriction and various design requirements of different levels, and the design is a process of integrating, compromising, optimizing and coordinating various requirements, so that the requirements are finally ensured to be comprehensively met. Certain orbital environments have certain particularity aiming at different task orbit types, and satellite configuration parameters need to be designed according to the particularity.
The ultra-low orbit is a satellite orbit outside the dense atmosphere and lower than the orbit height of a general spacecraft, and is generally defined as a flight orbit in a space range of 120 km or more and 300 km or less from the earth surface. The ultra-low orbit satellite is used as a platform to carry various effective loads such as optical imaging equipment, synthetic aperture radar, electronic reconnaissance equipment and the like, and can be widely applied to various emergency tasks such as rapid reconnaissance and monitoring, emergency response of emergency crisis, regional early warning and the like.
The satellite flies at such an altitude as an ultra-low orbit, although the atmospheric density is only 10-9-10-11kg/m3Magnitude, but the aerodynamic force acting on the ultra-low orbit satellite can reach the degree of tens of milli-newtons, is higher by several magnitude than the aerodynamic force of the traditional low orbit satellite, and has great influence on the interference of the satellite orbit and the attitude along with long-term accumulation. On an ultra-low orbit, atmospheric resistance will dominate, and strong air resistance perturbation is the most important factor influencing ultra-low orbit attenuation and attitude disturbance, so that the ultra-low orbit is different from the orbit of the traditional satellite, so that the configuration of the traditional satellite is not suitable for the ultra-low orbit, and the design of satellite configuration parameters must be carried out aiming at the special environment of the ultra-low orbit.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the design method can effectively reduce the aerodynamic resistance of the ultra-low orbit satellite, reduce the interference influence on the orbit and the attitude of the satellite due to the aerodynamic resistance, and improve the stability of the ultra-low orbit satellite.
In order to solve the technical problems, the invention adopts the technical scheme that:
a design method for ultra-low orbit satellite configuration parameters comprises the following steps:
1) initializing and determining the initial satellite length L and the diameter D of an external tangent circle of a windward surface of the ultra-low orbit satellite;
2) aerodynamic drag F at specified orbital altitude according to ultra-low orbit satelliteDVolume resistance ratio RV/FDetermining the optimal windward shape according to the relationship between the two and the windward shape;
3) determining aerodynamic drag F for ultra-low orbit satellite at specified orbital altitudeDA minimum satellite slenderness ratio L/D;
4) according to the aerodynamic resistance F of the ultra-low orbit satellite at the designated orbit heightDAnd calculating the relation with the diffuse scattering coefficient sigma to obtain the critical angle beta of each side face of the ultra-low orbit satellite for designing the diffuse scattering coefficient sigma.
Optionally, step 2) comprises: respectively calculating aerodynamic resistance F aiming at each windward shape to be selectedDVolume resistance ratio RV/FSelection of aerodynamic drag FDVolume resistance ratio RV/FThe optimal windward shape.
Optionally, the functional expression of the relationship between aerodynamic resistance and windward shape in step 2) is as follows:
FD＝Fwelcome to+FSide wall
＝q·CD welcome·SWelcome to+q·CSide D·SSide wall
In the above formula, FDFor aerodynamic drag, FWelcome toFor aerodynamic drag on the windward side, FSide wallIs the aerodynamic resistance of the side, q is the dynamic pressure to which the satellite is subjected, CD welcomeIs the coefficient of resistance of the windward side, CSide DIs the coefficient of lateral resistance, SWelcome toIs the frontal area, SSide wallIs the side area.
Alternatively, the volumetric resistance ratio R in step 2)V/FThe functional expression of the relationship with the windward shape is shown as follows:
in the above formula, RV/FRepresenting volumetric resistance ratio, V representing satellite volume, FDRepresenting the aerodynamic resistance.
Optionally, the length-to-slenderness ratio L/D of the satellite that minimizes aerodynamic drag is determined in step 3) as:
in the above formula, L/D is the slenderness ratio of the satellite, L is the length of the satellite, D is the diameter of the tangent circle outside the windward surface, CD welcomeIs the coefficient of resistance of the windward side, CSide DThe lateral drag coefficient.
Optionally, step 4) comprises: coefficient of resistance CDDecomposition into a diffuse scattering coefficient dependent drag coefficient CDσCoefficient of resistance C independent of the diffuse scattering coefficientDDetermining a coefficient of resistance C related to the diffuse scattering coefficientDσA coefficient of drag C that is not related to the diffuse scattering coefficient σ, the angle of attack α, and the diffuse scattering coefficientDCorrelation between angle of attack alpha and coefficient of drag C that correlates diffuse scattering coefficientsDσThe angle of attack α at 0 is taken as the critical angle β.
Optionally, the diffuse scattering coefficient-dependent drag coefficient CDσCoefficient of resistance C that is not related to the diffuse scattering coefficient σ, the correlation curve between the angle of attack α, and the diffuse scattering coefficientDThe correlation curve between the angle of attack α is shown as follows:
in the above formula, S is the molecular velocity ratio, TrIs the reflected gas temperature, T∞For the incoming flow temperature, erf is the error function.
In addition, the invention also provides an ultra-low orbit satellite which is designed by adopting the ultra-low orbit satellite configuration parameter design method.
In addition, the present invention also provides an ultra-low orbit satellite configuration parameter design system, comprising a computer device programmed or configured to perform the steps of the ultra-low orbit satellite configuration parameter design method, or a computer program programmed or configured to perform the ultra-low orbit satellite configuration parameter design method stored in a memory of the computer device.
In addition, the present invention also provides a computer readable storage medium having stored therein a computer program programmed or configured to perform the ultra-low orbit satellite configuration parameter design method.
Compared with the prior art, the invention has the following advantages: the method determines the windward shape which enables the pneumatic resistance and the volume resistance ratio to be optimal by calculating the relationship between the pneumatic resistance and the volume resistance ratio of the ultra-low orbit satellite at the specified orbit height and the windward shape respectively; determining a satellite slenderness ratio which enables the minimum pneumatic resistance of the ultra-low orbit satellite at a specified orbit height; according to the relationship between the aerodynamic resistance and the diffuse scattering coefficient of the ultra-low orbit satellite at the designated orbit height, the optimal diffuse scattering coefficient is obtained, so that the design of three parameters of the windward surface shape, the satellite slenderness ratio and the diffuse scattering coefficient aiming at reducing the aerodynamic resistance is realized, the aerodynamic resistance of the ultra-low orbit satellite can be effectively reduced, the interference influence of the aerodynamic resistance on the orbit and the attitude of the satellite is reduced, the stability of the ultra-low orbit satellite is improved, and the on-orbit time of the ultra-low orbit satellite is prolonged.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic diagram of a basic flow of a method according to an embodiment of the present invention.
Fig. 2 is a schematic perspective view of an ultra-low orbit satellite in an embodiment of the invention.
Fig. 3 shows the windward side of satellites with different shapes designed in the embodiment of the invention.
FIG. 4 is a graph of aerodynamic resistance versus the number of windward edges in an embodiment of the present invention.
FIG. 5 is a plot of volumetric resistance ratio versus number of windward sides for an embodiment of the present invention.
FIG. 6 is a graph of aerodynamic drag versus satellite slenderness ratio for an embodiment of the present invention.
FIG. 7 is a plot of drag coefficient versus angle of attack for an embodiment of the present invention.
FIG. 8 is a plot of drag coefficient versus diffuse scattering coefficient for an embodiment of the present invention.
FIG. 9 is a graph of aerodynamic drag versus diffuse scattering coefficient for an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to specific examples.
As shown in fig. 1, the method for designing configuration parameters of an ultra-low orbit satellite in this embodiment includes:
1) initializing and determining the initial satellite length L and the diameter D of an external tangent circle of a windward surface of the ultra-low orbit satellite;
2) aerodynamic drag F at specified orbital altitude according to ultra-low orbit satelliteDVolume resistance ratio RV/FDetermining the optimal windward shape according to the relationship between the two and the windward shape;
3) determining aerodynamic drag F for ultra-low orbit satellite at specified orbital altitudeDA minimum satellite slenderness ratio L/D;
4) according to the aerodynamic resistance F of the ultra-low orbit satellite at the designated orbit heightDAnd calculating the relation with the diffuse scattering coefficient sigma to obtain the critical angle beta of each side face of the ultra-low orbit satellite for designing the diffuse scattering coefficient sigma.
Referring to fig. 2, in step 1) of this embodiment, an elongated satellite with a length of 3 meters and a radius of 0.5m (diameter of 1m) is selected as a design object. And the specified orbital height of the ultra-low orbit satellite is 268 km. Of course, the method of the present embodiment is not limited by the specific shape of the satellite and the specified orbital height.
The operating environment of the ultra-low orbit satellite belongs to high-rise atmosphere, the gas is thin, the molecular mean free path is far longer than the characteristic length of the satellite, and therefore, the aerodynamic force applied to the satellite is analyzed according to the theory of free molecular flow. The present example uses a plate method to simulate the motion and action process of free molecular flow. The flat plate method does not consider the problems of shielding and multiple reflections, considers that aerodynamic forces generated by each part of the satellite are not interfered with each other, can divide the aerodynamic forces into a plurality of parts, distributes and calculates the aerodynamic forces, and then superposes and calculates to obtain the total aerodynamic force. The calculation formula is expressed as:
in the above formula, FDN is the number of divided parts for aerodynamic drag, q is the dynamic pressure to which the satellite is subjected, CDiIs the drag coefficient of the i-th part, AiIs the area of the ith section. Wherein, the dynamic pressure q received by the satellite is:
in the above equation, ρ is the atmospheric density and U is the satellite velocity.
Coefficient of resistance C of any partDThe formula of the calculation function is:
in the above formula, S is the molecular velocity ratio, α is the angle of attack, σ is the diffuse scattering coefficient, TrIs the reflected gas temperature, T∞For incoming temperature, erf is errorA function. The calculated function expression of the error function erf is:
the ultra-low orbit satellite configuration key parameters comprise: the satellite body, the windward surface shape, the size, the slenderness ratio, the diffuse scattering coefficient and the like. The design method of the ultra-low orbit satellite configuration parameters can be used for carrying out design work of the ultra-low orbit satellite configuration parameters from three aspects of windward surface shape, slenderness ratio and diffuse scattering coefficient.
The windward shape is a key parameter influencing the aerodynamic resistance of the satellite, so the design considering the windward shape of the satellite must be carried out. The step 2) comprises the following steps: respectively calculating aerodynamic resistance F aiming at each windward shape to be selectedDVolume resistance ratio RV/FSelection of aerodynamic drag FDVolume resistance ratio RV/FThe optimal windward shape.
Fig. 3 shows different shapes of the selected windward surfaces designed in this embodiment, and it should be noted that the method of this embodiment can be applied to various windward surface shapes, such as circles, polygons, irregular shapes, etc., and the difference is only that the windward surface areas are different from each other in calculation.
In the embodiment, the functional expression of the relationship between the aerodynamic resistance and the windward shape in step 2) is shown as follows:
FD＝Fwelcome to+FSide wall
＝q·CD welcome·SWelcome to+q·CSide D·SSide wall
In the above formula, FDFor aerodynamic drag, FWelcome toFor aerodynamic drag on the windward side, FSide wallIs the aerodynamic resistance of the side, q is the dynamic pressure to which the satellite is subjected, CD welcomeIs the coefficient of resistance of the windward side, CSide DIs the coefficient of lateral resistance, SWelcome toIs the frontal area, SSide wallIs the side area. For example, taking a regular polygon as an example, the functional expression of the relationship between aerodynamic resistance and windward shape in step 2) may further be based on the face of the regular polygonThe product calculation is expressed as:
in the above formula, n is the number of windward sides, R is the windward outside tangent circle radius, and L is the satellite length.
The functional expression of the relationship between the volume resistance ratio and the windward shape in step 2) of this embodiment is shown as follows:
in the above formula, RV/FRepresenting volumetric resistance ratio, V representing satellite volume, FDRepresenting the aerodynamic resistance. As an example of a regular polygon, the functional expression of the relationship between the volume resistance ratio and the windward shape in step 2) is shown as follows:
in the above formula, RV/FRepresenting volumetric resistance ratio, V representing satellite volume, FDRepresenting aerodynamic resistance, n is the number of windward sides, L is the length of the satellite, R is the radius of an external tangent circle of the windward side, q is the dynamic pressure applied to the satellite, CD welcomeIs the coefficient of resistance of the windward side, CSide DThe lateral drag coefficient.
For the sake of simplicity, in this embodiment, when the unfolding device such as the solar sailboard is not considered, the number of windward sides and the aerodynamic resistance F are calculated when the track height is 268kmDAnd volume resistance ratio RV/FAs shown in fig. 4 and 5. It can be seen that as the number of sides of the windward shape increases (the number of sides of the circle is infinite), the aerodynamic resistance of the satellite increases, the volume increases, and the volume resistance ratio also increases. The design of the ultra-low orbit satellite necessarily requires that the resistance is as small as possible and the volume is as large as possible, i.e. the volume resistance is as large as possible. The satellite configuration with a circular windward side therefore has optimum aerodynamic performance. In actual engineering, the windward side with a large number of shape sides should be selected as much as possible according to the size and limitation of equipment such as a payload, a control system and the like.
In step 3) of this embodiment, the length-to-slenderness ratio L/D of the satellite that minimizes aerodynamic drag is determined as:
in the above formula, L/D is the slenderness ratio of the satellite, L is the length of the satellite, D is the diameter of the tangent circle outside the windward surface, CD welcomeIs the coefficient of resistance of the windward side, CSide DThe lateral drag coefficient. The specific derivation process is as follows:
for the satellite with circumcircle on the windward side, the aerodynamic resistance F is applied to the satelliteDCan be expressed as:
in the above formula, FDFor aerodynamic drag, FWelcome toFor aerodynamic drag on the windward side, FSide wallIs the aerodynamic resistance of the side, q is the dynamic pressure to which the satellite is subjected, CD welcomeIs the coefficient of resistance of the windward side, CSide DIs the coefficient of lateral resistance, SWelcome toIs the frontal area, SSide wallIs the side area, D is the diameter of the tangent circle outside the windward surface, and V is the satellite volume.
Will the aerodynamic resistance FDThe derivation of the diameter D of the tangent circle outside the windward surface is as follows:
because the satellite volume V is:
thus, it is possible to obtain:
namely, the slenderness ratio L/D satisfies:
aerodynamic drag F of time-ultralow orbit satelliteDAnd minimum.
In this embodiment, the volume V of the satellite is 1 cubic meter, and the change rule of the aerodynamic resistance of the satellite along with the length-to-thickness ratio (L/D) of the satellite when the orbital height is 268km is calculated, as shown in fig. 6. As can be seen in fig. 6: aerodynamic drag FDThe length-to-fineness ratio is increased, and the length-to-fineness ratio is decreased and then increased; when the length-thin ratio L/D of the satellite is smaller, the side area is small, the influence of the side area on the total resistance of the satellite is smaller, the total resistance of the satellite approaches the resistance when only the windward area is considered, and therefore the aerodynamic resistance FDThe slenderness ratio L/D increases and decreases; when the slenderness ratio L/D is increased to a certain degree, the resistance effect of the side area is obvious, and the aerodynamic resistance FDIncreases with increasing slenderness ratio L/D; the aspect ratio (L/D) of a cylindrical satellite is about 20 with the least aerodynamic drag. The aerodynamic drag values for different slenderness ratios L/D are given in Table 2.
Table 2: aerodynamic drag values at different slenderness ratios.
In this embodiment, step 4) includes: coefficient of resistance CDDecomposition into a diffuse scattering coefficient dependent drag coefficient CDσCoefficient of resistance C independent of the diffuse scattering coefficientD*Determining a coefficient of resistance C related to the diffuse scattering coefficientDσWith diffuse scattering coefficient sigma, angle of attack alphaThe correlation between them, and the coefficient of resistance C for which the diffuse scattering coefficient is not correlatedD*Correlation with the angle of attack α, the drag coefficient C that correlates the diffuse scattering coefficient is foundDσThe angle of attack α at 0 is taken as the critical angle β.
In this embodiment, the coefficient of resistance C associated with the diffuse scattering coefficientDσCoefficient of resistance C that is not related to the diffuse scattering coefficient σ, the correlation curve between the angle of attack α, and the diffuse scattering coefficientD*The correlation curve with the angle of attack α is shown as follows:
in the above formula, S is the molecular velocity ratio, TrIs the reflected gas temperature, T∞For the incoming flow temperature, erf is the error function.
In the embodiment, the change rule of the resistance coefficient along with the attack angle is analyzed when the track height is 268km, as shown in fig. 7. It can be seen that: coefficient of resistance C with increasing angle of attack alphaDCoefficient of resistance C independent of the diffuse scattering coefficientD*Increasing and diffuse scattering coefficient dependent drag coefficient CDσIncreasing and then decreasing and a critical angle beta occurs, so that the drag coefficient C related to the diffuse scattering coefficientDσVariation of the diffuse scattering coefficient σ to the aerodynamic drag F at 0, i.e. the angle of attack is the critical angle βDHas no influence. Analysis of the aerodynamic resistance F by calculationDThe optimal diffuse scattering coefficient sigma can be obtained according to the relation of the diffuse scattering coefficient sigma.
In this embodiment, when the angle of attack α is 15 degrees (smaller than the critical angle β) and 75 degrees (larger than the critical angle β), respectively, the drag coefficient C isDThe law of variation with diffuse scattering coefficient is shown in fig. 8. It can be seen that:
at an angle of attack of 15 degrees (less than the critical angle β), the coefficient of drag C increases with the diffuse scattering coefficient σDIncreasing;
at an angle of attack of 75 degrees (greater than the critical angle β), the coefficient of drag C increases with the diffuse scattering coefficient σDAnd decreases.
In the satellite configuration design, the attack angle alpha of a normal windward side is larger, and the aerodynamic resistance F is increased along with the increase of the diffuse scattering coefficient sigmaDTherefore, the normal windward side can adopt a common industrial processing technology, the diffuse scattering coefficient sigma is about 0.9, special processing and treatment technologies are not needed, but the side attack angle is small, and a side smoothing technology is adopted to reduce the side resistance.
In this embodiment, for a selected satellite with an elongated body having a length of 3 meters and a radius of 0.5m, the orbit height is 268km, and the drag reduction effect after the side surface is analyzed by smoothing is shown in fig. 9. Referring to fig. 9, it can be seen that when the track height is 268km, the aerodynamic drag F is when the lateral diffuse scattering coefficient σ is 1D0.00320N, aerodynamic drag F when the diffuse scattering coefficient of the flank is 0.5D0.00277N, the aerodynamic drag can be reduced by 13.44% compared to 1 for diffuse scattering coefficient, F for 0 for diffuse scattering coefficient σD0.00235N, the aerodynamic resistance can be reduced by about 26.56%.
In summary, in the design method for the configuration parameters of the ultra-low orbit satellite of the embodiment, the windward shape which enables the optimal aerodynamic resistance and volume resistance ratio is determined by calculating the relationship between the aerodynamic resistance and volume resistance ratio of the ultra-low orbit satellite at the specified orbital height and the windward shape; determining a satellite slenderness ratio which enables the minimum pneumatic resistance of the ultra-low orbit satellite at a specified orbit height; according to the relationship between the aerodynamic resistance and the diffuse scattering coefficient of the ultra-low orbit satellite at the designated orbit height, the optimal diffuse scattering coefficient is obtained, so that the optimal design of three parameters of the windward shape, the satellite slenderness ratio and the diffuse scattering coefficient aiming at reducing the aerodynamic resistance is realized, the aerodynamic resistance of the ultra-low orbit satellite can be effectively reduced, the interference influence on the orbit and the attitude of the satellite due to the aerodynamic resistance is reduced, and the stability of the ultra-low orbit satellite is improved.
In addition, the embodiment also provides an ultra-low orbit satellite, which is an ultra-low orbit satellite designed by adopting the design method for the configuration parameters of the ultra-low orbit satellite.
In addition, the present embodiment also provides an ultra-low orbit satellite configuration parameter design system, which includes a computer device programmed or configured to execute the steps of the ultra-low orbit satellite configuration parameter design method, or a computer program programmed or configured to execute the ultra-low orbit satellite configuration parameter design method stored in a memory of the computer device.
In addition, the present embodiment also provides a computer-readable storage medium, in which a computer program programmed or configured to execute the ultra-low orbit satellite configuration parameter design method is stored.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-readable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein. The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks. These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks. These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may occur to those skilled in the art without departing from the principle of the invention, and are considered to be within the scope of the invention.
Claims (10)
1. A design method for ultra-low orbit satellite configuration parameters is characterized by comprising the following steps:
1) initializing and determining the initial satellite length L and the diameter D of an external tangent circle of a windward surface of the ultra-low orbit satellite;
2) aerodynamic drag F at specified orbital altitude according to ultra-low orbit satelliteDVolume resistance ratio RV/FDetermining the optimal windward shape according to the relationship between the two and the windward shape;
3) determining aerodynamic drag F for ultra-low orbit satellite at specified orbital altitudeDA minimum satellite slenderness ratio L/D;
4) according to the aerodynamic resistance F of the ultra-low orbit satellite at the designated orbit heightDAnd calculating the relation with the diffuse scattering coefficient sigma to obtain the critical angle beta of each side face of the ultra-low orbit satellite for designing the diffuse scattering coefficient sigma.
2. According to the rightThe design method for the configuration parameters of the ultra-low orbit satellite in claim 1, wherein the step 2) comprises the following steps: respectively calculating aerodynamic resistance F aiming at each windward shape to be selectedDVolume resistance ratio RV/FSelection of aerodynamic drag FDVolume resistance ratio RV/FThe optimal windward shape.
3. The design method for configuration parameters of ultra-low orbit satellite according to claim 1, wherein the aerodynamic resistance F in step 2)DThe functional expression of the relationship with the windward shape is shown as follows:
FD＝Fwelcome to+FSide wall
＝q·CD welcome·SWelcome to+q·CSide D·SSide wall
In the above formula, FDFor aerodynamic drag, FWelcome toFor aerodynamic drag on the windward side, FSide wallIs the aerodynamic resistance of the side, q is the dynamic pressure to which the satellite is subjected, CD welcomeIs the coefficient of resistance of the windward side, CSide DIs the coefficient of lateral resistance, SWelcome toIs the frontal area, SSide wallIs the side area.
4. The method for designing configuration parameters of ultra-low orbit satellite according to claim 1, wherein the volume resistance ratio R in step 2)V/FThe functional expression of the relationship with the windward shape is shown as follows:
in the above formula, RV/FRepresenting volumetric resistance ratio, V representing satellite volume, FDRepresenting the aerodynamic resistance.
5. The design method for configuration parameters of ultra-low orbit satellites as claimed in claim 1, wherein the length-to-width ratio L/D of the satellite which minimizes aerodynamic drag is determined in step 3) as follows:
in the above formula, L/D is the slenderness ratio of the satellite, L is the length of the satellite, D is the diameter of the tangent circle outside the windward surface, CD welcomeIs the coefficient of resistance of the windward side, CSide DThe lateral drag coefficient.
6. The method for designing configuration parameters of an ultra-low orbit satellite according to claim 1, wherein the step 4) comprises: coefficient of resistance CDDecomposition into a diffuse scattering coefficient dependent drag coefficient CDσCoefficient of resistance C independent of the diffuse scattering coefficientD*Determining a coefficient of resistance C related to the diffuse scattering coefficientDσA coefficient of drag C that is not related to the diffuse scattering coefficient σ, the angle of attack α, and the diffuse scattering coefficientD*Correlation with the angle of attack α, the drag coefficient C that correlates the diffuse scattering coefficient is foundDσThe angle of attack α at 0 is taken as the critical angle β.
7. The method for designing configuration parameters of an ultra-low orbit satellite according to claim 6, wherein the diffuse scattering coefficient-related drag coefficient CDσCoefficient of resistance C that is not related to the diffuse scattering coefficient σ, the correlation curve between the angle of attack α, and the diffuse scattering coefficientD*The correlation curve with the angle of attack α is shown as follows:
in the above formula, S is the molecular velocity ratio, TrIs the reflected gas temperature, T∞For the incoming flow temperature, erf is the error function.
8. An ultra-low orbit satellite, which is designed by the ultra-low orbit satellite configuration parameter design method according to any one of claims 1 to 7.
9. An ultra-low orbit satellite configuration parameter design system comprising a computer device, wherein the computer device is programmed or configured to perform the steps of the ultra-low orbit satellite configuration parameter design method of any one of claims 1 to 7, or a computer program programmed or configured to perform the ultra-low orbit satellite configuration parameter design method of any one of claims 1 to 7 is stored in a memory of the computer device.
10. A computer readable storage medium having stored thereon a computer program programmed or configured to perform the ultra-low orbit satellite configuration parameter design method of any one of claims 1 to 7.
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|---|---|---|---|---|
| CN112591150A (en) * | 2021-01-05 | 2021-04-02 | 成都天巡微小卫星科技有限责任公司 | Atmospheric moment of resistance compensation method and system for controlling attitude of ultra-low orbit satellite |
Non-Patent Citations (2)
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| 夏灿英: "卫星大气阻力系数的计算公式", 《天文研究与技术》 * |
| 温生林等: "超低轨道卫星摄动特性分析及轨道维持方法", 《国防科技大学学报》 * |
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