Satellite assembly large centroid offset engine layout and thrust synthesis method

Abstract

The present application relates to a kind of satellite assembly large centroid deviation engine layout and thrust synthesis method.The present application method includes the steps of installing engine based on top edge top angle layout principle and carrying out the reconstruction of orbit control thrust distribution matrix.The present method realizes the maximum of the distance span between each engine by using the engine installation layout of top edge top angle installation,enhances the tolerance ability of orbit control engine group to the centroid deviation of assembly;The present method uses the oblique installation design with 25 ° angle with Z axis,so that the tolerance ability of orbit control engine group to the centroid deviation of assembly can be automatically proportional to the change of assembly centroid in Z direction and enhanced;The present method realizes +Z direction thrust synthesis by orbit control thrust distribution matrix reconstruction,without additional coupling interference moment generation,reduce the efficiency loss of orbit control engine,realize the reconstruction and synthesis of the orbit control thrust of large centroid deviation assembly.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of satellite engine layout method, and particularly relates to a satellite assembly large-moment-of-center deviation engine layout and thrust synthesis method. BACKGROUND

[0002] In recent years, a large number of space debris, failed satellites and other space garbage (non-cooperative targets) have posed a serious threat to space safety. The number of space garbage around the Earth has approached the critical point of the maximum tolerable, and the cleaning problem of space garbage has become one of the most urgent and most concerned problems in the international aerospace field. At present, the space garbage cleaning schemes published at home and abroad mainly approach the space garbage, capture the target by using a capture mechanism, form a semi-rigid / rigid assembly, and finally realize cleaning by using a drag sail, chemical propulsion, electric propulsion and other deorbiting / orbiting means (as shown in Figure 3 and Figure 4 However, due to the uncertainty of the target mass, inertia, attitude, angular velocity and capture process, the moment of center and inertia characteristics of the assembly formed by the captured "space garbage" and the "garbage cleaning satellite" change obviously and have high uncertainty, which leads to the problem of large moment-of-center deviation of the assembly.

[0003] We know that in the past, various satellites were mainly designed and verified on the ground. The mass and inertia characteristics of the satellites in each stage of the life cycle were designed, adjusted and confirmed in detail, and the engine layout and thrust synthesis method were designed accordingly to ensure that the synthesized thrust of the propulsion system engine passes through the center of mass when performing orbit maintenance, orbit transfer and deorbiting control, so as to avoid strong coupling disturbance torque and reduce the equivalent translational thrust, thereby avoiding serious problems such as sharp decline in orbit control efficiency and attitude instability and orbit control failure. However, when the assembly has large moment-of-center deviation, the synthesized thrust of the propulsion system engine will deviate from the center of mass, and the probability of the above-mentioned serious problems will greatly increase.

[0004] At present, the related research on space non-cooperative target capture at home and abroad mainly focuses on target identification, relative navigation, relative control, target capture locking and other aspects. There is no related method and design for how to carry out engine layout and thrust synthesis when the assembly has large moment-of-center deviation after the non-cooperative target is captured. SUMMARY

[0005] In order to avoid the problem of strong coupling disturbance torque caused by large moment-of-center deviation of the satellite assembly, leading to failure of orbit control task, and at the same time not to significantly sacrifice the orbit control efficiency, to reduce fuel consumption as much as possible, to ensure that the satellite assembly successfully performs orbit transfer and deorbiting, and finally to achieve the purpose of garbage cleaning, we design a solution.

[0006] The application provides an engine layout and thrust synthesis method for a satellite combination under a large center-of-mass deviation condition.

[0007] Specifically, the application provides a satellite combination large center-of-mass deviation engine layout and thrust synthesis method, which comprises the following steps:

[0008] S1. installing engines based on a top-edge-top-corner layout principle;

[0009] S2. performing orbit control thrust distribution matrix reconstruction.

[0010] Further, according to some embodiments of the application, the installing engines based on the top-edge-top-corner layout principle in step S1 of the satellite combination large center-of-mass deviation engine layout and thrust synthesis method of the application refers to installing 16 engines according to the top-edge-top-corner layout principle, comprising the following steps:

[0011] (1) 1#, 2#, 3# and 4# engines are installed on the satellite combination-Z plane, and are installed close to the top corner, each engine has an angle of 25° with the-Z axis, and has an angle of 45° with the X / Y axis in the projection around different directions and the + / Z plane;

[0012] (2) 5# and 6# engines are installed on the satellite combination+Y plane, and have an angle of 60° between the two engines, and the projection is parallel to the + / -Z plane;

[0013] (3) 7# and 8# engines are installed on the satellite combination-Y plane, and have an angle of 60° between the two engines, and the projection is parallel to the + / -Z plane;

[0014] (4) 9# and 10# engines are installed on the satellite combination+X plane, and have an angle of 60° between the two engines, and the projection is parallel to the + / -Z plane;

[0015] (5) 11# and 12# engines are installed on the satellite combination-X plane, and have an angle of 60° between the two engines, and the projection is parallel to the + / -Z plane;

[0016] (6) 13# engine has an angle of 60° with the +Y plane, and is installed close to the edge, and the projection is parallel to the Z axis;

[0017] (7) 14# engine has an angle of 60° with the-Y plane, and is installed close to the edge, and the projection is parallel to the Z axis;

[0018] (8) 15# engine is installed at the edge with an angle of 60° to the +X plane, and the projection is parallel to the Z axis;

[0019] (9) 16# engine is installed at the edge with an angle of 60° to the -X plane, and the projection is parallel to the Z axis.

[0020] Further, according to some embodiments of the present application, in the large-mass-center-deviation engine layout and thrust synthesis method of the satellite combination, the 1#, 2#, 3# and 4# engines are orbit-controlling positive thrust engines, and the 13#, 14#, 15# and 16# engines are orbit-controlling negative thrust engines, and the 5# to 12# engines are attitude-controlling engines.

[0021] Further, according to some embodiments of the present application, in the large-mass-center-deviation engine layout and thrust synthesis method of the satellite combination, when the mass center of the satellite combination has no XY plane deviation, the orbit control is determined by the +Z direction thrust, the +Z direction thrust is synthesized by the 1#, 2#, 3# and 4# engines, and at this time, the +Z direction thrust synthesis matrix based on the 1#, 2#, 3# and 4# engines is as follows:

[0022]

[0023] In the formula, F1 is the thrust of the 1#, 2#, 3# and 4# engines, F is the expected synthesized +Z direction thrust, and λ1-λ4 are the engine opening ratios of the 1#, 2#, 3# and 4# engines respectively (i.e. the proportion of the working time to the total time when the engine works in an on-off mode). z z

[0024] Further, according to some embodiments of the present application, in the large-mass-center-deviation engine layout and thrust synthesis method of the satellite combination, when the mass center of the satellite combination has a large XY plane deviation, the orbit-controlling thrust distribution matrix reconstruction in step S2 of the method is that at this time, the +Z direction thrust synthesis matrix based on the 1#, 2#, 3# and 4# engines is reconstructed as follows:

[0025]

[0026] In the formula, F1 is the thrust of the 1#, 2#, 3# and 4# engines, F is the expected synthesized +Z direction thrust, λ1-λ4 are the engine opening ratios of the 1#, 2#, 3# and 4# engines respectively, L is the length of each side of the -Z plane of the satellite combination, L dx , L dy are the distances of the mass center of the satellite combination deviating to the -X and +Y directions respectively, and the +Z direction thrust synthesis can be realized through the thrust synthesis matrix reconstruction, and no additional coupling moment is generated in the process, and no additional fuel cost is paid.

[0027] ​​In addition, the application also relates to application of the satellite assembly large-moment-of-center-of-mass engine layout and thrust synthesis method to space garbage removal satellite manufacturing.

[0028] In addition, the application also relates to application of the satellite assembly large-moment-of-center-of-mass engine layout and thrust synthesis method to space garbage removal satellite manufacturing.

[0029] In summary, the technical key points of the application are as follows:

[0030] Firstly, in the orbit control main engine installation surface, the engine positions are located at the top corners of the main body structure, the distance span between the engines can be maximized, as long as the moment-of-center-of-mass offset of the assembly does not exceed the rectangular region formed by the installation positions, the combined force vector of the orbit control engines can pass through the moment-of-center-of-mass of the assembly through reasonable opening configuration between the engines, so that the serious coupling interference torque on the attitude can be avoided, and the smooth progress of the orbit control task can be ensured. Meanwhile, the maximum moment-of-center-of-mass offset range of the assembly can be estimated according to the maximum mass inertia envelope of the space garbage fragments and the capture characteristics of the capture mechanism in the ground design stage, and it is confirmed that the moment-of-center-of-mass is still in the rectangular region formed by the orbit control engine installation positions in the extreme case. Through the above design, the large moment-of-center-of-mass offset of the assembly and the coupling interference torque problem possibly caused by the large moment-of-center-of-mass offset can be effectively handled.

[0031] Secondly, the orbit control engines in the specific layout of the method adopt the oblique installation design with a 25° angle with the Z axis, the orbit control efficiency is cos(25°)=0.9063, that is, there is about 10% efficiency loss, but due to the outward expansion of the engine thrust line, the actual tolerance capacity of the orbit control engine group to the moment-of-center-of-mass offset of the assembly in the XY plane can be further increased, especially when the space garbage is heavy and the moment-of-center-of-mass of the assembly changes obviously in the Z direction before and after capture, the tolerance capacity increment is proportional to the distance of the -Z plane and the moment-of-center-of-mass after capture, and the proportional magnification relationship is sin(25°)=0.4226. In addition, the application can reserve greater moment-of-center-of-mass offset tolerance capacity for the extreme case on the basis of the top edge top corner installation design, and the capacity can be automatically proportionally magnified with the change of the moment-of-center-of-mass of the assembly in the Z direction.

[0032] Finally, the layout positions of the orbit control reverse thrust engines 13#-16# can effectively offset the obvious change of the moment-of-center-of-mass of the assembly in the Z direction, and the attitude coupling torque generated by the attitude control engines 5#-12# when the attitude control engines 5#-12# are synthesized in the X and Y directions also has strong adaptability.

[0033] In short, the method has the following advantages:

[0034] The present application overcomes the defects that the existing engine layout and thrust synthesis method may cause strong coupling interference torque in the case of large mass center deviation of the combination body, resulting in sharp decline of the orbit control efficiency or mission failure. The present method realizes maximization of the distance span between each engine by adopting the engine installation layout of top edge top corner installation, thereby greatly enhancing the tolerance ability of the orbit control engine group to the mass center deviation of the combination body. The present method adopts the oblique installation design with a 25° angle with the Z axis, so that the tolerance ability of the orbit control engine group to the mass center deviation of the combination body can be automatically enhanced in proportion to the change of the mass center of the combination body in the Z direction. The present method realizes +Z direction thrust synthesis through the orbit control thrust distribution matrix reconstruction, and no additional coupling interference torque is generated, so that the orbit control thrust of the large mass center deviation combination body can be reconstructed and synthesized under the condition that the efficiency reduction of the orbit control engine is acceptable. In view of the above characteristics, the present method can be popularized as a general method for engine layout and thrust synthesis of non-cooperative target capture satellite. BRIEF DESCRIPTION OF DRAWINGS

[0035] In order to more clearly illustrate the background and technical solutions of the embodiments of the present application, the drawings used in the background and embodiment description will be briefly introduced. Obviously, the drawings in the following description are only specific embodiments described by the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of the following drawings.

[0036] Figure 1 It is an engine layout installation schematic diagram (tail view) in the method of the present application.

[0037] Figure 2 It is an engine layout installation schematic diagram (three-way view) in the method of the present application.

[0038] Figure 3 It is a schematic diagram of a garbage removal satellite capturing a non-cooperative target (space garbage).

[0039] Figure 4 It is a satellite combination body rendering diagram formed after the garbage removal satellite captures the non-cooperative target (space garbage).

[0040] Figure 5 It is a schematic diagram of the mass center deviation of the satellite combination body in the method of the present application.

[0041] Figure 6 It is a flow chart of the implementation steps of the method of the present application. DETAILED DESCRIPTION

[0042] Following, the embodiments of the present application will be described through specific examples, and other advantages and effects of the present application can be easily understood by those skilled in the art from the disclosure of the present specification. The present application can also be implemented or applied through other different embodiments, and various modifications or changes can be made to the details in the present specification based on different views and applications without departing from the spirit of the present application.

[0043] Before further describing the embodiments of the present application, it should be understood that the scope of protection of the present application is not limited to the following specific embodiments; and it should also be understood that the terms used in the embodiments of the present application are used to describe the specific embodiments, but not to limit the scope of protection of the present application.

[0044] Unless otherwise defined, all technical and scientific terms used in the present application have the same meanings as commonly understood by those skilled in the art. In addition to the specific methods, devices, materials used in the examples, any methods, devices and materials similar or equivalent to those described in the embodiments of the present application can also be used to implement the present application according to the mastery of the prior art by those skilled in the art and the description of the present application.

[0045] In the present application, all components, devices and software involved can be obtained from commercial channels or manufactured by conventional methods in the industry, unless otherwise specified.

[0046] A satellite assembly large centroid offset engine layout and thrust synthesis method (as shown in Figure 6 , comprising:

[0047] (I) install the engine based on the layout principle of the top edge top corner (as shown in Figure 1 and Figure 2 )

[0048] Install 16 engines according to the layout principle of the top edge top corner, specifically:

[0049] (1) 1#, 2#, 3#, 4# engines are installed on the satellite assembly-Z plane, all installed near the top corner, each engine has an angle of 25° with the-Z axis, and the projection on the-Z plane has an angle of 45° with the X / Y axis in different directions;

[0050] (2) 5#, 6# engines are installed on the satellite assembly+Y plane, the angle between the two engines is 60°, and the projection is parallel to + / -Z plane;

[0051] (3) 7#, 8# engines are installed on the satellite assembly-Y plane, the angle between the two engines is 60°, and the projection is parallel to + / -Z plane;

[0052] (4) 9# and 10# engines are installed on the +X face of the satellite assembly, the included angle between the two engines is 60°, and the projection is parallel to the + / -Z plane;

[0053] (5) 11# and 12# engines are installed on the -X face of the satellite assembly, the included angle between the two engines is 60°, and the projection is parallel to the + / -Z plane;

[0054] (6) 13# engine is installed on the side with an included angle of 60° with the +Y face, and the projection is parallel to the Z axis;

[0055] (7) 14# engine is installed on the side with an included angle of 60° with the -Y face, and the projection is parallel to the Z axis;

[0056] (8) 15# engine is installed on the side with an included angle of 60° with the +X face, and the projection is parallel to the Z axis;

[0057] (9) 16# engine is installed on the side with an included angle of 60° with the -X face, and the projection is parallel to the Z axis.

[0058] Among them, 1#, 2#, 3# and 4# engines are orbit control positive thrust engines (assuming thrust F1), 13#, 14#, 15# and 16# engines are orbit control negative thrust engines (assuming thrust F1), and 5# to 12# are attitude control engines (assuming thrust F2).

[0059] In the engine installation layout designed in the method of the application, for the combination of the "garbage removal satellite" and the "non-cooperative target (space garbage)", assuming that the center of mass has no XY plane offset, the thrust and torque characteristics of each engine are as follows:

[0060] Table 1 Thrust and torque characteristics of each engine

[0061]

[0062]

[0063]

[0064] In Table 1 above, L1X~L16X, L1Y~L16Y, L1Z~L16Z are the force arm coefficients of the relative relationship between the engine thrust and the center of mass of the combination, and in this case, the synthesis method of three-axis force (required for orbit control) and three-axis torque (required for attitude control) is as follows:

[0065] Table 2 Synthesis method of three-axis force and three-axis torque of the combination

[0066]

[0067] At this time, the orbit control of the satellite assembly is determined by the +Z direction thrust, which is synthesized by the 1#, 2#, 3# and 4# engines, at this time, the +Z direction thrust synthesis matrix based on the 1#, 2#, 3# and 4# engines is as follows:

[0068]

[0069] In the formula, F1 is the thrust of the 1#, 2#, 3# and 4# engines, F z is the expected synthesized +Z direction thrust, and λ1-λ4 are the engine opening ratios of the 1#, 2#, 3# and 4# engines respectively (i.e. the proportion of the working time to the total time when the engine works in an on-off mode).

[0070] (II) Orbit control thrust distribution matrix reconstruction

[0071] In another case, when the center of mass of the satellite assembly is greatly offset in the XY plane (as shown in Figure 5 ), the method needs to perform orbit control thrust distribution matrix reconstruction, specifically, +Z direction thrust synthesis matrix reconstruction based on the 1#, 2#, 3# and 4# engines, assuming that the length of each side of the -Z plane of the satellite assembly is L, and the distance of the center of mass of the satellite assembly offset to the -X and +Y directions is L dx , L dy , the algorithm is as follows:

[0072]

[0073] In the formula, F1 is the thrust of the 1#, 2#, 3# and 4# engines, F z is the expected synthesized +Z direction thrust, and λ1-λ4 are the engine opening ratios of the 1#, 2#, 3# and 4# engines respectively, and the +Z direction thrust synthesis can be realized through the thrust synthesis matrix reconstruction, in this process, no additional coupling moment is generated, and no additional fuel cost is paid.

[0074] The preferred specific embodiments and examples of the present application are described in detail above, but the present application is not limited to the above-mentioned embodiments and examples, and various changes can be made within the knowledge of those skilled in the art without departing from the concept of the present application.

Claims

1. A method of satellite constellation large center of mass offset engine layout and thrust vectoring, comprising: The method comprises: S1. installing the engine based on the layout principle of the top edge top corner, 16 engines are installed according to the layout principle of the top edge top corner, comprising: (1) 1#, 2#, 3#, 4# engines are installed on the satellite assembly-Z surface, and are installed close to the top corner, the included angle between each engine and the-Z axis is 25°, and the projection on the-Z surface is at an included angle of 45° with the X / Y axis in different directions; (2) 5#, 6# engines are installed on the satellite assembly+Y surface, the included angle between the two engines is 60°, and the projection is parallel to the + / -Z plane; (3) 7#, 8# engines are installed on the satellite assembly-Y surface, the included angle between the two engines is 60°, and the projection is parallel to the + / -Z plane; (4) 9#, 10# engines are installed on the satellite assembly+X surface, the included angle between the two engines is 60°, and the projection is parallel to the + / -Z plane; (5) 11#, 12# engines are installed on the satellite assembly-X surface, the included angle between the two engines is 60°, and the projection is parallel to the + / -Z plane; (6) 13# engine is installed close to the edge with an included angle of 60° with the +Y surface, and the projection is parallel to the Z axis; (7) 14# engine is installed close to the edge with an included angle of 60° with the-Y surface, and the projection is parallel to the Z axis; (8) 15# engine is installed close to the edge with an included angle of 60° with the +X surface, and the projection is parallel to the Z axis; (9) 16# engine is installed close to the edge with an included angle of 60° with the-X surface, and the projection is parallel to the Z axis; The 1#, 2#, 3#, 4# engines are orbit control positive thrust engines, and the 13#, 14#, 15#, 16# engines are orbit control reverse thrust engines, and the 5# to 12# are attitude control engines; S2. Perform orbit control thrust distribution matrix reconstruction; When the center of mass of the satellite assembly has no XY plane offset, the orbit control is determined by the +Z direction thrust, and the +Z direction thrust is synthesized by the 1#, 2#, 3#, 4# engines, at this time the +Z direction thrust synthesis matrix based on the 1#, 2#, 3#, 4# engines is as follows: ； In the formula, F1 is the thrust of the 1st, 2nd, 3rd, and 4th engine, the desired synthesized +Z thrust, are the engine opening ratios of the 1st, 2nd, 3rd, and 4th engine, respectively. When the center of mass of the satellite assembly is greatly offset in the XY plane, the orbit control thrust distribution matrix reconstruction in step S2 means that the +Z direction thrust synthesis matrix based on the 1#, 2#, 3#, 4# engines is reconstructed as follows: ； F1 is the thrust of the 1st, 2nd, 3rd and 4th engine, the desired resultant +Z thrust, are the engine opening ratios of the 1st, 2nd, 3rd and 4th engine respectively, L is the length of each side of the -Z face of the satellite assembly, dx L dy are the distances of the centroid of the satellite assembly from the -X and +Y directions respectively.

2. The application of the satellite assembly large center of mass offset engine layout and thrust synthesis method in claim 1 in the manufacture of space garbage removal satellites.

3. The application of the satellite assembly large center of mass offset engine layout and thrust synthesis method in claim 1 in space garbage removal operations.

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