Real-time characterization method and device for atomic oxygen inflow and windward surface considering attitude

Abstract

The present invention provides a method and device for real-time characterization of atomic oxygen inflow and windward surface considering attitude. The method comprises obtaining the spatial position, movement speed and running attitude of an aircraft at each simulation moment, and obtaining the atomic oxygen number density environment and the transverse wind environment in which the aircraft is located according to the position, speed and attitude in combination with an atomic oxygen environment model and a transverse wind environment model, and obtaining the atomic oxygen inflow speed according to the speed of the aircraft and the transverse wind speed in which the aircraft is located, thereby realizing real-time characterization of atomic oxygen on the windward surface in the space atomic oxygen environment of a spacecraft with a complex structure considering the inflow speed and the change of the aircraft's own attitude.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a method and device for real-time characterization of an atomic oxygen incoming flow and a windward surface taking attitude into consideration. Background Art

[0002] Atomic oxygen is a relatively active oxidizing substance distributed in space. Man-made spacecraft may pass through an atomic oxygen environment during their in-orbit flight. Atomic oxygen reacts with the surface material of the spacecraft, which will cause atomic oxygen corrosion reactions on the structural materials and key parts of the spacecraft, reducing the reliability of key parts such as the structure electronics of the spacecraft. When analyzing the interaction between atomic oxygen and spacecraft, the main environmental parameters involved include the energy, flux and injection of atomic oxygen, which are related to the flight speed of the spacecraft, the thermal motion speed of atomic oxygen and the flight attack angle of atomic oxygen.

[0003] In LEO space, the average thermal motion speed of gas molecules is originally very low, but due to the high-speed operation of the spacecraft, atomic oxygen hits the surface of the spacecraft with an energy of about 5eV, causing changes in the chemical and physical properties of the material. The materials used in spacecraft are mainly polymer materials. When atomic oxygen hits the surface of the material, a series of physical and chemical processes will occur. For example, atomic oxygen may simply scatter from the surface in its original charged state or change its charged state, or it may chemically react with nitrogen atoms or form excited nitric oxide when it hits the surface of the spacecraft, and then produce a glow and deactivate; or atomic oxygen may be physically adsorbed on the surface of the material, causing etching of the surface of the material; or atomic oxygen may be captured by potential wells on or under the surface to form oxides, or it may migrate from the surface to the inside of the material matrix. In short, the mechanism of action between atomic oxygen and materials is complex and is the result of the synergistic action of multiple effects, including surface material loss caused by atomic sputtering and chemical reactions that change the structure of the polymer.

[0004] In order to study the effect of atomic oxygen during the in-orbit operation of spacecraft, there are currently two main research methods, namely satellite in-orbit test research and ground experiments. In-orbit tests have defects such as high cost and many test restrictions, and it is difficult to simulate the low-Earth orbit environment. The erosion yield of the material may be affected by many factors such as atomic oxygen flux, atomic oxygen integrated flux, synergistic effect of solar rays, atomic oxygen impact energy, atomic oxygen impact angle and material temperature. Therefore, ground experiments are generally difficult to reproduce the atomic oxygen erosion rate in low-Earth orbit. Summary of the invention

[0005] The problem solved by the present invention is how to characterize the atomic oxygen environment in space so as to facilitate the study of the effects of atomic oxygen in the earth's atmosphere on a spacecraft during its on-orbit operation.

[0006] In order to solve the above problems, the present invention provides a method for real-time characterization of atomic oxygen inflow and windward surface considering attitude, comprising:

[0007] Obtain the spatial position, motion speed and running attitude of the aircraft at the current simulation moment, and obtain the control parameters of the atomic oxygen environment model and the control parameters of the lateral wind environment model;

[0008] Obtaining the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model;

[0009] Obtaining the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model;

[0010] Obtaining the atomic oxygen inflow velocity of the aircraft according to the moving velocity of the aircraft and the lateral wind velocity of the aircraft;

[0011] The simulation results of the space atomic oxygen environment during the on-orbit operation of the aircraft are analyzed based on the operating attitude of the aircraft, the atomic oxygen density of the aircraft, the lateral wind speed of the aircraft, and the atomic oxygen inflow speed of the aircraft.

[0012] In one embodiment, obtaining the spatial position and movement speed of the aircraft at the current simulation time includes:

[0013] According to the orbital parameters of the aircraft at the previous simulation time, the orbital extrapolation model is used to obtain the spatial position and movement speed of the aircraft at the current simulation time. The orbital parameters are defined using the six orbital numbers, which include the major semi-axis, eccentricity, inclination, right ascension of the ascending node, argument of perigee, and perigee angle.

[0014] In one embodiment, the spatial position and movement speed are the three-dimensional coordinates and flight speed of the aircraft in the geocentric J2000 inertial coordinate system.

[0015] In one embodiment, obtaining the current operating posture of the aircraft includes:

[0016] Define a satellite body coordinate system, the origin of the satellite body coordinate system is located at the center of mass of the aircraft, the X-axis, Y-axis, and Z-axis of the satellite body coordinate system are respectively the three principal inertia axes of the aircraft, and when the aircraft has no attitude deviation, the X-axis, Y-axis, and Z-axis of the satellite body coordinate system coincide with the X-axis, Y-axis, and Z-axis of the orbital coordinate system, the Z-axis of the orbital coordinate system points to the center of the earth, the X-axis of the orbital coordinate system coincides with the direction of movement of the aircraft, the Y-axis of the orbital coordinate system points to the negative normal direction of the orbital plane of the aircraft, and forms a right-handed rectangular coordinate system with the X-axis and Z-axis of the orbital coordinate system;

[0017] The attitude quaternion of the aircraft in the satellite body coordinate system at the current moment is obtained, and the attitude quaternion q is:

[0018]

[0019] Among them, q1, q2, q3 are vector components, q0 is a scalar component, and q1 2 +q2 2 +q3 2 +q0 2 =1, α is the angle required for the orbital coordinate system to rotate around the spatial rotation axis e to coincide with the satellite body coordinate system, wherein the direction vector of the spatial rotation axis e in the orbital coordinate system is e=(C x , C y , C z ), (C x , C y , C z ) represents direction cosines.

[0020] In one embodiment, the method for real-time characterization of the atomic oxygen inflow and the windward surface considering the attitude further includes:

[0021] Get the simulation start time, simulation end time and simulation step length in the simulation calculation;

[0022] Obtaining a simulation time range according to the simulation start time and the simulation end time;

[0023] Within the simulation time range, the simulation results of each model in the scene at each simulation moment are obtained, and the time is stepped according to the simulation step size to obtain the next simulation moment, and the simulation results of each model in the scene at each simulation moment are traversed;

[0024] In the simulation calculation, the time is expressed in Julian day, and the Julian day is calculated according to a first formula, which is:

[0025]

[0026] Among them, JD represents Julian day, INT represents rounding, Year represents year in the Gregorian calendar, Month represents month, Day represents day, Hour represents hour, Minute represents minute, and Second represents second.

[0027] In one embodiment, obtaining the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model includes:

[0028] Using the time data corresponding to the current simulation time, the spatial position of the aircraft at the current simulation time, and the control parameters of the atomic oxygen environment model as input parameters of the atomic oxygen environment model, and performing calculations according to the atomic oxygen environment model to obtain output parameters of the atomic oxygen environment model, wherein the output parameters include atomic oxygen density;

[0029] The control parameters of the atomic oxygen environment model include the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and an 8-bit array obtained based on the average geomagnetic index of the day and the 20 3-hour average geomagnetic indices before the solution time.

[0030] In one embodiment, obtaining the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model includes:

[0031] Using the time data corresponding to the current simulation time, the spatial position of the aircraft at the current simulation time, and the control parameters of the lateral wind environment model as input parameters of the lateral wind environment model, and performing calculations according to the lateral wind environment model to obtain output parameters of the lateral wind environment model, wherein the output parameters include a longitudinal wind speed and a latitudinal wind speed;

[0032] Among them, the control parameters of the lateral wind environment model include the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and an 8-bit array obtained based on the average geomagnetic index of the day and the 20 3-hour average geomagnetic indices before the solution time.

[0033] The present invention also provides a device for real-time characterization of atomic oxygen inflow and windward surface taking into account attitude, comprising:

[0034] An acquisition unit is used to acquire the spatial position, motion speed and running attitude of the aircraft at the current simulation moment, and to acquire the control parameters of the atomic oxygen environment model and the control parameters of the lateral wind environment model;

[0035] an atomic oxygen density characterization unit, used to obtain the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model;

[0036] A lateral wind environment characterization unit, used to obtain the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model;

[0037] an atomic oxygen velocity characterization unit, used to obtain the atomic oxygen incoming velocity of the aircraft according to the moving velocity of the aircraft and the lateral wind velocity of the aircraft;

[0038] The analysis unit is used to analyze the simulation results of the space atomic oxygen environment during the on-orbit operation of the aircraft according to the operating attitude of the aircraft, the atomic oxygen density of the aircraft, the lateral wind speed of the aircraft, and the atomic oxygen inflow speed of the aircraft.

[0039] The present invention also provides a computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the above-mentioned method when executing the computer program.

[0040] The present invention also provides a computer-readable storage medium having a computer program stored thereon, and when the computer program is executed by a processor, the steps of the method for real-time characterization of the atomic oxygen inflow and the windward surface taking into account the attitude are implemented.

[0041] The advantages of the method for real-time characterization of atomic oxygen inflow and windward surface considering posture of the present invention compared with the prior art are:

[0042] The present invention obtains the spatial position, movement speed and running attitude of the aircraft at each simulation moment, and obtains the atomic oxygen number density environment and the lateral wind environment of the aircraft according to the position, speed and attitude in combination with the atomic oxygen environment model and the lateral wind environment model, and obtains the atomic oxygen incoming flow velocity according to the speed of the aircraft and the lateral wind speed of the aircraft, thereby realizing the real-time characterization of the atomic oxygen on the windward side in the space atomic oxygen environment of a complex structure spacecraft taking into account the incoming flow velocity and the aircraft's own attitude changes.

[0043] The advantages of the device for real-time characterization of atomic oxygen inflow and windward surface considering posture, computer equipment, and computer-readable storage medium of the present invention over the prior art are the same as the advantages of the method for real-time characterization of atomic oxygen inflow and windward surface considering posture over the prior art, and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 This is a diagram of the application environment of the method for real-time characterization of atomic oxygen inflow and windward surface considering posture in an embodiment of the present invention;

[0045] Figure 2 A flow chart of a method for real-time characterization of atomic oxygen inflow and windward surface considering posture in an embodiment of the present invention;

[0046] Figure 3 Schematic diagram of the J2000 inertial coordinate system and the satellite body coordinate system in an embodiment of the present invention;

[0047] Figure 4 Schematic diagram of quaternion posture change in an embodiment of the present invention;

[0048] Figure 5is a simulation calculation flow chart in an embodiment of the present invention;

[0049] Figure 6 The step-by-step changes of the aircraft attitude quaternion with the simulation time in the embodiment of the present invention;

[0050] Figure 7 The figure shows the step-by-step changes of the velocity of the incoming atomic oxygen flow and the longitude and latitude components of the space position of the aircraft with the simulation time in the embodiment of the present invention;

[0051] Figure 8 Schematic diagram of a device for real-time characterization of atomic oxygen inflow and windward surface taking attitude into consideration in an embodiment of the present invention. DETAILED DESCRIPTION

[0052] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0053] Figure 1 This is an application environment diagram of the method for real-time characterization of atomic oxygen inflow and windward surface considering posture in an embodiment of the present invention. Figure 1 The method for real-time characterization of atomic oxygen inflow and windward surface considering attitude is applied to a real-time characterization system for atomic oxygen inflow and windward surface considering attitude. The characterization system includes a terminal 110 and a server 120. The terminal 110 and the server 120 are connected via a network. The terminal 110 can be a desktop terminal or a mobile terminal, and the mobile terminal can be at least one of a mobile phone, a tablet computer, a laptop computer, etc. The server 120 can be implemented by an independent server or a server cluster consisting of multiple servers.

[0054] The calculation of the atomic oxygen effect on the surface of a complex spacecraft is usually complicated. In addition to considering the structure of the spacecraft itself, it is also necessary to obtain the spatial position, velocity, attitude state and atomic oxygen environment of the spacecraft in real-time on-orbit motion, as well as the incoming velocity vector of atomic oxygen. In order to be able to solve the above-mentioned real-time state quantities, an embodiment of the present invention provides a real-time simulation characterization method for the windward side that can simultaneously consider the attitude and the atomic oxygen environment of the earth during the on-orbit operation of a complex spacecraft, so as to facilitate the study of the interaction between the on-orbit spacecraft and the atomic oxygen environment of the earth's atmosphere. Please refer to Figure 2 As shown, this embodiment provides a method for real-time characterization of atomic oxygen inflow and windward surface considering attitude, including:

[0055] Step 210, obtaining the spatial position, motion speed and running attitude of the aircraft at the current simulation time, and obtaining the control parameters of the atomic oxygen environment model and the control parameters of the lateral wind environment model;

[0056] Step 221, obtaining the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model;

[0057] Step 222, obtaining the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model;

[0058] Step 223, obtaining the atomic oxygen inflow velocity of the aircraft according to the moving velocity of the aircraft and the lateral wind velocity of the aircraft;

[0059] Step 230, analyzing the simulation results of the space atomic oxygen environment during the on-orbit operation of the aircraft according to the operating attitude of the aircraft, the atomic oxygen density of the aircraft, the lateral wind speed of the aircraft, and the atomic oxygen inflow speed of the aircraft.

[0060] In order to solve the problem of solving the incoming flow on the windward side encountered in the simulation calculation of the atomic oxygen effect during the operation of the orbiting spacecraft, the embodiment of the present invention first considers several factors that need to be provided when solving the atomic oxygen effect on the asymmetric structure of the spacecraft surface during the space operation, including the atomic oxygen concentration of the spacecraft's spatial position, the atomic oxygen relative velocity vector to which the spacecraft is subjected, and the attitude of the spacecraft in space. Therefore, this embodiment needs to obtain the spatial position, movement speed and running attitude of the aircraft at each simulation moment, and according to the position, speed and attitude of the aircraft, in combination with the atomic oxygen environment model and the transverse wind environment model, obtain the atomic oxygen number density environment and the transverse wind environment in which the aircraft is located, and according to the speed of the aircraft and the transverse wind speed in which the aircraft is located, obtain the atomic oxygen incoming flow velocity, thereby realizing the real-time characterization of the atomic oxygen on the windward side in the space atomic oxygen environment of the complex structure spacecraft considering the incoming flow velocity and the change of the aircraft's own attitude.

[0061] In some of the implementation modes, in step 210, obtaining the spatial position and movement speed of the aircraft at the current simulation moment includes: obtaining the spatial position and movement speed of the aircraft at the current simulation moment using an orbital extrapolation model based on the orbital parameters of the aircraft at the previous simulation moment, wherein the orbital parameters are defined using six orbital numbers, and the six orbital numbers include semi-major axis, eccentricity, inclination, right ascension of ascending node, argument of perigee, and perigee angle.

[0062] In this embodiment, the descriptions of the spatial position, attitude and movement speed used in this embodiment are all based on the geocentric J2000 inertial coordinate system. Therefore, the spatial position and movement speed are the three-dimensional coordinates and flight speed of the aircraft in the geocentric J2000 inertial coordinate system. The geocentric inertial coordinate system uses the celestial equator and the equinox at J2000 (12:00 on January 1, 2000) to define the celestial reference coordinate system. See Figure 3 As shown, the origin of the J2000 coordinate system coincides with the center of mass of the earth, the X-axis points to the mean equinox at J2000, the Z-axis points to the North Pole, and the Y-axis, X-axis and Z-axis form a right-handed rectangular coordinate system, which is an inertial coordinate system.

[0063] The orbit extrapolation model in this embodiment adopts the HPOP orbit calculation model. The HPOP orbit calculation model (The High-precision orbit propagator) is a high-precision orbit prediction model that can be used to process any circular, elliptical, parabolic and hyperbolic orbits with orbital altitudes from the earth's surface to the moon's surface or even farther. The model is embedded with the JGM-3 (70*70) earth gravity model, solid tide, ocean tide model, atmospheric resistance model, solar light pressure model, sun and moon gravitational field model, and can accurately simulate the orbit state of the satellite.

[0064] In some implementation modes, in step 210, obtaining the current operating attitude of the aircraft includes: defining a satellite body coordinate system, and obtaining the attitude quaternion of the aircraft in the satellite body coordinate system at the current moment, wherein the attitude quaternion q is:

[0065]

[0066] Among them, q1, q2, q3 are vector components, q0 is a scalar component, and q1 2 +q2 2 +q3 2 +q0 2 =1, α is the angle required for the orbital coordinate system to rotate around the spatial rotation axis e to coincide with the satellite body coordinate system, wherein the direction vector of the spatial rotation axis e in the orbital coordinate system is e=(C x , C y , C z ), (C x , C y , C z ) represents direction cosines.

[0067] In an embodiment of the present invention, in order to describe the attitude change of the satellite body, a satellite body coordinate system is first defined, the origin of the satellite body coordinate system is located at the center of mass of the aircraft, the X-axis, Y-axis, and Z-axis of the satellite body coordinate system are respectively the three principal inertia axes of the aircraft, and in the absence of attitude deviation, the three coordinate axes of the satellite body coordinate system, the X-axis, the Y-axis, and the Z-axis, coincide with the orbital coordinate system, that is, at this time, the Z-axis of the satellite points to the center of the earth, the X-axis coincides with the direction of movement of the aircraft, and the Y-axis points to the negative normal direction of the orbital plane of the aircraft, and forms a right-handed rectangular coordinate system with the X-axis and the Z-axis.

[0068] The posture description method involved in the embodiment of the present invention uses the quaternion posture description method because the Euler angle description method has a singularity problem, that is, there are two sets of Euler angle data describing the same posture state. Therefore, this embodiment uses the quaternion posture description method.

[0069] Quaternion consists of two parts: scalar and vector, in the form of:

[0070] q=q0+q1i+q2j+q3k=[q s ,q v ];

[0071] Among them, q s represents the scalar part, with unit of 1; and q s =q0;q v represents the vector part, i, j, k are imaginary units. i, j, k can be understood as unit vectors that are orthogonal to each other.

[0072] The geometric description of quaternion is that the direction vector of a certain rotation axis e in the orbital coordinate system is: e = (C x ,C y ,C z ), where C x ,C y ,C z represents direction cosines, orbital coordinate system O O X O Y O Z O Rotate α around e to get the body coordinate system O b X b Y b Z b ,like Figure 4 As shown. Thus, the attitude quaternion q of the above satellite is obtained.

[0073] In some of the embodiments, the method for real-time characterization of the atomic oxygen inflow and the windward surface considering the attitude further comprises:

[0074] Get the simulation start time, simulation end time and simulation step length in the simulation calculation;

[0075] Obtaining a simulation time range according to the simulation start time and the simulation end time;

[0076] Within the simulation time range, the simulation results of each model in the scene at each simulation moment are obtained, and the time is stepped according to the simulation step size to obtain the next simulation moment, and the simulation results of each model in the scene at each simulation moment are traversed.

[0077] In the simulation calculation, the time is expressed in Julian day, and the Julian day is calculated according to a first formula, which is:

[0078]

[0079] Among them, JD represents Julian day, INT represents rounding, Year represents year in the Gregorian calendar, Month represents month, Day represents day, Hour represents hour, Minute represents minute, and Second represents second.

[0080] In this embodiment, the simulation start time is taken as the first simulation moment, the Julian day time representation model is used in the internal simulation calculation, the Gregorian calendar time is converted into a continuous real number to represent the time, the simulation step is converted into the Julian time unit, and the simulation step is accumulated one by one at the task start time to step the time and obtain each simulation moment in turn.

[0081] In some implementation modes, in step 221, obtaining the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model includes:

[0082] Using the time data corresponding to the current simulation time, the spatial position of the aircraft at the current simulation time, and the control parameters of the atomic oxygen environment model as input parameters of the atomic oxygen environment model, and performing calculations according to the atomic oxygen environment model to obtain output parameters of the atomic oxygen environment model, wherein the output parameters include atomic oxygen density;

[0083] Among them, the control parameters of the atomic oxygen environment model include the solar 10.7cm radiation flux (F107 value) of the previous day, the average solar 10.7cm radiation flux (F107A value) of 81 days, and an 8-bit array obtained based on the average geomagnetic index of the day (AP value) and the 20 3-hour average geomagnetic indices before the solution time.

[0084] In this embodiment, the simulation of the atomic oxygen environment uses the NRLMSISE-00 model. Through the internal interface of the program, the time data corresponding to the simulation moment, the spatial position data of the aircraft at that moment, and the model control parameter data set by the user are used as input parameters of the model. The model is used for calculation, and finally the spatial atmospheric environment data of the current aircraft is obtained, including the total mass density of the atmosphere, the atmospheric temperature, and the particle number density of the main components of the atmosphere, including the atomic oxygen number density, which is the simulation result data required to be obtained in this embodiment.

[0085] In some of the implementation modes, in step 222, obtaining the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model includes:

[0086] Using the time data corresponding to the current simulation time, the spatial position of the aircraft at the current simulation time, and the control parameters of the lateral wind environment model as input parameters of the lateral wind environment model, and performing calculations according to the lateral wind environment model to obtain output parameters of the lateral wind environment model, wherein the output parameters include a longitudinal wind speed and a latitudinal wind speed;

[0087] Among them, the control parameters of the lateral wind environment model include the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and an 8-bit array obtained based on the average geomagnetic index of the day and the 20 3-hour average geomagnetic indices before the solution time.

[0088] In this embodiment, the simulation of the lateral wind environment uses the HWM93 model, which is similar to the atomic oxygen environment. The time data corresponding to the simulation moment, the spatial position data of the aircraft at that moment, and the model control parameter data set by the user are used as input parameters of the model through the internal interface of the program. The model is used for calculation, and finally the longitudinal wind speed and latitudinal wind speed in the space where the current aircraft is located are obtained.

[0089] In some implementation modes, in step 223, the incoming atomic oxygen velocity of the aircraft at the current simulation moment can be obtained by solving the sum of the moving velocity of the aircraft and the lateral wind velocity.

[0090] In some of the embodiments, the method for real-time characterization of the atomic oxygen inflow and the windward surface considering the attitude further includes initializing various initial data in the simulation scene, specifically including:

[0091] Initialize the simulation start time and simulation end time. These two initialization data constrain the simulation time range in this embodiment. Coordinated Universal Time is used as the time definition. The user setting interface is the Gregorian calendar year, month, day, hour, minute, and second.

[0092] Initialize the simulation step length in seconds. After the simulation starts, calculate the simulation result data of each model in the scene at each simulation moment from the simulation start time, then step the time according to the simulation step length to get the next simulation moment, and traverse the simulation results of the scene model at each simulation moment one by one until the simulation moment reaches or just exceeds the simulation end time;

[0093] Initialize satellite orbit parameters. The definition of satellite orbit mission is defined by six orbit elements: 1) Semi-major axis, a, describes the size of the orbit. 2) Eccentricity, e, describes the shape of the orbit. 3) Inclination, i, describes the inclination angle of the orbital plane relative to the equatorial plane. 4) Ascending node right ascension, Ω, describes the position of the ascending node relative to the vernal equinox. 5) Argument of perigee, ω, describes the position of the perigee relative to the ascending node. 6) True anomaly, f, describes the position of the satellite relative to the perigee.

[0094] Initialize the satellite attitude quaternion. In this embodiment, quaternion is used to express the satellite attitude;

[0095] Initialize the space atmosphere model parameters. This embodiment uses the NRLMSISE-00 Earth upper atmosphere model. Three model control parameters that need to be initialized in the model are AP value, F107 value, and F107A value;

[0096] Initialize the earth's lateral wind model. This embodiment uses the HWM93 model. Three model control parameters that need to be initialized in the model are AP value, F107 value, and F107A value.

[0097] The present invention is further described below in conjunction with specific embodiments.

[0098] The task start time is 12:0:00 on January 1, 2017, and the simulation step length is 20 seconds.

[0099] In this embodiment, the spacecraft attitude and orbit parameters are initialized in the spacecraft mission. The six numbers of the spacecraft's initial orbit are: apogee 500km, perigee 500km, inclination 60 degrees, right ascension of ascending node 0 degrees, argument of perigee 0 degrees, and perigee angle 0 degrees.

[0100] like Figure 5 As shown in FIG. 1 , the simulation calculation process of this embodiment is firstly initialized, and then the calculation is started from the simulation moment corresponding to the mission start time. At each simulation moment, based on the result of the previous moment, the HPOP orbit calculation model is used to obtain the spatial position and motion speed at the current simulation moment, and the attitude quaternion is used to describe and output the current spatial operation attitude of the satellite. Figure 6 The figure shows the change of the aircraft attitude quaternion with the step of simulation time. Since the quaternion is a dimensionless number, it has no unit but only value. Figure 6 Here, QUAT_ORB1, i.e. quaternion 1, represents the scalar component value in the quaternion, QUAT_ORB2, i.e. quaternion 2, QUAT_ORB3, i.e. quaternion 3, and QUAT_ORB4, i.e. quaternion 4, correspond to the x, y, and z values ​​of the vector components in the quaternion, respectively.

[0101] In the simulation of atomic oxygen environment, the NRLMSISE-00 model is used for calculation. In the simulation of crosswind environment, the HWM93 model is used for calculation. The atomic oxygen inflow velocity of the aircraft at the current simulation moment is obtained by solving the sum of the aircraft's motion velocity and the crosswind velocity. Figure 7 It represents the magnitude of the incoming flow velocity and the earth's longitude and latitude components of the aircraft's spatial position as the simulation time progresses.

[0102] Finally, determine whether the current simulation time is equal to or greater than the task end time. If so, terminate the simulation. Otherwise, step the time according to the simulation step size to obtain the next simulation time and solve the simulation again.

[0103] Corresponding to the above-mentioned method for real-time characterization of atomic oxygen inflow and windward surface considering posture, an embodiment of the present invention further provides a device for real-time characterization of atomic oxygen inflow and windward surface considering posture, such as Figure 8 As shown, the device comprises:

[0104] The acquisition unit 810 is used to acquire the spatial position, motion speed and running attitude of the aircraft at the current simulation time, and acquire the control parameters of the atomic oxygen environment model and the control parameters of the lateral wind environment model;

[0105] An atomic oxygen density characterization unit 820, configured to obtain the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model;

[0106] A lateral wind environment characterization unit 830, configured to obtain the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model;

[0107] The atomic oxygen velocity characterization unit 840 is used to obtain the atomic oxygen flow velocity of the aircraft according to the movement velocity of the aircraft and the lateral wind velocity of the aircraft;

[0108] The analysis unit 850 is used to analyze the simulation results of the space atomic oxygen environment during the on-orbit operation of the aircraft according to the operating attitude of the aircraft, the atomic oxygen density of the aircraft, the lateral wind speed of the aircraft, and the atomic oxygen inflow speed of the aircraft.

[0109] The acquisition unit 810 acquires the spatial position of the aircraft at the current moment by using an orbital extrapolation model to obtain the spatial position and movement speed of the aircraft at the current simulation moment according to the orbital parameters of the aircraft at the previous simulation moment, wherein the orbital parameters are defined using six orbital numbers.

[0110] The acquisition unit 810 acquires the current operating attitude of the aircraft, including: defining a satellite body coordinate system, and acquiring the attitude quaternion of the aircraft in the satellite body coordinate system at the current moment, wherein the attitude quaternion q is:

[0111]

[0112] Among them, q1, q2, q3 are vector components, q0 is a scalar component, and q1 2 +q2 2 +q3 2+q0 2 =1, α is the angle required for the orbital coordinate system to rotate around the spatial rotation axis e to coincide with the satellite body coordinate system, wherein the direction vector of the spatial rotation axis e in the orbital coordinate system is e=(C x , C y , C z ), (C x , C y , C z ) represents direction cosines.

[0113] In some implementations, the acquisition unit 810 is further used to acquire control parameters of the atomic oxygen environment model;

[0114] The atomic oxygen density characterization unit is used to obtain the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model, wherein the control parameters of the atomic oxygen environment model include the solar 10.7cm radiation flux (F107 value) of the previous day, the average solar 10.7cm radiation flux (F107A value) of 81 days, and an 8-bit array obtained according to the average geomagnetic index (AP value) of the day and the 20 3-hour average geomagnetic indices before the solution time.

[0115] In some implementations, the acquisition unit 810 is further used to acquire control parameters of the lateral wind environment model;

[0116] The lateral wind environment characterization unit is used to obtain the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model, wherein the control parameters of the lateral wind environment model include the solar 10.7cm radiation flux (F107 value) of the previous day, the average solar 10.7cm radiation flux (F107A value) of 81 days, and an 8-bit array obtained based on the average geomagnetic index of the day (AP value) and the 20 3-hour average geomagnetic indices before the solution time.

[0117] In one embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the following steps when executing the computer program:

[0118] Obtain the spatial position, motion speed and running attitude of the aircraft at the current simulation moment, and obtain the control parameters of the atomic oxygen environment model and the control parameters of the lateral wind environment model;

[0119] Obtaining the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model;

[0120] Obtaining the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model;

[0121] Obtaining the atomic oxygen inflow velocity of the aircraft according to the moving velocity of the aircraft and the lateral wind velocity of the aircraft;

[0122] The simulation results of the space atomic oxygen environment during the on-orbit operation of the aircraft are analyzed based on the operating attitude of the aircraft, the atomic oxygen density of the aircraft, the lateral wind speed of the aircraft, and the atomic oxygen inflow speed of the aircraft.

[0123] In one embodiment, a computer readable storage medium is provided, on which a computer program is stored, and when the computer program is executed by a processor, the following steps are implemented:

[0124] Obtain the spatial position, motion speed and running attitude of the aircraft at the current simulation moment, and obtain the control parameters of the atomic oxygen environment model and the control parameters of the lateral wind environment model;

[0125] Obtaining the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model;

[0126] Obtaining the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model;

[0127] Obtaining the atomic oxygen inflow velocity of the aircraft according to the moving velocity of the aircraft and the lateral wind velocity of the aircraft;

[0128] The simulation results of the space atomic oxygen environment during the on-orbit operation of the aircraft are analyzed based on the operating attitude of the aircraft, the atomic oxygen density of the aircraft, the lateral wind speed of the aircraft, and the atomic oxygen inflow speed of the aircraft.

[0129] In one embodiment, when the computer program is executed by the processor, the steps of the above-mentioned method for real-time characterization of the atomic oxygen inflow and the windward surface considering the attitude are also implemented.

[0130] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be completed by instructing the relevant hardware through a computer program, and the program can be stored in a non-volatile computer-readable storage medium. When the program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided by the present invention can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0131] Although the disclosure is disclosed as above, the protection scope of the disclosure is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the disclosure, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A method for real-time characterization of atomic oxygen inflow and windward surface considering attitude, characterized in that: include: Obtain the spatial position, motion speed and running attitude of the aircraft at the current simulation moment, and obtain the control parameters of the atomic oxygen environment model and the control parameters of the lateral wind environment model; Obtaining the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model; Obtaining the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model; Obtaining the atomic oxygen inflow velocity of the aircraft according to the moving velocity of the aircraft and the lateral wind velocity of the aircraft; The simulation results of the space atomic oxygen environment during the on-orbit operation of the aircraft are analyzed based on the operating attitude of the aircraft, the atomic oxygen density of the aircraft, the lateral wind speed of the aircraft, and the atomic oxygen inflow speed of the aircraft.

2. The method for real-time characterization of atomic oxygen inflow and windward surface considering attitude according to claim 1, characterized in that: The acquisition of the spatial position and movement speed of the aircraft at the current simulation time includes: According to the orbital parameters of the aircraft at the previous simulation time, the orbital extrapolation model is used to obtain the spatial position and movement speed of the aircraft at the current simulation time. The orbital parameters are defined using the six orbital numbers, which include the major semi-axis, eccentricity, inclination, right ascension of the ascending node, argument of perigee, and perigee angle.

3. The method for real-time characterization of atomic oxygen inflow and windward surface considering attitude according to claim 2, characterized in that: The spatial position and movement speed are the three-dimensional coordinates and flight speed of the aircraft in the geocentric J2000 inertial coordinate system.

4. The method for real-time characterization of atomic oxygen inflow and windward surface considering attitude according to claim 1, characterized in that: The acquisition of the operating attitude of the aircraft at the current simulation time includes: Define a satellite body coordinate system, the origin of the satellite body coordinate system is located at the center of mass of the aircraft, the X-axis, Y-axis, and Z-axis of the satellite body coordinate system are respectively the three principal inertia axes of the aircraft, and when the aircraft has no attitude deviation, the X-axis, Y-axis, and Z-axis of the satellite body coordinate system coincide with the X-axis, Y-axis, and Z-axis of the orbital coordinate system, the Z-axis of the orbital coordinate system points to the center of the earth, the X-axis of the orbital coordinate system coincides with the direction of movement of the aircraft, the Y-axis of the orbital coordinate system points to the negative normal direction of the orbital plane of the aircraft, and forms a right-handed rectangular coordinate system with the X-axis and Z-axis of the orbital coordinate system; The attitude quaternion of the aircraft in the satellite body coordinate system at the current moment is obtained, and the attitude quaternion q is: Among them, q1, q2, q3 are vector components, q v represents the vector part, q0 is the scalar component, and q1 2 +q2 2 +q3 2 +q0 2 =1, α is the angle required for the orbital coordinate system to rotate around the spatial rotation axis e to coincide with the satellite body coordinate system, wherein the direction vector of the spatial rotation axis e in the orbital coordinate system is e=(C x , C y , C x ), (C x , C y , C z ) represents direction cosines.

5. The method for real-time characterization of atomic oxygen inflow and windward surface considering attitude according to claim 1, characterized in that: The method further comprises: Get the simulation start time, simulation end time and simulation step length in the simulation calculation; Obtaining a simulation time range according to the simulation start time and the simulation end time; Within the simulation time range, the simulation results of each model in the scene at each simulation moment are obtained, and the time is stepped according to the simulation step size to obtain the next simulation moment, and the simulation results of each model in the scene at each simulation moment are traversed; In the simulation calculation, the time is expressed in Julian day, and the Julian day is calculated according to a first formula, which is: Among them, JD represents Julian day, INT represents rounding, Year represents year in the Gregorian calendar, Month represents month, Day represents day, Hour represents hour, Minute represents minute, and Second represents second.

6. The method for real-time characterization of atomic oxygen inflow and windward surface considering attitude according to claim 1, characterized in that: The obtaining, according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model, the atomic oxygen density of the aircraft comprises: Using the time data corresponding to the current simulation time, the spatial position of the aircraft at the current simulation time, and the control parameters of the atomic oxygen environment model as input parameters of the atomic oxygen environment model, and performing calculations according to the atomic oxygen environment model to obtain output parameters of the atomic oxygen environment model, wherein the output parameters include atomic oxygen density; The control parameters of the atomic oxygen environment model include the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and an 8-bit array obtained based on the average geomagnetic index of the day and the 20 3-hour average geomagnetic indices before the solution time.

7. The method for real-time characterization of atomic oxygen inflow and windward surface considering attitude according to claim 1, characterized in that: The obtaining, according to the spatial position of the aircraft and the control parameters of the lateral wind environment model, the lateral wind speed of the aircraft comprises: Using the time data corresponding to the current simulation time, the spatial position of the aircraft at the current simulation time, and the control parameters of the lateral wind environment model as input parameters of the lateral wind environment model, and performing calculations according to the lateral wind environment model to obtain output parameters of the lateral wind environment model, wherein the output parameters include a longitudinal wind speed and a latitudinal wind speed; Among them, the control parameters of the lateral wind environment model include the solar 10.7cm radiation flux of the previous day, the average solar 10.7cm radiation flux of 81 days, and an 8-bit array obtained based on the average geomagnetic index of the day and the 20 3-hour average geomagnetic indices before the solution time.

8. A device for real-time characterization of atomic oxygen inflow and windward surface taking into account attitude, characterized in that: include: An acquisition unit is used to acquire the spatial position, motion speed and running attitude of the aircraft at the current simulation moment, and to acquire the control parameters of the atomic oxygen environment model and the control parameters of the lateral wind environment model; an atomic oxygen density characterization unit, used to obtain the atomic oxygen density of the aircraft according to the spatial position of the aircraft and the control parameters of the atomic oxygen environment model; A lateral wind environment characterization unit, used to obtain the lateral wind speed of the aircraft according to the spatial position of the aircraft and the control parameters of the lateral wind environment model; an atomic oxygen velocity characterization unit, used to obtain the atomic oxygen incoming velocity of the aircraft according to the moving velocity of the aircraft and the lateral wind velocity of the aircraft; The analysis unit is used to analyze the simulation results of the space atomic oxygen environment during the on-orbit operation of the aircraft according to the operating attitude of the aircraft, the atomic oxygen density of the aircraft, the lateral wind speed of the aircraft, and the atomic oxygen inflow speed of the aircraft.

9. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method for real-time characterization of atomic oxygen inflow and windward surface considering attitude according to any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method for real-time characterization of atomic oxygen inflow and windward surface considering attitude according to any one of claims 1 to 7 are implemented.

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