A target observation task planning method of a rotary scanning imaging remote sensing satellite

Abstract

This invention relates to a target observation mission planning method for rotating scanning imaging remote sensing satellites. Specifically, it focuses on mission planning methods for satellites with rotating Earth imaging payloads. A method for calculating imaging on / off times is proposed, which involves first determining the azimuth angle, then the elevation phase angle. Considering that the time corresponding to different lateral swing angles in each strip of the rotating payload is different, and that the elevation angle of the line connecting the satellite and the target is strongly correlated with the azimuth angle of the target, this invention simplifies the rotating imaging model. First, the imaging strips are screened using the azimuth angle, and then a second screening is performed using the elevation phase angle, ultimately obtaining all strips suitable for imaging the target.

Description

Technical Field

[0001] This invention relates to the field of satellite target observation planning technology, and is a method for planning target observation missions for rotating scanning imaging remote sensing satellites. Background Technology

[0002] Traditional remote sensing satellite imaging methods can be broadly categorized into two types: passive pushbroom and active pushbroom. In passive pushbroom mode, the satellite's optical axis is fixed and does not maneuver; therefore, it's necessary to calculate whether the bands formed during the satellite's pushbroom process cover the target point. In active pushbroom mode, the satellite's optical axis can rotate, requiring the calculation of the visible time window based on the maximum rotation angle. However, the rotating payload remote sensing satellite imaging mode differs from both of these modes, therefore its visibility calculation method cannot follow the methods used for the aforementioned imaging modes. The innovation of the rotating payload remote sensing satellite visibility calculation method is specifically reflected in the following imaging characteristics: (1) Unlike passive pushbroom imaging satellites, the optical axis of a rotating payload remote sensing satellite continuously rotates around the x-axis of its own system. (2) Unlike active imaging satellites, the optical axis of a rotating payload remote sensing satellite cannot be actively adjusted. (3) Passive pushbroom imaging satellites have only one fixed imaging time for the target during a single pass, and the payload power-on and power-off time is fixed; active pushbroom imaging satellites have a longer visible window for the target during a single pass, and the payload power-on and power-off time can be adjusted arbitrarily within the window; rotating payload remote sensing satellites can have multiple imaging windows during each pass, but the power-on and power-off time of each imaging window is fixed.

[0003] Technical background and limitations of existing technologies: In the field of remote sensing satellites, the imaging performance of a payload is directly related to the accuracy of mission planning. Traditional passive pushbroom satellites are limited by fixed observation geometry, and have limited opportunities to access specific targets during a single pass, making it difficult to meet the requirements of high-timeliness observation. While active pushbroom satellites increase flexibility in side-swing and pitch directions, their control systems are complex, and frequent attitude maneuvers consume a lot of energy, shortening the satellite's lifespan.

[0004] In contrast, rotating payload remote sensing satellites achieve ultra-wide swath scanning through the continuous rotation of the payload itself, balancing observation range with platform stability. However, this highly dynamic imaging method presents significant challenges to mission planning: its instantaneous field of view changes rapidly with rotational angular velocity, resulting in complex spiral or overlapping stripe patterns on the ground. Existing window calculation methods based on static geometry or simple envelopes cannot accurately describe the dynamic pointing of the rotating payload within extremely short imaging times (on the order of seconds), easily leading to image stripe shifts or missed targets. Therefore, establishing a time window calculation model that balances computational efficiency and pointing accuracy while adapting to rotational characteristics is crucial to improving the success rate of this rotating payload remote sensing satellite mission. Summary of the Invention

[0005] This invention addresses the problems of high computational complexity, low pointing accuracy, and easy target omission in existing rotating payload satellite mission planning, and discloses a target observation mission planning method for rotating scanning imaging remote sensing satellites.

[0006] This invention provides the following technical solutions: A method for planning target observation missions on a rotating scanning imaging remote sensing satellite, the method comprising the following steps: Step 1: Start timing from the beginning of the imaging scene, and take the moment when the satellite's optical axis points to the nadir point as the midpoint of the corresponding strip, and record the position and velocity of the satellite in the WGS_84 geocentric-earth-fixed system at the midpoint of each strip; Step 2: Convert the latitude and longitude of the target point to coordinates in the WGS_84 geocentric coordinate system; Step 3: Calculate whether the satellite and the target point are blocked by the Earth at the midpoint of each strip, and filter out all strips that are not blocked by the Earth; Step 4: For strips that are not obscured by the Earth, calculate the azimuth angle of the line connecting the satellite and the target point at the midpoint of the strip, determine whether it meets the azimuth field of view constraint, and filter out strips that meet the azimuth angle constraint. Step 5: For strips that satisfy the azimuth constraint, calculate the actual imaging time when the optical axis points to the target point based on the midpoint time of the strip and the optical axis rotation angular velocity. Then calculate the elevation phase angle corresponding to the line connecting the satellite and the target point at that time, determine whether it satisfies the elevation field of view constraint, filter out all visible strips and record the corresponding actual imaging time. Step 6: Calculate the load switching time corresponding to the visible strip based on the shortest duration of a single power-on / off cycle of the rotating load and the actual imaging time. If the power-on / off time exceeds the imaging range, make corrections.

[0007] Preferably, the initial UTC time is T0; the initial position and velocity of the satellite in the WGS_84 geocentric Earth-fixed system are... Initial satellite optical axis azimuth angle ; angular velocity of the optical axis about the x-axis of this system Pitch-to-image field of view Lateral tilt imaging field of view Target point latitude and longitude .

[0008] Preferably, the midpoint time of all stripes is determined: Starting moment of the scene The timing is as follows: the moment when the satellite's optical axis points to the nadir point is:

[0009] Among them, each time the optical axis points to the sub-star point At that time, the satellite's position and velocity in the Earth-fixed system .

[0010] Preferably, the latitude and longitude of the target point are... Convert to Earth-centered and Earth-fixed coordinate system ; Calculate the Earth's occlusion conditions and the midpoint of each strip. Record whether the satellite and target are obstructed by the Earth, and record all stripes that are not obstructed by the Earth.

[0011] Preferably, the azimuth constraints between the midpoint of all strips and the target point are determined: When the target point is with the If a band is not obstructed by the Earth, then continue calculating the intermediate time of that band. Satellite position and velocity in the Earth-fixed system The azimuth angle corresponding to the line connecting the strips And determine the azimuth. Does it satisfy the azimuth field of view constraint?

[0012] If azimuth angle If the above inequality constraints are satisfied, then record all stripes that currently satisfy the azimuth constraint.

[0013] Preferably, the pitch phase angle constraint between the strip and the target point is determined: When strip If the target is not obstructed by Earth and the azimuth constraint is satisfied, then the stripe is calculated. The pitch phase angle of the target point is used to calculate the optical axis azimuth angle. The time corresponding to the time is the actual imaging time. :

[0014] calculate Time satellite in Pitch phase angle along the target line Determine the bands Pitch phase angle of the line connecting the target Does the pitch field of view constraint satisfy: .

[0015] Preferably, when the pitch phase angle is... If the pitch field of view constraint is satisfied, then all stripes that currently satisfy the azimuth constraint are recorded as all visible stripes. And record the actual imaging time of the target point. .

[0016] Preferably, the actual power-on and power-off time is calculated, and the minimum duration of a single power-on / off cycle for the rotating load is set as follows: For point target imaging scenarios, the actual on / off time of the payload is calculated as follows:

[0017]

[0018] If the power-on / off time exceeds the imaging range, correction is required. The specific method is as follows:

[0019] Calculate the set of visible stripes sequentially In the middle, the load imaging on / off time of all visible stripes.

[0020] A computer-readable storage medium having a computer program stored thereon, which is executed by a processor to implement a target observation mission planning method for a rotating scanning imaging remote sensing satellite.

[0021] A computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program to implement a target observation mission planning method for a rotating scanning imaging remote sensing satellite.

[0022] The present invention has the following beneficial effects: This invention focuses on mission planning methods for satellites with rotating Earth imaging payloads. It proposes a method for calculating imaging on / off times that first determines the azimuth angle, then the elevation phase angle. Considering that the timing corresponds to different side-swing angles in each strip of the rotating payload, and that the elevation angle of the line connecting the satellite and the target is strongly correlated with the azimuth angle of the target, this invention simplifies the rotating imaging model. First, the imaging strips are screened using the azimuth angle, and then a second screening is performed using the elevation phase angle, ultimately obtaining all strips suitable for imaging the target.

[0023] The calculation method proposed in this invention shows significant advantages in practical applications: First, computational efficiency is significantly improved. Compared to traditional numerical integration methods, the computational complexity of this method is greatly reduced.

[0024] Secondly, by employing a two-stage filtering logic of "azimuth first, then elevation," pointing accuracy was ensured, a large number of invalid stripes were eliminated, and pointing errors were kept within the field of view, thus ensuring the success rate of rotational imaging capture.

[0025] Third, this method does not rely on high-performance spaceborne computers and can be widely applied to low-cost micro- and nano-satellite constellations, demonstrating strong engineering applicability. With the construction of my country's large-scale rotating payload remote sensing constellation, this algorithm can effectively solve emergency mission response problems and has extremely high engineering application value in fields such as disaster prevention and mitigation, marine monitoring, and tracking of key targets. Attached Figure Description

[0026] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram showing the imaging angle constraint of a point target by a remote sensing satellite with a rotating payload. Figure 2 The diagram shows a remote sensing satellite image strip with a rotating payload. Figure 3 This is displayed as a calculation process for planning a remote sensing satellite mission with a rotating payload. Detailed Implementation

[0028] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] The present invention will be described in detail below with reference to specific embodiments. Specific Implementation Example 1: according to Figures 1 to 3 As shown, the specific optimized technical solution adopted by the present invention to solve the above-mentioned technical problems is: The present invention relates to a target observation mission planning method for a rotating scanning imaging remote sensing satellite.

[0031] This invention provides a target observation mission planning method for a rotating scanning imaging remote sensing satellite, the method comprising the following steps: Step 1: Start timing from the beginning of the imaging scene, and take the moment when the satellite's optical axis points to the nadir point as the midpoint of the corresponding strip, and record the position and velocity of the satellite in the WGS_84 geocentric-earth-fixed system at the midpoint of each strip; Step 2: Convert the latitude and longitude of the target point to coordinates in the WGS_84 geocentric coordinate system; Step 3: Calculate whether the satellite and the target point are blocked by the Earth at the midpoint of each strip, and filter out all strips that are not blocked by the Earth; Step 4: For strips that are not obscured by the Earth, calculate the azimuth angle of the line connecting the satellite and the target point at the midpoint of the strip, determine whether it meets the azimuth field of view constraint, and filter out strips that meet the azimuth angle constraint. Step 5: For strips that satisfy the azimuth constraint, calculate the actual imaging time when the optical axis points to the target point based on the midpoint time of the strip and the optical axis rotation angular velocity. Then calculate the elevation phase angle corresponding to the line connecting the satellite and the target point at that time, determine whether it satisfies the elevation field of view constraint, filter out all visible strips and record the corresponding actual imaging time. Step 6: Calculate the load switching time corresponding to the visible strip based on the shortest duration of a single power-on / off cycle of the rotating load and the actual imaging time. If the power-on / off time exceeds the imaging range, make corrections.

[0032] Obtain input parameters: initial UTC time T0; initial satellite position and velocity in WGS_84 geocentric-earth-fixed frame. Initial satellite optical axis azimuth angle ; angular velocity of the optical axis about the x-axis of this system Pitch-to-image field of view Lateral tilt imaging field of view Target point latitude and longitude .

[0033] Determine the midpoint of all stripes: Starting moment of the scene The timing is as follows: the moment when the satellite's optical axis points to the nadir point is:

[0034] Among them, each time the optical axis points to the sub-star point At that time, the satellite's position and velocity in the Earth-fixed system .

[0035] latitude and longitude of the target point Convert to Earth-centered and Earth-fixed coordinate system ; Calculate the Earth's occlusion conditions and the midpoint of each strip. Record whether the satellite and target are obstructed by the Earth, and record all stripes that are not obstructed by the Earth.

[0036] Determine the azimuth constraints between the midpoint of all strips and the target point: When the target point is with the If a band is not obstructed by the Earth, then continue calculating the intermediate time of that band. Satellite position and velocity in the Earth-fixed system The azimuth angle corresponding to the line connecting the strips And determine the azimuth. Does it satisfy the azimuth field of view constraint?

[0037] If azimuth angle If the above inequality constraints are satisfied, then record all stripes that currently satisfy the azimuth constraint.

[0038] Determine the pitch phase angle constraint between the strip and the target point: When strip If the target is not obstructed by Earth and the azimuth constraint is satisfied, then the stripe is calculated. The pitch phase angle of the target point is used to calculate the optical axis azimuth angle. The time corresponding to the time is the actual imaging time. :

[0039] calculate Time satellite in Pitch phase angle along the target line Determine the bands Pitch phase angle of the line connecting the target Does the pitch field of view constraint satisfy: .

[0040] When pitch phase angle pitch phase angle If the pitch field of view constraint is satisfied, then all stripes that currently satisfy the azimuth constraint are recorded as all visible stripes. And record the actual imaging time of the target point. .

[0041] Calculate the actual start-up and shutdown time, and set the minimum start-up and shutdown duration for a single rotational load as follows: For point target imaging scenarios, the actual on / off time of the payload is calculated as follows:

[0042]

[0043] If the power-on / off time exceeds the imaging range, correction is required. The specific method is as follows:

[0044] Calculate the set of visible stripes sequentially In the middle, the load imaging on / off time of all visible stripes.

[0045] The present invention also provides a computer-readable storage medium having a computer program stored thereon, which is executed by a processor to implement a target observation mission planning method for a rotating scanning imaging remote sensing satellite.

[0046] The present invention also provides a computer device, including a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement a target observation mission planning method for a rotating scanning imaging remote sensing satellite. Specific Implementation Example 2: The only difference between Embodiment 2 and Embodiment 1 of this application is that: Rotating payload remote sensing satellites have a rotatable imaging payload, whose imaging strips are as follows: Figure 1 As shown. Its optical axis rotates around the x-axis of this system at an angular velocity. Continuous rotation. A linear array imaging mode is used, with a group of CCD cameras distributed along the x-axis of the system. The elevation imaging field of view is... To ensure image quality, the azimuth imaging field of view is limited to [specific value]. .

[0048] Traditional remote sensing satellite imaging methods can be broadly categorized into two types: passive pushbroom and active pushbroom. In passive pushbroom mode, the satellite's optical axis is fixed and does not maneuver; therefore, it's necessary to calculate whether the bands formed during the satellite's pushbroom process cover the target point. In active pushbroom mode, the satellite's optical axis can rotate, requiring the calculation of the visible time window based on the maximum rotation angle. However, the rotating payload remote sensing satellite imaging mode differs from both of these modes, therefore its visibility calculation method cannot follow the methods used for the aforementioned imaging modes. The innovation of the rotating payload remote sensing satellite visibility calculation method is specifically reflected in the following imaging characteristics: (1) Unlike passive pushbroom imaging satellites, the optical axis of a rotating payload remote sensing satellite continuously rotates around the x-axis of its own system. (2) Unlike active imaging satellites, the optical axis of a rotating payload remote sensing satellite cannot be actively adjusted. (3) Passive pushbroom imaging satellites have only one fixed imaging time for the target during a single pass, and the payload power-on and power-off time is fixed; active pushbroom imaging satellites have a longer visible window for the target during a single pass, and the payload power-on and power-off time can be adjusted arbitrarily within the window; rotating payload remote sensing satellites can have multiple imaging windows during each pass, but the power-on and power-off time of each imaging window is fixed.

[0049] Imaging model simplification and error analysis The satellite's rotating payload rotates at an angular velocity of [value missing] around the velocity direction. The satellite's field of view along the azimuth direction is... If the satellite is By scanning and imaging within the azimuth angle range, imaging strips can be obtained. The time required for each imaging strip is... Due to the Earth's rotation, there is a relative displacement between the nadir point and the target during the period of satellite imaging. Assuming the satellite is in a sun-synchronous orbit at an altitude of 500 km, and the maximum azimuth imaging field of view is 120°, If the angle is 15°, then the imaging time for a single strip is 8 seconds. Within 8 seconds, the distance the satellite's nadir point moves relative to the target point along the azimuth direction is approximately 3.7 km at the equator, gradually decreasing with increasing latitude; the distance it moves along the elevation direction is approximately 60.9 km. Considering the movement of the satellite's nadir point in both directions would significantly increase the complexity of visibility calculations. Therefore, to simplify the calculation process, this invention does not consider the movement of the satellite's nadir point along the azimuth direction during the strip imaging period. Thus, the azimuth angle between the satellite and the target can be calculated based on the satellite's position at the midpoint of the strip, thereby initially determining which strip the satellite is located in, and then further determining the elevation phase angle.

[0050] The core of the simplified model proposed in this invention lies in the decoupling of "azimuth-elevation". Within the given 8-second imaging duration, although the azimuth displacement of the satellite relative to the target (approximately 3.7 km at the equator) is much smaller than the elevation displacement (approximately 60.9 km), ignoring azimuth movement is not an unfounded approximation. However, this paper assumes that this error meets the accuracy requirements of the imaging mission. Furthermore, the model introduces the center-of-strip time as a reference point. Due to the rotational angular velocity... The sweeping process of the strips is constant and exhibits high time symmetry. By locking the midpoint time, the complex continuous dynamic scanning process can be transformed into a discretized strip selection process. This innovation simplifies the traditional complex partial differential geometry problem into an algebraic constraint judgment problem, significantly reducing the computational load of the ground planning system and enabling it to have the potential for online planning or on-board autonomous planning.

[0051] Calculation of time window for remote sensing satellite imaging with rotating payload Assume the following conditions are known: initial UTC time T0; initial satellite position and velocity in the WGS_84 geocentric Earth-fixed frame. Initial satellite optical axis azimuth angle (Values) ); angular velocity of optical axis rotation about the x-axis of this system Pitch-to-image field of view Lateral tilt imaging field of view Target point latitude and longitude .

[0052] A schematic diagram of point target imaging by a rotating payload remote sensing satellite is shown below. Figure 1 As shown, the remote sensing satellite imaging stripes are as follows Figure 2 As shown. Because this method appropriately simplifies the rotating load imaging model, during the imaging of a single strip, it is not necessary to consider the change in the azimuth angle of the line connecting the satellite and the target over time, but it is necessary to consider the change in the satellite's elevation phase angle over time within a single strip. Therefore, this paper first considers the azimuth angle of the line connecting the satellite and the target at the intermediate time. A first-stage screening is performed on all bands. Before this screening, it is necessary to determine the Earth's occlusion conditions. After the first-stage screening, the following results can be obtained: Figure 2 The strips shown satisfying the azimuth constraint are: strip 1, strip 2, strip 3, etc. Figure 2The three stripes shown clearly satisfy the azimuth constraint. Further, the elevation phase angle constraint needs to be calculated. Since the change in elevation phase angle over time needs to be considered, we can calculate the moment when the optical axis points to the target point based on the angular velocity at the midpoint of the strip, i.e., the moment when the optical axis points to the bottom of the line. This moment is then used as the actual moment of image formation on the target point. The elevation phase angle corresponding to the line connecting the satellite and the target point at this moment needs to be calculated. Then, it is determined whether the pitch field of view constraint is satisfied. If all the above constraints are satisfied, the visible stripe of the target and the actual imaging time of the target in that stripe can be determined.

[0053] according to Figure 3 The algorithm implementation idea is to calculate the time window for remote sensing satellite imaging with rotating payloads. The specific process is as follows: (1) Determine the midpoint of all stripes Starting moment of the scene The timing is as follows: the moment when the satellite's optical axis points to the nadir point is:

[0054] It is also the midpoint of each strip, at the point where the optical axis points below the star. At that time, the satellite's position and velocity in the Earth-fixed system .

[0055] (2) Set the latitude and longitude of the target point Convert to Earth-centered and Earth-fixed coordinate system .

[0056] (3) Calculate Earth's shading conditions Calculate the midpoint of each strip Record whether the satellite and target are obstructed by the Earth, and record all stripes that are not obstructed by the Earth.

[0057] ( Determine the azimuth constraints between the midpoint of all strips and the target point. If the target point is the same as the first If a band is not obstructed by the Earth, then continue calculating the intermediate time of that band. Satellite position and velocity in the Earth-fixed system The azimuth angle corresponding to the line connecting the strips And determine the azimuth. Does it satisfy the azimuth field of view constraint?

[0058] If azimuth angle If the above inequality constraints are satisfied, then record all stripes that currently satisfy the azimuth constraint.

[0059] ( Determine the pitch phase angle constraint between the strip and the target point. If strip If the target is not obstructed by Earth and the azimuth constraint is satisfied, then the stripe is calculated. The elevation phase angle relative to the target point. First, calculate the optical axis azimuth angle as follows: The time corresponding to the time is the actual imaging time. :

[0060] calculate Time satellite in Pitch phase angle along the target line Determine the bands Pitch phase angle of the line connecting the target Does the pitch field of view constraint satisfy:

[0061] If pitch phase angle If the above inequality constraints are satisfied, then all stripes that currently satisfy the azimuth constraint are recorded as all visible stripes. And record the actual imaging time of the target point. .

[0062] ( Calculate the actual power-on and power-off times. Assuming the shortest duration of a single power-on / off cycle for a rotating load is For point target imaging scenarios, the actual on / off time of the payload is calculated as follows:

[0063]

[0064] If the power-on / off time exceeds the imaging range, correction is required. The specific method is as follows:

[0065] Calculate the set of visible stripes sequentially In the middle, the load imaging on / off time of all visible stripes.

[0066] The calculation method proposed in this invention shows significant advantages in practical applications: First, computational efficiency is significantly improved. Compared to traditional numerical integration methods, the computational complexity of this method is greatly reduced.

[0067] Secondly, by employing a two-stage filtering logic of "azimuth first, then elevation," pointing accuracy is ensured, a large number of invalid stripes are eliminated, and pointing errors are controlled within the field of view, thus guaranteeing a high success rate for rotating imaging. Thirdly, this method does not rely on high-performance spaceborne computers and can be widely applied to low-cost micro / nano satellite constellations, demonstrating strong engineering applicability. With the construction of my country's large-scale rotating payload remote sensing constellation, this algorithm can effectively solve emergency mission response problems and has extremely high engineering application value in fields such as disaster prevention and mitigation, marine monitoring, and tracking of key targets.

[0068] The above description is merely a preferred embodiment of a target observation mission planning method for a rotating scanning imaging remote sensing satellite. The scope of protection for this method is not limited to the above embodiments; all technical solutions falling within this conceptual framework are within the scope of protection of this invention. It should be noted that for those skilled in the art, any improvements and variations made without departing from the principles of this invention should also be considered within the scope of protection of this invention.

Claims

1. A target observation mission planning method for a rotating scanning imaging remote sensing satellite, characterized by: The method includes the following steps: Step 1: Start timing from the beginning of the imaging scene, and take the moment when the satellite's optical axis points to the nadir point as the midpoint of the corresponding strip, and record the position and velocity of the satellite in the WGS_84 geocentric-earth-fixed system at the midpoint of each strip; Step 2: Convert the latitude and longitude of the target point to coordinates in the WGS_84 geocentric coordinate system; Step 3: Calculate whether the satellite and the target point are blocked by the Earth at the midpoint of each strip, and filter out all strips that are not blocked by the Earth; Step 4: For strips that are not obscured by the Earth, calculate the azimuth angle of the line connecting the satellite and the target point at the midpoint of the strip, determine whether it meets the azimuth field of view constraint, and filter out strips that meet the azimuth angle constraint. Step 5: For strips that satisfy the azimuth constraint, calculate the actual imaging time when the optical axis points to the target point based on the midpoint time of the strip and the optical axis rotation angular velocity. Then calculate the elevation phase angle corresponding to the line connecting the satellite and the target point at that time, determine whether it satisfies the elevation field of view constraint, filter out all visible strips and record the corresponding actual imaging time. Step 6: Calculate the load switching time corresponding to the visible strip based on the shortest duration of a single power-on / off cycle of the rotating load and the actual imaging time. If the power-on / off time exceeds the imaging range, make corrections.

2. The method according to claim 1, characterized in that: Set the input parameters as follows: Initial UTC time T0; initial satellite position and velocity in WGS_84 geocentric Earth-fixed system. Initial satellite optical axis azimuth angle ; angular velocity of the optical axis about the x-axis of this system Pitch-to-image field of view Lateral tilt imaging field of view Target point latitude and longitude .

3. The method according to claim 2, characterized in that: Determine the midpoint of all stripes: Starting moment of the scene The timing is as follows: the moment when the satellite's optical axis points to the nadir point: Among them, each time the optical axis points to the sub-star point At that time, the satellite's position and velocity in the Earth-fixed system .

4. The method according to claim 3, characterized in that: latitude and longitude of the target point Convert to Earth-centered and Earth-fixed coordinate system ; Calculate the Earth's occlusion conditions and the midpoint of each strip. Record whether the satellite and target are obstructed by the Earth, and record all stripes that are not obstructed by the Earth.

5. The method according to claim 4, characterized in that: Determine the azimuth constraints between the midpoint of all strips and the target point: When the target point is with the If a band is not obstructed by the Earth, then continue calculating the intermediate time of that band. Satellite position and velocity in the Earth-fixed system The azimuth angle corresponding to the line connecting the strips And determine the azimuth. Does it satisfy the azimuth field of view constraint? If azimuth angle If the above inequality constraints are satisfied, then record all stripes that currently satisfy the azimuth constraint.

6. The method according to claim 5, characterized in that: Determine the pitch phase angle constraint between the strip and the target point: When strip If the target is not obstructed by Earth and meets the azimuth constraint, then the stripe is calculated. The elevation phase angle of the target point is used to calculate the optical axis azimuth angle. The time corresponding to the time is the actual imaging time. : calculate Time satellite in Pitch phase angle along the target line Determine the bands Pitch phase angle of the line connecting the target Does the pitch field of view constraint satisfy: 。 7. The method according to claim 6, characterized in that: When pitch phase angle If the pitch field of view constraint is satisfied, then all stripes that currently satisfy the azimuth constraint are recorded as all visible stripes. And record the actual imaging time of the target point. .

8. The method according to claim 7, characterized in that: Calculate the actual start-up and shutdown time, and set the minimum start-up and shutdown duration for a single rotational load as follows: For point target imaging scenarios, the actual on / off time of the payload is calculated as follows: If the power-on / off time exceeds the imaging range, correction is required. The specific method is as follows: Calculate the set of visible stripes sequentially In the middle, the load imaging on / off time of all visible stripes.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that, The program is executed by the processor to implement the method as claimed in any one of claims 1-8.

10. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that: When the processor executes the computer program, it implements the method of any one of claims 1-8.

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