A returnable aircraft carried by an ultra-low-orbit satellite and a control method thereof

Abstract

The present invention discloses a recoverable aircraft and control method carried by an ultra-low-orbit satellite. The recoverable aircraft is carried on an ultra-low-orbit satellite platform and connected through an unlocking device. The ultra-low-orbit satellite platform supplies power to the recoverable aircraft through a power supply path. The recoverable aircraft relies on the electric thrust of the ultra-low-orbit satellite platform to fly in orbit and carry out on-orbit experimental tasks. At the separation point, in response to ground commands, the ultra-low-orbit satellite platform and the recoverable aircraft are separated, and the power supply path between the two is synchronously disconnected; after the combination is separated, the ultra-low-orbit satellite relies on the propulsion subsystem to return to the ultra-low-orbit orbit and continue to perform long-term on-orbit missions; the recoverable aircraft relies on the propulsion subsystem to aim at the 100km altitude orbit re-entry point for adaptive guidance, while carrying out short-term experiments, and returning to the ground after completing the experiments. Using the ultra-low-orbit satellite platform, the recoverable aircraft can achieve low-cost, high-performance mission flights.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft design, and in particular relates to a recoverable aircraft carried by an ultra-low-orbit satellite and a control method. Background Art

[0002] Traditional reusable spacecraft typically consist of an instrument module, a return capsule, and a service module. They are equipped with comprehensive subsystems for measurement and control, attitude and orbit control, propulsion, and power (including solar panels), resulting in high costs. The payloads carried by these vehicles can be divided into two categories: those designed to conduct long-term in-orbit experiments, and those that do not require such long-term experiments and can complete their missions after a short period of in-orbit recovery. To reduce costs, reusable spacecraft use thrusters for attitude control while in orbit. Longer in-orbit operation consumes more fuel, and upon return, chemical engine braking is required, consuming a large amount of fuel and being costly.

[0003] With the recent development of electric propulsion technology, the realization of ultra-low-orbit satellites has become possible. Ultra-low-orbit satellites generally refer to satellites operating at an altitude of less than 300 km and more than 150 km. Deploying satellites in this orbit can significantly shorten the distance between payloads and the ground, thereby improving payload efficiency and reducing satellite development and launch costs.

[0004] If an ultra-low-orbit satellite is used to carry a recoverable spacecraft, the part of the traditional recoverable spacecraft that needs to be carried for a long time for experiments can be placed on the ultra-low-orbit satellite, and the part that needs to be returned and recovered can be placed on the recoverable spacecraft. In this way, the mission of the long-term in-orbit satellite can be completed, and the mission of the recoverable spacecraft can be completed at a low cost and conveniently, greatly reducing the cost of the recoverable spacecraft. Summary of the Invention

[0005] In response to the shortcomings of the existing technology, the present invention proposes a recoverable aircraft and control method carried by an ultra-low-orbit satellite, which carries the recoverable aircraft on an ultra-low-orbit satellite platform and utilizes the ultra-low-orbit satellite platform to achieve low-cost, high-performance mission flight.

[0006] A recoverable aircraft carried by an ultra-low-orbit satellite comprises an ultra-low-orbit satellite platform and a recoverable aircraft.

[0007] The ultra-low-orbit satellite platform includes a satellite platform and an on-orbit experiment module, wherein the on-orbit experiment module is carried on the satellite platform to conduct long-term on-orbit experiments.

[0008] The returning aircraft includes an aircraft platform and a returning experimental cabin, wherein the returning experimental cabin is carried on the returning aircraft, and returns to the ground after completing a short experiment as the aircraft platform brakes and re-enters.

[0009] The ultra-low-orbit satellite platform and the recoverable aircraft are connected by an unlocking device to form a combination. The ultra-low-orbit satellite platform supplies power to the recoverable aircraft through a power supply path. The combination relies on the electric thrust of the ultra-low-orbit satellite platform to fly in orbit and carry out on-orbit experimental tasks. At the separation point, in response to ground commands, the unlocking device is unlocked, the ultra-low-orbit satellite platform and the recoverable aircraft are separated, and the power supply path between the two is synchronously disconnected; after the combination is separated, the ultra-low-orbit satellite relies on the propulsion subsystem to return to the ultra-low-orbit orbit and continue to perform long-term on-orbit missions; the recoverable aircraft relies on the propulsion subsystem to aim at the 100km altitude orbital re-entry point for adaptive guidance, while carrying out short-term experiments, and returning to the ground after completing the experiments.

[0010] Preferably, the satellite platform and the spacecraft platform both include independent integrated electronic subsystems, structure and mechanism subsystems, measurement and control subsystems, attitude and orbit control subsystems, propulsion subsystems, power supply and overall circuit subsystems, and thermal control subsystems.

[0011] Preferably, the integrated electronic subsystem includes a GNSS receiver and an onboard computer, and the structure and mechanism subsystem is used to design the drag reduction shape.

[0012] Preferably, the attitude and orbit control subsystem of the satellite platform includes a gyroscope, a star sensor, a reaction momentum wheel, a magnetic torquer and a solar sensor, the propulsion subsystem adopts electric propulsion, and the power supply and overall circuit subsystem includes a power controller, a battery and a solar wing battery array.

[0013] Preferably, the attitude and orbit control subsystem of the aircraft platform includes an inertial unit IMU and a star sensor, the propulsion subsystem includes 6 attitude control thrusters and 1 chemical thrust and orbit control thruster, and the power supply and overall circuit subsystem includes a power controller and a battery.

[0014] A control method for a recoverable aircraft carried by an ultra-low-orbit satellite comprises the following steps:

[0015] Step 1: The returnable vehicle is carried on the ultra-low orbit satellite platform and enters a low orbit of 500 km together. The on-orbit experimental module and the returnable experimental module conduct low-orbit in-orbit testing. Then, the ultra-low orbit satellite platform uses electric propulsion to enter an ultra-low orbit of 250 km together with the returnable vehicle. The on-orbit experimental module and the returnable experimental module conduct ultra-low orbit in-orbit testing.

[0016] Step 2: After the returnable experimental module completes the experiment, the ultra-low-orbit satellite platform relies on electric propulsion to enter the braking orbit of the returnable spacecraft together with the returnable spacecraft. According to ground instructions, when the ascending node and orbital inclination conditions are met, the returnable spacecraft separates from the ultra-low-orbit satellite platform.

[0017] Step 3: After separating from the ultra-low-orbit satellite platform, the reentry vehicle uses attitude control thrusters to adjust its braking attitude at the braking point. It then uses chemical propulsion and trajectory control thrusters to target the reentry point at an altitude of 100 km for adaptive guidance and complete braking. The ultra-low-orbit satellite platform uses electric propulsion to return to ultra-low orbit, as required by the mission.

[0018] As a preferred method, the ultra-low orbit satellite platform relies on electric propulsion and the returning vehicle to enter the braking orbit of the returning vehicle from the ultra-low orbit together with the returning vehicle as follows:

[0019] Considering the effects of thrust, J2 perturbation and atmospheric drag, the motion model of the ultra-low orbit satellite platform in the polar coordinate system is established:

[0020]

[0021] in, represent the first derivative and the second derivative respectively, μ is the earth's gravitational constant, θ is the polar angle, γ is the flight path angle, T a is the thrust acceleration amplitude, δ is the thrust point angle relative to the horizontal plane, a J2,ar and a J2,a⊥ They represent the radial and lateral components of the J2 perturbation acceleration, respectively, and a drag,ar and a drag,a⊥ They represent the radial and lateral components of the atmospheric drag acceleration, respectively, and r is the radial vector amplitude:

[0022]

[0023] Among them, the true anomaly f1 = f 10 +θ, true anomaly f2=f1-△ω,△ω=ω2-ω1,f 10 is the initial true anomaly of the ultra-low orbit maneuvering position, θ is the transfer angle with reference to the initial position, e is the orbit eccentricity, ω is the argument of perigee, and the subscripts "1" and "2" represent the ultra-low orbit and the return vehicle braking orbit, respectively. The semi-major axes a3 and a4 are expressed as sixth-order polynomials:

[0024]

[0025] The coefficients (α0, α1, α2) are determined by the initial position in the ultra-low orbit, the coefficients (β0, β1, β2) are determined by the target position in the braking orbit, and the coefficients (α4, α5, α6, β4, β5, β6) are determined by β3.

[0026] Assume that the ultra-low orbit satellite platform is at a given fixed time t fixed The inner part is transferred from the initial position to the target position, and β3 is solved iteratively using the golden secant method:

[0027]

[0028] Among them, the initial value of the iteration of β3 is β 3,0 =0 and a2 is the semi-major axis of the brake track, θ f is the final transfer angle.

[0029] Due to the radial velocity of the ultra-low orbit satellite platform lateral speed Therefore, the flight path angle of the ultra-low orbit satellite platform The first and second derivatives of the radial vector magnitude are:

[0030]

[0031] Combining formula (1) and considering the use of tangential thrust δ = γ, the angular velocity can be obtained and angular acceleration The thrust acceleration is further obtained as:

[0032]

[0033] Where A = 1-r 2 (a J2,ar +a drag,ar -a J2,a⊥ tanγ-a drag,a⊥ tanγ).

[0034] Therefore, the required velocity increment △V of the ultra-low orbit satellite platform is:

[0035]

[0036] Formula (7) is used to calculate the velocity increment of the ultra-low-orbit satellite platform at different orbital altitudes in real time, and to control the movement of the ultra-low-orbit satellite platform to overcome the atmospheric perturbation and the error of orbit control implementation, eliminate their adverse effects, and achieve higher orbit control accuracy.

[0037] The present invention has the following beneficial effects:

[0038] 1. The recoverable vehicle is carried on a very-low-orbit satellite platform. The very-low-orbit satellite can use its electric thrusters for orbital control, allowing it to operate stably in a very-low-orbit orbit for a long time and complete in-orbit experimental missions. The advantages are high specific impulse, and the fuel cost required for the very-low-orbit satellite is significantly lower than the fuel used by the chemical thrusters of traditional recoverable vehicles. The very-low-orbit satellite can operate in the orbit of a very-low-orbit satellite or change its orbit to the return orbit of the recoverable vehicle. After completing the mission of releasing the recoverable vehicle, it can return to its operating orbit at a low cost without affecting normal operation.

[0039] 2. Ultra-low-orbit satellites have a complete and high-precision attitude control system. The high-power sail panels provide sufficient power, which can provide solar power for the returning spacecraft for its on-orbit experiments. When the returning spacecraft is released, it is separated by an unlocking device. Therefore, the returning spacecraft does not need to be equipped with solar cells, reaction wheels, magnetic torquers and other control components in the process of completing the on-orbit experimental mission. Compared with the traditional returning spacecraft using jet thrusters for attitude control, it can ensure its higher-precision on-orbit attitude and sufficient energy supply.

[0040] 3. The integrated orbital control design allows the returnable vehicle to utilize the ultra-low-orbit satellite platform to perform large-scale orbit changes at low cost, with lower adjustment costs and higher orbital change accuracy than traditional returnable vehicles. Furthermore, since ultra-low-orbit satellites fly at altitudes as low as 250km, the returnable vehicle can be lowered to an altitude of 180-200km upon release. When the returnable vehicle brakes, the fuel consumed by its chemical orbital control engine is greatly reduced, thereby reducing costs. For example, a traditional returnable vehicle, calculated at 300kg, would consume 22.9kg of chemical propellant to descend from an altitude of 500km to 200km, not including the fuel consumption for attitude control during orbit. The solution designed in this application can save this fuel.

[0041] 4. The recoverable vehicle described in the patent can utilize the orbital maneuverability of the ultra-low-orbit satellite platform to fly to a specified orbital position at a specified time point, providing orbital guarantee for the precise re-entry guidance of the recoverable vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 This is a system block diagram of the ultra-low-orbit satellite platform;

[0043] Figure 2 This is a block diagram of the return vehicle system;

[0044] Figure 3 Block diagram of the recoverable vehicle system for ultra-low-orbit satellites. DETAILED DESCRIPTION

[0045] The present invention will be further explained below with reference to the accompanying drawings;

[0046] A recoverable aircraft carried by an ultra-low-orbit satellite comprises an ultra-low-orbit satellite platform and a recoverable aircraft.

[0047] like Figure 1As shown, the ultra-low-orbit satellite platform comprises a satellite platform and an on-orbit experimental module. The on-orbit experimental module is carried on the satellite platform for long-term on-orbit experiments. The satellite platform includes an integrated electronic subsystem, a structure and mechanism subsystem, a measurement and control subsystem, an attitude and orbit control subsystem, a propulsion subsystem, a power supply and general circuit subsystem, and a thermal control subsystem. The integrated electronic subsystem includes a GNSS receiver and an onboard computer. The structure and mechanism subsystem is used to design the drag reduction shape. The attitude and orbit control subsystem includes a gyroscope, a star sensor, a reaction momentum wheel, a magnetic torquer, and a solar sensor. The propulsion subsystem uses electric propulsion. The power supply and general circuit subsystem includes a power controller, batteries, and a solar array.

[0048] like Figure 2 As shown, the reusable vehicle includes an aircraft platform and a reusable experimental module. The reusable experimental module is carried on the reusable vehicle and returns to the ground after completing a short experiment as the aircraft platform brakes and reenters. The reusable vehicle also includes an integrated electronic subsystem, a structure and mechanism subsystem, a measurement and control subsystem, an attitude and orbit control subsystem, a propulsion subsystem, a power supply and overall circuit subsystem, and a thermal control subsystem. The attitude and orbit control subsystem includes an inertial unit (IMU) and a star sensor, the propulsion subsystem includes six attitude control thrusters and one chemical thruster for orbit control, and the power supply and overall circuit subsystem includes a power controller and batteries.

[0049] like Figure 3 As shown, the ultra-low-orbit satellite platform and the recoverable vehicle are connected via an unlocking device to form a combination. The ultra-low-orbit satellite platform supplies power to the recoverable vehicle via a power supply path. The combination flies at an orbital altitude of 150km to 500km and can carry out ultra-low-orbit remote sensing, communications, navigation, and new technology verification services. At the separation point, in response to ground commands, the unlocking device unlocks, the ultra-low-orbit satellite platform and the recoverable vehicle separate, and the power path between them is simultaneously disconnected. After separation, the ultra-low-orbit satellite relies on the propulsion subsystem to return to the ultra-low-orbit orbit and continue its long-term on-orbit mission. The recoverable vehicle relies on the propulsion subsystem to target the 100km altitude orbital re-entry point for adaptive guidance, while conducting short-term experiments and returning to the ground after completion.

[0050] A control method for a recoverable aircraft carried by an ultra-low-orbit satellite comprises the following steps:

[0051] Step 1: The returnable vehicle is carried on the ultra-low orbit satellite platform and enters a low orbit of 500 km together. The on-orbit experimental module and the returnable experimental module conduct low-orbit in-orbit testing. Then, the ultra-low orbit satellite platform uses electric propulsion to enter an ultra-low orbit of 250 km together with the returnable vehicle. The on-orbit experimental module and the returnable experimental module conduct ultra-low orbit in-orbit testing.

[0052] Step 2: After the returnable experimental module completes the experiment, the ultra-low-orbit satellite platform relies on electric propulsion to enter the returnable vehicle's braking orbit at an altitude of 180 km. The control method of the ultra-low-orbit satellite platform is as follows:

[0053] Considering the effects of thrust, J2 perturbation and atmospheric drag, the motion model of the ultra-low orbit satellite platform in the polar coordinate system is established:

[0054]

[0055] in, represent the first derivative and the second derivative respectively, μ is the earth's gravitational constant, θ is the polar angle, γ is the flight path angle, T a is the thrust acceleration amplitude, δ is the thrust point angle relative to the horizontal plane, a J2,ar and a J2,a⊥ They represent the radial and lateral components of the J2 perturbation acceleration, respectively, and a drag,ar and a drag,a⊥ They represent the radial and lateral components of the atmospheric drag acceleration, respectively, and r is the radial vector amplitude:

[0056]

[0057] Among them, the true anomaly f1 = f 10 +θ, true anomaly f2=f1-△ω,△ω=ω2-ω1,f 10 is the initial true anomaly of the ultra-low orbit maneuvering position, θ is the transfer angle with reference to the initial position, e is the orbit eccentricity, ω is the argument of perigee, and the subscripts "1" and "2" represent the ultra-low orbit and the return vehicle braking orbit, respectively. The semi-major axes a3 and a4 are expressed as sixth-order polynomials:

[0058]

[0059] The coefficients (α0, α1, α2) are determined by the initial position in the ultra-low orbit, the coefficients (β0, β1, β2) are determined by the target position in the braking orbit, and the coefficients (α4, α5, α6, β4, β5, β6) are determined by β3.

[0060] Assume that the ultra-low orbit satellite platform is at a given fixed time t fixed The inner part is transferred from the initial position to the target position, and β3 is solved iteratively using the golden secant method:

[0061]

[0062] Among them, the initial value of the iteration of β3 is β 3,0 =0 and a2 is the semi-major axis of the brake track, θ f is the final transfer angle.

[0063] Due to the radial velocity of the ultra-low orbit satellite platform lateral speed Therefore, the flight path angle of the ultra-low orbit satellite platform The first and second derivatives of the radial vector magnitude are:

[0064]

[0065] Combining formula (1) and considering the use of tangential thrust δ = γ, the angular velocity can be obtained and angular acceleration The thrust acceleration is further obtained as:

[0066]

[0067] Where A = 1-r 2 (a J2,ar +a drag,ar -a J2,a⊥ tanγ-a drag,a⊥ tanγ).

[0068] Therefore, the required velocity increment △V of the ultra-low orbit satellite platform is:

[0069]

[0070] Formula (7) is used to calculate the velocity increment of the ultra-low-orbit satellite platform at different orbital altitudes in real time, and to control the movement of the ultra-low-orbit satellite platform to overcome the atmospheric perturbation and the error of orbit control implementation, eliminate their adverse effects, and achieve higher orbit control accuracy.

[0071] Step 3: Based on ground control, the returnable vehicle separates from the ultra-low-orbit satellite platform when the ascending node and orbital inclination conditions are met. After separation, the returnable vehicle uses attitude control thrusters to adjust its braking attitude at the braking point. It then uses chemically driven orbit control thrusters to adaptively guide the vehicle to the reentry point at an altitude of 100 km, completing braking. The ultra-low-orbit satellite platform then uses electric propulsion to return to ultra-low orbit, as required by the mission.

Claims

1. A recoverable vehicle carried by an ultra-low-orbit satellite, characterized by: Including ultra-low-orbit satellite platforms and recoverable vehicles; The ultra-low-orbit satellite platform includes a satellite platform and an on-orbit experiment module, wherein the on-orbit experiment module is carried on the satellite platform for conducting long-term on-orbit experiments; the returnable aircraft includes an aircraft platform and a returnable experiment module, wherein the returnable experiment module is carried on the returnable aircraft and returns to the ground after completing a short-term experiment as the aircraft platform brakes and re-enters; the ultra-low-orbit satellite platform and the returnable aircraft are connected by an unlocking device, and the ultra-low-orbit satellite platform supplies power to the returnable aircraft through a power supply path, and the two form a combination; The combination relies on the electric thrust of the ultra-low orbit satellite platform to fly in orbit, carry out on-orbit experimental tasks, respond to ground commands at the separation point, and the ultra-low orbit satellite platform separates from the returning spacecraft, and the power supply path between the two is synchronously disconnected; the low-orbit satellite relies on the propulsion subsystem to return to the ultra-low orbit and continue to perform long-term on-orbit missions; the returning spacecraft relies on the propulsion subsystem to aim at the re-entry point of the guidance orbit for adaptive guidance, while carrying out short-term experiments, and returns to the ground after completing the experiments.

2. The recoverable vehicle carried by an ultra-low-orbit satellite according to claim 1, characterized in that: The satellite platform and the spacecraft platform both include independent integrated electronic subsystems, structure and mechanism subsystems, measurement and control subsystems, attitude and orbit control subsystems, propulsion subsystems, power supply and overall circuit subsystems, and thermal control subsystems.

3. The recoverable vehicle carried by an ultra-low-orbit satellite as claimed in claim 2, characterized in that: The integrated electronic subsystem includes a GNSS receiver and an onboard computer, and the structure and mechanism subsystem is used to design the drag reduction shape.

4. The recoverable vehicle carried by an ultra-low-orbit satellite according to claim 2, characterized in that: The attitude and orbit control subsystem of the satellite platform includes a gyroscope, a star sensor, a reaction momentum wheel, a magnetic torquer and a solar sensor; the propulsion subsystem adopts electric propulsion; the power supply and overall circuit subsystem includes a power controller, a battery and a solar wing battery array.

5. The recoverable vehicle carried by an ultra-low-orbit satellite as claimed in claim 2, characterized in that: The attitude and orbit control subsystem of the aircraft platform includes an inertial unit IMU and a star sensor, the propulsion subsystem includes 6 attitude control thrusters and 1 chemical thrust and orbit control thruster, and the power supply and overall circuit subsystem includes a power controller and a battery.

6. A control method for a recoverable vehicle carried by an ultra-low-orbit satellite, characterized in that: The method is used to control a recoverable vehicle carried by an ultra-low-orbit satellite according to any one of claims 1 to 5, specifically comprising the following steps: Step 1: The returnable spacecraft is carried on the ultra-low orbit satellite platform and enters the low orbit together. The on-orbit experimental module and the returnable experimental module carry out low-orbit on-orbit testing. After completing the low-orbit on-orbit testing, the ultra-low orbit satellite platform relies on electric propulsion to enter the ultra-low orbit together with the returnable spacecraft. The on-orbit experimental module and the returnable experimental module carry out ultra-low orbit on-orbit testing. Step 2: After the returnable experimental module completes the experiment, the ultra-low-orbit satellite platform relies on electric propulsion to enter the returnable spacecraft's braking orbit together with the returnable spacecraft. According to ground instructions, when the ascending node and orbital inclination conditions are met, the returnable spacecraft separates from the ultra-low-orbit satellite platform. Step 3: After separation from the ultra-low orbit satellite platform, the returning vehicle uses the attitude control thrusters at the braking point to adjust the braking attitude, and uses the chemical propulsion orbit control thrusters to aim at the re-entry point of the 100km altitude orbit for adaptive guidance to complete braking; the ultra-low orbit satellite platform uses electric propulsion to return to the ultra-low orbit according to mission requirements.

7. The control method of a recoverable vehicle carried by an ultra-low-orbit satellite as claimed in claim 6, characterized in that: The method by which the ultra-low-orbit satellite platform relies on electric propulsion and the returning vehicle to enter the braking orbit of the returning vehicle from the ultra-low-orbit orbit is as follows: Considering the effects of thrust, J2 perturbation and atmospheric drag, the motion model of the ultra-low orbit satellite platform in the polar coordinate system is established: in,( · )、( ·· ) represent the first derivative and the second derivative respectively, μ is the earth's gravitational constant, θ is the polar angle, γ is the flight path angle, T a is the thrust acceleration amplitude, δ is the thrust point angle relative to the horizontal plane, a J2,ar and a J2,a⊥ They represent the radial and lateral components of the J2 perturbation acceleration, respectively, and a drag,ar and a drag,a⊥ They represent the radial and lateral components of the atmospheric drag acceleration, respectively, and r is the radial vector amplitude: Among them, the true anomaly f1 = f 10 +θ, true anomaly f2=f1-△ω,△ω=ω2-ω1,f 10 is the initial true anomaly of the ultra-low orbit maneuvering position, θ is the transfer angle with reference to the initial position, e is the orbit eccentricity, ω is the argument of perigee, and the subscripts "1" and "2" represent the ultra-low orbit and the return vehicle braking orbit, respectively. The semi-major axes a3 and a4 are expressed as sixth-order polynomials: The coefficients (α0, α1, α2) are determined by the initial position in the ultra-low orbit, the coefficients (β0, β1, β2) are determined by the target position in the braking orbit, and the coefficients (α4, α5, α6, β4, β5, β6) are determined by β3; Assume that the ultra-low orbit satellite platform is at a given fixed time t fixed The inner part is transferred from the initial position to the target position, and β3 is solved iteratively using the golden secant method: Among them, the initial value of the iteration of β3 is β 3,0 =0 and a2 is the semi-major axis of the brake track, θ f is the final transfer angle; Due to the radial velocity of the ultra-low orbit satellite platform lateral speed Therefore, the flight path angle of the ultra-low orbit satellite platform The first and second derivatives of the radial vector magnitude are: Combining formula (1) and considering the use of tangential thrust δ = γ, the angular velocity can be obtained and angular acceleration The thrust acceleration is further obtained as: where A = 1 - r 2 (a J2,ar + a drag,ar - a J2,a⊥ tanγ - a drag,a⊥ tanγ); Therefore, the required velocity increment △V of the ultra-low orbit satellite platform is: Formula (7) is used to calculate the velocity increment of the ultra-low-orbit satellite platform at different orbital altitudes in real time to control the movement of the ultra-low-orbit satellite platform.

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