Method for improving multi-satellite cooperative pulse type orbit control efficiency of single-component satellites in orbit

Abstract

The invention discloses a method for improving the multi-satellite cooperative pulse type orbit control efficiency of a single-component satellite in orbit. The method comprises the steps that 1, the temperature of a single-component thruster catalyst bed is heated to the set temperature; 2, an electromagnetic valve of the current orbit control thruster is controlled to be opened for a certain time T; 3, after waiting for a certain time delta T, repeating the step 2; 4, if the circulation stopping condition is met, stopping circulation of the steps 2-3; otherwise, continuing the circulation of the steps 2-3; 5, if other orbit control thrusters exist, the steps 2-4 are repeated for each other orbit control thruster; otherwise, executing the step 6; and 6, pulse type orbit control is executed through the satellite control computer, and a single-component thruster catalytic bed heating loop is closed. The method provided by the invention is suitable for the condition that multi-satellite networking cooperative work adopts pulse-type orbit control, can effectively solve the problem of low efficiency of multi-satellite networking accurate phase adjustment pulse-type orbit control, and realizes accurate and meticulous phase adjustment between networking satellites.

Description

Technical Field

[0001] The present invention belongs to the technical field of multi-satellite network coordination, and in particular relates to a method for improving the efficiency of pulsed orbit control of multi-satellite coordination of monopropellant satellites on orbit. Background Art

[0002] Currently, more and more constellation satellites are working in a collaborative manner in the form of networking. For the collaborative work of multiple satellites, when phase fine-tuning is required, a pulsed orbit control method can be used. The orbit control time is tens to hundreds of milliseconds, realizing precise and detailed phase adjustment between networked satellites.

[0003] Currently, most satellite monopropellant propulsion systems use a catalytic decomposition reaction to generate gas as a propellant, providing kinetic energy for the satellite. Catalytic decomposition requires the absorption of thermal energy, so the catalyst bed must be heated for a certain period of time before the propellant can fully react. In the case of pulsed orbit control, the short pulse duration of the orbit control thruster results in low orbit control efficiency, affecting orbit control accuracy. In addition, since the orbit control thruster valve uses a solenoid valve with a rubber sealing ring inside, the rubber material may experience hysteresis when the solenoid valve is suddenly opened after being closed for a long time. As a result, the solenoid valve opening will be less than the preset value, causing the amount of propellant entering the reaction chamber to be less than the theoretical value, resulting in a small thrust. After the solenoid valve undergoes the opening action, the rubber material is in a "wake-up" state, and the subsequent valve action returns to normal, and the propellant flow and thrust values tend to be normal. For general launch missions, when a single satellite is working in orbit, the impact of a single satellite's orbit control error on the satellite mission is usually negligible. However, for the working condition analysis of multiple satellite networks, a certain phase relationship must be maintained between the multiple satellites. The orbit control strategy between the multiple satellites is uniformly designed through the constraints of the phase box. If the orbit control accuracy of each single satellite is low, it will lead to increased fuel consumption and inaccurate phase layout of the networked satellites, and multiple orbit adjustments are required to achieve the corresponding networking purpose. Summary of the Invention

[0004] The technology of the present invention solves the problem: it overcomes the shortcomings of the existing technology and provides a method for improving the efficiency of pulse orbit control of multi-satellite collaboration of single-component satellites on orbit. The method is suitable for the situation where pulse orbit control is adopted for the collaborative work of multiple satellite networks. It can effectively solve the problem of low efficiency of pulse orbit control for precise phase adjustment of multi-satellite networks and realize precise and detailed phase adjustment between networked satellites.

[0005] In order to solve the above technical problems, the present invention discloses a method for improving the efficiency of pulsed orbit control of multiple satellites coordinated by a monopropellant satellite on orbit, comprising:

[0006] Step 1: according to the ground injection instruction, the monopropellant thruster catalyst bed heating circuit is turned on to heat the monopropellant thruster catalyst bed temperature to the set temperature;

[0007] Step 2: Based on the orbit control pre-injection pulse width sequence of the current orbit control thruster recorded on the ground, the satellite control computer controls the solenoid valve of the current orbit control thruster to open for a certain time T;

[0008] Step 3: After waiting for a certain time ΔT, repeat step 2;

[0009] Step 4: In the loop of steps 2 and 3, determine whether a loop stop condition is met based on the change in angular velocity Δω of the satellite's gyroscope on a certain axis corresponding to the current orbit control thruster; if the loop stop condition is met, stop the loop of steps 2 and 3 and execute step 5; otherwise, continue the loop of steps 2 and 3;

[0010] Step 5: Determine whether there are other orbital control thrusters. If there are other orbital control thrusters, repeat steps 2 to 4 for each of the other orbital control thrusters. Otherwise, proceed to step 6.

[0011] Step 6: Based on the satellite pulsed orbit control data block injected on the ground, the satellite control computer executes pulsed orbit control and closes the monopropellant thruster catalytic bed heating circuit.

[0012] In the above-mentioned method for improving the efficiency of pulsed orbit control of multiple monopropellant satellites in orbit, the set temperature refers to: meeting the temperature required for catalytic decomposition of the propellant.

[0013] The above-mentioned method for improving the efficiency of pulsed orbit control of multiple monopropellant satellites in orbit also includes: determining T and ΔT based on a pre-injection pulse width sequence before orbit control.

[0014] In the above-mentioned method for improving the efficiency of pulsed orbit control of a monopropellant satellite with multiple satellites coordinated on-orbit, T=100ms.

[0015] In the above-mentioned method for improving the efficiency of pulsed orbit control of multiple-satellite coordinated monopropellant satellites on orbit, ΔT=20s.

[0016] In the above-mentioned method for improving the efficiency of pulsed orbit control of a monopropellant satellite in multi-satellite coordinated operation, the change in angular velocity of a certain axis of the satellite, Δω, is used to characterize the thrust of the corresponding orbit control thruster.

[0017] In the above-mentioned method for improving the efficiency of pulsed orbit control of a monopropellant satellite in multi-satellite coordination on-orbit, in step 4, if Δω reaches the set value, it is determined that the thrust of the corresponding orbit control thruster reaches the nominal thrust value, and the cycle stop condition is met.

[0018] In the above-mentioned method for improving the efficiency of pulsed orbit control of a monopropellant satellite in multi-satellite coordination on orbit, the thrust F of the orbit control thruster and Δω satisfy the following relationship:

[0019] F=(I×Δω) / (Δt×L)

[0020] Where I represents the moment of inertia of a satellite axis corresponding to the orbit control thruster, Δt represents the change time, and L represents the size of the lever arm.

[0021] The present invention has the following advantages:

[0022] (1) The present invention discloses a method for improving the efficiency of pulsed orbit control of a monopropellant satellite in orbit, which can effectively solve the problem of low efficiency of pulsed orbit control for a monopropellant propulsion system with the need for precise phase adjustment of a multi-satellite network, and greatly improve the efficiency of pulsed orbit control.

[0023] (2) The present invention discloses a method for improving the efficiency of pulsed orbit control of multiple satellites in a single-component satellite in orbit, so that the satellite can achieve precise control of the orbital phase, improve the orbital control accuracy of each single satellite in the networked satellites, reduce the fuel consumption of the networked satellites, and achieve precise phase layout of the networked satellites.

[0024] (3) The present invention discloses a method for improving the efficiency of pulsed orbit control of multiple satellites in a single-component satellite in orbit, which can be widely used in spacecraft propulsion systems. It is not limited to multi-satellite collaboration and can be extended to single-satellite pulsed orbit control application scenarios. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 Schematic diagram of factors affecting the performance of a track control thruster according to an embodiment of the present invention;

[0026] Figure 2 This is a graph of a steady-state ignition combustion pressure curve for a monopropellant thruster according to an embodiment of the present invention;

[0027] Figure 3 This is a continuous pulse combustion pressure curve diagram of a monopropellant thruster in an embodiment of the present invention;

[0028] Figure 4 This is a flow chart of a method for improving the efficiency of multi-satellite coordinated pulse orbit control of a monopropellant satellite in orbit according to an embodiment of the present invention. DETAILED DESCRIPTION

[0029] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be described in further detail below with reference to the accompanying drawings.

[0030] When the orbital control thruster is working on orbit, it is in a vacuum environment. The main factor that determines the thrust characteristics of the orbital control thruster is the catalytic reaction efficiency. Figure 1As shown, the efficiency of the catalytic reaction is related to three points: the temperature of the catalyst bed, the mixing degree of hydrazine and the catalyst, and the catalytic reaction time. If the heat energy provided for the decomposition is insufficient, the catalytic efficiency of the catalyst in the thruster will be reduced, the chemical reaction will be insufficient, the temperature and speed of the generated gas will be lower than the rated operating conditions, and the thrust will be lower than the theoretical value, resulting in the orbit control effect being lower than expected.

[0031] Further, such as Figure 2 and Figure 3 ( Figure 2 and Figure 3 A comparison of the propellant flow rates (all obtained from actual ground-based thruster firings) shows that under short-pulse conditions, the amount of propellant flowing from the solenoid valve into the orbital thruster reaction chamber is small, preventing it from fully mixing with the catalyst installed there. Consequently, the distribution of the propellant within the reaction chamber is highly random. Furthermore, the short reaction time results in an incomplete catalytic reaction between the propellant and catalyst, resulting in an unpredictable and below-rated temperature and pressure for the generated propellant vapor. Consequently, occasional thrust output instability is unavoidable under short-pulse conditions.

[0032] In addition, the orbital control thruster solenoid valve contains a rubber sealing ring. When the solenoid valve is suddenly opened after being closed for a long time, the rubber material may experience hysteresis. As a result, the solenoid valve opening will be less than the preset value, causing the amount of propellant entering the reaction chamber to be less than the theoretical value, resulting in low thrust.

[0033] In response to the above problems, the present invention discloses a method for improving the efficiency of pulsed orbit control of multi-satellite coordinated monopropellant satellites on orbit, wherein the catalytic bed of the monopropellant thruster is preheated by short pulse jets, thereby improving the efficiency of pulsed orbit control, improving the orbit control accuracy and saving fuel; through the subsequent steps of this method, pre-jet is performed so that the rubber material is in a "wake-up" state after the solenoid valve undergoes an opening action; at the same time, the catalyst and the propellant are pre-contacted, a small amount of catalytic reaction occurs, and the temperature of the catalytic bed is increased, which can make the subsequent reaction more sufficient and maintain a stable pressure output; this method is applicable to the situation where pulsed orbit control is adopted for the coordinated work of multiple satellite networks, and can effectively solve the problem of low efficiency of pulsed orbit control for precise phase adjustment of multiple satellite networks, and realize precise and detailed phase adjustment between networked satellites.

[0034] Reference Figure 4 In this embodiment, the method for improving the efficiency of pulsed orbit control of a multi-satellite coordinated monopropellant satellite on orbit includes:

[0035] Step 1: Based on the ground injection command, the monopropellant thruster catalyst bed heating circuit is activated to heat the monopropellant thruster catalyst bed to a set temperature. The set temperature refers to the temperature required for catalytic decomposition of the propellant.

[0036] Step 2: Based on the orbit control pre-injection pulse width sequence of the current orbit control thruster recorded on the ground, the satellite control computer controls the solenoid valve of the current orbit control thruster to open for a certain time T (i.e., pulse duration).

[0037] Step 3: After waiting for a certain time ΔT (i.e., interval time), repeat step 2.

[0038] In this embodiment, T and ΔT are determined based on the pre-track control pre-injection pulse width sequence. Specifically, the pre-track control pre-injection pulse width sequence includes the duration of each solenoid valve opening and the interval between two adjacent solenoid valve openings. The pre-track control pre-injection pulse width sequence can be determined based on actual conditions, i.e., T and ΔT can be determined based on actual conditions, for example: T = 100 ms, ΔT = 20 s.

[0039] Step 4: In the loop of steps 2 to 3, determine whether the loop stop condition is met based on the change in gyro angular velocity Δω of a certain axis of the satellite corresponding to the current orbit control thruster.

[0040] In this embodiment, the change in gyro angular velocity Δω of a satellite axis is used to represent the thrust of the corresponding orbital control thruster. If Δω reaches a set value, it is determined that the thrust of the corresponding orbital control thruster has reached the nominal thrust value, meeting the loop stop condition. Steps 2 and 3 are stopped and step 5 is executed. Otherwise, the loop of steps 2 and 3 continues.

[0041] The thrust F of the orbit control thruster and Δω satisfy the following relationship:

[0042] F=(I×Δω) / (Δt×L)

[0043] Where I represents the moment of inertia of a satellite axis corresponding to the orbit control thruster, Δt represents the change time, and L represents the size of the lever arm.

[0044] Step 5: Determine whether there are other orbital control thrusters.

[0045] In this embodiment, if there are other orbit control thrusters, steps 2 to 4 are repeated for each of the other orbit control thrusters; otherwise, step 6 is executed.

[0046] Step 6: Based on the satellite pulsed orbit control data block injected on the ground, the satellite control computer executes pulsed orbit control and closes the monopropellant thruster catalytic bed heating circuit.

[0047] In this embodiment, it should be noted that the aforementioned T, ΔT, and thrust nominal values may be set according to the actual conditions of the orbital control thruster, and this embodiment does not impose any limitation thereto.

[0048] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

[0049] The contents not described in detail in the specification of the present invention belong to the common knowledge of professionals in this field.

Claims

1. A method for improving the efficiency of pulsed orbit control of a multi-satellite coordinated monopropellant satellite on orbit, characterized in that: include: Step 1: according to the ground injection instruction, the monopropellant thruster catalyst bed heating circuit is turned on to heat the monopropellant thruster catalyst bed temperature to the set temperature; Step 2: Based on the orbit control pre-injection pulse width sequence of the current orbit control thruster recorded on the ground, the satellite control computer controls the solenoid valve of the current orbit control thruster to open for a certain time T; Step 3: After waiting for a certain time ΔT, repeat step 2; Step 4: In the loop of steps 2 and 3, determine whether a loop stop condition is met based on the change in angular velocity Δω of the satellite's gyroscope on a certain axis corresponding to the current orbit control thruster; if the loop stop condition is met, stop the loop of steps 2 and 3 and execute step 5; otherwise, continue the loop of steps 2 and 3; Step 5: Determine whether there are other orbital control thrusters. If there are other orbital control thrusters, repeat steps 2 to 4 for each of the other orbital control thrusters. Otherwise, proceed to step 6. Step 6: Based on the satellite pulsed orbit control data block injected on the ground, the satellite control computer executes pulsed orbit control and closes the monopropellant thruster catalytic bed heating circuit.

2. The method for improving the efficiency of pulsed orbit control of a monopropellant satellite in orbit according to claim 1, characterized in that: The set temperature refers to the temperature required to meet the catalytic decomposition of the propellant.

3. The method for improving the efficiency of pulsed orbit control of a monopropellant satellite in orbit according to claim 1, characterized in that: Also includes: Determine T and ΔT based on the pre-injection pulse width sequence before orbit control.

4. The method for improving the efficiency of pulsed orbit control of a monopropellant satellite in orbit according to claim 1 or 3, characterized in that: T=100ms.

5. The method for improving the efficiency of pulsed orbit control of a monopropellant satellite in orbit according to claim 1 or 3, characterized in that: ΔT=20s.

6. The method for improving the efficiency of pulsed orbit control of a monopropellant satellite in orbit according to claim 1, characterized in that: The change in the angular velocity of the satellite's gyroscope on a certain axis, Δω, is used to characterize the thrust of the corresponding orbit control thruster.

7. The method for improving the efficiency of pulsed orbit control of a monopropellant satellite in orbit according to claim 1 or 6, characterized in that: In step 4, if Δω reaches the set value, it is determined that the thrust of the corresponding orbit control thruster reaches the nominal thrust value, and the cycle stop condition is met.

8. The method for improving the efficiency of pulsed orbit control of a monopropellant satellite in orbit according to claim 1, characterized in that: The thrust F of the orbit control thruster and Δω satisfy the following relationship: F=(I×Δω) / (Δt×L) Where I represents the moment of inertia of a satellite axis corresponding to the orbit control thruster, Δt represents the change time, and L represents the size of the lever arm.

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