Energy self-closed-loop LEO satellite-borne relay terminal power supply system

Abstract

The energy self-closed-loop LEO satellite-borne relay terminal power supply system comprises a flexible solar wing and a capacitor array, the capacitor array comprises a plurality of capacitors, and each capacitor is connected with two voltage stabilizing diodes in parallel. The flexible solar wing is used for switching an operation state according to an orbit state of a satellite and supplying power to the satellite-borne terminal and the capacitor array when the satellite is in an illumination area, and the capacitor array supplies power to the satellite-borne terminal when the satellite is in a non-illumination area, so that energy self-closed-loop of the satellite-borne terminal is realized. The system can be used for meeting the electricity demand when the satellite-borne phased array terminal works, and meanwhile, the demand and the influence on an LEO satellite bus power supply when the satellite-borne phased array terminal works are reduced.

Description

Technical Field

[0001] The present invention relates to the field of low-earth orbit satellites, and specifically to a power supply system for an on-board relay terminal of a LEO satellite with an energy self-closed loop. Background Art

[0002] The LEO satellite is equipped with an on-board phased array terminal, which is connected to a GEO relay satellite for data relay transmission. The traditional on-board phased array terminal obtains energy from the satellite bus as power supply. Since the distance between the LEO satellite and the GEO satellite exceeds 30,000 kilometers, the on-board phased array terminal requires a large transmission power to compensate for the link loss caused by the long distance, which has a great impact on the satellite energy. Summary of the Invention

[0003] To solve these problems, the present invention designs a power supply system that can provide autonomous power supply for the on-board phased array terminal of a low-earth orbit (LEO) satellite relay, which is used to solve the power consumption requirements during the operation of the on-board phased array terminal, and at the same time reduce the demand and impact on the power supply of the LEO satellite bus when the on-board phased array terminal is working.

[0004] According to the first aspect of the present invention, there is provided a power supply system for an on-board relay terminal of a LEO satellite with an energy self-closed loop, including a flexible solar wing and a capacitor array. The capacitor array includes a plurality of series capacitors, and each capacitor of the plurality of series capacitors is respectively connected in parallel with two voltage stabilizing diodes. The flexible solar wing is used to switch the operating state according to the orbital state of the satellite and supply power to the on-board terminal and the capacitor array when the satellite is in the illuminated area. The capacitor array supplies power to the on-board terminal when the satellite is in the non-illuminated area, realizing the energy self-closed loop of the on-board terminal.

[0005] The flexible solar wing collects solar energy and converts it into electrical energy during the illumination period to supply power to the on-board terminal and charge the capacitor array. During the non-illumination period, the electrical energy stored in the capacitor array is used for power supply, realizing the energy self-closed loop of the on-board terminal throughout the working cycle, and ensuring a continuous and stable energy supply for the on-board terminal. This enables the on-board terminal to effectively cope with changes in illumination conditions in the complex space environment and ensure the normal operation of the equipment. Among them, to prevent overvoltage of a single capacitor, two voltage stabilizing diodes are connected in parallel to each capacitor to achieve overvoltage protection design, and at the same time, the voltage balance of each capacitor unit can be ensured.

[0006] Preferably, the capacitor array includes three parallel-connected capacitor groups. Each of the capacitor groups includes 11 series-connected capacitors. The discharge voltage range of the capacitor array is 6 to 20V, the withstand voltage value is 36.6V, the capacitance is 218F, and the withstand voltage value of each capacitor in the capacitor array is 3.3V, and the capacitance is 800F. As a power backup capacitor array, it is necessary to consider and calculate the energy storage required for the on-board terminal to supply power by relying on its own energy storage within a certain period of time without shortening the service life. This special selection and design of energy storage capacitors ensure that the energy storage capacitors can store and release electrical energy stably and efficiently in the space environment, providing a reliable energy storage guarantee for the energy self-closed loop.

[0007] Preferably, the energy density of each capacitor in the capacitor array is ≥10 Wh / kg, and the cycle life is >1 million times. Selecting supercapacitors with high energy density can withstand faster charge and discharge cycles.

[0008] Preferably, the withstand voltage design value of the capacitor array is higher than 1.5 times the series voltage of the flexible solar wing. The optimal operating point voltage of the flexible solar wing is within the discharge voltage range of the capacitor array and is close to the midpoint position of the discharge voltage range of the capacitor array. During circuit design, the capacitor array is deliberately designed to be used with derating to ensure the stability and reliability of the power system, and the optimal operating point voltage of the battery array of the flexible solar wing is designed within the discharge area to ensure the charging efficiency of the capacitor array.

[0009] Preferably, the area of the flexible solar wing is 0.2053 m 2 , the optimal operating point voltage Vmax is 16V, the optimal operating point current Imax is 1.584A, the maximum open-circuit voltage Voc is 22.4V, and the optimal operating point power generation is 25.33W. Through the parameter design of the flexible solar wing, the energy balance during the on-orbit operation of the satellite is achieved.

[0010] Preferably, the orbital period of the on-board terminal is 94 min, the maximum shadow area time is 35 min, the minimum sun illumination area time is 59.2 min, the maximum solar incidence angle is 2°, the working period is 520 ms, where the standby mode power consumption is 12W / 500ms, the receiving mode power consumption is 30W / 10ms, the transmitting mode power consumption is 220W / 10ms, and the average power of the on-board terminal is 16.35W.

[0011] Preferably, the on-board terminal includes a DCDC regulated power supply. The DCDC regulated power supply selects a wide-input, 28V regulated output power supply module, with an input voltage range of 5 to 24V, an output voltage of 28.5V, a maximum output power of 250W, and a power supply efficiency of 85%. The DCDC regulated power supply is used to output appropriate voltage and power, and has functions such as overvoltage protection and overcurrent protection, and can provide safe and stable energy for the operation of the on-board terminal.

[0012] Preferably, it further includes a control and protection circuit, which includes a satellite bus, a diode and a switch. The control and protection circuit is connected to the on-board terminal and supplies power to the on-board terminal when there is a power supply failure or insufficiency in the on-board terminal. The satellite bus input is unidirectionally isolated by a diode to avoid mutual influence with the power supply of the on-board terminal power supply, and when there is a power system failure or the capacitor electric energy is insufficient to support the operation of the on-board terminal, the on-board phased array terminal of the on-board terminal is powered through the satellite bus. The design of multiple power supply modes ensures the safe and stable operation of the on-board terminal.

[0013] The beneficial effects of the present invention are as follows:

[0014] (1) A power supply system for an on-board relay terminal with an energy self-closed loop function is proposed. Among them, the flexible solar wing realizes the conversion of solar energy into electrical energy and the charging function, the capacitor array realizes the function of storing and releasing electrical energy, the DCDC power supply stably outputs appropriate voltage and power, and the control and protection circuit ensures the safe and stable operation of the power supply system and the satellite bus, without the need to additionally consider the energy consumption problem of the on-board phased array terminal. It reduces the complex design and investment in the energy management system, reduces the operation cost, and improves the convenience and economy of satellite applications.

[0015] (2) The configuration parameters of a power supply system for an on-board relay terminal with an energy self-closed loop function are disclosed: the LEO satellite orbit parameters, the power of the on-board terminal in different working modes, the flexible solar wing parameters, the super capacitor array parameters, etc. are optimized and configured to achieve a good adaptation of the power supply system to the satellite and the on-board terminal, and can be used as a reference design for product engineering implementation. Description of the Drawings

[0016] The drawings are included to provide a further understanding of the embodiments and are incorporated into and constitute a part of this specification. The drawings illustrate the embodiments and are used together with the description to explain the principles of the present invention. Other embodiments and many of the expected advantages of the embodiments will be readily recognized, as they become better understood by reference to the following detailed description. The elements of the drawings are not necessarily to scale with each other. The same reference numerals refer to corresponding similar components.

[0017] Figure 1 It shows a schematic structural diagram of a power supply system for an on-board relay terminal of a LEO satellite with an energy self-closed loop. Detailed Embodiments

[0018] The present application will be further described in detail below with reference to the accompanying drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the related invention, rather than limiting the invention. In addition, it should be noted that for the convenience of description, only the parts related to the invention are shown in the drawings.

[0019] In the description of the present invention, it should be noted that the terms "comprising", "including" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed, or further includes elements inherent to such process, method, article or device. The terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features.

[0020] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installed", "provided with", "sheathed / connected", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection, it can be a mechanical connection, an electrical connection, it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0021] For the convenience of those skilled in the art to understand, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments.

[0022] As Figure 1 shown, a power supply system for a LEO satellite on-board relay terminal with an energy self-closed loop includes a flexible solar wing 1, a capacitor array 2, an on-board terminal 3, and a control and protection circuit 4. The flexible solar wing 1 is provided with a solar cell array, and the solar cell array is connected in a 16-series and 4-parallel manner, and switches the operating state according to the orbital state of the satellite to convert light energy into electrical energy for power supply. The flexible solar wing 1 is in a retracted and locked state when the orbital state of the satellite is not in orbit, and is in an unfolded state when the orbital state of the satellite is in orbit.

[0023] The capacitor array 2 includes a plurality of series capacitors, and each capacitor of the plurality of series capacitors is respectively connected in parallel with two voltage stabilizing diodes. The flexible solar wing 1 is used to switch the operating state according to the orbital state of the satellite and supply power to the on-board terminal 3 and the capacitor array 2 when the satellite is in the illuminated area. The capacitor array 2 supplies power to the on-board terminal 3 when the satellite is in the non-illuminated area, realizing the energy self-closed loop of the on-board terminal 3.

[0024] Select an 800F / 3.3V supercapacitor and connect 11 in series and 3 in parallel to form a 363F / 36.3V capacitor array. That is, the capacitor array 2 includes three parallel capacitor groups. Among them, each of the capacitor groups includes 11 series-connected capacitors. The withstand voltage value of the capacitor array is greater than 1.5 times of the open-circuit voltage of the solar cell array after the first derating of 22.4V, that is, 33.6V. The discharge voltage range of the capacitor array 2 is 6-20V, and the capacitance is 218F. The withstand voltage value of each capacitor in the capacitor array is 3.3V, and the capacitance is 800F. The energy density of each capacitor in the capacitor array is ≥10Wh / kg, and the cycle life is >1 million times.

[0025] The connection method and the regulated voltage value of the two zener diodes connected in parallel on each capacitor are the same. In one embodiment, according to the design of the capacitor array 2, two zener diodes with a regulated voltage value of 3.3V are selected for each capacitor in parallel, and the current-carrying capacity of the circuit of the capacitor array 2 is improved through the two zener diodes.

[0026] The withstand voltage design value of the capacitor array 2 is higher than 1.5 times of the series voltage of the flexible solar wing 1. The optimal operating point voltage of the flexible solar wing 1 is within the discharge voltage range of 6-20V of the capacitor array, and is close to the midpoint position of the 6-20V range. The purpose is to make the optimal operating point voltage of the flexible solar wing 1 within the actual operating voltage of the capacitor array 2, improve the power generation efficiency of the flexible solar wing 1, and achieve the optimal operating point power generation power of the flexible solar wing.

[0027] The area of the flexible solar wing 1 is 0.2053m 2 , the optimal operating point voltage Vmax is 16V, the optimal operating point current Imax is 1.584A, the maximum open-circuit voltage Voc is 22.4V, and the optimal operating point power generation power is 25.33W. During on-orbit operation, the flexible solar wing can output 25.33Wh of electric energy per orbit.

[0028] The orbital period of the on-board terminal 3 is 94min, the maximum shadow area time is 35min, the minimum sun illumination area time is 59.2min, the maximum solar incidence angle is 2°, the working period is 520ms, among which the standby mode power consumption is 12W / 500ms, the receiving mode power consumption is 30W / 10ms, the transmitting mode power consumption is 220W / 10ms, and the average power of the on-board terminal is 16.35W.

[0029] According to the calculation of E = 1 / 2 * C * (U 12 -U 22 ), the capacitor array 2 can store 11.35Wh of electric energy. Considering the losses of power supplies, diodes, etc., the capacitor array 2 can provide at most 9.65Wh of electric energy at the output end of the power supply system, and can support the on-board terminal to work for 35.43min per orbit.

[0030] After the above calculations and verifications, at any time within an orbital period, the on-board terminal power supply system can rely on its own power generation, energy storage, and power supply functions to support a maximum working duration of about 35 minutes per orbit, basically realizing the function of the on-board terminal energy self-closed loop.

[0031] The on-board terminal 3 includes a DCDC regulated power supply 31. The DCDC regulated power supply selects a wide-input, 28V regulated-output power supply module with an input voltage range of 5 - 24V, an output voltage of 28.5V, a maximum output power of 250W, and a power efficiency of 85%. The DCDC regulated power supply is used to output appropriate voltage and power and has functions such as overvoltage protection and overcurrent protection, which can provide safe and stable energy for the operation of the on-board terminal.

[0032] The control and protection circuit 4 includes a 28V satellite bus, a diode, and a switch. The control and protection circuit is connected in series with the on-board phased array terminal 32 of the on-board terminal. When the on-board terminal 3 has insufficient power supply or a fault in the flexible solar wing 1 and the capacitor array 2, it can rely on the satellite bus for power supply, and the satellite bus can avoid being affected by the on-board terminal fault; when necessary, the relay switch can be controlled by an instruction to disconnect the connection between the on-board terminal and the bus. The branches where the DCDC regulated power supply 31 and the satellite bus are located are respectively isolated unidirectionally by diodes to avoid mutual influence on power supply.

[0033] The above description is only the preferred embodiment of the present application and the explanation of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by the specific combination of the above technical features, but also covers other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above inventive concept. For example, the technical solutions formed by mutually replacing the above features with the (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. An on-board relay terminal power supply system for LEO satellites with an energy self-closed loop, characterized in that, It includes a flexible solar wing and a capacitor array. The capacitor array includes a plurality of capacitors, and each of the plurality of capacitors is respectively connected in parallel with two zener diodes. The flexible solar wing is used to switch the operating state according to the orbital state of the satellite and supply power to the on-board terminal and the capacitor array when the satellite is in the illuminated area. The capacitor array supplies power to the on-board terminal when the satellite is in the non-illuminated area, realizing the energy self-closed loop of the on-board terminal.

2. The power supply system of the LEO satellite on-board relay terminal with an energy self-closed loop according to claim 1, characterized in that, The capacitor array includes three parallel-connected capacitor groups. Among them, each capacitor group includes 11 series-connected capacitors. The discharge voltage range of the capacitor array is 6-20V, the withstand voltage value is 36.6V, and the capacitance is 218F. The withstand voltage value of each capacitor in the capacitor array is 3.3V, and the capacitance is 800F.

3. The power supply system of the LEO satellite on-board relay terminal with an energy self-closed loop according to claim 2, characterized in that, The energy density of each capacitor in the capacitor array is ≥10Wh / kg, and the cycle life is >1 million times.

4. The on-board relay terminal power supply system of a LEO satellite with an energy self-closed loop according to claim 2, wherein, The withstand voltage value of the capacitor array is higher than 1.5 times the maximum open-circuit voltage of the flexible solar wing. The optimal operating point voltage of the flexible solar wing is within the discharge voltage range of the capacitor array and is close to the midpoint position of the discharge voltage range of the capacitor array.

5. The power supply system of a LEO satellite on-board relay terminal with an energy self-closed loop according to claim 4, characterized in that, The area of the flexible solar wing is 0.2053 m 2 , the optimal operating point voltage Vmax is 16 V, the optimal operating point current Imax is 1.584 A, the maximum open-circuit voltage Voc is 22.4 V, and the power generation at the optimal operating point is 25.33 W.

6. The power supply system of the LEO satellite on-board relay terminal with an energy self-closed loop according to claim 5, characterized in that The orbital period of the on-board terminal is 94min, the maximum shadow area time is 35min, the minimum sunlit area time is 59.2min, the maximum solar incidence angle is 2°, and the operating cycle is 520ms. Among them, the standby mode power consumption is 12W / 500ms, the receiving mode power consumption is 30W / 10ms, the receiving mode power consumption is 220W / 10ms, and the average power of the on-board terminal is 16.35W.

7. The power supply system of the LEO satellite on-board relay terminal with an energy self-closed loop according to claim 6, characterized in that, The on-board terminal includes a DCDC voltage regulator power supply. The DCDC voltage regulator power supply selects a wide-input, 28V regulated output power supply module. The input voltage range is 5-24V, the output voltage is 28.5V, the maximum output power is 250W, and the power supply efficiency is 85%.

8. The on-board relay terminal power supply system of a LEO satellite with an energy self-closed loop according to claim 1, characterized in that, It further includes a control and protection circuit. The control and protection circuit includes a satellite bus, a diode and a switch. The control and protection circuit is connected to the on-board terminal and supplies power to the on-board terminal in case of power supply failure or insufficiency of the on-board terminal.

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