A power system for a cross-airspace reusable spaceplane

Abstract

This invention discloses a reusable, cross-spacecraft power system for aerospace vehicles, relating to the field of aerospace technology. The power system includes a parallel-connected TBCC power extraction system, a solar thermal power generation system, a high-voltage battery, a solar cell array, and a first high-voltage bus (HV). BUS 1. Second high-voltage busbar HV BUS 2. Low-voltage busbar LV BUS The system comprises a first DC / DC converter, a second DC / DC converter, a third DC / DC converter, and a series of circuit breakers controlling the power supply switching status. The parallel TBCC power extraction system, in conjunction with the solar thermal power generation system, the solar cell array, and the high-voltage battery, achieves uninterrupted power supply across space. This invention integrates space transportation and on-orbit operation capabilities, exhibiting extremely high adaptability and mobility.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a reusable power system for aerospace vehicles that can operate across airspace. Background Technology

[0002] With the increasing demand for integrated aerospace transportation and missions, trans-space vehicles, as a new generation of aircraft, can freely shuttle between the atmosphere and space, possessing both space transportation and on-orbit operation capabilities. They exhibit extremely high adaptability and maneuverability, representing an important direction for the future development of integrated aerospace. These trans-space operations place higher demands on the vehicle's power system, requiring it to simultaneously meet characteristics such as multi-energy supply, strong power adaptability, wide environmental adaptability, and reusability.

[0003] Most existing aircraft power systems are powered by a single energy source and are often limited to a specific airspace or operating mode. For example, systems relying solely on solar cells or chemical batteries struggle to simultaneously support high-speed flight and carry high-power loads. Furthermore, traditional power architectures exhibit significant limitations in energy scheduling, load isolation, and system redundancy when faced with complex variations in sunlight and ground shadows and changes in aircraft status. Therefore, there is an urgent need for a comprehensive power supply system architecture for aerospace vehicles that is multimodal, can traverse large airspaces, and is reusable. Summary of the Invention

[0004] The purpose of this invention is to provide a reusable power system for aerospace vehicles that can be used across airspace, enabling dynamic coordination of different power supply modules based on the airspace status and operating conditions of the vehicle, thereby providing continuous power supply for multi-stage flight missions.

[0005] To achieve the above objectives, the present invention provides the following solution: A reusable aerospace vehicle power system that spans multiple airspaces is characterized by comprising: a parallel TBCC (Turbine-Based Combined Cycle) power extraction system, a solar thermal power generation system, a high-voltage battery, a solar cell array, a first high-voltage bus, a second high-voltage bus, a low-voltage bus, a first DC / DC converter, a second DC / DC converter, a third DC / DC converter, and a series of circuit breakers for controlling the power supply switching status; The parallel TBCC power extraction system switches modes within the atmosphere according to the Mach number of the aircraft. In the low Mach number phase, the turbine engine drives the generator to generate electricity, while in the high Mach number phase, the ramjet engine drives the generator to generate electricity. After the aircraft enters orbit, the solar thermal power generation system and the solar cell array jointly provide power in the sunlit area, while the high-voltage battery mainly powers the critical loads in the shadow area, achieving uninterrupted power supply across airspace. The output of the parallel TBCC power extraction system is connected to the first high-voltage bus; the output of the solar thermal power generation system is connected to the second high-voltage bus via the third circuit breaker; the output of the high-voltage battery is connected to the second high-voltage bus via the first DC / DC converter and the battery circuit breaker; the output of the solar cell array is connected to the low-voltage bus via the third DC / DC converter and the solar cell circuit breaker. The first high-voltage busbar supplies power to the electrically operated loads and critical loads; the second high-voltage busbar is connected to the first high-voltage busbar via a busbar circuit breaker and supplies power to the thruster. The second high-voltage bus is connected to the low-voltage bus via a second DC / DC converter and a converter circuit breaker; the low-voltage bus supplies power to general loads.

[0006] According to specific embodiments provided by the present invention, the present invention has the following technical effects: This invention achieves seamless power supply switching for the spacecraft during Mach number flight and orbital operation phases by combining an atmospheric parallel TBCC power extraction system with a high-voltage battery, solar thermal power generation system, and solar cell array during the orbital phase. The synergistic power generation of the solar thermal power generation system and the solar cell array improves power generation efficiency and adaptability to sunlight. This is achieved through the first high-voltage bus HV... BUS 1. Second high-voltage busbar HV BUS 2 and low voltage bus LV BUS The separate design allows for independent power supply to different types of loads when power is sufficient, improving system power supply stability. The high-voltage battery can power critical loads in the Earth's shadow and during unpowered reentry phases. It supports bidirectional energy flow between solar and chemical energy and possesses bidirectional energy control capabilities, adapting to multi-condition energy dispatch strategies. This invention integrates space transportation and on-orbit operation capabilities, demonstrating extremely high adaptability and maneuverability. Attached Figure Description

[0007] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0008] Figure 1 A schematic diagram of the power system structure for a reusable aerospace vehicle that spans multiple airspaces is provided as an embodiment of the present invention. Figure 2 This is a schematic diagram of different mission conditions of an aircraft provided in an embodiment of the present invention; Figure 3This is a schematic diagram of the system power flow direction during high-speed flight within the atmosphere, provided as an embodiment of the present invention. Figure 4 This is a schematic diagram of the power flow direction of the system in the illuminated area after orbit insertion, provided by an embodiment of the present invention. Figure 5 This is a schematic diagram of the system power flow direction in the shadow region after orbit insertion, provided as an embodiment of the present invention. Detailed Implementation

[0009] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. 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.

[0010] The purpose of this invention is to provide a reusable power system for aerospace vehicles that can be used across airspace, enabling dynamic coordination of different power supply modules based on the airspace status and operating conditions of the vehicle, thereby providing continuous power supply for multi-stage flight missions.

[0011] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0012] Example 1

[0013] like Figure 1 As shown, this embodiment provides a cross-space reusable aerospace vehicle power system, including: a parallel TBCC power extraction system, a solar thermal power generation system, a high-voltage battery, a solar cell array, and a first high-voltage bus HV. BUS 1. Second high-voltage busbar HV BUS 2. Low-voltage busbar LV BUS The system includes a first DC / DC converter (DC / DC1), a second DC / DC converter (DC / DC2), a third DC / DC converter (DC / DC3), and a series of circuit breakers that control the switching status of the power supply.

[0014] The parallel TBCC power extraction system switches modes within the atmosphere according to the aircraft's Mach number. In the low Mach number phase, the turbine engine drives the generator to generate electricity, while in the high Mach number phase, the ramjet engine drives the generator to generate electricity.

[0015] Solar thermal power generation systems are used to convert solar heat into electricity in the orbital sunshine zone after an aircraft enters orbit.

[0016] The output of the parallel TBCC power extraction system is connected to the first high-voltage bus HV. BUS1. The output of the solar thermal power generation system is connected to the second high-voltage bus HV via the third circuit breaker GCB3. BUS 2. The output of the high-voltage battery is connected to the second high-voltage bus HV via the first DC / DC converter DC / DC1 and the battery circuit breaker BATB. BUS 2. The output of the solar array is connected to the low-voltage bus LV via the third DC / DC converter DC / DC3 and the solar circuit breaker PVB. BUS .

[0017] First high-voltage bus HV BUS 1. Power is supplied to electrically actuated loads, such as electric fuel pumps and electric brakes, and critical loads, such as avionics and communications. Second High-Voltage Bus HV BUS 2. The circuit breaker BTB is connected to the first high-voltage bus HV via the busbar. BUS Connected to 1, it supplies power to the thruster; Second high-voltage bus HV BUS 2. Connected to the low-voltage bus LV via the second DC / DC converter DC / DC2 and the converter circuit breaker CONVB. BUS Low-voltage busbar LV BUS Powers general loads (low-power loads).

[0018] The parallel TBCC power extraction system works in conjunction with the solar thermal power generation system, solar cell array, and high-voltage battery to achieve uninterrupted power supply across airspace.

[0019] The parallel TBCC power extraction system includes a turbine engine, a ramjet engine, a first generator (generator 1), a second generator (generator 2), a first AC / DC converter (AC / DC1), a second AC / DC converter (AC / DC2), a first circuit breaker (GCB1), and a second circuit breaker (GCB2). The turbine engine drives the first generator at low Mach numbers (0–3 Ma), while the ramjet engine drives the second generator at high Mach numbers (3–5 Ma). The output of the first generator is connected to the first high-voltage bus HV via the first AC / DC converter (AC / DC1) and the first circuit breaker (GCB1). BUS 1. The output of the second generator is connected to the first high-voltage bus HV via the second AC / DC converter AC / DC2 and the second circuit breaker GCB2. BUS 1.

[0020] The first DC / DC converter and the second DC / DC converter have bidirectional power flow control capabilities. The first DC / DC converter controls the charging and discharging of the high-voltage battery, while the second DC / DC converter coordinates the power between the high-voltage and low-voltage buses.

[0021] The solar thermal power generation system includes a solar thermal power system, a third generator (generator 3), and a third AC / DC converter (AC / DC3). Its energy conversion process is solar energy → thermal energy → mechanical energy → electrical energy. The solar thermal power system is an energy conversion system that integrates solar radiation and converts thermal energy into mechanical energy to drive the third generator (generator 3). The output of the third generator is connected to the second high-voltage bus HV via the third AC / DC converter (AC / DC3) and the third circuit breaker (GCB3). BUS 2. When sunlight conditions are good, the solar thermal power generation system and the solar cell array work together to charge the high-voltage battery, enabling battery recycling and improving energy utilization efficiency and energy storage capacity.

[0022] The cross-space reusable aerospace vehicle power system of the present invention adopts a multi-bus design, including a first high-voltage bus HV. BUS 1. Second high-voltage busbar HV BUS 2 and low-voltage bus LV BUS Among them, the low-voltage bus LV BUS Primarily supplies power to low-power loads such as airborne payloads, with relatively low voltage levels; the first high-voltage bus HV BUS 1 and Second High Voltage Bus HV BUS 2 respectively supply power to critical loads, electrically operated loads and high-power loads such as thrusters, with voltages up to 270V, 540V or even higher.

[0023] This invention covers the entire process of an aircraft, from takeoff to automatic landing. For example... Figure 2 As shown, from takeoff to orbit insertion, the system is powered by a parallel TBCC (Total Biologically Targeted Controlled Carrier) power extraction system. This includes typical modes such as turbine engine operation, mode switching, and ramjet engine operation, covering the acceleration and hypersonic flight phases. After orbit insertion, the system is divided into a lit zone and a shadow zone based on sunlight intensity. The lit zone is powered by a combination of a solar thermal power generation system and a solar array; if sunlight intensity is high, excess power can be stored in high-voltage batteries. In the shadow zone, high-voltage batteries primarily power critical loads. During the return flight, the high-voltage batteries primarily power critical loads during the unpowered return phase, ensuring uninterrupted power supply to critical loads before the engine restart phase. Subsequently, with the turbine engine starting, the turbine engine drives the first generator (generator 1) to power the loads until landing.

[0024] This invention enables aircraft to fly at high speeds within the atmosphere. For example... Figure 3 As shown, during the takeoff and turbine engine operation phase, the turbine engine drives generator 1 to supply power to the critical loads and electrically operated loads.

[0025] During the mode switching phase, generator 1, driven by the turbine engine, and generator 2, driven by the ramjet engine, work together to supply power to the load. If generator 1 and generator 2 cannot meet the load's power supply needs at this time, a high-voltage battery can be connected in parallel via a busbar connected to the circuit breaker (BTB) to supplement the power deficit. After the mode switching is completed, the turbine engine exits the system, and generator 2, driven by the ramjet engine, supplies power to the load entirely.

[0026] This invention enables continuous power supply and charging of high-voltage batteries in illuminated areas. For example... Figure 4 As shown, when the spacecraft is in the sunlit area of ​​its orbit, the solar array and the solar thermal power generation system work together to generate electricity and continuously supply power to the thrusters and general loads through the high-voltage bus. At the same time, if there is power redundancy, the high-voltage battery can be charged.

[0027] This invention enables power supply to critical loads in the shadow region. For example... Figure 5 As shown, when the spacecraft enters the orbital shadow zone and solar power cannot directly supply power, the system automatically switches to high-voltage battery power supply mode, mainly to provide reliable power support for critical loads and ensure the continuity and safety of orbital operation.

[0028] High-voltage batteries support redundant power storage when supplying power to solar arrays or solar thermal power generation systems, thereby enabling them to power critical loads during the return phase and possessing reusability.

[0029] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0030] This document uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A power system for a spaceplane that is reusable across airspaces, characterized by: It includes a parallel TBCC power extraction system, a solar thermal power generation system, a high-voltage battery, a solar cell array, a first high-voltage bus, a second high-voltage bus, a low-voltage bus, a first DC / DC converter, a second DC / DC converter, a third DC / DC converter, and a series of circuit breakers for controlling the switching status of the power supply; The parallel TBCC power extraction system switches modes within the atmosphere according to the Mach number of the aircraft. In the low Mach number phase, the turbine engine drives the generator to generate electricity, while in the high Mach number phase, the ramjet engine drives the generator to generate electricity. After the aircraft enters orbit, the solar thermal power generation system and the solar cell array jointly provide power in the sunlit area, while the high-voltage battery mainly powers the critical loads in the shadow area, achieving uninterrupted power supply across airspace. The output of the parallel TBCC power extraction system is connected to the first high-voltage bus; the output of the solar thermal power generation system is connected to the second high-voltage bus via the third circuit breaker; the output of the high-voltage battery is connected to the second high-voltage bus via the first DC / DC converter and the battery circuit breaker; the output of the solar cell array is connected to the low-voltage bus via the third DC / DC converter and the solar cell circuit breaker. The first high-voltage busbar supplies power to the electrically operated loads and critical loads; the second high-voltage busbar is connected to the first high-voltage busbar via a busbar circuit breaker and supplies power to the thruster. The second high-voltage bus is connected to the low-voltage bus via a second DC / DC converter and a converter circuit breaker; the low-voltage bus supplies power to general loads.

2. The cross-space reusable aerospace vehicle power system according to claim 1, characterized in that: The parallel TBCC power extraction system includes a turbine engine, a ramjet engine, a first generator, a second generator, a first AC / DC converter, a second AC / DC converter, a first circuit breaker, and a second circuit breaker. The turbine engine drives the first generator to generate electricity in the low Mach number stage, and the ramjet engine drives the second generator to generate electricity in the high Mach number stage. The output of the first generator is connected to the first high-voltage bus via the first AC / DC converter and the first circuit breaker, and the output of the second generator is connected to the first high-voltage bus via the second AC / DC converter and the second circuit breaker.

3. The cross-space reusable aerospace vehicle power system according to claim 1, characterized in that: The first DC / DC converter and the second DC / DC converter have bidirectional power flow control capability. The first DC / DC converter realizes the charging and discharging control of the high-voltage battery, and the second DC / DC converter realizes the power coordination between the high-voltage and low-voltage buses.

4. The cross-airspace reusable spaceplane power system of claim 1, wherein: The solar thermal power generation system includes a solar thermal power system, a third generator, and a third AC / DC converter. The solar thermal power system drives the third generator to generate electricity. The output of the third generator is connected to the second high-voltage bus via the third AC / DC converter and a third circuit breaker. When the solar thermal power generation system and the solar cell array are in good sunlight conditions, they work together to charge the high-voltage battery, realizing battery recycling and improving energy utilization efficiency and energy storage capacity.

5. The cross-space reusable aerospace vehicle power system according to claim 1, characterized in that: The high-voltage battery supports redundant power storage when the solar cell array or solar thermal power generation system is powered, thereby realizing power supply for key loads in the return phase and having a reusable characteristic.

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