Carrier rocket power supply system and carrier rocket
By designing a reused power system between the launch vehicle and the orbital platform, the problem of redundant resource allocation was solved, the shared use of battery modules was realized, the cost of the launch vehicle was reduced, and the payload was increased.
Patent Information
- Application Number
- CN202511382678.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-25
- Publication Date
- 2026-02-10
AI Technical Summary
The use of separate lithium batteries for launch vehicles and orbital platforms leads to redundant resource allocation, resulting in resource waste and reduced payload capacity of launch vehicles.
Design a launch vehicle power system by setting a first self-holding circuit and a first switching module on the orbit-deployed platform, and a second self-holding circuit, a second switching module, and a battery module on the launch vehicle, to achieve battery module reuse and ensure that the orbit-deployed platform can utilize the rocket's battery modules after the rocket's flight, reducing redundant configuration.
This enables the reuse of launch vehicle battery modules, reducing launch vehicle costs, increasing payload capacity, and reducing resource waste.
Smart Images
Figure CN121508101A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aerospace technology, and more particularly to a launch vehicle power system and a launch vehicle. Background Technology
[0002] The launch vehicle and its onboard orbital platform are each designed with independent power systems, using separate lithium batteries for power. While this approach meets the power requirements of both the launch vehicle and the orbital platform, the use of independent lithium batteries leads to resource duplication.
[0003] Therefore, how to make full use of the power system in launch vehicles and reduce the cost of launch vehicles has become a technical problem that the industry urgently needs to solve. Summary of the Invention
[0004] This invention provides a launch vehicle power system and a launch vehicle, which solves the technical problem of how to make full use of the power system in a launch vehicle and reduce the cost of the launch vehicle.
[0005] The present invention provides a power system for a launch vehicle, including a first self-holding circuit and a first switching module disposed on an orbital platform, and a second self-holding circuit, a second switching module and a battery module disposed on the launch vehicle; The first self-holding circuit includes: a first control component and a normally open contact; The first control component and the second switch module are connected in series and draw power from the power supply branch of the launch vehicle; The normally open contact of the first self-holding circuit is connected to the battery module and is used to connect the power supply branch of the track-holding platform when the first control component is energized and to keep the power supply branch of the track-holding platform connected when the first control component is de-energized. The second self-holding circuit includes: a second control component and a normally closed contact; The second control component is connected in series with the first switch module and draws power from the power supply branch of the track-staying platform; The normally closed contact of the second self-holding circuit is connected to the battery module, and is used to keep the power supply branch of the launch vehicle connected when the second control component is de-energized, and to disconnect the power supply branch of the launch vehicle when the second control component is energized. The first switch module is used to control the second control component to be energized; The second switch module is used to control the first control component to receive power.
[0006] In some embodiments, the first positive power supply terminal of the battery module is connected to the first terminal of the first normally closed contact of the second self-holding circuit; The second end of the first normally closed contact of the second self-holding circuit is connected to the first end of the second switching module; The second end of the second switch module is connected to the first end of the first control component; The second end of the first control component is connected to the first end of the second normally closed contact of the second self-holding circuit; The second terminal of the second normally closed contact of the second self-holding circuit is connected to the first negative power supply terminal of the battery module.
[0007] In some embodiments, the second positive power supply terminal of the battery module is connected to the first terminal of the first normally open contact of the first self-holding circuit; The second end of the first normally open contact of the first self-holding circuit is connected to the first end of the first switching module; The second end of the first switch module is connected to the first end of the second control component; The second end of the second control component is connected to the first end of the second normally open contact of the first self-holding circuit; The second end of the second normally open contact of the first self-holding circuit is connected to the second negative power supply terminal of the battery module.
[0008] In some embodiments, the first self-holding circuit includes a first self-holding relay and a second self-holding relay connected in parallel; The first normally open contact of the first self-holding circuit is the normally open contact of the first self-holding relay; The second normally open contact of the first self-holding circuit is the normally open contact of the second self-holding relay.
[0009] In some embodiments, the second self-holding circuit includes a third self-holding relay and a fourth self-holding relay connected in parallel; The first normally closed contact of the second self-holding circuit is the normally closed contact of the third self-holding relay; The second normally closed contact of the second self-holding circuit is the normally closed contact of the fourth self-holding relay.
[0010] In some embodiments, the second end of the first normally open contact of the first self-holding circuit is connected to the positive power supply terminal of the track-holding platform; The first end of the second normally open contact of the first self-holding circuit is connected to the negative power supply terminal of the track-holding platform.
[0011] In some embodiments, the second end of the first normally closed contact of the second self-holding circuit is connected to the positive power supply terminal of the launch vehicle; The first end of the second normally closed contact of the second self-holding circuit is connected to the negative power supply terminal of the launch vehicle.
[0012] In some embodiments, the second switch module is configured to receive a power-on command for the orbital platform sent by the launch vehicle, and control the first control component to be powered on based on the power-on command for the orbital platform.
[0013] In some embodiments, the first switch module is configured to receive a launch vehicle power-off command sent by the orbital platform, and based on the launch vehicle power-off command, control the second control component to be powered on.
[0014] The present invention provides a launch vehicle, including an upper stage; the upper stage is used to carry an orbital platform; the upper stage includes the launch vehicle power system.
[0015] The present invention provides a launch vehicle power system and a launch vehicle, including a first self-holding circuit and a first switching module disposed on the orbit-delayed platform, and a second self-holding circuit, a second switching module, and a battery module disposed on the launch vehicle; the first self-holding circuit includes: a first control component and a normally open contact; the first control component and the second switching module are connected in series and draw power from the power supply branch of the launch vehicle; the normally open contact of the first self-holding circuit is connected to the battery module, for connecting the power supply branch of the orbit-delayed platform when the first control component is energized, and maintaining the connection of the power supply branch of the orbit-delayed platform when the first control component is de-energized; the second self-holding circuit includes: a second control component and a normally closed contact; the second control component and the first switching module are connected in series and draw power from the power supply branch of the orbit-delayed platform; the normally closed contact of the second ... energized; the second self-holding circuit includes: a second control component and a normally closed contact; the second control component and the first switching module are connected in series and draw power from the power supply branch of the orbit-delayed platform; the normally closed contact of the second self-holding circuit is connected to the battery module, for connecting the power supply branch of the orbit-delayed platform when the first control component is The second control component maintains the power supply to the launch vehicle when it is de-energized, and disconnects the power supply when it is energized. The first switch module controls the energization of the second control component, and the second switch module controls the energization of the first control component. The second switch module can be used to first activate the power supply to the orbital platform, allowing it to utilize the battery modules. Then, the first switch module can deactivate the power supply to the launch vehicle, stopping its use of the battery modules. This allows both the launch vehicle and the orbital platform to utilize the battery modules sequentially, achieving battery module reuse in the launch vehicle and eliminating the need for redundant battery modules in the orbital platform. This fully utilizes the launch vehicle's power system, increasing its payload and reducing its cost. Attached Figure Description
[0016] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.
[0017] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.
[0018] Figure 1 This is one of the structural schematic diagrams of the launch vehicle power system provided by the present invention.
[0019] Figure 2 This is the second schematic diagram of the power supply system for a launch vehicle provided by the present invention.
[0020] Figure 3 This is a structural schematic diagram of the launch vehicle provided by the present invention. Detailed Implementation
[0021] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. 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 should fall within the scope of protection of the present invention.
[0022] It should be noted that the terms "first," "second," etc., used in this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or device that comprises a series of steps, units, or modules is not necessarily limited to those explicitly listed, but may include other steps, units, or modules not explicitly listed or inherent to such processes, methods, products, or devices.
[0023] Figure 1 This is one of the structural schematic diagrams of the launch vehicle power system provided by the present invention, such as... Figure 1 As shown, the launch vehicle power system 100 includes a first self-holding circuit 110 and a first switching module 120 disposed on the orbital platform, and a second self-holding circuit 130, a second switching module 140 and a battery module 150 disposed on the launch vehicle.
[0024] The first self-holding circuit 110 includes: a first control component 111 and a normally open contact 112; The first control unit and the second switch module are connected in series and draw power from the power supply branch of the launch vehicle; The normally open contact of the first self-holding circuit is connected to the battery module and is used to connect the power supply branch of the track-holding platform when the first control component is energized and to maintain the connection of the power supply branch of the track-holding platform when the first control component is de-energized. The second self-holding circuit 130 includes: a second control component 131 and a normally closed contact 132; The second control unit is connected in series with the first switch module and draws power from the power supply branch of the track-staying platform; The normally closed contact of the second self-holding circuit is connected to the battery module and is used to keep the power supply branch of the launch vehicle connected when the second control component is de-energized and to disconnect the power supply branch of the launch vehicle when the second control component is energized. The first switch module is used to control the power supply of the second control component; The second switch module is used to control the power supply of the first control component.
[0025] Specifically, a launch vehicle is a vehicle used to send payloads (such as satellites, spacecraft, and spaceships) into space orbit. Launch vehicles are typically equipped with navigation and attitude control systems to ensure that the rocket flies along a predetermined trajectory and accurately delivers the payload into the target orbit.
[0026] An orbital platform (also known as an orbital platform or space platform) is a spacecraft that operates in orbit for an extended period, primarily to support various space missions. It can be a standalone spacecraft or part of a launch vehicle, continuing to operate in orbit after the rocket has completed its mission. Orbital platforms can carry a variety of payloads, such as scientific experimental equipment, communication equipment, and remote sensing equipment. They can be used for scientific research, communication relay, Earth observation, and many other missions.
[0027] Both the launch vehicle and the orbital platform contain a large number of devices with power requirements. Using independent battery modules (such as lithium batteries) leads to resource duplication. From a temporal perspective, after the launch vehicle's flight, its lithium batteries cease operation, while the orbital platform's lithium batteries begin working, resulting in a waste of rocket battery resources. Furthermore, using multiple lithium batteries reduces the launch vehicle's carrying capacity and payload capacity.
[0028] The launch vehicle power system provided in this embodiment of the invention reuses battery modules from the launch vehicle, eliminating the need for a separate battery module on the orbital platform and thus not affecting the power systems of the original launch vehicle and the orbital platform. After the rocket's flight, the rocket's battery modules are switched to the orbital platform for use. All added circuitry employs redundancy measures, ensuring no impact on the reliability of the original system.
[0029] The launch vehicle power system may include a first self-holding circuit, a first switching module, a second self-holding circuit, a second switching module, and a battery module. The first self-holding circuit and the first switching module are located on the orbit-deployed platform, while the second self-holding circuit, the second switching module, and the battery module are located on the launch vehicle.
[0030] The battery module can be a lithium battery or a lithium battery pack. During the launch and flight phases of the launch vehicle, the battery module provides power to various devices on board, for example, it can provide 28V (volts) DC power.
[0031] The normally closed contacts of the second self-holding circuit are connected to the battery module and are used to control the on / off state of the power supply branch of the launch vehicle. A normally closed contact is a contact that is closed when the control components of the self-holding circuit are de-energized, and the circuit is conductive. When the control components of the self-holding circuit are energized, the normally closed contacts open, and the circuit is de-energized.
[0032] The first control unit and the second switch module are connected in series and draw power from the launch vehicle's power supply branch. A first self-holding circuit is used to connect the power supply branch to the orbital platform when the first control unit is energized, and to maintain the connection of the power supply branch to the orbital platform when the first control unit is de-energized. The second switch module is used to control the energization of the first control unit.
[0033] The normally open contact of the first self-holding circuit is connected to the battery module and is used to control the on / off state of the power supply branch of the track-holding platform. A normally open contact is a contact that is open when the control component of the self-holding circuit is de-energized, and the circuit is not conductive. When the control component of the self-holding circuit is energized, the normally open contact closes, and the circuit becomes conductive.
[0034] The second control unit is connected in series with the first switch module and draws power from the power supply branch of the orbital platform. A second self-holding circuit is used to keep the power supply branch of the launch vehicle connected when the second control unit is de-energized and to disconnect the power supply branch of the launch vehicle when the second control unit is energized. The first switch module is used to control the energization of the second control unit.
[0035] Circuit analysis shows that: The first self-holding circuit and the second switch module can control the on / off state of the power supply branch of the track-staying platform. Specifically, the second switch module controls the first control component to be energized, the normally open contact of the first self-holding circuit closes, and the power supply branch of the track-staying platform is turned on.
[0036] The second self-holding circuit and the first switching module can control the on / off state of the power supply branch of the launch vehicle. Specifically, the first switching module controls the second control component to be energized, the normally closed contact of the second self-holding circuit is opened, and the power supply branch of the launch vehicle is not connected.
[0037] The launch vehicle power system provided in this embodiment of the invention includes a first self-holding circuit and a first switching module disposed on the orbit-delayed platform, and a second self-holding circuit, a second switching module, and a battery module disposed on the launch vehicle. The first self-holding circuit includes a first control component and a normally open contact; the first control component and the second switching module are connected in series and draw power from the power supply branch of the launch vehicle; the normally open contact of the first self-holding circuit is connected to the battery module, used to connect the power supply branch of the orbit-delayed platform when the first control component is energized, and to maintain the connection of the power supply branch of the orbit-delayed platform when the first control component is de-energized. The second self-holding circuit includes a second control component and a normally closed contact; the second control component and the first switching module are connected in series and draw power from the power supply branch of the orbit-delayed platform; the normally closed contact of the second self-holding circuit is connected to the battery module, used to connect the power supply branch of the orbit-delayed platform when the first control component is energized, and to maintain the connection of the power supply branch of the orbit-delayed platform when the first control component is de-energized. The second control unit maintains the power supply to the launch vehicle while in a de-energized state, and disconnects the power supply to the launch vehicle while in an energized state. The first switch module controls the energization of the second control unit, and the second switch module controls the energization of the first control unit. The second switch module can be used to first activate the power supply to the orbital platform, allowing it to utilize the battery modules. Then, the first switch module can deactivate the power supply to the launch vehicle, stopping its use of the battery modules. This allows both the launch vehicle and the orbital platform to operate sequentially using the battery modules, achieving battery module reuse in the launch vehicle and eliminating the need for redundant battery modules in the orbital platform. This fully utilizes the launch vehicle's power system, increasing its payload and reducing its cost.
[0038] In some embodiments, the first positive power supply terminal of the battery module is connected to the first terminal of the first normally closed contact of the second self-holding circuit; The second end of the first normally closed contact of the second self-holding circuit is connected to the first end of the second switching module; The second end of the second switch module is connected to the first end of the first control component; The second end of the first control component is connected to the first end of the second normally closed contact of the second self-holding circuit; The second terminal of the second normally closed contact of the second self-holding circuit is connected to the first negative power supply terminal of the battery module.
[0039] Specifically, the first positive power supply terminal of the battery module is connected to the first end of the first normally closed contact of the second self-holding circuit; the second end of the second normally closed contact of the second self-holding circuit is connected to the first negative power supply terminal of the battery module. This connection method allows the normally closed contact of the second self-holding circuit to be connected to the battery module, thus controlling the on / off state of the launch vehicle's power supply branch.
[0040] The second end of the first normally closed contact of the second self-holding circuit is connected to the first end of the second switching module; the second end of the second switching module is connected to the first end of the first control component; and the second end of the first control component is connected to the first end of the second normally closed contact of the second self-holding circuit. Through this connection method, the first control component and the second switching module are connected in series, drawing power from the launch vehicle's power supply branch.
[0041] The launch vehicle's power supply branch can only be energized when the first and second normally closed contacts of the second self-holding circuit are closed. The first self-holding circuit can only be energized when the launch vehicle's power supply branch is energized and the second switching module is powered on. Energization of the control components of the first self-holding circuit is necessary to connect the power supply branch to the orbital platform.
[0042] Current flows out from the first positive power supply terminal of the battery module, passes through the first normally closed contact of the second self-holding circuit, the second switch module, the first self-holding circuit, and the second normally closed contact of the second self-holding circuit, and then flows into the first negative power supply terminal of the battery module.
[0043] The power supply system for the launch vehicle provided in this embodiment of the invention is such that whether the first self-holding circuit is energized is affected by the power supply branch of the launch vehicle. The control component of the first self-holding circuit can be energized by controlling the second switching module on the launch vehicle side, thereby connecting the power supply branch of the orbital platform.
[0044] In some embodiments, the second positive power supply terminal of the battery module is connected to the first terminal of the first normally open contact of the first self-holding circuit; The second end of the first normally open contact of the first self-holding circuit is connected to the first end of the first switching module; The second end of the first switch module is connected to the first end of the second control component; The second end of the second control component is connected to the first end of the second normally open contact of the first self-holding circuit; The second terminal of the second normally open contact of the first self-holding circuit is connected to the second negative power supply terminal of the battery module.
[0045] Specifically, the second positive power supply terminal of the battery module is connected to the first end of the first normally open contact of the first self-holding circuit; the second end of the second normally open contact of the first self-holding circuit is connected to the second negative power supply terminal of the battery module. This connection method allows the normally open contact of the first self-holding circuit to be connected to the battery module, thus controlling the on / off state of the power supply branch of the track-staying platform.
[0046] The second end of the first normally open contact of the first self-holding circuit is connected to the first end of the first switching module; the second end of the first switching module is connected to the first end of the second control component; and the second end of the second control component is connected to the first end of the second normally open contact of the first self-holding circuit. Through this connection method, the second control component and the first switching module are connected in series, drawing power from the power supply branch of the track-holding platform.
[0047] The power supply branch of the orbit-deployed platform can only be energized when the first normally open contact and the second normally open contact of the first self-holding circuit are closed. The second self-holding circuit can only be energized when the power supply branch of the orbit-deployed platform is energized and the first switching module is powered on. Only when the control component of the second self-holding circuit is energized can the power supply branch of the launch vehicle be disconnected.
[0048] Current flows out from the second positive power supply terminal of the battery module, passes through the first normally open contact of the first self-holding circuit, the first switch module, the second self-holding circuit, and the second normally open contact of the first self-holding circuit, and then flows into the second negative power supply terminal of the battery module.
[0049] The power supply system for the launch vehicle provided in this embodiment of the invention is such that whether the second self-holding circuit is energized is affected by the power supply branch of the orbital platform. The control component of the second self-holding circuit can be energized by controlling the first switch module on the orbital platform side, thereby disconnecting the power supply branch of the launch vehicle.
[0050] In some embodiments, the first self-holding circuit includes a first self-holding relay and a second self-holding relay connected in parallel; the first normally open contact of the first self-holding circuit is the normally open contact of the first self-holding relay; and the second normally open contact of the first self-holding circuit is the normally open contact of the second self-holding relay.
[0051] The second self-holding circuit includes a third self-holding relay and a fourth self-holding relay connected in parallel; the first normally closed contact of the second self-holding circuit is the normally closed contact of the third self-holding relay; the second normally closed contact of the second self-holding circuit is the normally closed contact of the fourth self-holding relay.
[0052] Specifically, the control component of a self-holding relay is a coil.
[0053] Figure 2 This is the second structural schematic diagram of the launch vehicle power system provided by the present invention, as shown below. Figure 2 As shown, the first self-holding circuit includes a first self-holding relay K1 and a second self-holding relay K2 connected in parallel. The first normally open contacts of the first self-holding circuit are redundantly configured as normally open contacts K1-1 and K1-2 of the first self-holding relay K1; the second normally open contacts of the first self-holding circuit are redundantly configured as normally open contacts K2-1 and K2-2 of the second self-holding relay K2.
[0054] The second self-holding circuit includes a third self-holding relay K3 and a fourth self-holding relay K4 connected in parallel; the first normally closed contact of the second self-holding circuit is redundantly configured as the normally closed contacts K3-1 and K3-2 of the third self-holding relay K3; the second normally closed contact of the second self-holding circuit is redundantly configured as the normally closed contacts K4-1 and K4-2 of the fourth self-holding relay K4.
[0055] The launch vehicle power system provided in this embodiment of the invention redundantly sets the first normally open contact and the second normally open contact of the first self-holding circuit, thereby improving the reliability of the power supply branch of the orbit-detaining platform; and redundantly sets the first normally closed contact and the second normally closed contact of the second self-holding circuit, thereby improving the reliability of the power supply branch of the launch vehicle.
[0056] In some embodiments, the second end of the first normally open contact of the first self-holding circuit is connected to the positive power supply terminal of the track-holding platform; the first end of the second normally open contact of the first self-holding circuit is connected to the negative power supply terminal of the track-holding platform.
[0057] The second end of the first normally closed contact of the second self-holding circuit is connected to the positive power supply terminal of the launch vehicle; the first end of the second normally closed contact of the second self-holding circuit is connected to the negative power supply terminal of the launch vehicle.
[0058] Specifically, such as Figure 2 As shown, the second end of the first normally open contact of the first self-holding circuit is connected to the positive power supply terminal C of the track-holding platform; the first end of the second normally open contact of the first self-holding circuit is connected to the negative power supply terminal D of the track-holding platform. Through this connection method, the normally open contact of the first self-holding circuit can control the on / off state of the power supply branch of the track-holding platform.
[0059] The second terminal of the first normally closed contact of the second self-holding circuit is connected to the positive power supply terminal A of the launch vehicle; the first terminal of the second normally closed contact of the second self-holding circuit is connected to the negative power supply terminal B of the launch vehicle. This connection method allows the normally closed contact of the second self-holding circuit to control the on / off state of the launch vehicle's power supply branch.
[0060] The launch vehicle power system provided in this embodiment of the invention can control the on / off of the power supply branch of the orbit-deployed platform through the normally open contact of the first self-holding circuit, and can control the on / off of the power supply branch of the launch vehicle through the normally closed contact of the second self-holding circuit, so that the launch vehicle and the orbit-deployed platform can work using the battery modules in turn, realizing the reuse of battery modules in the launch vehicle.
[0061] In some embodiments, the second switch module is configured to receive a power-on command from the launch vehicle for the orbital platform, and based on the power-on command, control the first control component to be powered on. The first switch module is configured to receive a power-off command from the orbital platform for the launch vehicle, and based on the power-off command, control the second control component to be powered on.
[0062] Specifically, the first switch module can be redundantly configured, which is represented by K_OFF1 and K_OFF2 in the circuit. The second switch module can also be redundantly configured, which is represented by K_ON1 and K_ON2 in the circuit.
[0063] The second switch module receives a power-on command from the launch vehicle for the orbit-detaining platform, closes, and energizes the control components of the first self-holding circuit. The second switch module also receives a power-off command from the orbit-detaining platform for the launch vehicle, closes, and energizes the control components of the second self-holding circuit.
[0064] like Figure 2 As shown, the control terminals K1-1K and K1-2K in the first self-holding relay K1, and the control terminals K2-1K and K2-2K in the second self-holding relay K2 constitute the first control component.
[0065] K1-1 and K1-2 are the normally open contacts of the first self-holding relay K1. K1-1K is the control terminal corresponding to normally open contact K1-1 in the first self-holding relay K1; K1-2K is the control terminal corresponding to normally open contact K1-2 in the first self-holding relay K1. When the contacts are closed, the positive terminal (28V+) of the battery module (original rocket battery) is connected to the positive power supply terminal C of the orbital platform. When the contacts are open, the positive terminal (28V+) of the battery module is disconnected from the positive power supply terminal C of the orbital platform.
[0066] K2-1 and K2-2 are the normally open contacts of the second self-holding relay K2. K2-1K is the control terminal corresponding to normally open contact K2-1 in the second self-holding relay K2; K2-2K is the control terminal corresponding to normally open contact K2-2 in the second self-holding relay K2. When the contacts are closed, the negative terminal (28V-) of the battery module is connected to the negative power supply terminal D of the track-holding platform. When the contacts are open, the negative terminal (28V-) of the battery module is disconnected from the negative power supply terminal D of the track-holding platform.
[0067] The control terminals K3-1K and K3-2K in the third self-holding relay K3, and the control terminals K4-1K and K4-2K in the fourth self-holding relay K4, constitute the second control component.
[0068] K3-1 and K3-2 are normally closed contacts of the third self-holding relay K3. K3-1K is the control terminal corresponding to the normally closed contact K3-1 in the third self-holding relay K3; K3-2K is the control terminal corresponding to the normally closed contact K3-2 in the third self-holding relay K3. When the contacts are closed, the positive terminal (28V+) of the battery module is connected to the positive power supply terminal A of the launch vehicle. When the contacts are open, the positive terminal (28V+) of the battery module is disconnected from the positive power supply terminal A of the launch vehicle.
[0069] K4-1 and K4-2 are the normally closed contacts of the fourth self-holding relay K4. K4-1K is the control terminal corresponding to the normally closed contact K4-1 in the fourth self-holding relay K4; K4-2K is the control terminal corresponding to the normally closed contact K4-2 in the fourth self-holding relay K4. When the contacts are closed, the negative terminal (28V-) of the battery module is connected to the negative power supply terminal B of the launch vehicle. When the contacts are open, the negative terminal (28V-) of the battery module is disconnected from the negative power supply terminal B of the launch vehicle.
[0070] K_ON1 and K_ON2 are normally open contacts of the second switch module. When the contacts close, K1-1, K1-2, K2-1, and K2-2 close, connecting the battery module output to power the track-staying platform, and the track-staying platform's power system starts working. When the contacts open, K1-1, K1-2, K2-1, and K2-2 open, disconnecting the battery module output from the track-staying platform's power supply, and the track-staying platform's power system is de-energized.
[0071] K_OFF1 and K_OFF2 are normally open contacts of the first switch module. When the contacts are closed, K3-1, K3-2, K4-1, and K4-2 are open, disconnecting the battery module from the launch vehicle and de-energizing the launch vehicle's power system. When the contacts are open, K3-1, K3-2, K4-1, and K4-2 are closed, connecting the battery module output to the launch vehicle's power system and energizing the launch vehicle's power system.
[0072] During the active phase of flight of the launch vehicle, control relays K_ON1, K_ON2, K_OFF1, and K_OFF2 are disconnected, K1-1, K1-2, K2-1, and K2-2 are disconnected, and K3-1, K3-2, K4-1, and K4-2 are closed. The power system of the launch vehicle is powered on, and the power system of the orbital platform is powered off.
[0073] After the rocket flight mission is completed, control K_ON1 and K_ON2 are closed, K1-1, K1-2, K2-1, and K2-2 are closed, and the orbital platform is powered on and begins to work.
[0074] After the orbital platform is powered on, K_OFF1 and K_OFF2 are closed according to the preset timing sequence, and rockets K3-1, K3-2, K4-1, and K4-2 are disconnected, thus de-energizing the launch vehicle's power system.
[0075] The orbital platform is powered on, the launch vehicle is powered off, and the handover of the power supply systems of the orbital platform and the launch vehicle is completed.
[0076] The launch vehicle power system provided in this embodiment of the invention uses a time-sharing battery module between the orbital platform and the launch vehicle, so that the orbital platform no longer needs to be equipped with a separate battery, saving costs and carrying capacity; redundant relays are used to increase system reliability; both the positive and negative terminals of the battery output are controlled, and the negative terminals of the orbital platform and the rocket power supply system are isolated.
[0077] Figure 3 This is a structural schematic diagram of the launch vehicle provided by the present invention, as shown below. Figure 3 As shown, the launch vehicle 300 includes an upper stage 310; the upper stage 310 is used to carry the orbital platform 320; the upper stage includes the launch vehicle power system 100 in the above embodiment.
[0078] Specifically, the upper stage is the outermost one or more stages of a launch vehicle, located above the base stage, and is used to further deliver the payload from the transition orbit entered by the base stage into the intended working orbit. The upper stage can carry a platform for staying in orbit. The launch vehicle's power system can be located in the upper stage.
[0079] The launch vehicle provided in this embodiment of the invention allows the launch vehicle and the orbital platform to work sequentially using battery modules, realizing the reuse of battery modules in the launch vehicle and eliminating the need to repeatedly install battery modules in the orbital platform. This fully utilizes the power system of the launch vehicle, increases the effective payload of the launch vehicle, and reduces the cost of the launch vehicle.
[0080] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.
[0081] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.
[0082] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims
1. A power supply system for a launch vehicle, characterized in that, include: The first self-holding circuit and the first switch module are installed on the orbital platform, and the second self-holding circuit, the second switch module and the battery module are installed on the launch vehicle; The first self-holding circuit includes: a first control component and a normally open contact; The first control component and the second switch module are connected in series and draw power from the power supply branch of the launch vehicle; The normally open contact of the first self-holding circuit is connected to the battery module and is used to connect the power supply branch of the track-holding platform when the first control component is energized and to keep the power supply branch of the track-holding platform connected when the first control component is de-energized. The second self-holding circuit includes: a second control component and a normally closed contact; The second control component is connected in series with the first switch module and draws power from the power supply branch of the track-staying platform; The normally closed contact of the second self-holding circuit is connected to the battery module, and is used to keep the power supply branch of the launch vehicle connected when the second control component is de-energized, and to disconnect the power supply branch of the launch vehicle when the second control component is energized. The first switch module is used to control the second control component to be energized; The second switch module is used to control the first control component to receive power.
2. The launch vehicle power system according to claim 1, characterized in that, The first positive power supply terminal of the battery module is connected to the first terminal of the first normally closed contact of the second self-holding circuit. The second end of the first normally closed contact of the second self-holding circuit is connected to the first end of the second switching module; The second end of the second switch module is connected to the first end of the first control component; The second end of the first control component is connected to the first end of the second normally closed contact of the second self-holding circuit; The second terminal of the second normally closed contact of the second self-holding circuit is connected to the first negative power supply terminal of the battery module.
3. The launch vehicle power system according to claim 2, characterized in that, The second positive power supply terminal of the battery module is connected to the first terminal of the first normally open contact of the first self-holding circuit. The second end of the first normally open contact of the first self-holding circuit is connected to the first end of the first switching module; The second end of the first switch module is connected to the first end of the second control component; The second end of the second control component is connected to the first end of the second normally open contact of the first self-holding circuit; The second end of the second normally open contact of the first self-holding circuit is connected to the second negative power supply terminal of the battery module.
4. The launch vehicle power system according to claim 3, characterized in that, The first self-holding circuit includes a first self-holding relay and a second self-holding relay connected in parallel; The first normally open contact of the first self-holding circuit is the normally open contact of the first self-holding relay; The second normally open contact of the first self-holding circuit is the normally open contact of the second self-holding relay.
5. The launch vehicle power system according to claim 4, characterized in that, The second self-holding circuit includes a third self-holding relay and a fourth self-holding relay connected in parallel; The first normally closed contact of the second self-holding circuit is the normally closed contact of the third self-holding relay; The second normally closed contact of the second self-holding circuit is the normally closed contact of the fourth self-holding relay.
6. The launch vehicle power system according to claim 3, characterized in that, The second end of the first normally open contact of the first self-holding circuit is connected to the positive power supply terminal of the track-holding platform; The first end of the second normally open contact of the first self-holding circuit is connected to the negative power supply terminal of the track-holding platform.
7. The launch vehicle power system according to claim 3, characterized in that, The second end of the first normally closed contact of the second self-holding circuit is connected to the positive power supply terminal of the launch vehicle; The first end of the second normally closed contact of the second self-holding circuit is connected to the negative power supply terminal of the launch vehicle.
8. The launch vehicle power system according to any one of claims 1 to 7, characterized in that, The second switch module is configured to receive a power-on command from the launch vehicle for the orbital platform, and based on the power-on command, control the first control component to be powered on.
9. The launch vehicle power system according to any one of claims 1 to 7, characterized in that, The first switch module is configured to receive a power-off command for the launch vehicle sent by the orbital platform, and based on the power-off command, control the second control component to be powered on.
10. A launch vehicle, characterized in that, Including the superordinate level; The upper stage is used to carry the track-keeping platform; The upper stage includes the launch vehicle power system as described in any one of claims 1 to 9.