CN114815901A - Rocket-mounted electrical system of carrier rocket - Google Patents
Rocket-mounted electrical system of carrier rocket Download PDFInfo
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Abstract
The application provides an electric system on arrow of carrier rocket includes: the master control electrical subsystem and the sub-control electrical subsystem respectively comprise at least one functional device and a wireless sensor node, the functional device and the wireless sensor node respectively comprise corresponding power supply units and wireless communication units, the master control electrical subsystem further comprises a wireless center node and a comprehensive control computer which are electrically connected, power is uniformly supplied through the corresponding power supply units, each sub-control electrical subsystem further comprises at least one relay forwarding antenna which is used for receiving the functional devices in the corresponding sub-control electrical subsystem and data sent by the wireless sensor nodes through the corresponding wireless communication units and forwarding the data to the wireless center node, and the relay forwarding antenna is further used for receiving control instructions sent by the comprehensive control computer through the wireless center node and forwarding the control instructions to target equipment. The loading capacity and the production efficiency of the rocket can be improved, and the use cost is reduced.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to an rocket-mounted electrical system of a carrier rocket.
Background
The rocket-mounted electrical system is a general name for completing functions of electrical equipment, electronic equipment and software and is an important component of a carrier rocket. Fig. 1 is a schematic structural diagram of an rocket-mounted electrical system of a launch vehicle in the prior art, and as shown in fig. 1, the rocket-mounted electrical system adopts a centralized wired architecture, components in the system are connected by a cable network, the cable network comprises components such as an electrical connector, a lead, a shielding network and a protective sleeve, and the electrical connector connects the rocket-mounted computer (i.e. a comprehensive control computer), a battery, a servo device (including a servo controller and an actuator), a remote measuring device (i.e. a radio frequency front end), a sensor and other electrical devices together. For multi-stage launch vehicles, inter-stage separation connectors (i.e., breakaway connectors) are also present, connecting the entire rocket in series. The cable network of customization design runs through the arrow entirely to pass through the interstage separation connector many times, in order to realize the transmission of data and instruction with centralized power supply and distribution, the overall layout is complicated.
With the increasing demand of multi-stage launch vehicle applications, higher requirements are also put on the loading capacity, production efficiency and use cost of the launch vehicle. However, the load capacity of the carrier rocket is too low due to the large weight of the cable network in the conventional rocket electrical system; and for carrier rockets of different models and different launching occasions, the corresponding customized cable network structures are different, which causes the problems of long time consumption of the design of the electric system on the rocket, uncontrollable production period and poor transportability.
Disclosure of Invention
The application provides an electric system on rocket of carrier rocket to be used for solving the problem that electric system on rocket builds inefficiency, use cost height and rocket load-carrying capacity are low that current electric system on rocket weight is big, design time-consuming duration, production cycle are uncontrollable and portability is poor to lead to, improve carrier rocket's load-carrying capacity and production efficiency, reduce use cost.
The application provides an electric system on arrow of carrier rocket includes:
the main control electric subsystem and the at least one sub-control electric subsystem are sequentially arranged in a plurality of cabin sections of the carrier rocket from the head to the tail;
the main control electrical subsystem and the sub control electrical subsystem respectively comprise at least one functional device and at least one wireless sensor node, and the functional device and the wireless sensor node respectively comprise a corresponding power supply unit and a corresponding wireless communication unit;
the master control electric subsystem further comprises a wireless central node and a comprehensive control computer, the wireless central node is electrically connected with the comprehensive control computer, and the wireless central node and the comprehensive control computer are uniformly powered through corresponding power supply units;
each sub-control electrical subsystem also comprises at least one relay forwarding antenna, and the relay forwarding antenna is used for receiving the functional equipment in the corresponding sub-control electrical subsystem and the data sent by the wireless sensor node through the corresponding wireless communication unit and forwarding the data to the wireless center node; and the relay forwarding antenna is also used for receiving the control instruction sent by the comprehensive control computer through the wireless central node and forwarding the control instruction to the target equipment.
According to the rocket-mounted electrical system of the carrier rocket, the functional equipment is any one of an inertial navigation device, an ignition control device, a servo device or a camera device;
the comprehensive control computer comprises a power supply and distribution module, the power supply and distribution module is used for sending a power supply control instruction to a target power supply unit in the main control electric subsystem and/or the sub-control electric subsystem through the wireless center node, and the power supply control instruction is used for adjusting the working state of the target power supply unit so as to realize dormancy, awakening and function synchronization of corresponding electric equipment.
According to the rocket electrical system of the carrier rocket provided by the application, the comprehensive control computer further comprises a remote measuring and collecting module and a radio frequency front end, wherein the remote measuring and collecting module is used for receiving data fed back by functional equipment and wireless sensor nodes in each electrical system through the wireless center node, collecting frames of the data, and sending the collected data to the ground measuring and sending control system through the radio frequency front end.
According to the rocket-mounted electrical system of the carrier rocket, the comprehensive control computer further comprises a time sequence module, and the time sequence module is used for sending an ignition control instruction to an ignition control device in an electrical subsystem corresponding to a target cabin section based on a preset time sequence so as to realize orderly control of initiating explosive device detonation and cabin section separation.
According to the rocket-mounted electrical system of the carrier rocket provided by the application, the wireless center node is further used for screening data fed back by the functional equipment and the wireless sensor node in the target electrical subsystem based on the separation time of the cabin section corresponding to the target electrical subsystem.
According to the rocket-mounted electrical system of the carrier rocket provided by the application, the data fed back by the functional equipment and the wireless sensor node in the target electrical subsystem are screened based on the separation time of the cabin section corresponding to the target electrical subsystem, and the method specifically comprises the following steps:
determining corresponding functional equipment and wireless sensor node identifications based on data fed back by the functional equipment and the wireless sensor nodes;
determining a corresponding target electrical subsystem and a cabin section corresponding to the target electrical subsystem based on the functional equipment and the wireless sensor node identification;
determining the separation time of the cabin section corresponding to the target electrical subsystem based on the preset time sequence;
and screening the data based on the separation time and the acquisition time of the data fed back by the functional equipment and the wireless sensor node.
According to the rocket electrical system of the carrier rocket, redundancy setting is carried out on target wireless sensor nodes, and the redundancy quantity is determined based on the types of the target wireless sensor nodes;
wherein the type of the wireless sensor node is any one of a vibration sensor, an impact sensor, a temperature sensor, a pressure sensor and a heat flow sensor.
According to the on-rocket electrical system of the carrier rocket provided by the application, the comprehensive control computer further comprises a flight control module, wherein the flight control module is used for receiving data fed back by a target inertial navigation system through the wireless center node, determining whether the track of the carrier rocket deviates or not based on the data fed back by the target inertial navigation system, and sending a control instruction to a target servo device to correct the track of the carrier rocket under the condition that the track of the carrier rocket deviates.
According to the on-rocket electrical system of the carrier rocket, the wireless center node is an ultra wide band UWB wireless transmission main node, and the wireless communication unit is an UWB wireless transmission slave node.
According to the rocket-mounted electrical system of the carrier rocket, each power supply unit is charged through the wireless charging window of the corresponding cabin section.
The application provides an electric system on arrow of carrier rocket includes: the main control electric subsystem and the at least one sub-control electric subsystem are sequentially arranged in a plurality of cabin sections of the carrier rocket from the head to the tail; the main control electrical subsystem and the sub control electrical subsystem respectively comprise at least one functional device and at least one wireless sensor node, and the functional device and the wireless sensor node respectively comprise a corresponding power supply unit and a corresponding wireless communication unit; the master control electrical subsystem further comprises a wireless central node and a comprehensive control computer, the wireless central node is electrically connected with the comprehensive control computer, and the wireless central node and the comprehensive control computer are uniformly powered through corresponding power supply units; each sub-control electrical subsystem also comprises at least one relay forwarding antenna, and the relay forwarding antenna is used for receiving the functional equipment in the corresponding sub-control electrical subsystem and the data sent by the wireless sensor node through the corresponding wireless communication unit and forwarding the data to the wireless center node; and the relay forwarding antenna is also used for receiving the control instruction sent by the comprehensive control computer through the wireless central node and forwarding the control instruction to the target equipment. The wireless transmission is used for replacing the wired connection of the traditional cable network, the number of electric connectors and wires is reduced, the rocket interstage unplugging connectors are omitted, the loading capacity of the rocket is improved, meanwhile, the design time of the cable network is reduced, the production period of the cable network is shortened, and the electrical cost of the carrier rocket is reduced. In addition, based on a distributed wireless electrical system framework, the modularized design of the cabin is realized, the system has good transportability, the production efficiency of the carrier rocket is improved, and the use cost is reduced.
Drawings
In order to more clearly illustrate the technical solutions in the present application or the prior art, the drawings needed for the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic diagram of a prior art rocket-borne electrical system of a launch vehicle;
FIG. 2 is a schematic diagram of the structure of an rocket electrical system of a launch vehicle provided herein;
FIG. 3 is a schematic diagram of a data interaction pattern of an on-rocket electrical system of a launch vehicle provided herein;
FIG. 4 is a schematic diagram of an example on-rocket electrical system of a launch vehicle provided herein.
Detailed Description
To make the objects, technical solutions and advantages of the present application clearer, the technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings in the present application, and it is obvious that the described embodiments are some, but not all embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
As shown in fig. 1, a conventional rocket-mounted electrical system is a centralized wired architecture, and a control system uses a bus to transmit information and instructions on a rocket and a rocket ground. The power supply and distribution are designed in a centralized mode, and the system nodes are numerous. The cable network of customization design runs through the arrow entirely, and the overall arrangement is numerous and jumbled to pass through interstage release connector many times, the overall arrangement is comparatively complicated. The rocket-mounted electrical system of the conventional carrier rocket is connected by a traditional cable network, and the rocket-mounted computer (namely, a comprehensive control computer), a battery, servo equipment (comprising a servo controller and an actuator), remote measuring equipment (namely, a radio frequency front end), a sensor and other electrical equipment on the rocket are connected together through an electrical connector to form the rocket-mounted electrical system of the carrier rocket. The traditional cable net comprises an electric connector, a lead, a shielding net, a protective sleeve and other parts, and is a 'neural network' of the carrier rocket. With the rise of commercial aerospace and the increase of the requirements of multi-stage carrier rockets, the traditional cable network has the defects of low load capacity of the carrier rocket due to heavy weight, and different customized cable network structures corresponding to carrier rockets of different models and different launching occasions, so that the problems of long time consumption of the design of an electric system on the rocket, uncontrollable production period and poor transportability are caused. Meanwhile, the cable network bears important tasks of instruction transmission, data transmission, power supply and distribution transmission and the like of an electric system on the rocket, and the electric connector and the wire are slightly wrong in design and bring immeasurable consequences to the carrier rocket.
Based on this, the embodiment of the application provides an electric system on rocket of carrier rocket for solve the problems of low efficiency of building electric system on rocket, high use cost and low load capacity of rocket caused by large weight, long design time consumption, uncontrollable production period and poor transportability of the existing electric system on rocket, improve the load capacity and production efficiency of carrier rocket, and reduce use cost.
Fig. 2 is a schematic structural diagram of an on-rocket electrical system of a launch vehicle provided in the present application, and as shown in fig. 2, the system includes:
the main control electric subsystem and the at least one sub-control electric subsystem are sequentially arranged in a plurality of cabin sections of the carrier rocket from the head to the tail;
the master control electrical subsystem and the sub control electrical subsystem respectively comprise at least one functional device and at least one wireless sensor node, and the functional device and the wireless sensor node respectively comprise a corresponding power supply unit and a corresponding wireless communication unit;
the master control electrical subsystem further comprises a wireless central node and a comprehensive control computer, the wireless central node is electrically connected with the comprehensive control computer, and the wireless central node and the comprehensive control computer are uniformly powered through corresponding power supply units;
each sub-control electrical subsystem also comprises at least one relay forwarding antenna, and the relay forwarding antenna is used for receiving the functional equipment in the corresponding sub-control electrical subsystem and the data sent by the wireless sensor node through the corresponding wireless communication unit and forwarding the data to the wireless center node; and the relay forwarding antenna is also used for receiving a control instruction sent by the comprehensive control computer through the wireless central node and forwarding the control instruction to target equipment.
Specifically, the distributed wireless on-rocket electrical system is designed for a multi-stage launch vehicle, and as shown in fig. 2, the on-rocket electrical system of the embodiment of the present application includes a main control electrical subsystem and at least one sub-control electrical subsystem, and the main control electrical subsystem and the at least one sub-control electrical subsystem are sequentially arranged in a plurality of cabin sections from the head to the tail of the launch vehicle. It can be understood that, based on the number of the cabin sections of the launch vehicle, the number of the sub-control electric subsystems can be freely adjusted, and only the electric subsystems corresponding to each cabin section of the launch vehicle are required to be included in each cabin section.
The main control electrical subsystem and the sub control electrical subsystem respectively comprise at least one functional device and at least one wireless sensor node, and the functional device and the wireless sensor node respectively comprise a corresponding power supply unit and a corresponding wireless communication unit. The functional equipment is any one of an inertial navigation device, an ignition control device, a servo device or a camera device. The system comprises an inertial navigation device, an ignition control device, a servo device and a camera device, wherein the inertial navigation device is used for collecting flight state data of a rocket, such as flight speed, flight angle, angular velocity and the like, the ignition control device is used for controlling initiating explosive devices to detonate so as to provide flight power and cabin separation power for the rocket, the servo device is used for adjusting the flight state of the rocket, and the camera device is used for acquiring state pictures or videos of the rocket in the processes of takeoff and flight. It is understood that, in order to ensure that each stage of cabin can be normally ignited and separated so as to ensure the normal flight of the launch vehicle, at least one functional device, namely an ignition control device, is included in the main control electrical subsystem and the sub-control electrical subsystem. As for other functional devices, the functional devices can be added according to actual needs. The wireless sensor nodes are used for collecting state data of the rocket so that the ground command center can accurately know the running state of the rocket.
It is worth noting that the functional device and the wireless sensor node respectively comprise a power supply unit and a wireless communication unit which correspond to each other, namely, the rocket electrical system of the embodiment of the application is as large as each functional device, and as small as each independent sensor is provided with the power supply unit and the wireless communication unit, so as to realize independent power supply and wireless communication. Compared with the traditional cable network, a large number of electric connectors are omitted, the number of wires is reduced, the weight of an electric system on the rocket is greatly reduced, and the carrying capacity of the carrier rocket is improved; the reduction of the cable network also greatly reduces the working hours of designers, accelerates the design speed, reduces the production period of the electric system on the rocket, improves the matching speed and obviously reduces the material cost; in addition, the design enables the rocket-mounted electrical system to have good transportability, solves the problem that cable network systems of different rocket models and different launching occasions cannot be reused, and reduces the cost of the rocket-mounted electrical system. Meanwhile, a distributed power supply mode is adopted, the problem that once a main battery is damaged, the rocket cannot take off if the main battery is light and the whole rocket is paralyzed in the flying process if the main battery is heavy in the traditional rocket concentrated power supply mode is solved, and the reliability of an electric system on the rocket is improved. It is to be understood that the power supply unit may employ a battery, and may also employ other power supply devices, and the wireless communication unit may employ a wireless transceiver, and may also employ other wireless transceiver devices, which is not specifically limited in this embodiment of the present invention.
The master control electric subsystem further comprises a wireless center node and a comprehensive control computer, the wireless center node is electrically connected with the comprehensive control computer, and the wireless center node and the comprehensive control computer are supplied with power in a unified mode through corresponding power supply units. The wireless center node is used for receiving data sent by the functional equipment and the wireless sensor node in each electrical subsystem and forwarding a control instruction sent by the comprehensive control computer to the functional equipment and the wireless sensor node in each electrical subsystem so as to realize the unified management of the equipment on the rocket and reduce the difficulty in use, operation and maintenance of the electrical system on the rocket. Meanwhile, due to the adoption of a distributed wireless design, functional equipment and wireless sensor nodes in the electric system can be subjected to extended design according to actual needs, so that the fault tolerance rate and the transportability of the rocket-mounted electric system are greatly improved. Moreover, the wireless central node is electrically connected with the comprehensive control computer, and the wireless central node and the comprehensive control computer are uniformly powered through corresponding power supply units, so that the integration degree of the system is also improved. Specifically, the wireless central node may be electrically connected to the integrated control computer in a plug-in unit, and of course, other feasible integration manners may also be adopted, which is not specifically limited in this embodiment of the present application.
Each sub-control electrical subsystem also comprises at least one relay forwarding antenna, and the relay forwarding antenna is used for receiving the functional equipment in the corresponding sub-control electrical subsystem and the data sent by the wireless sensor node through the corresponding wireless communication unit and forwarding the data to the wireless center node; and the relay forwarding antenna is also used for receiving the control instruction sent by the comprehensive control computer through the wireless central node and forwarding the control instruction to the target equipment. In consideration of the influence of the distances between different cabin sections on the rocket and the influence of the cabin walls on the wireless signal transmission stability, in the embodiment of the application, at least one relay forwarding antenna is arranged in each sub-control electrical subsystem (corresponding to each cabin section) and is used for receiving the functional equipment in the corresponding sub-control electrical subsystem, transmitting data sent by the wireless sensor node through the corresponding wireless communication unit to the wireless central node, and simultaneously receiving the control instruction sent by the comprehensive control computer through the wireless central node and forwarding the control instruction to the target equipment, so that the stability of wireless signal transmission is ensured, and the reliability of the electric system on the rocket is improved. Meanwhile, the relay forwarding antenna is adopted to replace a traditional interstage disconnection connector, data interaction and information collection penetrating through the whole rocket are completed, the weight of an electric system on the rocket is reduced, meanwhile, electric subsystems in each cabin section can be networked to form a distributed small system, the communication pressure with the wireless center node is reduced, and the communication efficiency is improved. It is understood that the target device may be a wireless sensor node, and may also be a functional device.
The rocket-mounted electrical system of the carrier rocket provided by the embodiment of the application comprises: the main control electric subsystem and the at least one sub-control electric subsystem are sequentially arranged in a plurality of cabin sections of the carrier rocket from the head to the tail; the main control electrical subsystem and the sub control electrical subsystem respectively comprise at least one functional device and at least one wireless sensor node, and the functional device and the wireless sensor node respectively comprise a corresponding power supply unit and a corresponding wireless communication unit; the master control electrical subsystem further comprises a wireless central node and a comprehensive control computer, the wireless central node is electrically connected with the comprehensive control computer, and the wireless central node and the comprehensive control computer are uniformly powered through corresponding power supply units; each sub-control electrical subsystem also comprises at least one relay forwarding antenna, and the relay forwarding antenna is used for receiving the functional equipment in the corresponding sub-control electrical subsystem and the data sent by the wireless sensor node through the corresponding wireless communication unit and forwarding the data to the wireless center node; and the relay forwarding antenna is also used for receiving the control instruction sent by the comprehensive control computer through the wireless central node and forwarding the control instruction to the target equipment. The wireless transmission is used for replacing the wired connection of the traditional cable network, the number of electric connectors and wires is reduced, the inserting and disconnecting connectors between rocket stages are omitted, the load capacity of the rocket is improved, meanwhile, the design time of the cable network is reduced, the production period of the cable network is shortened, and the electrical cost of the carrier rocket is reduced. In addition, based on a distributed wireless electrical system framework, the modularized design of the cabin is realized, the system has good transportability, the production efficiency of the carrier rocket is improved, and the use cost is reduced.
Based on the above embodiment, the functional device is any one of an inertial navigation device, an ignition control device, a servo device or an image pickup device;
the comprehensive control computer comprises a power supply and distribution module, the power supply and distribution module is used for sending a power supply control instruction to a target power supply unit in the main control electric subsystem and/or the sub-control electric subsystem through the wireless center node, and the power supply control instruction is used for adjusting the working state of the target power supply unit so as to realize dormancy, awakening and function synchronization of corresponding electric equipment.
Specifically, based on the distributed power supply scheme of the foregoing embodiment, the integrated control computer of the embodiment of the present application further includes a power supply and distribution module, where the power supply and distribution module is configured to send a power supply control instruction to a target power supply unit in the main control electrical subsystem and/or the sub-control electrical subsystem through the wireless center node, and the power supply control instruction is configured to adjust a working state of the target power supply unit to implement sleep, wake-up and function synchronization of corresponding electric devices. The power supply and distribution module adjusts the working state of the power supply unit, so that the power supply centralized control of each device on the rocket can be realized, the function synchronization is realized, and the normal operation of the rocket is ensured. Meanwhile, through the adjustment of the working state of the power supply unit, the dormancy and awakening control of each device on the arrow can be realized, and the overall power consumption of the electric system on the arrow is reduced. The specific control manner of the sleep and the wake-up may be implemented by adjusting a power supply voltage of the target power supply unit or on/off of a power supply line of an electrical appliance in the target device, which is not specifically limited in this embodiment of the present application. According to the embodiment of the application, low-power-consumption design can be performed on the rocket equipment needing power supply, such as the wireless sensor nodes, so that the overall power consumption of the rocket-mounted electrical system is further reduced.
According to the rocket-mounted electrical system of the carrier rocket, the functional equipment is any one of an inertial navigation device, an ignition control device, a servo device or a camera device, the comprehensive control computer comprises a power supply and distribution module, the power supply and distribution module is used for sending a power supply control instruction to a target power supply unit in the main control electrical subsystem and/or the sub-control electrical subsystem through the wireless center node, and the power supply control instruction is used for adjusting the working state of the target power supply unit so as to achieve dormancy, awakening and function synchronization of corresponding electrical equipment, normal operation of the rocket can be guaranteed, and meanwhile the overall power consumption of the rocket-mounted electrical system is reduced.
Based on any of the above embodiments, the integrated control computer further includes a telemetry, acquisition and editing module and a radio frequency front end, wherein the telemetry, acquisition and editing module is configured to receive data fed back by the functional devices and the wireless sensor nodes in each electrical subsystem through the wireless center node, frame the data, and send the framed data to the ground measurement, transmission and control system through the radio frequency front end.
Specifically, the telemetry, acquisition and editing module and the radio frequency front end in the comprehensive control computer can receive data fed back by functional devices and wireless sensor nodes in each electrical subsystem collected by the wireless center node, frame the data, and send the framed data to the ground measurement and transmission control system, so that the ground control center can accurately and timely acquire running state information of the rocket and process abnormal conditions to ensure stable running of the rocket.
According to the on-rocket electrical system of the carrier rocket provided by the embodiment of the application, the comprehensive control computer further comprises a telemetering collecting and editing module and a radio frequency front end, wherein the telemetering collecting and editing module is used for receiving data fed back by functional equipment and wireless sensor nodes in each electrical system through the wireless center node, framing the data, and sending the framed data to the ground measuring and sending control system through the radio frequency front end. The system can ensure that the ground control center accurately and timely acquires the running state information of the rocket and processes the abnormal conditions so as to ensure the stable running of the rocket.
Based on any one of the above embodiments, the integrated control computer further includes a timing module, and the timing module is configured to send an ignition control instruction to an ignition control device in an electrical subsystem corresponding to the target cabin segment based on a preset timing, so as to realize ordered control of initiating explosive device detonation and cabin segment separation.
Specifically, the time sequence module can send an ignition control instruction to an ignition control device in an electric subsystem corresponding to the target cabin section based on a preset time sequence so as to realize initiating explosive device detonation, further control the ordered separation of different cabin sections and ensure the normal operation of the carrier rocket. Because the time sequence module is arranged at the cabin section of the rocket head, the functions of the time sequence module can not be influenced even other cabin sections are separated in time, the need of arranging corresponding time sequence modules in all the cabin sections to control the separation of the corresponding cabin sections is avoided, and the cost and the complexity of the rocket electrical system are reduced.
The rocket-mounted electrical system of the carrier rocket provided by the embodiment of the application further comprises a time sequence module, wherein the time sequence module is used for sending an ignition control instruction to an ignition control device in the electrical subsystem corresponding to the target cabin section based on a preset time sequence so as to realize orderly control of initiating explosive device detonation and cabin section separation, can ensure normal operation of the carrier rocket, and simultaneously reduces cost and complexity of the rocket-mounted electrical system.
Based on any of the above embodiments, the wireless center node is further configured to screen data fed back by the functional device and the wireless sensor node in the target electrical subsystem based on the separation time of the cabin segment corresponding to the target electrical subsystem.
Specifically, the conventional rocket-mounted electrical system is wired through a cable network, and when a target cabin section is separated, the electrical equipment in the cabin section is disconnected, so that the functional equipment and the wireless sensor node in the cabin section stop communicating with the comprehensive control computer, and the comprehensive control computer only needs to frame the received data and feed the data back to the ground measurement and control system. However, for the distributed wireless rocket-mounted electrical system in the embodiment of the application, because each functional device and each wireless sensor node are independently powered, even if the target cabin segment is separated, the functional devices and the wireless sensor nodes in the cabin segment are still in a working state, and therefore, in a period of time after the target cabin segment is separated, the functional devices and the wireless sensor nodes in the electrical subsystem corresponding to the cabin segment still keep communication with the wireless central node and feed back data to the wireless central node until the target cabin segment and the rocket front end lose communication connection due to too long distance. However, for the separated cabin segment, the data fed back by the functional devices and the wireless sensor nodes has no reference value (namely useless data) for judging the running state of the rocket, and if the useless data is collected, framed and sent to the ground measurement and control system, a large amount of memory, framed and communication resources are wasted.
Based on this, the wireless center node in the embodiment of the present application is further configured to screen data fed back by the functional device and the wireless sensor node in the target electrical subsystem based on the separation time of the cabin segment corresponding to the target electrical subsystem, so as to eliminate data fed back by the electrical subsystem in the cabin segment after the cabin segment is separated, thereby avoiding waste of memory, framing and communication resources.
According to the rocket-mounted electrical system of the carrier rocket provided by the embodiment of the application, the wireless center node is further used for screening the data fed back by the functional equipment and the wireless sensor node in the target electrical subsystem based on the separation time of the cabin section corresponding to the target electrical subsystem, so that the data fed back by the electrical subsystem in the cabin section after the cabin section is separated can be eliminated, and the waste of memory, framing and communication resources is avoided.
Based on any one of the above embodiments, the screening, based on the separation time of the cabin segment corresponding to the target electrical subsystem, of the data fed back by the functional device and the wireless sensor node in the target electrical subsystem specifically includes:
determining corresponding functional equipment and wireless sensor node identifications based on data fed back by the functional equipment and the wireless sensor nodes;
determining a corresponding target electrical subsystem and a cabin section corresponding to the target electrical subsystem based on the functional equipment and the wireless sensor node identification;
determining the separation time of the cabin section corresponding to the target electrical subsystem based on the preset time sequence;
and screening the data based on the separation time and the acquisition time of the data fed back by the functional equipment and the wireless sensor node.
Specifically, since the functional device and the wireless sensor node both correspond to a unique identity, and the identity is added to the data packet when data is transmitted, the wireless center node may determine the corresponding functional device and the corresponding wireless sensor node identity based on the data fed back by the functional device and the wireless sensor node. Meanwhile, the corresponding relation between the functional equipment and the wireless sensor node and the electric subsystem and the cabin section can be stored in the wireless center node in advance, and on the basis, the corresponding target electric subsystem and the cabin section corresponding to the target electric subsystem can be determined through the functional equipment and the wireless sensor node identification. The cabin section corresponding to the target electrical subsystem is determined, namely the separation time of the cabin section can be determined based on the preset time sequence, and meanwhile, the data packets fed back by the functional device and the wireless sensor node also contain the data acquisition time, so that useless data (namely the data fed back by the functional device and the wireless sensor node in the target electrical subsystem after the cabin section is separated) can be determined and eliminated based on the separation time and the data acquisition time fed back by the functional device and the wireless sensor node. Based on the scheme, the useless data can be accurately determined and eliminated, and waste of memory, framing and communication resources in the rocket electrical system is avoided.
The rocket-mounted electrical system of a launch vehicle provided in the embodiment of the present application, based on the separation time of the cabin section corresponding to the target electrical subsystem, screens data fed back by functional devices and wireless sensor nodes in the target electrical subsystem, specifically including: the method comprises the steps of determining corresponding functional equipment and wireless sensor node identifications based on data fed back by the functional equipment and the wireless sensor nodes, determining corresponding target electrical subsystems and cabin sections corresponding to the target electrical subsystems based on the functional equipment and the wireless sensor node identifications, determining separation time of the cabin sections corresponding to the target electrical subsystems based on the preset time sequence, screening the data based on the separation time and acquisition time of the data fed back by the functional equipment and the wireless sensor nodes, and accurately eliminating useless data to avoid waste of memory, framing and communication resources in the rocket electrical systems.
Based on any one of the embodiments, redundancy setting is carried out on a target wireless sensor node, and the redundancy quantity is determined based on the type of the target wireless sensor node;
wherein the type of the wireless sensor node is any one of a vibration sensor, an impact sensor, a temperature sensor, a pressure sensor and a heat flow sensor.
Specifically, the type of the wireless sensor node is any one of a vibration sensor, an impact sensor, a temperature sensor, a pressure sensor and a heat flow sensor, and preferably, the electrical subsystem corresponding to each cabin section is provided with the above five types of wireless sensor nodes, so as to ensure the comprehensive collection of rocket state information. Of course, the types of the wireless sensor nodes in different cabin segments may also be adjusted based on actual needs, which is not specifically limited in the embodiment of the present application.
In general, a sensor mounted on an arrow is required to have high reliability. However, the problem that the rocket state cannot be accurately acquired due to damage of sensor nodes is solved by means of redundant setting of multiple sensors in consideration of the fact that the sensors are easily damaged due to the fact that external conditions are severe in the rocket flying process. Specifically, for the wireless sensor nodes of the same type in the same cabin section, the importance degree of the data acquired by the wireless sensor nodes for rocket state judgment is judged based on the type of the wireless sensor nodes, and whether redundant setting is performed on the wireless sensor nodes and the number of redundant sensors are determined based on the importance degree. For example, for a temperature sensor, the importance degree of the acquired data to rocket state judgment is low, so that redundant setting is not needed, and correspondingly, if the wireless center node judges that the temperature sensor is damaged based on the feedback data, the corresponding feedback data is directly removed; for the vibration sensor, the acquired data is of high importance for rocket state judgment, and therefore redundant setting is needed. It is worth noting that for a common sensor (such as a temperature sensor), if the sensor is damaged, the acquired data of the sensor is obviously abnormal, so that only two redundant sensors are needed to be arranged, and the data acquired by the two redundant sensors are compared to determine that the damaged sensor exists. However, even if a special sensor such as a vibration sensor is damaged, the acquired data cannot be obviously abnormal, so that if only two redundant sensors are arranged, the damaged target sensor cannot be judged.
The inventor of the application finds out through research that at most one sensor fails to work in the case of a plurality of redundant sensors even in the extreme case of rocket operation. Based on this, for the consideration of both cost and accuracy of collected data, the preferred redundancy number of the embodiment of the present application is three for the sensors with higher importance (such as the aforementioned vibration sensors). On the basis, if one sensor is damaged, the data of the sensor is greatly different from those of the other two normal sensors, correspondingly, the wireless center node can quickly determine a fault sensor through comparison, and directly takes the data fed back by the normal wireless sensor node for subsequent framing, so that the accuracy of the acquired rocket state information can be ensured as much as possible on the basis of controlling the cost.
It is noted that, similarly, a redundant power supply unit may be provided for the target device based on the importance of the target device, so as to avoid rocket failures or accidents caused by damage to the power supply unit during the operation of the rocket.
According to the rocket electrical system of the carrier rocket, the redundancy of the target wireless sensor nodes is set, the redundancy number is determined based on the type of the target wireless sensor nodes, and the type of the wireless sensor nodes is any one of a vibration sensor, an impact sensor, a temperature sensor, a pressure sensor and a heat flow sensor. The accuracy of the acquired rocket state information can be ensured as much as possible on the basis of controlling the cost.
Based on any of the above embodiments, the integrated control computer further includes a flight control module, where the flight control module is configured to receive data fed back by a target inertial navigation system through the wireless center node, determine whether a trajectory of the launch vehicle deviates based on the data fed back by the target inertial navigation system, and send a control instruction to a target servo device to correct the trajectory of the launch vehicle when the trajectory of the launch vehicle deviates.
Specifically, a preset flight trajectory of the rocket is prestored in the flight control module, the flight control module receives data fed back by a target inertial navigation system through the wireless central node, and based on the data fed back by the target inertial navigation system, whether the trajectory of the carrier rocket deviates (i.e., deviates from the preset flight trajectory) can be determined, and under the condition that the trajectory of the carrier rocket deviates, a control instruction is sent to a target servo device to correct the trajectory of the carrier rocket, so that the correctness of the running trajectory of the rocket is ensured. It will be appreciated that the target inertial navigation system may be an inertial navigation system disposed in one or more of the bays.
The on-rocket electrical system of the carrier rocket provided by the embodiment of the application, the comprehensive control computer further comprises a flight control module, wherein the flight control module is used for receiving data fed back by a target inertial navigation system through the wireless center node, determining whether the track of the carrier rocket deviates or not based on the data fed back by the target inertial navigation system, and sending a control instruction to a target servo device to correct the track of the carrier rocket under the condition that the track of the carrier rocket deviates, so that the correctness of the running track of the rocket can be ensured.
Based on any one of the above embodiments, the wireless central node is an ultra wide band UWB wireless transmission master node, and the wireless communication unit is an UWB wireless transmission slave node.
Specifically, fig. 3 is a schematic diagram of a data interaction mode of an rocket electrical system of a launch vehicle provided in the present application. As shown in fig. 3, the wireless sensor node and the servo controller (i.e., the function device) transmit data to the repeater (i.e., the relay forwarding antenna) through the wireless communication unit, and the repeater transmits the data to the wireless central node (not shown), and then the wireless central node transmits the data to the integrated control computer. Of course, the wireless sensor nodes and the functional equipment can also directly send data to the wireless central node, and then the data is transmitted to the comprehensive control computer by the wireless central node. Based on this, can realize the wireless interaction of information in the electric system on the arrow.
The wireless center node and the wireless communication unit may be implemented based on an Ultra Wide Band (UWB) wireless transmission technology, and specifically, the wireless center node is a UWB wireless transmission master node, and the wireless communication unit is a UWB wireless transmission slave node. The performance indexes of the UWB wireless transmission main node are as follows:
transmission distance: less than or equal to 20m (in an elastomer environment and in a single cabin body);
the transmission regime: UWB (Ultra Wide Band );
the transmission power: less than or equal to 1 mW;
the transmission frequency: 3.0-6.0 GHz;
UWB channel bandwidth: not less than 500 MHz;
available channels: more than or equal to 8 channels;
signal transmission bandwidth: less than or equal to 6 Mbps;
a data interface: differential RS422 levels;
ambient temperature: the working temperature is-45 ℃ to 85 ℃, and the storage temperature is-55 ℃ to 125 ℃.
The performance indexes of the slave nodes of the UWB wireless transmission are as follows:
the transmission regime: UWB (Ultra Wide Band );
the transmission power: less than or equal to 1 mW;
the transmission frequency: 3.0-6.0 GHz;
data transmission bandwidth: more than or equal to 6 Mbps;
networking capability: the total number of the nodes is not limited, and the nodes can be distributed within the bandwidth limit;
a built-in battery;
the slow-varying sensor sampling rate: the frequency of the filter is 1-100 Hz;
sampling rate of the speed variation sensor: the frequency range of 1kHz to 20kHz can be configured;
power consumption: less than or equal to 0.5W (in a full working state);
standby current: less than or equal to 0.5 uA;
ambient temperature: the working temperature is-45 ℃ to 85 ℃, and the storage temperature is-55 ℃ to 125 ℃.
The inventor of the application verifies the feasibility of the scheme based on experiments, and the UWB-based wireless transmission scheme can realize wireless transmission with low time delay and high reliability on the arrow.
According to the rocket-mounted electrical system of the carrier rocket, the wireless center node is the ultra wide band UWB wireless transmission main node, and the wireless communication unit is the UWB wireless transmission slave node, so that low-time-delay and high-reliability wireless transmission can be realized.
Based on any of the above embodiments, each power supply unit is charged through the wireless charging window of the corresponding cabin segment.
Specifically, in the embodiment of the application, before the rocket takes off, the electric quantity management system of each power supply unit detects the electric quantity of each power supply unit before taking off, feeds back the detection data to the comprehensive control computer in a wireless transmission mode, and transmits the detection data to the ground measurement and launch control system through the comprehensive control computer. For the target power supply unit with insufficient electric quantity, the ground measurement and control system can feed back a charging control instruction to charge the target power supply unit through the wireless charging window corresponding to the cabin section, so that electric energy can be supplied in time, the flight fault or flight accident caused by the insufficient electric quantity of the power supply unit in the rocket flight process is avoided, and the normal work of the rocket is ensured.
According to the rocket-mounted electrical system of the carrier rocket, each power supply unit is charged through the wireless charging window corresponding to the cabin section, so that flight faults or flight accidents caused by insufficient electric quantity of the power supply units in the rocket flight process can be avoided, and the normal work of the rocket is guaranteed.
Next, a specific structure of the rocket-mounted electrical system of the launch vehicle of the present application is described with a specific example, and as shown in fig. 4, a schematic structural diagram of an example of the rocket-mounted electrical system of the launch vehicle of the present application is provided. As can be seen from fig. 4, the three-level corresponds to a master control electrical subsystem, which includes a plurality of sensor nodes, a radio frequency front end, a wireless center node, a main battery, and a comprehensive control computer. The comprehensive control computer comprises a telemetering collecting and compiling module, a time sequence module, a flight control module and a power supply and distribution module. The wireless central node, the radio frequency front end and the main battery are all electrically connected with the comprehensive control computer, and the main battery supplies power for the comprehensive control computer and the wireless central node in a unified mode.
The second level and the first level correspond to sub-control electrical subunits, wherein the sub-control electrical subunits corresponding to the second level comprise a plurality of sensor nodes, a wireless camera, an ignition control device and an inertial navigation system. The plurality of sensor nodes, the wireless camera, the ignition control device and the inertial navigation system respectively comprise a power supply unit (namely a camera battery, an ignition battery and an inertial navigation battery in the figure, wherein the sensor node battery is not shown) and a wireless communication unit (namely a wireless transceiver and a corresponding antenna in the figure) which respectively correspond to the sensor nodes. The sub-control electrical subunit corresponding to the first stage is similar to the second stage and comprises a plurality of sensor nodes, an ignition control device, a servo controller and an actuator (namely a servo device). The plurality of sensor nodes, the ignition control device and the servo device all comprise power supply units (namely an ignition battery and a servo battery in the figure, wherein the sensor node battery is not shown) and wireless communication units (namely a wireless transceiver and an antenna in the figure) which correspond to each other.
It is understood that the master electrical subsystem should also include the same ignition control devices (not shown) as the primary and secondary stages for ignition control.
Based on the foregoing embodiments, in a state that the electrical system is most stable and reliable, the electrical subsystems corresponding to other stages except the top stage (corresponding to the three stages in fig. 4) may have the same composition, that is, include the sensor, the wireless camera, the ignition control device, the servo device and the inertial navigation system, and the top stage further includes the radio frequency front end, the wireless central node and the integrated control computer besides the above components. In the practical application process, however, the common components of the electrical subsystems corresponding to each stage can be adjusted according to the practical requirements. Fig. 4 is an example of one of the adjustment manners, and it should be noted that although the common components may be adjusted, each stage of the electrical subsystem at least needs to include an ignition control device to ensure that the rocket flies normally. As for the sensor, the wireless camera, the servo device and the inertial navigation system, only at least one of the whole arrow needs to be ensured.
The distributed wireless electric system is applied, and data interaction and instruction transmission are carried out on rocket equipment, sensors and the like in rockets at all levels by adopting wireless communication. The wireless transmission is used for replacing the wired connection of the traditional cable network, the number of equipment electric connectors and wires is reduced, the inter-stage release connectors of the rocket are eliminated, the loading capacity of the rocket is improved, the design working hours of the cable network are reduced, the production period of the cable network is shortened, the electrical cost of the carrier rocket is reduced, and the road is paved for the batch production of the carrier rocket. In addition, based on the distributed wireless electrical system framework design, the modularized design of the cabin section is realized, the system has good portability, and the problem of recycling of cable network systems of different rocket models and different launching occasions is solved.
The above-described embodiments of the apparatus are merely illustrative, and the units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions in the embodiments of the present application.
Claims (10)
1. An on-rocket electrical system for a launch vehicle, comprising:
the main control electric subsystem and the at least one sub-control electric subsystem are sequentially arranged in a plurality of cabin sections of the carrier rocket from the head to the tail;
the main control electrical subsystem and the sub control electrical subsystem respectively comprise at least one functional device and at least one wireless sensor node, and the functional device and the wireless sensor node respectively comprise a corresponding power supply unit and a corresponding wireless communication unit;
the master control electrical subsystem further comprises a wireless central node and a comprehensive control computer, the wireless central node is electrically connected with the comprehensive control computer, and the wireless central node and the comprehensive control computer are uniformly powered through corresponding power supply units;
each sub-control electrical subsystem also comprises at least one relay forwarding antenna, and the relay forwarding antenna is used for receiving the functional equipment in the corresponding sub-control electrical subsystem and the data sent by the wireless sensor node through the corresponding wireless communication unit and forwarding the data to the wireless center node; and the relay forwarding antenna is also used for receiving the control instruction sent by the comprehensive control computer through the wireless central node and forwarding the control instruction to the target equipment.
2. An on-rocket electrical system for a launch vehicle according to claim 1 wherein said functional apparatus is any one of an inertial navigation device, an ignition control device, a servo device or a camera device;
the comprehensive control computer comprises a power supply and distribution module, the power supply and distribution module is used for sending a power supply control instruction to a target power supply unit in the main control electric subsystem and/or the sub-control electric subsystem through the wireless center node, and the power supply control instruction is used for adjusting the working state of the target power supply unit so as to realize dormancy, awakening and function synchronization of corresponding electric equipment.
3. The rocket-mounted electrical system of a launch vehicle according to claim 2, wherein said integrated control computer further comprises a telemetry coding module and a radio frequency front end, said telemetry coding module is used for receiving data fed back by functional devices and wireless sensor nodes in each electrical subsystem through said wireless center node, framing said data, and sending the framed data to a ground test and transmission control system through said radio frequency front end.
4. The on-rocket electrical system of a launch vehicle of claim 3, wherein said integrated control computer further comprises a timing module for sending an ignition control command to an ignition control device in an electrical subsystem corresponding to a target bay section based on a preset timing to achieve orderly control of initiating explosive device detonation and bay section separation.
5. The rocket-mounted electrical system of a launch vehicle according to claim 4 wherein said wireless central node is further configured to screen data fed back by functional devices and wireless sensor nodes in a target electrical subsystem based on separation time of a bay segment corresponding to said target electrical subsystem.
6. The rocket-mounted electrical system of a launch vehicle according to claim 5, wherein the screening of the data fed back by the functional devices and the wireless sensor nodes in the target electrical subsystem based on the separation time of the cabin segment corresponding to the target electrical subsystem specifically comprises:
determining corresponding functional equipment and wireless sensor node identifications based on data fed back by the functional equipment and the wireless sensor nodes;
determining a corresponding target electrical subsystem and a cabin section corresponding to the target electrical subsystem based on the functional equipment and the wireless sensor node identification;
determining the separation time of the cabin section corresponding to the target electrical subsystem based on the preset time sequence;
and screening the data based on the separation time and the acquisition time of the data fed back by the functional equipment and the wireless sensor node.
7. The on-rocket electrical system of a launch vehicle according to claim 1 wherein a redundancy setting is made for a target wireless sensor node, the number of redundancies being determined based on the type of the target wireless sensor node;
wherein the type of the wireless sensor node is any one of a vibration sensor, an impact sensor, a temperature sensor, a pressure sensor and a heat flow sensor.
8. The on-rocket electrical system according to claim 6, wherein said integrated control computer further comprises a flight control module, said flight control module is configured to receive data fed back from a target inertial navigation system via said wireless central node, determine whether the trajectory of said carrier rocket is deviated based on the data fed back from said target inertial navigation system, and send a control command to a target servo device to correct the trajectory of said carrier rocket in case of deviation of the trajectory of said carrier rocket.
9. An on-rocket electrical system for a launch vehicle according to claim 1 wherein said wireless central node is an ultra-wideband UWB wireless transmission master node and said wireless communication units are UWB wireless transmission slave nodes.
10. The rocket-mounted electrical system of a launch vehicle according to claim 1 wherein each power supply unit is charged through a wireless charging window of the corresponding bay section.
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Address after: 100176 room 12b03, 12b floor, building 40, yard 1, Desheng North Street, Beijing Economic and Technological Development Zone, Beijing Patentee after: Oriental space technology (Beijing) Co.,Ltd. Country or region after: China Patentee after: Dongfang space technology (Shandong) Co.,Ltd. Patentee after: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Address before: 100176 room 12b03, 12b floor, building 40, yard 1, Desheng North Street, Beijing Economic and Technological Development Zone, Beijing Patentee before: Oriental space technology (Beijing) Co.,Ltd. Country or region before: China Patentee before: Dongfang space technology (Shandong) Co.,Ltd. Patentee before: Oriental space (Xi'an) Aerospace Technology Co.,Ltd. |
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| TR01 | Transfer of patent right |
Effective date of registration: 20240204 Address after: 100176 room 12b03, 12b floor, building 40, yard 1, Desheng North Street, Beijing Economic and Technological Development Zone, Beijing Patentee after: Oriental space technology (Beijing) Co.,Ltd. Country or region after: China Patentee after: Dongfang space technology (Shandong) Co.,Ltd. Patentee after: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. Patentee after: Orient Space (Hainan) Technology Co.,Ltd. Address before: 100176 room 12b03, 12b floor, building 40, yard 1, Desheng North Street, Beijing Economic and Technological Development Zone, Beijing Patentee before: Oriental space technology (Beijing) Co.,Ltd. Country or region before: China Patentee before: Dongfang space technology (Shandong) Co.,Ltd. Patentee before: Dongfang Space (Jiangsu) Aerospace Power Co.,Ltd. |