CN112146525B - Carrier rocket upper-level recovery method and recovery system - Google Patents
Carrier rocket upper-level recovery method and recovery system Download PDFInfo
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- CN112146525B CN112146525B CN202010917288.4A CN202010917288A CN112146525B CN 112146525 B CN112146525 B CN 112146525B CN 202010917288 A CN202010917288 A CN 202010917288A CN 112146525 B CN112146525 B CN 112146525B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
- F42B10/50—Brake flaps, e.g. inflatable
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
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Abstract
The invention provides a carrier rocket upper-level recovery method and a carrier rocket upper-level recovery system, wherein the method comprises the following steps: acquiring recovery parameters, and controlling the upper stage to be recovered to perform attitude adjustment when the recovery parameters meet the preset recovery requirements; when the upper stage to be recovered reaches the first position of the preset return track, braking the speed of the upper stage to be recovered to a preset speed; and when the upper stage to be recovered reaches a second position of the preset return track, controlling the pneumatic speed reducer to be unfolded, and recovering the upper stage to be recovered. The pneumatic speed reducer is arranged on the upper stage of the carrier rocket to be recovered, so that the whole lift force of the carrier rocket is ensured, and the reentry speed reduction and the attitude stability are improved; monitoring whether the recovery parameters meet the preset recovery requirements, controlling the posture adjustment of the upper stage to be recovered, and ensuring that the operation direction of the upper stage to be recovered is aligned with the recovery landing point; the pneumatic expansion type speed reduction technology is adopted, the problems of complex structure and difficult installation of the traditional speed reducer are solved, and the accuracy of the landing position is ensured.
Description
Technical Field
The invention relates to the technical field of carrier rocket control systems, in particular to a carrier rocket upper-level recovery method and a carrier rocket upper-level recovery system.
Background
The upper-level recovery technology of the carrier rocket mainly aims to solve the problems of upper-level separation, atmosphere reentry, safe landing, recovery and reuse by utilizing a spacecraft reentry return technology, so that the recovery technology is quite complex and closely related to the return process and the flight orbit after separation; for a conventional two-stage carrier rocket, the upper stage sends the payload to a low-ground orbit or a transfer orbit, the upper stage also obtains the orbit speed and enters the orbit, the recovery difficulty is caused by the orbit height and the speed of the upper stage, and the large loss of the carrying capacity of the upper stage cannot be ensured in the recovery process, so that the recovery difficulty of the upper stage is further increased, and how to accurately and efficiently recover the upper stage is of great significance to the recovery of the whole carrier rocket.
Disclosure of Invention
In view of this, the embodiment of the present invention provides a recovery method and a recovery system for a top stage of a carrier rocket, which solve the problem in the prior art that the top stage recovery is difficult.
The embodiment of the invention provides a carrier rocket upper stage recovery method, wherein a pneumatic reducer is arranged on an upper stage to be recovered of a carrier rocket, and the carrier rocket upper stage recovery method comprises the following steps: acquiring recovery parameters, and controlling the upper stage to be recovered to perform attitude adjustment when the recovery parameters meet preset recovery requirements; when the upper stage to be recovered reaches a first position of a preset return track, braking the speed of the upper stage to be recovered to a preset speed; and when the upper stage to be recovered reaches the second position of the preset return track, controlling the pneumatic speed reducer to be unfolded, and recovering the upper stage to be recovered.
Optionally, after the controlling the upper stage to be recovered performs attitude adjustment, the method for recovering the upper stage of the launch vehicle further includes: acquiring a recovery type instruction; determining the recycling type of the upper stage to be recycled according to the recycling type instruction, wherein the recycling type comprises: overall recovery and engine recovery.
Optionally, when the recovery type is engine recovery, before braking the speed of the upper stage to be recovered to a preset speed, the upper stage recovery method of the launch vehicle further comprises: when the upper stage to be recovered enters a preset separation position, sending a separation instruction to the recoverable engine of the upper stage to be recovered to separate the recoverable engine from the unrecoverable section of the upper stage to be recovered, and updating the upper stage to be recovered to the recoverable engine.
Optionally, the upper-stage recovery method of the launch vehicle provided in the embodiment of the present invention further includes: monitoring the running state of the upper stage to be recovered, and judging whether the running track of the upper stage to be recovered is within the running range of a preset return track or not according to the running state; and if the upper stage to be recovered is not in the running range of the preset return track, adjusting the posture of the upper stage to be recovered according to the running state and the running range of the preset return track until the running track of the upper stage to be recovered is in the running range of the preset return track.
Optionally, when the recovery type is engine recovery, the pneumatic speed reducer is arranged in a transition cabin of an engine to be recovered; when the recovery type is integral recovery, the pneumatic speed reducer is arranged in an equipment cabin of an upper stage to be recovered.
According to a second aspect, an embodiment of the present invention provides a recovery system for an upper stage of a launch vehicle, wherein a pneumatic retarder is disposed on the upper stage of the launch vehicle to be recovered, and the recovery system for the upper stage of the launch vehicle comprises: the first processing module is used for acquiring recovery parameters and controlling the upper stage to be recovered to perform posture adjustment when the recovery parameters meet the preset recovery requirement; the second processing module is used for braking the speed of the upper stage to be recovered to a preset speed when the upper stage to be recovered after the posture is adjusted enters a first position of a preset return track; and the third processing module is used for controlling the pneumatic speed reducer to be unfolded when the upper stage to be recovered braked to the preset speed enters the second position of the preset return track, and recovering the upper stage of the carrier rocket.
Optionally, the upper-stage recovery system of the launch vehicle provided in the embodiment of the present invention further includes: and the fourth processing module is used for sending a separation instruction to the recyclable engine of the upper stage to be recycled when the upper stage to be recycled enters a preset separation position, so that the recyclable engine is separated from the non-recyclable section of the upper stage to be recycled, and the upper stage to be recycled is updated to be the recyclable engine.
Optionally, the upper-stage recovery system of the launch vehicle provided in the embodiment of the present invention further includes: the monitoring module is used for monitoring the running state of the upper stage to be recovered and judging whether the running track of the upper stage to be recovered is within the running range of a preset return track or not according to the running state; and the adjusting module is used for adjusting the posture of the upper stage to be recovered according to the operation state and the operation range of the preset return track if the upper stage to be recovered is not in the operation range of the preset return track until the operation track of the upper stage to be recovered is in the operation range of the preset return track.
An embodiment of the present invention provides a non-transitory computer-readable storage medium storing computer instructions, which when executed by a processor, implement the launch vehicle upper level recovery method according to the first aspect and any one of the alternatives of the present invention.
An embodiment of the present invention provides an electronic device, including: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory having stored therein computer instructions, the processor executing the computer instructions to perform the launch vehicle upper level recovery method according to the first aspect of the present invention and any one of the alternatives.
The technical scheme of the invention has the following advantages:
the embodiment of the invention provides a recovery method and a recovery system for an upper stage of a carrier rocket, wherein a pneumatic reducer is arranged on the upper stage of the carrier rocket to be recovered, so that the whole lift force of the carrier rocket is ensured, and the reentry deceleration and attitude stability are improved; controlling the upper stage to be recovered to perform attitude adjustment by monitoring whether the recovery parameters meet the preset recovery requirements, and ensuring that the running direction of the upper stage to be recovered is aligned with the recovery landing point; when the upper stage to be recovered reaches the first position of the preset return track, the speed of the upper stage to be recovered is braked to the preset speed, when the upper stage to be recovered reaches the second position of the preset return track, the pneumatic reducer is controlled to expand, the upper stage to be recovered is recovered, the pneumatic expansion type speed reduction technology is adopted, the problems that the traditional speed reducer is complex in structure and difficult to install are solved, and the accuracy of the landing position is guaranteed.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic illustration of a pneumatic retarder in an embodiment of the present invention;
FIG. 2 is a flow chart of a launch vehicle upper stage recovery method in an embodiment of the invention;
FIG. 3 is a schematic illustration of the configuration of an engine recovery scheme in an embodiment of the present invention;
FIG. 4 is a schematic view of the configuration of an integrated recycling scheme in an embodiment of the present invention;
FIG. 5 is a block diagram of a recovery system of an upper stage of a launch vehicle according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of an electronic device in an embodiment of the present invention.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. 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 invention.
Furthermore, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
In practical application, the successful recovery of the second substage or the upper stage of the rocket is not precedent, the on-orbit height and the speed of the upper stage lead to the complex recovery technology and the increased difficulty, and the failure of large loss of carrying capacity is one of the constraint conditions, so that the recovery system and the operation are required to be simple, the cost is low, the reliability is high, and the quality is strictly controlled. The need to balance the mission of the launch vehicle and the corresponding design considerations due to the constraints of carrying capacity and reusability in the recovery process of the upper stage, and the need to recover the upper stage with the redundancy of the launch vehicle capacity, therefore, greater flexibility in the design requirements for the recovery solution and operation requirements of the upper stage, such as the upper stage can be designed for staged recovery solutions, i.e., engine recovery and tank structure recovery, because of the higher cost and value of the engine, but considering the additional cost of reusability that may be incurred with staged recovery, the more likely result is to recover only higher value systems such as the engine, while tank structures and other electronic equipment are not recovered.
The embodiment of the invention provides a carrier rocket upper stage recovery method, which is applied to a carrier rocket recovery control system, wherein a pneumatic reducer and an inflatable expanded pneumatic reducer are arranged at an upper stage of a carrier rocket to be recovered, and the pneumatic reducer is shown in figure 1 and comprises the following components: the pneumatic reduction gear comprises an inflation ring, a heat-proof nose cone, an inflation device (a nitrogen cylinder), a flexible heat-proof cover, an initiating explosive cutter and a packaging rope, wherein the initiating explosive cutter and the packaging rope are not shown in the figure, a pneumatic reduction gear which is not inflated is folded and contained in a rigid packaging bag, the packaging rope is opened by the aid of the cutter, the packaging bag is contained around a cabin body structure, a recovery structure of the pneumatic reduction gear can obtain a pneumatic appearance suitable for a ballistic or ballistic-lifting (or quasi-ballistic) returner, the power of a rocket cannot be greatly sacrificed, and the soft landing recovery of the upper level can be realized.
The large blunt profile (which can be geometrically simplified into a spherical cone assembly) of the speed reducer is a typical pneumatic profile of a ballistic reflector, and because of the large resistance coefficient, the speed reducer is quickly decelerated after entering a dense atmosphere, so that pneumatic heating is greatly reduced, the thermal environment is improved, and the peak value of a pneumatic load is effectively controlled; the upper stage to be recovered of the carrier rocket further comprises a flexible heat shield, the flexible heat shield is used for isolating the heat of the upper stage to be recovered, which runs in a preset return track, and the running state is controlled to meet the preset requirement, the flexible heat shield sequentially comprises a heat-proof layer, a heat insulating layer and a bearing layer from outside to inside, the heat-proof layer is made of high-temperature-resistant ceramic fiber fabric materials, the heat insulating layer is made of inorganic heat-insulating composite materials, and the bearing layer is made of fiber fabrics; the design of the multilayer structure of the air bag is based on the principle of easy maintenance and replacement, the outer layer of the heat shield similar to a sandwich tile structure can be quickly replaced, and the flexible heat insulation layer in the air bag can be repeatedly used.
As shown in fig. 2, the upper stage recovery method of a launch vehicle provided in the embodiment of the present invention includes the following steps:
step S1: and acquiring recovery parameters, and controlling the upper stage to be recovered to perform attitude adjustment when the recovery parameters meet the preset recovery requirements.
In the embodiment of the invention, the recovery parameters of the upper stage to be recovered of the carrier rocket are obtained in real time, and when the recovery parameters meet the preset recovery requirement, the upper stage to be recovered is controlled to carry out attitude adjustment; when the recovery parameter does not meet the preset recovery requirement, the recovery parameter of the upper stage to be recovered of the carrier rocket is continuously monitored until the obtained recovery parameter meets the preset recovery requirement, wherein the recovery parameter comprises parameters such as a recovery orbit parameter, an operation height, an operation speed and the like, and other parameters can be included.
Exemplarily, when the recovery parameters meet the preset recovery requirements, sending a posture adjusting instruction; the variable thrust engine is the simplest choice of the upper stage, and is controlled to carry out cold air jet flow according to the attitude adjusting instruction, so as to generate a cold air jet flow acting force; and controlling the thrust change of the upper stage to be recovered according to the cold air jet flow action force, and finishing the posture adjustment of the upper stage to be recovered.
Step S2: and when the upper stage to be recovered reaches the first position of the preset return track, braking the speed of the upper stage to be recovered to a preset speed.
In the embodiment of the invention, after the recovery landing point is determined, the return track is set in advance according to actual needs, after the posture adjustment of the upper stage to be recovered is completed, when the upper stage to be recovered reaches the first position of the preset return track, the speed of the upper stage to be recovered is braked to the preset speed, wherein the preset speed is measured and calculated by utilizing the existing algorithm after the performance of the return track and the pneumatic speed reducer is determined, and the adjustment can be carried out according to actual needs.
And step S3: and when the upper stage to be recovered reaches a second position of the preset return track, controlling the pneumatic speed reducer to be unfolded, and recovering the upper stage to be recovered.
In the embodiment of the invention, after the upper stage to be recovered is braked and falls to the second position of the preset return track, the pneumatic speed reducer is controlled to be unfolded, wherein the pneumatic speed reducer is used for sending a command for controlling the opening of the packaging rope to the cutter, the pneumatic speed reducer which is folded and contained in the rigid package is unfolded and inflated, and the upper stage to be recovered is recovered.
The embodiment of the invention provides a carrier rocket upper stage recovery method, wherein a pneumatic reducer is arranged on an upper stage to be recovered of a carrier rocket, so that the whole lift force of the carrier rocket is ensured, and the reentry deceleration and attitude stability are improved; controlling the upper stage to be recovered to perform attitude adjustment by monitoring whether the recovery parameters meet the preset recovery requirements, and ensuring that the running direction of the upper stage to be recovered is aligned with the recovery landing point; when the upper stage to be recovered reaches the first position of the preset return track, the speed of the upper stage to be recovered is braked to the preset speed, when the upper stage to be recovered reaches the second position of the preset return track, the pneumatic reducer is controlled to expand, the upper stage to be recovered is recovered, the pneumatic expansion type speed reduction technology is adopted, the problems that the traditional speed reducer is complex in structure and difficult to install are solved, and the accuracy of the landing position is guaranteed.
Specifically, in an embodiment, after controlling the upper stage to be recovered to perform attitude adjustment, the method for recovering the upper stage of the launch vehicle specifically includes the following steps:
step S01: a recycle type instruction is fetched.
Step S02: determining the recycling type of the upper stage to be recycled according to the recycling type instruction, wherein the recycling type comprises the following steps: overall recovery and engine recovery.
In the embodiment of the invention, after the posture adjustment of the upper stage to be recovered is completed, the running direction of the upper stage to be recovered is ensured to be aligned with the recovery landing point, then a recovery type instruction is obtained, the recovery type of the upper stage to be recovered is determined, the setting can be carried out according to the actual requirement, for example, in order to reduce the complexity of a recovery system and ensure that the recovery quality is as light as possible, as shown in fig. 3, an engine with high recovery price and high recovery value can be selected, some important instrument and equipment can be recovered along with the recovery of the engine, and the equipment and a pneumatic reducer are arranged at a transition section, if the equipment which can be repeatedly used is required to be recovered as much as possible, as shown in fig. 4, the whole recovery can be selected, the pneumatic reducer and an electrical system of the upper stage to be recovered can be arranged in an electronic equipment cabin, and a storage box is connected with the engine cabin and the electronic equipment cabin.
Specifically, in an embodiment, when the recovery type is engine recovery, before braking the speed of the upper stage to be recovered to a preset speed, the method for recovering the upper stage of the launch vehicle specifically further includes the following steps:
step S04: and when the upper stage to be recovered enters a preset separation position, sending a separation instruction to the recyclable engine of the upper stage to be recovered to separate the recyclable engine from the non-recyclable section of the upper stage to be recovered, and updating the upper stage to be recovered into the recyclable engine.
In the embodiment of the invention, when an upper stage to be recovered enters a preset separation position, three mechanical lock devices are arranged on a separation surface of an engine recovery transition cabin and an upper storage box, after the upper stage is subjected to posture adjustment and braking, a separation instruction is sent out, then a high-pressure helium gas enables the mechanical lock to be unlocked, meanwhile, a helium gas drives a pusher to generate a separation acting force on a butt joint surface to separate the upper stage and the lower stage, an engine control circuit is inserted into and pulled out of a connector and separated from the lower stage through a connector, and a gas-liquid path is separated through electric unlocking and an nonelectric detonation cutter.
Specifically, in an embodiment, the above-mentioned launch vehicle upper-stage recovery method further includes the following steps:
and step S4: and monitoring the running state of the upper stage to be recovered, and judging whether the running track of the upper stage to be recovered is within the running range of the preset return track according to the running state.
In the embodiment of the invention, the running state of the upper stage to be recovered is monitored in real time through the monitor, and whether the running track of the upper stage to be recovered is within the running range of the preset return track or not is judged according to parameters in the running state, such as position, speed, height and the like. It should be noted that, the embodiment of the present invention only illustrates that the operation range is determined by each parameter in the operation state, and the determination may be performed by other parameters in practical application, and the present invention is not limited thereto.
Step S5: and if the upper stage to be recovered is not in the running range of the preset return track, adjusting the posture of the upper stage to be recovered according to the running state and the running range of the preset return track until the running track of the upper stage to be recovered is in the running range of the preset return track.
In the embodiment of the invention, a track design, navigation and guidance control system of the vehicle is the key for completing the launching task and safely and accurately returning the vehicle. After the flying of the ascending section is finished, the typical vertical take-off and landing carrier experiences a plurality of flying sections such as an attitude adjusting section, a braking and repairing section, a high-altitude gliding section, a power deceleration section, an atmospheric deceleration section and a vertical landing section in the returning process, the flying airspace and the speed range are wide, the engine is turned on and off for many times, the flying environment is complex and changeable, and the internal and external disturbance and uncertainty are strong. And if the upper stage to be recovered is not in the operation range of the preset return track, adjusting the posture of the upper stage to be recovered according to the operation state and the operation range of the preset return track until the operation track of the upper stage to be recovered is in the operation range of the preset return track.
The embodiment of the invention provides a carrier rocket upper stage recovery method, wherein a pneumatic reducer is arranged on an upper stage to be recovered of a carrier rocket, so that the whole lift force of the carrier rocket is ensured, and the reentry deceleration and attitude stability are improved; controlling the upper stage to be recovered to perform attitude adjustment by monitoring whether the recovery parameters meet the preset recovery requirements, and ensuring that the running direction of the upper stage to be recovered is aligned with the recovery landing point; when the upper stage to be recovered reaches the first position of the preset return track, the speed of the upper stage to be recovered is braked to the preset speed, and when the upper stage to be recovered reaches the second position of the preset return track, the pneumatic reducer is controlled to be expanded to recover the upper stage to be recovered; on the basis of the traditional rocket configuration (polished rod cylinder), the aerodynamic resistance, the moment and the appearance are not obviously increased, the carrying capacity is not obviously reduced, and the requirements of low-cost launching and technical economy are met; the deceleration technology and the thermal protection are organically combined, and the beneficial effects of the deceleration technology and the thermal protection on aerodynamic force and thermal problems are respectively exerted.
An embodiment of the present invention further provides a launch vehicle upper stage recovery system, as shown in fig. 5, including:
the first processing module 1 is used for acquiring recovery parameters and controlling the upper stage to be recovered to perform posture adjustment when the recovery parameters meet the preset recovery requirements; the module executes the method described in step S1, which is not described herein again.
The second processing module 2 is used for braking the speed of the upper stage to be recovered to a preset speed when the upper stage to be recovered after the posture is adjusted enters a first position of a preset return track; the module executes the method described in step S2, which is not described herein again.
The third processing module 3 is used for controlling the pneumatic reducer to be unfolded when the upper stage to be recovered braked to the preset speed enters a second position of the preset return track, and recovering the upper stage of the carrier rocket; the module executes the method described in step S3, which is not described herein again.
Specifically, in an embodiment, the above-mentioned upper-stage recovery system of a launch vehicle further includes:
the fourth processing module 4 is configured to send a separation instruction to the recyclable engine of the upper stage to be recycled when the upper stage to be recycled enters the preset separation position, so that the recyclable engine is separated from the non-recyclable section of the upper stage to be recycled, and the upper stage to be recycled is updated to be a recyclable engine; the module executes the method described in step S04, which is not described herein again.
The monitoring module 5 is used for monitoring the running state of the upper stage to be recovered and judging whether the running track of the upper stage to be recovered is within the running range of the preset return track or not according to the running state; the module executes the method described in step S4, which is not described herein again.
The adjusting module 6 is used for adjusting the posture of the upper stage to be recovered according to the operation state and the operation range of the preset return track if the upper stage to be recovered is not in the operation range of the preset return track until the operation track of the upper stage to be recovered is in the operation range of the preset return track; the module executes the method described in step S5, which is not described herein again.
Through the cooperative cooperation of the components, the upper-stage recovery system of the carrier rocket provided by the embodiment of the invention ensures the whole lift force of the carrier rocket and simultaneously improves the reentry deceleration and the attitude stability by arranging the pneumatic reducer on the upper stage of the carrier rocket to be recovered; controlling the upper stage to be recovered to perform attitude adjustment by monitoring whether the recovery parameters meet the preset recovery requirements, and ensuring that the running direction of the upper stage to be recovered is aligned with the recovery landing point; when the upper stage to be recovered reaches the first position of the preset return track, the speed of the upper stage to be recovered is braked to the preset speed, when the upper stage to be recovered reaches the second position of the preset return track, the pneumatic reducer is controlled to be expanded, the upper stage to be recovered is recovered, and the pneumatic expansion type speed reduction technology is adopted, so that the problems of complex structure and difficult installation of the traditional reducer are solved, the accuracy of the landing position is ensured, the quality and the reusable cost are reduced, and the accuracy of the landing position is ensured; on the basis of the traditional rocket configuration (polished rod cylinder), the aerodynamic resistance, the moment and the appearance are not obviously increased, the carrying capacity is not obviously reduced, and the requirements of low-cost launching and technical economy are met; the deceleration technology and the thermal protection are organically combined, and the beneficial effects of the deceleration technology and the thermal protection on aerodynamic force and thermal problems are respectively exerted.
An embodiment of the present invention further provides an electronic device, as shown in fig. 6, the electronic device may include a processor 901 and a memory 902, where the processor 901 and the memory 902 may be connected through a bus or in another manner, and fig. 6 takes the connection through the bus as an example.
The memory 902, which is a non-transitory computer readable storage medium, may be used to store non-transitory software programs, non-transitory computer executable programs, and modules, such as program instructions/modules corresponding to the methods in the embodiments of the present invention. The processor 901 executes various functional applications and data processing of the processor, i.e., implements the above-described method, by executing non-transitory software programs, instructions, and modules stored in the memory 902.
The memory 902 may include a program storage area and a data storage area, wherein the program storage area may store an operating system, an application program required for at least one function; the storage data area may store data created by the processor 901, and the like. Further, the memory 902 may include high speed random access memory, and may also include non-transitory memory, such as at least one magnetic disk storage device, flash memory device, or other non-transitory solid state storage device. In some embodiments, the memory 902 may optionally include memory located remotely from the processor 901, which may be connected to the processor 901 via a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.
One or more modules are stored in the memory 902, which when executed by the processor 901 performs the methods described above.
The specific details of the electronic device may be understood by referring to the corresponding related descriptions and effects in the above method embodiments, and are not described herein again.
Those skilled in the art will appreciate that all or part of the processes of the methods of the embodiments described above can be implemented by a computer program, which can be stored in a computer readable storage medium and can include the processes of the embodiments of the methods described above when executed. The storage medium may be a magnetic Disk, an optical Disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a Flash Memory (Flash Memory), a Hard Disk (Hard Disk Drive, abbreviated as HDD), a Solid State Drive (SSD), or the like; the storage medium may also comprise a combination of memories of the kind described above.
The above embodiments are only for illustrating the technical solutions of the present invention and not for limiting the same, and although the present invention is described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications and equivalents may be made to the embodiments of the invention without departing from the spirit and scope of the invention, which is to be covered by the claims.
Claims (5)
1. A carrier rocket upper stage recovery method is characterized in that a pneumatic reducer is arranged on an upper stage to be recovered of a carrier rocket, and the pneumatic reducer comprises: the pneumatic speed reducer is folded and contained in the rigid package when not inflated, the package rope is opened by the aid of the fire cutter, and the package is contained around the cabin structure;
the carrier rocket upper stage recovery method comprises the following steps:
acquiring recovery parameters, and controlling the upper stage to be recovered to perform attitude adjustment when the recovery parameters meet preset recovery requirements;
when the upper stage to be recovered reaches a first position of a preset return track, braking the speed of the upper stage to be recovered to a preset speed;
when the upper stage to be recovered reaches a second position of the preset return track, controlling the pneumatic speed reducer to be unfolded, and recovering the upper stage to be recovered; the unfolding of the pneumatic speed reducer sends an instruction for controlling opening of the wrapping rope to the firer cutter, the pneumatic speed reducer which is folded and stored in the rigid package is opened and inflated, and the upper stage to be recovered is recovered;
after the controlling the upper stage to be recovered to perform attitude adjustment, the method for recovering the upper stage of the carrier rocket further comprises the following steps:
acquiring a recovery type instruction;
determining the recycling type of the upper stage to be recycled according to the recycling type instruction, wherein the recycling type comprises: integral recovery and engine recovery;
when the recovery type is engine recovery, before the braking the speed of the upper stage to be recovered to a preset speed, the upper stage recovery method of the launch vehicle further includes:
when the upper stage to be recovered enters a preset separation position, sending a separation instruction to a recoverable engine of the upper stage to be recovered so as to separate the recoverable engine from a non-recoverable section of the upper stage to be recovered, and updating the upper stage to be recovered into the recoverable engine;
the carrier rocket upper stage recovery method further comprises the following steps:
monitoring the running state of the upper stage to be recovered, and judging whether the running track of the upper stage to be recovered is within the running range of a preset return track or not according to the running state;
and if the upper stage to be recovered is not in the running range of the preset return track, adjusting the posture of the upper stage to be recovered according to the running state and the running range of the preset return track until the running track of the upper stage to be recovered is in the running range of the preset return track.
2. The launch vehicle upper stage recovery method according to claim 1, wherein when the recovery type is engine recovery, the aerodynamic speed reducer is provided in a transition compartment of a recoverable engine;
when the recovery type is integral recovery, the pneumatic speed reducer is arranged in an equipment cabin of an upper stage to be recovered.
3. The upper stage recovery system of the carrier rocket is characterized in that a pneumatic reducer is arranged on an upper stage to be recovered of the carrier rocket, and comprises:
the first processing module is used for acquiring recovery parameters and controlling the upper stage to be recovered to perform posture adjustment when the recovery parameters meet the preset recovery requirement;
the second processing module is used for braking the speed of the upper stage to be recovered to a preset speed when the upper stage to be recovered after the posture is adjusted enters a first position of a preset return track;
the third processing module is used for controlling the pneumatic speed reducer to be unfolded and recovering the upper stage of the carrier rocket when the upper stage to be recovered, which is braked to the preset speed, enters a second position of the preset return track;
the fourth processing module is used for sending a separation instruction to the recyclable engine of the upper stage to be recycled when the upper stage to be recycled enters a preset separation position, so that the recyclable engine is separated from the non-recyclable section of the upper stage to be recycled, and the upper stage to be recycled is updated to be the recyclable engine; the monitoring module is used for monitoring the running state of the upper stage to be recovered and judging whether the running track of the upper stage to be recovered is within the running range of a preset return track or not according to the running state;
the adjusting module is used for adjusting the posture of the upper stage to be recovered according to the operation state and the operation range of the preset return track until the operation track of the upper stage to be recovered is within the operation range of the preset return track if the upper stage to be recovered is not within the operation range of the preset return track;
the pneumatic decelerator includes: the pneumatic speed reducer is folded and contained in the rigid envelope when the pneumatic speed reducer is not inflated, the envelope rope is unsealed by using the fire cutter, and the envelope is contained around the cabin body structure;
and unfolding the pneumatic speed reducer, namely sending an instruction for controlling opening of the packaging rope to the firer cutter, opening and inflating the pneumatic speed reducer which is folded and stored in the rigid packaging bag, and recovering the upper stage to be recovered.
4. A computer-readable storage medium storing computer instructions which, when executed by a processor, implement a launch vehicle upper level recovery method according to claim 1 or 2.
5. An electronic device, comprising:
a memory and a processor, the memory and the processor being communicatively coupled to each other, the memory having stored therein computer instructions, the processor executing the computer instructions to perform the launch vehicle upper level recovery method of claim 1 or 2.
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