516 results about "Launch vehicle" patented technology

The invention provides multichannel spinning and turning integrated equipment for a cylindrical part of a carrier rocket and a machining method. The multichannel spinning and turning integrated equipment comprises a lathe bed, a main spindle box, a closing-in spindle box, a spinning roller frame, a tail top, a heating system, a control system and a hydraulic system. The main spindle box, the closing-in spindle box, the spinning roller frame and the tail top are installed on the lathe bed. The main spindle box is connected with the closing-in spindle box and drives the closing-in spindle box to work, a cylindrical part blank is clamped between the closing-in spindle box and the tail top, the spinning roller frames are located on the two sides of the cylindrical part blank, and the heating system is installed on the spinning roller frames; the control system is connected with the main spindle box, the closing-in spindle box, the spinning roller frame, the heating system and the hydraulic system. The hydraulic system is connected with the main spindle box, the closing-in spindle box, the spinning roller frame and the tail top. Through cooperation of the main spindle box, the closing-in spindle box, the spinning roller frame, the tail top and the like, the in-situ machining function combining forced spinning machining, closing-in machining and turning machining of cylindrical parts, conical parts and curved-bus-shaped parts of the carrier rocket is achieved.

The invention provides a carrier rocket connector shedding monitoring system and method based on multi-source data. The system comprises a multi-source data acquisition module used for acquiring initial image data, initial sensor data and a host instruction of a carrier rocket connector; the multi-source data processing module is used for receiving and processing the initial image data and the initial sensor data to obtain target image data and target sensor data; the intelligent detection module is used for receiving the target image data, the target sensor data and the host instruction, and performing fusion processing on the target image data, the target sensor data and the host instruction so as to realize comparison between an actual state and a theoretical state and obtain a comparison result; and the falling early warning module is used for receiving the comparison result and performing early warning under the condition that the comparison result does not meet the preset condition. According to the scheme, the state of the carrier rocket connector is automatically monitored, and the fault phenomena such as abnormal falling and untimely falling of the connector are early warned in time.

The invention provides a carrier rocket engine stage-switching motor redundancy control system, which is combined with a multi-input instruction redundancy voting method, a voting path software and hardware arbitration method and the like to complete high-reliability carrier rocket engine stage-switching motor control. According to the system, two-out-of-three voting is carried out by using a triple-redundancy input control instruction and interactive heartbeat, software and hardware joint arbitration is carried out on voting results of three modules, and an instruction control channel is determined to complete phase sequence control of the stage conversion winding. The method has strong fault capability, has no single-point failure link, and can ensure the normal operation of the engine conversion motor in the flight process of the carrier rocket.

The invention relates to the technical field of rockets, in particular to a supporting device for a rocket and a transferring and erecting integrated launching vehicle. The supporting device comprises an erecting arm body and a plurality of auxiliary supporting mechanisms. The auxiliary supporting mechanism comprises a supporting bracket, a disc spring force limiter and at least two linear guide rails. The pre-pressure of the disc spring force limiter is adjustable, so that the rigidity of the supporting bracket is matched with the rigidity of the rocket body; the linear guide rails are arranged on the two sides of the supporting bracket respectively. According to the supporting device for the rocket and the transferring and erecting integrated launching vehicle, the supporting bracket is kept to be in a balanced state through the linear guide rail, the floating function is achieved, and the clamping stagnation phenomenon is prevented; force limiting supporting is achieved by adjusting the pre-pressure of the disc spring force limiter, the rigidity of the supporting bracket is made to be close to the rigidity of a rocket body, and therefore it is guaranteed that the additional bending moment cross section load generated by the erecting arm to the rocket is within the allowable range.

The invention provides a carrier rocket ground test system and method supporting visual process configuration. The system mainly comprises: (1) a visual process configuration module, which configures a test process file through a graphical interface; (2) a process analysis and scheduling module for analyzing a process file and converting the process file into a task sequence; the test execution engine module (3) is used for driving bottom hardware and executing a test instruction sequence; (4) the test resource library module is used for storing and managing various information of test elements and various information of test equipment; the execution monitoring and data management module (5) is used for displaying a test execution state in real time and recording whole-process data; according to the method, the test logic and the execution program are separated, and a user can quickly construct, modify and reuse an automatic test process in a graphical mode, so that the test flexibility is greatly improved, and the test adaptability and efficiency are remarkably improved.

The invention discloses a carrier rocket avionics system based on a TSN (Time Sensitive Network) and a carrier rocket avionics data transmission method, and belongs to the technical field of carrier rocket control. A network is physically or logically divided into a periodic time-sensitive data stream, a high-speed time-sensitive data stream and a best effort data stream, the three data streams are subjected to isolation management, and transparent interconnection between a 1553B bus network and a TSN switching network is realized on a protocol layer through an intelligent protocol conversion gateway. Meanwhile, in a network management layer, through an instruction response type configuration protocol, common Ethernet equipment is seamlessly incorporated into the global scheduling and control category of the TSN network. According to the invention, by constructing the avionics network system with three-layer partition and dual-network fusion, multi-network seamless fusion on the rocket can be realized, the real-time performance of the network is improved, and the key requirements of rocket recovery are met.

The invention discloses a reusable carrier rocket marine landing recovery device which comprises a tower body, a driving module, a first mechanical capturing arm, a second mechanical capturing arm, a first clamping arm and a second clamping arm. The tower body comprises first to fourth stand columns and first to eighth cross beams; the driving module comprises first to twelfth driving units; each of the first to twelfth driving units comprises a driving motor, a working track, a lead screw nut, a first bearing, a second bearing, a first bearing seat and a second bearing seat. On the premise that a simple electric control system is adopted, marine recovery of the carrier can be achieved, the structure is simple, response is rapid, good reliability and maintainability are achieved, the device is suitable for recovery tasks of carrier rockets of various models, and the launching cost is effectively reduced.

The invention discloses a mobile medium-large liquid carrier rocket capturing and recycling system, and relates to the technical field of rocket recycling. According to the mobile medium-large liquid carrier rocket capturing and recycling system, through the mobile platform design that a crane is adopted to carry a connecting truss, a switching frame and a capturing arm, rocket body information is obtained in real time in combination with a camera module, a rocket position sensor and the like, and interaction with a ground center is achieved through a data transmission module; the control module accurately controls the transmission assembly to adjust the capturing arm, the buffering assembly is matched to absorb impact, and a parachute landing mode is replaced to improve the control precision. According to the movable characteristic, the dependence on a fixed land or seaborne recovery site is reduced, the site construction and maintenance cost is reduced, the influence of environmental factors on recovery is reduced, and the problems that in an existing medium-large liquid carrier rocket recovery technology, parachute landing control is difficult, the land / seaborne recovery cost is high, and the influence of the environment is large are solved.

The invention provides a simulation method and system for the launch process of a carrier rocket and electronic equipment, and relates to the technical field of rocket launch simulation. The method comprises the steps that a launching scheme of the carrier rocket is determined, and the launching scheme comprises launching parameters of the carrier rocket; modeling and verifying the launching scheme; and performing simulation test on the launch process of the carrier rocket based on the verified launch scheme, and responding and correcting faults in the simulation test process. According to the invention, the problem that the safety of the launch task of the carrier rocket is threatened due to the fact that key design defects are not found in time due to multiple technical bottlenecks existing in the distributed simulation technology of the reusable carrier rocket is solved.

The invention discloses a carrier rocket propellant management device which comprises a porous partition plate, a screen structure, a screen support, a storage box, a conveying pipe and a pressurizing pipe. The porous partition plate is installed on the upper portion of the storage box and used for restraining the propellant from shaking in the long-time small negative overload section, and the low-temperature liquid propellant is prevented from being mixed with the air pillow. The porous partition plate is a disc formed by splicing fan-shaped pore plates and is mounted at the upper part of the storage box; the screen structure is positioned at the lower part of the storage box; the screen structure is formed by splicing a plurality of fan-shaped components into a circle and comprises an outer ring, a middle ring and an inner ring; the screen support comprises a plurality of vertical partition plates and a framework and is used for supporting the screen structure and playing an anti-vortex role at the same time; the framework is fixed on the vertical partition plate; the storage box is communicated to a rocket engine through a conveying pipe; and the pressurizing pipe is used for conveying pressurizing gas to the storage box. The device has the functions of gas isolation and liquid storage, can meet the matching requirements of a sinking engine, is beneficial to secondary weight reduction, and improves the effective load.

The invention relates to a reusable propellant storage tank of a carrier rocket, and belongs to the technical field of liquid rocket propellant storage and management. The propellant storage box comprises a storage box body, and a lower-layer partition plate assembly, a middle-layer partition plate assembly and an upper-layer partition plate assembly which are arranged in a storage cavity of the storage box body, and the three layers of partition plate assemblies are of disc-shaped structures covering the cross section of the storage box. A first circulation area is arranged in the middle of the lower-layer partition plate assembly, a sealing plate and a second circulation area surrounding the sealing plate are arranged in the middle of the middle-layer partition plate assembly, a third circulation area is arranged in the middle of the upper-layer partition plate assembly, and the first circulation area, the second circulation area and the third circulation area are staggered in the radial direction, so that a nonlinear damping type liquid circulation path is formed in the storage tank. Therefore, violent shaking of the propellant in a weightlessness or variable acceleration environment is inhibited, and reliable restarting of the engine is guaranteed. According to the storage box, the structure is simple and reliable, the shaking restraining effect is remarkable, and the storage box is particularly suitable for propellant management of a reusable carrier rocket.

The invention discloses a reusable carrier rocket ground active recovery system and recovery method.The system comprises a landing buffer mechanism, an omnidirectional self-driven carrying platform, a rocket body posture auxiliary stabilizing mechanism and a landing structure, the landing structure comprises bearing feet, the bearing feet are located on a rocket, and a positioning device is arranged on the omnidirectional self-driven carrying platform; the rocket body posture auxiliary stabilizing mechanism comprises two pairs of clamping rods which are arranged in parallel in a staggered mode, the two ends of each clamping rod are located on a sliding table, the clamping rods are driven by the sliding table to move, and the sliding table is located on a sliding rail; the landing buffering mechanism is located on the omni-directional self-driven carrying platform and comprises a force bearing buffering base and a flexible contact pad located on the force bearing buffering base. The rocket recovery control difficulty is reduced while the carrying capacity of the rocket is guaranteed, and the rocket recovery control device is reasonable and stable in structure, capable of being applied to recovery of rockets of multiple specifications, wide in applicability and wide in application prospect.

The invention discloses a dynamic pressure-based carrier rocket grid rudder control method, which comprises the following steps of: according to a pre-launch binding wind field and the speed of a carrier rocket at the current moment, calculating to obtain the relative airflow speed of the carrier rocket at the current moment; according to the current relative airflow velocity of the carrier rocket, calculating to obtain a current dynamic pressure estimated value; according to the dynamic pressure estimation value at the current moment, solving a control law parameter in the grid rudder online variable gain control law to obtain an optimal control law parameter at the current moment; according to the optimal control law parameters at the current moment, a grid rudder swing angle control instruction at the current moment is obtained through calculation, and real-time control over the grid rudder of the carrier rocket is completed. The method can effectively adapt to the rapid change pneumatic environment of the reentry flight section, remarkably reduces the flight deviation, is suitable for various carrier rocket reentry recovery scenes, and has the advantages of being high in engineering practicability, high in control efficiency and the like.

The invention provides a power measurement and control system and method for a liquid carrier rocket, and relates to the field. Comprising a to-be-tested real equipment system used for completing a rocket body test; the simulator is used for installing a simulation equipment system, and simulation equipment in the simulation equipment system is in one-to-one correspondence with real equipment in the real equipment system; the control machine is in communication connection with the real equipment system and / or the simulator and is used for issuing a target instruction to the real equipment system and / or the simulator in the rocket body testing process; the front-end machine is in communication connection with the control machine and the simulator and is used for forwarding first feedback information after the simulator executes the target instruction to generate the first feedback information; the monitoring machine is in communication connection with the front-end machine, the real equipment system and the simulator and is used for receiving first feedback information and / or second feedback information in the rocket body testing process and monitoring the first feedback information and / or the second feedback information; the second feedback information is feedback information generated after the real equipment system executes the target instruction.

The invention relates to a carrier rocket secondary reusable electrical system based on a modular TTE-TSN bus, and aims to solve the problems of reliability, light weight and maintenance efficiency in high-speed reentry and precise recovery of a secondary rocket. The system comprises a modular comprehensive control unit, a redundant TTE-TSN high-speed bus, a distributed thermal protection monitoring network and an intelligent health assessment module. Through the modular design, electrical equipment is greatly reduced, and the mass is obviously reduced; the redundant TTE-TSN high-speed bus realizes high-bandwidth and high-reliability transmission of messages on the rocket; the thermal protection monitoring network and the attitude coordination system dynamically optimize reentry thermal load distribution; the intelligent health assessment model predicts the structural life and reuse feasibility based on machine learning. According to the method, the reuse economy and reliability of the two-stage rocket are remarkably improved, and the method is suitable for commercial spaceflight and hypersonic flight vehicle tasks.

The invention provides a carrier rocket time sequence control full redundancy implementation method, and aims to improve the fault adaptability and the working reliability of a time sequence control system. The full-redundancy design method of three-path information source redundancy, three-path transmission line redundancy, two-out-of-three voting control redundancy and five-tube relay instruction driving redundancy is adopted in the sequential control system, the capacity of adapting to all first-degree faults and most second-degree faults is achieved, a single-point failure link does not exist, and the reliability is high. Normal work of the sequential control system can be ensured in the flight process of the carrier rocket. Based on a three-bus communication electrical architecture of a new generation carrier rocket electrical system, a full-redundancy design implementation method of information source redundancy, transmission line redundancy, voting control redundancy and instruction driving redundancy is adopted, high-reliability carrier rocket time sequence control is completed, the fault adaptive capacity of the time sequence control system is improved, and the time sequence control system has a wide application prospect. And the working reliability of the system in the rocket flight process is ensured.

The invention discloses a test run fixing device and method for a carrier rocket power system, and the device comprises an inhaul cable device which is suitable for being fixed to the top of the carrier rocket power system; the pre-tightening device is provided with a first end and a second end, the first end of the pre-tightening device is used for being connected with a test bed so as to fix the pre-tightening device, and the pre-tightening device can selectively adjust the pre-tightening force of the first end and the second end; the second end of the pre-tightening device is connected with the inhaul cable device through the rigging, and a sensor used for detecting the pulling force of the rigging is arranged on the rigging; and the monitoring device judges whether the tension detection value of the sensor meets a preset range or not and sends out an alarm signal and / or adjusts the pre-tightening force of the first end and the second end of the pre-tightening device after the tension detection value exceeds the preset range. According to the test run fixing device, the tension of the rigging can be adjusted through the pre-tightening device, the tension of the rigging is adjusted under the abnormal condition, and the safety and applicability of carrier rocket power system test run are improved.

The invention discloses a rocket fault reconstruction method for ensuring the safe height of an orbit under random factor disturbance. The method comprises the following steps: S1, establishing a deterministic trajectory optimization model of a carrier rocket; s2, on the basis of the deterministic trajectory optimization model, introducing random disturbance representing initial state deviation and engine thrust deviation, and establishing a random trajectory optimization model of the carrier rocket; s3, performing convex processing on the random trajectory optimization model, and converting an original problem including a nonlinear term and a non-convex constraint into a convex optimization problem; and S4, solving the convex optimization problem after the convex processing by adopting a sequence convex algorithm, and obtaining a rocket fault reconstruction trajectory capable of ensuring the safe height of the orbit under the disturbance of random factors. According to the method, efficient online solving of a strong nonlinear non-convex random trajectory optimization problem can be realized, so that a fault reconstruction trajectory which can strictly guarantee the safety height of an injection orbit in the probabilistic sense is generated.

The invention relates to a frame format online reconstruction system and method based on an FPGA (Field Programmable Gate Array) external memory, belongs to the technical field of carrier rockets, and solves the problems of long development period and code compatibility of single-task software. The system comprises a TOP module, a RESET function module, an MLVDS communication function module, an EEPROM storage function module and a frame format reconstruction function module, the EEPROM storage function module is used for performing write operation on configuration parameters sent by a main module according to function division of a storage space and solidifying the configuration parameters in an EEPROM, and after power-off restart reset is finished, the EEPROM storage function module is used for performing write operation on the configuration parameters sent by the main module. Reading operation is executed on the EEPROM, and read configuration parameters are distributed to a frame format reconstruction module according to functional area division; and the frame format reconstruction function module is used for executing reconstruction logic operation of the frame format. By means of the system, productization and generalization design of multi-task model software is achieved, and the software reuse rate is remarkably increased.

The application provides a small satellite platform structure which carries a large amount of propellant and is connected and separated in point mode, belongs to the technical field of spacecraft structure, and comprises a frame, a bottom plate, a lower cabin partition plate, a storage tank support rod, a middle layer plate, an upper cabin partition plate, a top plate and a side plate, so that the side plate surrounds the parallelly arranged bottom plate, middle layer plate and top plate into a closed box body, the bottom plate is connected to the frame, the storage tanks are arranged diagonally in the round holes on the bottom plate and the middle layer plate, and the storage tank support rods are uniformly distributed around the round holes; the middle layer plate separates the box body into an upper cabin and a lower cabin, the upper cabin partition plate is connected in the upper cabin, and the lower cabin partition plate is connected in the lower cabin. The application proposes a configuration of "point connection + storage tank sinking", meets the demand of the small satellite platform for carrying a large amount of propellant, effectively reduces the whole satellite center of mass, and improves the satellite dynamic environment; meanwhile, the bottom main load-bearing frame cooperates with a detachable adapter block, can adapt to different mechanical interfaces of launch vehicles, and realizes point connection and separation.

This invention addresses the common failure problems encountered by actuators during the flight of heavy-lift launch vehicles in disturbed environments. It studies a method for achieving rocket attitude stabilization and tracking under complex conditions, proposing an adaptive fault-tolerant backstepping attitude control design method. First, to avoid attitude singularities, a quaternion-based kinematic and dynamic model of the launch vehicle oriented towards actuator failures is established. Based on this model, an adaptive fault-tolerant backstepping attitude controller is designed to adaptively estimate and compensate for uncertainties and external disturbances, handling potential failures and ensuring the stability of the control system. The algorithm proposed in this invention is more effective and superior than traditional adaptive backstepping methods.

The embodiment of the invention provides a method, a device and equipment for determining a data flow of a system on a carrier rocket. The method comprises the following steps: acquiring operation data and working condition data of the carrier rocket; determining a task stage of the carrier rocket according to the operation data and the working condition data; according to the task stage, determining a data stream of a system on the carrier rocket, the data stream comprising at least one of transmission path planning, bandwidth allocation and priority adjustment; acquiring communication state data of the carrier rocket; according to the communication state data, adjusting a data flow of a system on the carrier rocket to obtain a target data flow; and outputting the target data stream. According to the embodiment of the invention, bandwidth requirements of different stages can be matched in real time, bandwidth waste or insufficiency caused by fixed allocation is avoided, and the problem of poor dynamic change adaptability of the task stage is solved.

1. The name of the design product: Launch Vehicle (Chirei 6). 2. The use of the design product: used for space transportation, sending the payload such as artificial earth satellites, manned spacecraft, space stations or space probes into the predetermined space orbit. 3. The design points of the design product: the combination of shape, pattern and color. 4. The picture or photo that best shows the design points: perspective view. 5. The design claimed contains color.

The invention discloses a head-tail double-end reverse thrust recoverable rocket based on double-layer spiral interlayer gas storage and a control method of the head-tail double-end reverse thrust recoverable rocket. A rocket body is of a double-layer stainless steel cylinder wall structure, a continuous spiral connecting grating is arranged between the inner wall and the outer wall, the cross section of the continuous spiral connecting grating is petal-shaped, and a closed high-pressure-resistant interlayer storage cavity is formed. An inert gas nozzle array driven by a plurality of independent electromagnetic control valves is arranged at the bottom of the rocket, and the inert gas nozzle array and the main propulsion engine are arranged cooperatively; the head part is provided with centralizing nozzles which are annularly distributed; a double-umbrella system is arranged on the top. Through a unique spiral grating structure and a head-tail double-end cooperative control strategy, the problems that a traditional rocket gas storage system is large in weight, and a long and thin rocket body is difficult to resist wind and stabilize the posture are solved, the landing precision and safety are remarkably improved, and the method is suitable for a reusable carrier which is low in cost and high in reliability.

The invention relates to the technical field of aerospace, in particular to a method for calculating the sea-launch take-off drift distance of a carrier rocket. The method comprises the steps that a launching platform shaking model is established under a launching platform body coordinate system, and a launching platform rolling angle and a launching platform pitching angle are obtained; establishing a carrier rocket vector form dynamical model under a carrier rocket body coordinate system to obtain the attitude angular velocity of the carrier rocket and the displacement of the carrier rocket mass center; obtaining relative displacement of a launch vehicle tail observation point and a launch platform motion reference point under a launch point gravity coordinate system according to the launch platform rolling angle, the launch platform pitching angle, the attitude angular velocity of the launch vehicle and the displacement of the launch vehicle mass center; and according to the relative displacement, obtaining the synthetic drift distance of the carrier rocket tail observation point relative to the launching platform under the body coordinate system of the launching platform. The method can reduce the prediction error of the sea-launch take-off drift distance of the carrier rocket, and meets the sea-launch high safety margin requirement.

The reusable high-temperature-resistant thermal protection structure comprises a flexible buffer layer, a high-temperature-resistant thermal insulation layer and a rigid thermal protection layer, the high-temperature-resistant thermal insulation layer is located on the upper surface of the flexible buffer layer, and the flexible buffer layer and the rigid thermal protection layer are bonded and combined through a high-temperature-resistant adhesive; the rigid heat-proof layer is positioned on the upper surface of the high-temperature-resistant heat-insulating layer and is screwed and combined in a mechanical manner; and the reusable high-temperature-resistant thermal protection structure is adhered to the surface of the base material through a high-temperature-resistant adhesive. By adopting the design thought that the flexible buffer layer and the high-temperature-resistant heat-insulating layer as well as the high-temperature-resistant heat-insulating layer and the rigid heat-proof layer are respectively screwed and combined in an adhesive and mechanical manner, the heat-proof composite material has the capability of resisting a high-temperature environment of more than 1400 DEG C and repeatedly preventing heat for multiple times, the engineering workload is reduced, and the working efficiency is improved. The problems that an existing carrier rocket surface thermal protection coating is low in heat-resistant temperature and cannot be repeatedly used are solved. Meanwhile, the adopted high-temperature-resistant heat insulation layer is made of aerogel materials, the efficient heat insulation capacity is achieved, and it is ensured that heat is lost in the transfer process.

The invention discloses a method for evaluating the carrying capacity of a carrier rocket under a power system fault, and the method comprises the steps: S1, collecting the state information of the carrier rocket, including the shutdown margin and speed of a first-stage pre-commanding shutdown moment, the first-stage shutdown type, and the speed, position and program angle of a first-stage and second-stage separation moment; s2, judging whether the state of the carrier rocket meets a carrying capacity evaluation starting condition or not, if the starting condition is met, starting carrying capacity evaluation, and otherwise, not starting carrying capacity evaluation; s3, the speed, the position and the program angle of the carrier rocket at the first-stage and second-stage separation moment serve as initial states, and the mass of an oxidizing agent needing to be consumed when the carrier rocket enters an original target orbit is calculated through dynamic integration; and S4, judging whether the mass of the oxidant needing to be consumed when the carrier rocket enters the original target orbit is greater than the mass of the available oxidant or not, if the mass of the oxidant needing to be consumed is greater than the mass of the available oxidant, sending out a trajectory reconstruction signal, otherwise, not sending out the trajectory reconstruction signal.

An acoustic blanket absorbs acoustic energy and reduces noise in a launch vehicle. The acoustic blanket may be overlaid on a wall of a payload fairing of the launch vehicle. Materials and construction of the acoustic blanket allow for a relatively thin and light sound barrier. The acoustic blanket may comprise vertically-lapped polyester that is overlaid with a lightweight melamine foam. This combination of materials creates an acoustic impedance mismatch between layers that leads to absorption of acoustic energy across a relatively broad range of frequency bands. The acoustic blanket has a particular heat seal pattern that helps absorb noise while allowing the acoustic blanket to be relatively soft and flexible, which is useful for attaching the acoustic blanket to a curved wall of a fairing or other launch vehicle shapes. The acoustic blanket utilizes micro-perforations on multiple sides to allow for movement of air / venting while maintaining the bulk materials inside.

The invention discloses a carrying capacity optimization method and device of a reusable carrier rocket and related equipment. The method comprises the following steps: constructing a trajectory model of the carrier rocket; designing a flight program based on the characteristics of each stage; determining orbit injection requirements, and determining constraint conditions based on the orbit injection requirements; establishing an optimization model; and iteratively optimizing the decision variable of the trajectory model according to the optimization model under the limitation of the constraint condition so as to maximize the carrying capacity of the carrier rocket. And on the basis of the optimized decision variable, the carrying capacity of the carrier rocket is maximized under the condition that complex injection constraints and harsh recovery requirements are met.

The invention relates to a flywheel nut unlocking and separating mechanism for a carrier rocket interstage separation technology, and belongs to the field of spaceflight. The device comprises a lock rope, a locking and separating assembly and a transmission assembly. The locking and separating assembly comprises an upper bolt, a flywheel nut and a lower bolt; a locking groove is formed in the outer wall of the flywheel nut; the lower end of the upper bolt penetrates through the upper end of the flywheel nut and is matched with the upper thread; the upper end of the lower bolt penetrates through the lower end of the flywheel nut and is matched with the lower thread; the transmission assembly comprises a connecting rod transmission mechanism and a check block. The stop block is fixedly connected with the connecting rod transmission mechanism. Lock rope driving is matched with a connecting rod transmission mechanism, and non-firework unlocking is achieved. Compared with initiating explosive devices such as explosive bolts, the initiating explosive device can be detected in advance, so that the performance consistency can be ensured, the risk of high-temperature fuel gas and scrap pollution is eliminated, and strong electromagnetic pulse interference is avoided. Meanwhile, the mode can be repeatedly operated, multiple locking and separation are supported, and the task cost is remarkably reduced.