763 results about "Launch vehicle" patented technology

The invention discloses a space-based telemetering transmission system for a carrier rocket, and relates to the technical field of rocket measurement and control communication, and the system comprises a rocket-borne network camera which is used for collecting video image data of a preset monitoring point position of the rocket, compressing the video image data, and outputting the compressed video image data as telemetering data; the telemetering transmission equipment is respectively connected with the rocket-borne network camera and the ground equipment, performs telemetering framing on the telemetering data, outputs first telemetering data and outputs second telemetering data to the ground equipment; the space-based power amplifier unit equipment is connected with the telemetering transmission equipment, receives the first telemetering data, amplifies the first telemetering data and then outputs the first telemetering data through radio frequency; the space-based telemetering antenna is connected with the space-based power amplifier unit equipment, receives the first telemetering data and then transmits the first telemetering data to a relay satellite, so that the satellite sends the first telemetering data to a ground measurement and control station; and the ground equipment is used for receiving the second telemetry data and then analyzing and uploading configuration parameter information. The problem that the coverage blind area of a telemetering system mainly based on ground-based measurement and control is large in the prior art is solved.

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 embodiment of the utility model provides a storage tank bottom structure, a storage tank and a carrier rocket, the storage tank bottom structure comprises a shell and a top cover, the shell is of a hollow arc-shaped revolving body structure which is through in the front-back direction, the two ends of the shell are the small-diameter end and the large-diameter end respectively in the axis direction of the shell, and the small-diameter end of the shell is fixedly connected with the top cover; a propellant is arranged on the top cover; a plurality of protruding structures are evenly distributed on the outer side face of the shell in the circumferential direction in the axis direction of the shell. According to the technical scheme, the bottom structure of the thrust bearing type storage tank is simple in process, easy to manufacture in batches and beneficial to achieving light weight of a carrier rocket.

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 discloses a damage tolerance evaluation method and system for a friction plug repair welding joint of a carrier rocket storage tank, and the method comprises the steps: detecting an interface of the friction plug repair welding joint of the carrier rocket storage tank, and obtaining defect information, constitutive parameters of a material, and material attributes; establishing a finite element model, and accurately setting corresponding distribution interface defects; quantizing in-plane and out-plane restraint effects of the crack tip by adopting restraint parameters; processing and preparing a unilateral notch tensile sample, and measuring a local J-R curve of the tip of the precrack at the interface of the friction plug repair welding joint; correcting a real J-R curve of the friction plug repair welding joint of the rocket tank based on the influence of the distribution interface defect characteristics; then the tensile strength values of the friction plug repair welding joint in all the positions in the circumferential direction are corrected, and a corrected real J-R curve is obtained; and the limit crack size under the action of the corresponding internal pressure is obtained by utilizing the crack tip extension driving force curve, and then the critical J integral of the crack is calculated, so that the maximum crack size under the specific load or the maximum internal pressure under the crack with the specific size is obtained.

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.

Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

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 relates to the technical field of aerospace, and discloses a multi-engine mounting cabin section and a carrier rocket. The multi-engine installation cabin section comprises a cabin section and a force transmission mechanism, the force transmission mechanism is located in a cabin section body and connected with a front end frame and a rear end frame of the cabin section, and thrust generated by a center engine is transmitted to a force transmission ring through a main cross beam and finally transmitted to the front end frame of the cabin section through a radial beam and a first force transmission beam. Thrust generated by the peripheral engine is transmitted to the radial beam, the rear end frame and the second force transmission beam through the outer cross beam and finally transmitted to the front end frame of the cabin section, the force transmission process is uniform in force transmission, high in efficiency and good in stability, and the carrying efficiency of the carrier rocket can be improved. The invention further provides a carrier rocket which comprises a rocket body and a plurality of engine installation cabin sections installed on the rocket body, and the rocket carrying requirement is met.

The invention relates to a multi-satellite stacking point type separation mechanism which comprises a carrying support, a satellite bearing frame, a connection unlocking device, a separation electric connector assembly and a travel switch assembly. Spring separation device mounting interfaces are reserved in the satellite bearing frames, each layer of satellite bearing frame is fixedly connected with each layer of flat satellite body, and the lowermost layer of satellite bearing frame is connected with a carrying support; the connecting and unlocking device is installed at the connecting position of every two adjacent layers of satellite force bearing frames, and connecting and orderly unlocking between each layer of satellites, the bottom layer of satellites and the carrying support are achieved. The separation electric connector assembly and the travel switch assembly are installed on each layer of satellite force bearing frame and provide separation on-off signals for the carrier rocket and each layer of satellites respectively, and the separation electric connector assembly further supplies power to each layer of connection unlocking device. The mechanism is good in connection rigidity, reliable in connection and locking and reliable in separation, and can adapt to launch tasks of carrier rockets with different stacking layer numbers of flat satellites.

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 provides a system device for core-level offshore recovery of a carrier rocket and a control method. The system device comprises an offshore recovery platform body, a core-level recovery capture rotary locking device, a dumping thrust reverser, an anti-dumping damping device, an auxiliary holding device and a locking device moving platform. The locking device moving platform can move to any position on the offshore recovery platform body; the core-level recycling, capturing and rotating locking device is used for receiving core-level position signals and supporting vertically descending cores; the dumping thrust reverser is used for holding the core; the anti-toppling damping device is matched with the toppling thrust reverser to enable the core to topple to a horizontal state; the auxiliary clasping device is used for clasping a core in a horizontal state. According to the invention, the carrier rocket core-level can be converted from a vertical fixed state to a horizontal fixed state after being recovered on the offshore recovery platform, the core-level mass center is reduced, the overturning risk of the core-level and the offshore recovery platform body is greatly reduced, and the harbor returning safety after core-level offshore recovery is improved.

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.

Flexible hole forming equipment suitable for a rocket tube section end frame comprises an axial hole forming device, a radial hole forming device, a rotary table, a flexible tool and a control system. Wherein the rotary table is fixed on a foundation through an adjusting sizing block and a foundation bolt; the flexible tool is mounted on the rotary table through a positioning pin and a screw; the axial hole forming device and the radial hole forming device are installed on the two sides of the rotary table at the interval of 90-degree azimuth angles. The device is mainly used for machining axial butt joint holes and radial riveting holes of multi-model cylinder section end frames of spaceflight carrier rockets and axial milling, flexible hole forming of the rocket cylinder section end frames with the diameter of phi 3350 mm and phi 3800 mm can be met, and machining of all inner L-shaped and outer L-shaped end frames with the diameter of phi 3350 mm and phi 3800 mm is considered; the problem that a multi-drill jig tool corresponding to multi-type end frames is tedious to replace is solved, the size precision and the position precision of end frame drilling are greatly improved, and the machining period is shortened.

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 device for holding down a mobile structure, e.g., a payload, to a launch vehicle and for releasing the payload comprises a base structure fixed to the launch vehicle, a plate fixed to the payload, a releasable actuator, a release payload mechanism and a release rod are driven to movement in an axial direction relative to the base structure upon activation of the actuator. The base structure and the plate comprises mating surfaces including a concentric shear feature capable of transferring combined shear, axial, and moment loads between the base structure and the plate, with a single point of preloaded axial-only retention.

The invention discloses a modular foldable grid rudder device driven by a single driving link and applied to attitude adjustment of a cylindrical launching navigation body, and relates to the technical field of underwater launching navigation bodies. The problems that an existing grid rudder structure is complex in control, the reliability of the variant process is poor, a traditional mechanism is prone to damaging the power appearance, and the existing grid rudder structure cannot be applied to a cylindrical navigation body are solved. Base assembly spaces vertically communicated with an inner cavity of a mounting base are arranged on the lower portions of grid rudder storage spaces, each grid rudder storage space is provided with a grid rudder folding module, grid rudders of the grid rudder folding modules are matched with the grid rudder storage spaces in shape, and folding and unfolding and variable attack angle driving mechanisms are embedded in the base assembly spaces. The folding, unfolding and variable attack angle driving mechanism is movably connected with the grid rudder so as to achieve the functions of folding, unfolding and variable attack angle of the grid rudder. The grid rudder follows the modular design principle and can serve as a middle section module to be mechanically and electrically connected with a navigation body to bear the action execution function.

The invention provides a carrier rocket attitude control method and device, a storage medium and electronic equipment, and the method comprises the steps: obtaining attitude angular velocity target values of pitching, yawing and rolling channels of a rocket body at a satellite-rocket separation moment in an offline manner; the method comprises the following steps: designing rocket body spin-up and spin-down time and attitude angular accelerations of pitching, yawing and rolling channels in spin-up and spin-down stages in an off-line manner, obtaining attitude angular velocity values of the pitching, yawing and rolling channels at the spin-up moments of the rocket body before and after satellite-rocket separation in an on-line and real-time manner, and calculating attitude angular velocity tracking instruction values of the pitching, yawing and rolling channels in an on-line and real-time manner; and according to the attitude angular velocity tracking instruction value, the actual attitude angular velocity of the carrier rocket is controlled in real time, so that the deviation between the actual attitude angular velocity and the attitude angular velocity tracking instruction values of the pitching, yawing and rolling channels is kept within a preset deviation range, and the flight attitude of the carrier rocket is stabilized.

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.