Adaptive saturated tracking control for solid launch vehicles in ascending based on differential inclusion stabilization

The large-range uncertainties of specific impulse,mass flow per second,aerodynamic coefficients and atmospheric density during rapid turning in solid launch vehicles(SLVs) ascending leads to the deviation of the actual trajectory from the reference one.One of the traditional trajectory tracking methods is to observe the uncertainties by Extended State Observer(ESO) and then modify the control commands.However,ESO cannot accurately estimate the uncertainties when the uncertainty ranges are large,which reduces the guidance accuracy.This paper introduces differential inclusion(DI) and designs a controller to solve the large-range parameter uncertainties problem.When above uncertainties have large ranges,it can be combined with the ascent dynamic equation and described as a DI system in the mathematical form of a set.If the DI system is stabilized,all the subsets are stabilized.Different from the traditional controllers,the parameters of the designed controller are calculated by the uncertain boundaries.Therefore,the controller can solve the problem of large-range parameter uncertainties of in ascending.Firstly,the ascent deviation system is obtained by linearization along the reference trajectory.The trajectory tracking system with engine parameters and aerodynamic uncertainties is described as an ascent DI system with respect to state deviation,which is called DI system.A DI adaptive saturation tracking controller(DIAST) is proposed to stabilize the DI system.Secondly,an improved barrier Lyapunov function(named time-varying tangent-log barrier Lyapunov function) is proposed to constrain the state deviations.Compared with traditional barrier Lyapunov function,it can dynamically adjust the boundary of deviation convergence,which improve the convergence rate and accuracy of altitude,velocity and LTIA deviation.In addition,the correction amplitudes of angle of attack(AOA) and angle of sideslip(AOS) need to be limited in order to guarantee that the overload constraint is not violated during actual flight.In this paper,a fixed time adaptive saturation compensation auxiliary system is designed to shorten the saturation time and accelerate the convergence rate,which eliminates the adverse effects caused by the saturation.Finally,it is proved that the state deviations are ultimately uniformly bounded under the action of DIAST controller.Simulation results show that the DI ascent tracking system is stabilized within the given uncertainty boundary values.The feasible bounds of uncertainty is broadened compared with Integrated Guidance and Control algorithm.Compared with Robust Gain-Scheduling Control method,the robustness to the engine parameters are greatly improved and the control variable is smoother.

Robust Attitude Control for Reusable Launch Vehicles Based on Fractional Calculus and Pigeon-inspired Optimization

In this paper, a robust attitude control system based on fractional order sliding mode control and dynamic inversion approach is presented for the reusable launch vehicle RLV during the reentry phase. By introducing the fractional order sliding surface to replace the integer order one, we design robust outer loop controller to compensate the error introduced by inner loop controller designed by dynamic inversion approach. To take the uncertainties of aerodynamic parameters into account, stochastic robustness design approach based on the Monte Carlo simulation and Pigeon-inspired optimization is established to increase the robustness of the controller. Some simulation results are given out which indicate the reliability and effectiveness of the attitude control system. © 2014 Chinese Association of Automation.

Flight Record of the Long March Series of Launch Vehicles

(Continued) The 75th Launch On December 30, 2003, the LM-2C/SM launch vehicle launched theTance 1 (TC-1) satellite into orbit from the Xichang Satellite Launch Center. The satellite entered a super geosynchronous orbit . Launch Site: Xichang Satellite Launch Center Launch Result: Success At 03:06 Beijing time on December 30, the LM-2C/SM launch vehicle lifted off into space with TC-1 (equatorial satellite) and precisely sent the satellite into

Flight Record of the Long March Series of Launch Vehicles

(Continued)The 71st Launch On October 15,2003,China's first manned spaceship,Shenzhou 5,was launched by a LM-2F launch vehicle.The first Chinese astronaut Yang Liwei stayed in space for 21 hours and landed back on the Earth safely on October 16。

Flight Record of the Long March Series of Launch Vehicles

(Continued)THE 67TH LAUNCHOn May 15, 2002, a LM-4B launch vehicle lifted off with FY-1D meteorological satellite and HY-1A oceanic satellite from Tai-yuan Satellite Launch Center and

Flight Record of the Long March Series of Launch Vehicles

(Continued)THE 67TH LAUNCHOn May 15, 2002, a LM-4B launch vehicle lifted off with FY-1D meteorological satellite and HY-1A oceanic satellite from Tai-yuan Satellite Launch Center and

Flight Record of the Long March Series of Launch Vehicles

(Continued) THE 59TH LAUNCH On November 20,1999,a LM-2F launch vehicle lifted off with China’s indigenous Shenzhou 1 experimental spaceship from Jiuquan Satellite Launch Center.Shenzhou 1 returned to Earth on November 21 after 21 hours of in-orbit operation and circling the Earth 14 times.

Long March Launch Vehicles Promote Quick and Sound Development of Satellite Applications

INTRODUCTION Launch vehicles are a precondition and main carrier for space activities for human beings.Their development have directly promoted the technology of satellite applications,manned spaceflight,deep space exploration,and promoted the development of communication,navigation,environmental monitoring,resource exploitation,scientific research and so on.

Flight Record of the Long March Series of Launch Vehicles

(Continued) The 79th Launch On September 9, 2004, a LM-4B launch vehicle launched two satellites, SJ-6A and SJ-6B, into space both for space environment exploration from the Taiyuan Satellite Launch Center. The two satellites entered their preset sun synchronous orbits. Launch Site: Taiyuan Satellite Launch Center Launch Result: Success At 07:14 Beijing time on September 9, the LM-4B launch vehicle was launched into space with SJ-6A and SJ-6B on board.

Hierarchical structured robust adaptive attitude controller design for reusable launch vehicles

Reentry attitude control for reusable launch vehicles （RLVs） is challenging due to the characters of fast nonlinear dy- namics and large flight envelop. A hierarchical structured attitude control system for an RLV is proposed and an unpowered RLV con- trol model is developed. Then, the hierarchical structured control frame consisting of attitude controller, compound control strategy and control allocation is presented. At the core of the design is a robust adaptive control （RAC） law based on dual loop time-scale separation. A radial basis function neural network （RBFNN） is implemented for compensation of uncertain model dynamics and external disturbances in the inner loop. And then the robust op- timization is applied in the outer loop to guarantee performance robustness. The overall control design frame retains the simplicity in design while simultaneously assuring the adaptive and robust performance. The hierarchical structured robust adaptive con- troller （HSRAC） incorporates flexibility into the design with regard to controller versatility to various reentry mission requirements. Simulation results show that the improved tracking performance is achieved by means of RAC.

Six-DOF trajectory optimization for reusable launch vehicles via Gauss pseudospectral method

To be close to the practical flight process and increase the precision of optimal trajectory, a six-degree-offreedom（6-DOF） trajectory is optimized for the reusable launch vehicle（RLV） using the Gauss pseudospectral method（GPM）. Different from the traditional trajectory optimization problem which generally considers the RLV as a point mass, the coupling between translational dynamics and rotational dynamics is taken into account. An optimization problem is formulated to minimize a performance index subject to 6-DOF equations of motion, including translational and rotational dynamics. A two-step optimal strategy is then introduced to reduce the large calculations caused by multiple variables and convergence confinement in 6-DOF trajectory optimization. The simulation results demonstrate that the 6-DOF trajectory optimal strategy for RLV is feasible.

The Development of Autonomous Dynamic Trajectory Optimization Control of Launch Vehicles

This paper first introduces the technical requirements for autonomous flight, with a brief review of the International Academy of Astronautics(IAA) study group, "autonomous dynamic trajectory optimization control of launch vehicle". Two research scenarios, ascent rescue and powered descent, are compared from the viewpoint of optimal control. On this basis, the technologies on the autonomous trajectory planning and control under the thrust-drop failures in the ascending phase, and the autonomous guidance method during the powered landing for the recovery of the rockets are discussed respectively. For the ascending problem, the characteristics of different solutions, including the iterative guidance method(IGM)-based residual carrying capacity evaluation, the state-triggered indices(STI), the joint planning with the payload’s performance, and the multiple graded optimization(MGO), are analyzed for comparison. For the landing problem, the challenges such as the feasible region reduction caused by high thrust weight ratio(HTWR) and the disturbance adaptability brought by the limited feasible region, are studied in detail, as well as the onboard planning demonstration flight in China are introduced. Finally, the foundations supporting the above methods are summarized, which play an important role in promoting the flight autonomy.

Intelligent and Autonomous Flight Technology for Launch Vehicles

This paper proposes the architecture of an intelligent flight launcher system as well as fundamental solutions to capability prediction and dynamic planning. This effort reflects the latest progress in the applications of intelligent and autonomous technology for launcher flights. The paper first describes the characteristics and capabilities of intelligent and autonomous systems and classifies various related technologies. In the context of intelligent and autonomous technology in aerospace engineering, it then focuses on technical difficulties involved with intelligent flight and reviews developments in the field. An E^3 classification model of an intelligent flight launcher is then proposed and its application scenarios are discussed. Based on an intelligent flight system configuration of the launcher, the online trajectory planning and initial value guess are examined, and vertical landing is provided as an example to explain the effects of the implementation of computational intelligence to flight systems.

Research on Unattended Loading Technologies of the New Generation Launch Vehicles

According to the unattended loading requirements of the new generation launch vehicles,auto-docking technology for the first stage fill-drain connector and zero-second quick detachment technology for the second stage fill-drain connector were proposed based on the analysis and summary of unattended loading connector technology at home and abroad.These technical solutions were verified to be reasonable and feasible by tests,and they had been successfully applied to the Long March 6 A(LM-6 A),laying a foundation for the unattended test and launch of the new generation launch vehicles.

LM-11--The Main Force in China＇s Small Launch Vehicles for Commercial Launch

The Long March 11 launch vehicle(LM-11) is the only solid launch vehicle within China's new-generation launch vehicle series, enabling a full spectrum of Chinese launch vehicles. Compared with other China's LM series launch vehicles, it has the shortest launch preparation time. With the characteristics of appropriate launch capability, quick response, easy-to-use, flexible operation, universal interface and strong task adaptability, LM-11 can better meet the launch requirements for various small networking satellite, replacement and for emergency use. After four successful launches, LM-11 has become the main Chinese launch vehicle oriented to the international small satellite commercial launch market.

Effect of Fuselage Cross Section on Aerodynamic Characteristics of Reusable Launch Vehicles

An experimental study on examining aerodynamic characteristics of fuselage cross sections for RLVs (Reusable Launch Vehicles) was conducted at Mach number 0.3, 0.9 and 4.0 in the wind tunnel of ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency). Three bodies, having the same projected area and length, with and without a set of fins, were tested. Their cross sections are a circle, a square and a triangle with rounded corners. The results showed that the fuselage cross sections had large effects on aerodynamic characteristics in subsonic and transonic flow. The lift coefficient of the model having the triangular cross section with a set of the fins was larger than that of the others in high angles of attack region due to contributions of the separation vortices generated from the fuselage expanding to the wing surface.

Technology and Market Prospect Analysis of Low Cost Small-lift Launch Vehicles for Small Satellites

The technological development status of new generation low cost small-lift launch vehicles applied to small satellite launch is investigated in this paper. The development trends are summarized, including low cost and rapid response capability, utilization of mature rocket and missile technology, the development of mobile launch technology adopting air-based platforms and use of innovative technology. Moreover, the external power and internal demand of the small-lift launch vehicle are analyzed and the market prospect is forecasted. Finally, proposals for the development of small-lift launch vehicles are put forward, including exploration of the potential of existing rocket and missile technology, development of multi-platform mobile launch technology and further application of innovative technology and ideas.

Compensated acceleration feedback based active disturbance rejection control for launch vehicles

In this paper, the attitude tracking and load relief control problems against wind disturbances and uncertain aerodynamics as well as the engine thrust of launch vehicles are studied.Firstly, a framework of Compensated Acceleration Feedback based Active Disturbance Rejection Control(CAF-ADRC) is established to achieve both desired attitude tracking and load relief performances. In particular, the total disturbance that includes the effects caused by both aerocoefficient perturbations and disturbances is estimated by constructing an Extended State Observer(ESO) to achieve attitude tracking. Furthermore, combined with the normal acceleration due to the engine thrust, the accelerometer measurement is also compensated to enhance the load relief effect.Secondly, the quantitative analysis of ESO and the entire closed-loop system are studied. It can be concluded that the desired attitude tracking and load relief performances can be achieved simultaneously under the proposed approach. Besides, tuning laws of the proposed approach are systematically given, which are divided into ESO, Proportional Derivative(PD) and Compensated Acceleration Feedback(CAF) modules. Moreover, the performances under CAF-ADRC approach can be better than those under CAF based PD(CAF-PD) approach by tuning load relief gain.Finally, the approach presented is applied to a typical control problem of launch vehicles with wind disturbances and parameter uncertainties.

A dual-mode integration framework and application to agile feedback design of launch vehicles

In recent decades,the design of complex systems like launch vehicles in the aerospace industry has presented engineers with challenges that go beyond system complexity.Issues such as time-to-market pressures and intricate industrial processes have underscored the increasing significance of agile design methodologies.Agile design is derived from the simplification of the design process and enhancing cross-domain data transmission and feedback.While methods based on model-based system engineering have improved iteration times in system architecture design,challenges persist in cross-domain data transmission.Due to the diversity of complex system models and data,a single-mode integration method is difficult to realize the data link construction of all tools used.To address this challenge,this paper proposes a dualmode data integration framework with expansibility,universality,and cost-efficiency which leverages the benefits of Remote Procedure Call and Intermediate Exchange Module,addressing the challenge of constructing cross-domain data links under single-mode integration.In this study,two critical requirements of the first-and second-stage separation systems,namely,weight and minimum separation gap,are selected for data feedback.A Modelica-based multiphysics simulation model is developed in MWorks;visualization and computation of the minimum gap are carried out in CoppeliaSim.To bridge the gap between domain-specific tools,Matlab and Functional Mock-up Unit modules are introduced as middleware,facilitating data feedback linkage.The entire simulation process is orchestrated using activity diagrams in the MagicDraw tool.The study delves into the influence of critical design parameters,such as the initial angular velocity of separation and the thrust of the retro rocket,on the minimum separation gap.It provides an analysis of minimum separation gap variations under uncertain operating conditions and examines design margins.Significantly,the paper highlights the significance of controlling the initial angular velocity during separation and the reliability of the retro rocket,providing essential decision supports and valuable insights to agile the process of system design.

Trajectory Design and Flight Result of Gravity-1 Launch Vehicle

Gravity-1(YL-1) launch vehicle completed its maiden flight from the Yellow Sea near Haiyang City, Shandong Province, on January 11, 2024, this mission successfully launched three Yunyao satellites into their 500 km orbit. The YL-1 has a performance of 4.2 tons for 500 km sun-synchronous orbit and 6.5 tons for low Earth orbit. The success of YL-1 has further enriched China's launch vehicle spectrum, and will facilitate the launch of medium and large satellites and satellite constellations. In this paper, the flight ballistic solution of YL-1 is introduced. The flight trajectory consists of seven flight segments. The trajectory design comprehensively considered the characteristics and safety requirements of the vehicle to achieve effective utilization of the performance. Through comparative analysis of the flight trajectory and the predicted trajectory, the result confirmed that the flight trajectory was consistent with the design results, the design methodology was correct, and the flight test met the expected requirements. Subsequently, the vehicle will be employed for commercial application launch services.