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25 June 2024, Volume 44 Issue 3 Previous Issue    Next Issue

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Architecture and development envision of cislunar space infrastructure YANG Mengfei, PENG Jing, LI Jionghui, NI Yanshuo, ZHU Shunjie, DU Ying, XU Baobi, HUANG Xiaofeng, ZHANG Zhengfeng 2024, 44 (3):  1-14.  doi: 10.16708/j.cnki.1000-758X.2024.0034 Abstract ( 1511 )   PDF (7849KB) ( 1719 )   Save  The construction of cislunar space infrastructure（CLSI）can provide basic and universal services for human activities in the cislunar space，including data communications，position navigation and timing（PNT），and situation monitoring for the development of lunar space，which can meet the needs of follow-up major national lunar exploration projects.At the same time，it has strategic significance for accelerating the development of the space industry into the cislunar space，and promoting China′s strength in science，technology and aerospace.On the basis of clarifying the concept of CLSI and analyzing the state-of-art development status，the top-level system architecture is proposed for the CLSI，regarding to the needs of major projects and the sustainable development of the aerospace industry.Then，the system services，the system composition，the “cloud-domain-end” network architecture as well as the internal and user interfaces architecture are defined and demonstrated.Finally，with the goal of gradually establishing a technologically advanced and reasonably deployed CLSI by phases and providing universal services that are open，safe，reliable，and operate continuously and stably in the long term，development prospects and suggestions are proposed to provide reference for the development and construction planning of CLSI. References | Related Articles | Metrics

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Orbit design method of near-lunar space constellation CHEN Shiyu, NI Yanshuo, PENG Jing 2024, 44 (3):  15-29.  doi: 10.16708/j.cnki.1000-758X.2024.0035 Abstract ( 1981 )   PDF (9757KB) ( 2282 )   Save  According to the requirements of relay communication and lunar navigation for future lunar exploration missions，an orbit design method of near-moon space constellation is proposed.First，the indexes of constellation design in relay communication，lunar navigation，cost for deployment and maintenance are sorted out，and analytic hierarchy process is applied to determine the weights of the indexes so that a comprehensive evaluation index can be proposed.The properties of various types of orbits are analyzed with full consideration of orbit resources near the moon，and the orbit types suitable for constellation deployment are initially screened.A construction route of the near-moon space constellation is proposed，where 100% quadruple cover for the whole moon is gradually realized in three stages.The constellation configurations in the three stages are designed successively.For each stage，different configurations are compared and the one with the best comprehensive evaluation index is selected.Based on the above method，the construction scheme of the constellation in near-moon space is obtained.In the first stage，2 satellites are deployed in elliptical lunar frozen orbit（ELFO）to provide full-time earth relay communication for the south pole region of the moon.In the second stage，6 ELFO satellites，2 near rectilinear halo orbit（NRHO）satellites，and 1 L2 halo orbit satellite are deployed to provide full-time navigation for the south pole region and fulltime earth communication for the entire lunar surface.In the third stage，4 ELFO satellites，2 NRHO satellites，1 L1 halo orbit satellite，and 3 distant retrograde orbit satellites are deployed to provide full-time navigation for the entire lunar surface.For any position in the whole lunar surface，the geometric dilution of precision of the designed constellation keeps below 5 in at least 72% of the time，leading to a long-term high-precision navigation for the whole lunar surface.Compared with the existing literature，the proposed design method of the near-lunar space constellation considers more orbit types，more comprehensive constellation performance indexes，and innovatively puts forward a phased construction scheme of the near-lunar space constellation. Related Articles | Metrics

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System architectures and key technologies of lunar surface communication and navigation infrastructure LI Jionghui, WANG Zijie, BAI Fan, GU Zheng, XIN Pengfei, JIA Min, ZHAO Hongbo, PENG Jing 2024, 44 (3):  30-42.  doi: 10.16708/j.cnki.1000-758X.2024.0036 Abstract ( 451 )   PDF (6199KB) ( 587 )   Save As a significant component of the cislunar space infrastructure（CSI），lunar surface communication and navigation infrastructure（LSCNI） provides more convenient communication networking services for the surface local users within hotspot areas，and also provides reference of surface local positioning and navigation as well as certain positioning，navigation and timing（PNT） capacities.On the basis of trend analysis，overall architectures of lunar surface communication and navigation infrastructure are proposed focusing on the medium and long-term strategic development of current major projects as well as future large-scale lunar activities.The architectures contain the network architecture and the lunar surface-space interfaces.Then，the solutions to some core issues such as lunar frequency planning，radio wave channel modeling，network access，high-speed transmissions，positioning and navigation methods are analyzed.Finally，suggestions for phased construction and technological development roadmap are proposed，providing reference for the planning and construction of communication and navigation systems for future lunar exploration missions. Related Articles | Metrics

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Cislunar cloud network：the cross-domain integrated cislunar-spatial network QIAO Liang, LI Chenghao, WANG Shanpeng, LI Jionghui, LIU Lei, XU Yong, YAN Hongcheng, SUN Zhelei 2024, 44 (3):  43-50.  doi: 10.16708/j.cnki.1000-758X.2024.0037 Abstract ( 350 )   PDF (5073KB) ( 407 )   Save To enhance the service efficiency of cislunar-spatial infrastructure for diverse users and to establish a cross-domain，integrated cislunar-spatial network，the concept of cislunar cloud network is introduced.Interconnecting various constellations and facilities through wireless links，the cislunar cloud network employed the integrated network protocols to facilitate cislunar-spatial networking.The operational deployment of the cislunar-spatial network promised a transformative change for traditional deep-space exploration missions，enabling continuous telemetry，efficient data transmission，and collaborative inter-probe tasks.However，the cislunar cloud network，characterized by high dynamics，significant latency，and strong heterogeneity，poses challenges to cislunar-spatial networking.The development and features of cislunarspatial networks are analyzed，a cislunar cloud network protocol stack is constructed adaptable to cislunar-spatial characteristics and meeting the interconnection needs of future deepspace exploration network nodes.The protocol stack is characterized by integration，universality，layering，intelligence，and internationalization.The design of its data plane and control plane is elaborated on.Additionally，a forward-looking perspective is provided on the future development of the cislunar cloud network protocols. Related Articles | Metrics

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Construction and transfer of space-based spatial-temporal reference in earth-moon space ZHOU Huichao, ZHENG Jinjun, WANG Haihong, BI Shaojun 2024, 44 (3):  51-59.  doi: 10.16708/j.cnki.1000-758X.2024.0038 Abstract ( 431 )   PDF (6434KB) ( 620 )   Save  Cislunar space is gradually becoming a focal area for human space exploration activities.Constructing a high-precision spatial-temporal reference and service is significant for planning and executing cislunar space missions.It is not only a systematic expansion of the spatial-temporal reference in the near-earth region，but also an important approach to enhance the guarantee capability of spatial-temporal information in cislunar space.With the development of GNSS，the infrastructure of spatial-temporal reference in the nearearth region is relatively comprehensive.The navigation system in the lunar region is similar to that of the near-earth region，and various solutions have been proposed.However，cislunar space also includes areas beyond the earth and the moon.Factors such as large airspace and particularity of dynamics should be adequately considered when the spatial-temporal reference is constructed，which can provide spatial-temporal information service with high benefits and connect the spatial-temporal reference of the earth and the moon organically.In this article，the spatial-temporal reference framework in cislunar space was designed based on the current demand of development.With characteristics of cislunar space beyond the earth and the moon considered，the scheme for constructing，tracing and transferring of the space-based earth-moon libration point spatial-temporal reference was researched and proposed.This scheme is anticipated to deliver a spatial-temporal information service with high accuracy and benefits，offering valuable reference for integrative construction and development of spatial-temporal reference in cislunar space. Related Articles | Metrics

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Receiver autonomous integrity monitoring of lunar surface in libration point navigation constellation LU Zhiwei, XU Chengdong, HUANG Guoxian, SHI Moran, WU Ming 2024, 44 (3):  60-68.  doi: 10.16708/j.cnki.1000-758X.2024.0039 Abstract ( 238 )   PDF (5984KB) ( 221 )   Save  In order to reduce the influence of complex environment for lunar exploration on navigation and to improve the reliability of libration point navigation constellation，a receiver autonomous integrity monitoring method of lunar surface based on multiple hypothesis separation solutions（MHSS）is proposed.This method takes advantage of the gravity asymmetry in cislunar space and realizes the user-level integrity monitoring of lunar surface by using the measurement information from only three libration point satellites.To meet the number requirement of visible satellites in more areas of the far side of the Moon for integrity monitoring，the number of Halo orbit satellites around L2 is increased and the amplitudes and initial phases of Halo are optimized by multipopulation genetic algorithm.Finally，the MHSS algorithm is used to verify the feasibility of integrity monitoring based on three satellites.The simulations show that fault detection is realized under the condition of two visible satellites，and that fault detection of the planar short-period orbit satellite is easier.Results also show that fault exclusion is realized under the condition of three visible satellites，and that fault detection and exclusion rate begin to rise to 100% when fault deviation reaches up to between 20σ and 30σ（σ=1m）.The feasibility of integrity monitoring based on libration point navigation constellation is analyzed for the first time and a method is proposed.The method can be applied to the navigation of lunar exploration missions and provides a useful reference for the design of both integrity monitoring algorithm and libration point navigation constellation for lunar exploration missions in the future. Related Articles | Metrics

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An earth-moon space navigation method based on the earth GNSS and navigation augmentation satellite TONG Zhao, ZHU Xiangpeng, CHEN Sufang, XU Lianjun, MENG Yansong 2024, 44 (3):  69-79.  doi: 10.16708/j.cnki.1000-758X.2024.0040 Abstract ( 302 )   PDF (11532KB) ( 358 )   Save It is of great significance that lunar spacecraft has the ability of GNSS autonomous navigation for the demands of high precision，low cost and autonomous navigation in the following human and unmanned lunar exploration task，which keeps up with the simple and low cost trends of the future lunar mission.However，the direct application of the earth GNSS navigation to the high precision earth-moon navigation scenario has the limited capacity of real-time navigation，which cannot meet the demand of the high precision navigation application for the future lunar exploration mission.Thus，the earth-moon space navigation method based on the GNSS and navigation  augmentation satellite was developed.By adding a moon navigation node which broadcasts navigation signal，the time synchronization link was built between GNSS and moon navigation satellite，and also between lunar users and moon navigation satellite，the clock and position error were decoupled and high precision real-time three-dimensional absolute navigation was realized.At last，the precision of the proposed navigation method was simulated and the results of simulation show that the PDOP of the user was highly improved.The positioning accuracy is better than 50 m and the method has high practicability. Related Articles | Metrics

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International rules and utilization status of frequency and orbit resources for cislunar space exploration SUN Qian, LIU Huiliang, WANG Jilian 2024, 44 (3):  80-88.  doi: 10.16708/j.cnki.1000-758X.2024.0041 Abstract ( 247 )   PDF (3908KB) ( 351 )   Save  Cislunar resources，such as radio spectrum，have attracted close attention among global major participants in space.However，the international rules in force centered on the earth cannot meet the upcoming practical requirements of cislunar resource utilization.The ambiguity of international rules intensifies resources competition and increases the risk of frequency interference between different spacecraft.Amending the international rules on space resources is in an important period of strategic opportunities.Aiming at the gap between international policies and exploration requirements of cislunar space，the existing international rules for frequency and orbit resources were comprehensively investigated.Regulations and mechanisms of international organizations such as the International Telecommunication Union（ITU）and Space Frequency Coordination Group（SFCG），both inter-governmental and nongovernmental，were sorted out.Taking Artemis as an example，a typical lunar exploration program was studied.In addition，the global status and trend of cislunar resources acquisition and utilization were analyzed in detail.Finally，considering the implementation objectives of international lunar research stations and manned lunar landing programs，suggestions for compliant submission following the rules in force were carried out.And proposals for international cooperation on resource utilization，matching the construction procedure，were put forward. Related Articles | Metrics

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Selection of asteroid exploration targets with high mining value LIN Qin, WANG Chao, YAO Wei 2024, 44 (3):  89-97.  doi: 10.16708/j.cnki.1000-758X.2024.0042 Abstract ( 209 )   PDF (4600KB) ( 172 )   Save  With the increasing global metal consumption and shortage of Earth energy，the development and utilization of asteroid resources has become one of the main ways to effectively solve the problems of mineral resources and energy reserves.Firstly，according to the value，estimated profit and profit value ratio of the asteroids，the target range of asteroids with high mining value is analyzed.Then the impact of orbital characteristics，size，rotation period and other constraints on the feasibility of asteroid exploration is analyzed，and the target range of mining is determined that can be achieved in the next few decades according to technical constraints.Finally，the primary targets with high mining value and low technical constraints are integrated，and a more detailed comparative analysis of these targets is carried out according to the launch window，target resources，profit to value ratio，minimum speed increment，and so on.The space exploration objects suitable for the exploration tasks in different time periods are selected to provide reference for the selection of asteroid exploration targets with high mining value in the coming decades. Related Articles | Metrics

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Space point object neuromorphological detection method WANG Ruilin, WANG Li, HE Yingbo, LI Lin 2024, 44 (3):  98-110.  doi: 10.16708/j.cnki.1000-758X.2024.0043 Abstract ( 144 )   PDF (11402KB) ( 98 )   Save  As the onorbit spacecraft face more and more threats，how to identify and evaluate the impact of these threats on the normal operation of the spacecraft has become an urgent problem to be solved.At present，the detection and tracking of space objects mainly rely on traditional framebased visual sensors，but these sensors have shortcomings in real-time performance and data volume.Meanwhile，neuromorphological visual sensors have been widely used in the field of moving objects detection and tracking.Due to the event stream data obtained only containing information of the changing parts in the field of view and having a microsecondlevel time resolution，the speed of object detection and tracking can reach the microsecond level，while significantly reducing the amount of data to be processed.Because of these advantages of neuromorphological visual sensors，they have become the current research focus in the field of space applications.Therefore，a space point object detection method is proposed based on a threelayer spiking neural network - space point object neuromorphological detection method，which uses only event stream data to achieve the detection and tracking of space point objects.The main components include a local motion perception layer，a global motion perception layer，and an output layer，using the fractional leaky integrate and fire neurons as the basic processing units，and utilizing their adaptability to suppress hot noise in the event stream data.The method is validated using collected space point object event stream data and event stream data from public datasets.On the collected space point object event stream data，the event denoising precision and event signaltonoise ratio of the denoising filtering part can reach 0.414 and -3.036 respectively，while the total tracking time，total tracking error count，and average tracking offset of the tracking part reach 9.3952s，100，and 0.3797 respectively.The experimental results show that the space point object neuromorphological detection method can detect single or multiple fastmoving space objects from complex event stream data and can continuously track the detected space point objects. Related Articles | Metrics

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An attitude control method of satellites with hybrid flywheel configuration for skew maneuvers LEI Yongjun, LU Dongning, YUAN li, CHEN chao 2024, 44 (3):  111-119.  doi: 10.16708/j.cnki.1000-758X.2024.0044 Abstract ( 193 )   PDF (3080KB) ( 267 )   Save  The combined configuration solution of momentum wheels and control methods for large satellites with high attitude stability performance were studied in this paper because the attitude maneuver duration time was too long to satisfy task requirements due to the small output torque of the ordinary momentum wheels.First of all，a combined configuration solution of momentum wheels was proposed by adding a series of large-torque flywheels along the roll axis to an ordinary momentum wheel assembly，and a corresponding control approach was designed to integrate the closed-loop feedback control of the ordinary momentum wheels with the open-loop feedforward control of the large-torque flywheels.Meanwhile，a feedforward torque distribution law for the large-torque flywheels was adopted to realize the efficient management of the angular momentum of large-torque flywheels，where the output torque was proportional to each flywheel providable angular momentum；together with an angular momentum servo tracking control method，the deviation of the output torque from the command torque caused by the flywheel model uncertainty was mitigated simultaneously.Furthermore，to ensure high attitude stability realization，a disturbance estimator was utilized to accomplish the real time disturbance torque compensation.At last，the effectiveness of the proposed solution and methods was illustrated by the in-orbit application.The application shows that the stabilization time of roll-axis maneuver reduces more than 100s，and the attitude stability error during non-maneuver period is less than 3.75×10-5（°）/s. Related Articles | Metrics

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Optimization of drag reduction configuration on windward side of very low orbit spacecraft JIANG Yipeng, CUI Yufu, LIU Zhijia, QING Jiang 2024, 44 (3):  120-126.  doi: 10.16708/j.cnki.1000-758X.2024.0045 Abstract ( 225 )   PDF (2289KB) ( 299 )   Save Aiming at the problem that the windward side of very low orbit spacecraft is subjected to too much aerodynamic resistance，based on the theoretical solution to the aerodynamic drag of free molecular flow，the aerodynamic resistance of several typical windward side configurations with different length was calculated and the reasons for their changes were analyzed.After which an expression of the windward side was designed and an intelligent algorithm was introduced to iteratively optimize it.Given the constraints of the configuration，the penalty function was introduced to reduce the fitness of the infeasible solution.The results show that this method can obtain the approximate optimal solution of the windward side with minimum resistance.Under the constraints of existing materials，the maximum drag reduction of this method can be more than 5% compared with the conical structure，and the head volume of the spacecraft can be effectively increased.With the increase of windward height，the minimum resistance configuration gradually changes from near frustum to cone.The optimization method proposed in this paper can provide a reference for subsequent drag-reducing configuration design of very low orbit spacecraft. Related Articles | Metrics

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Space application and test design of dual-comb ranging technique ZHOU Siyu, GU Yingying, YANG Yuetang, SHI Liheng, MA Yuxuan, ZHU Feihu, ZHANG Yunfang, WU Guanhao 2024, 44 (3):  127-135.  doi: 10.16708/j.cnki.1000-758X.2024.0046 Abstract ( 236 )   PDF (4447KB) ( 263 )   Save The dual-comb ranging technique has the advantages of high precision，fast response speed，large unambiguity range and on-site traceability.It has broad applications in space missions，such as spacecraft rendezvous and docking，satellites formation-flying，positioning of large deployment mechanisms.Under the scenario of rendezvous and docking between cargo spacecraft and space station，a space application and test scheme of high-precision dual-comb ranging was proposed.Firstly，basic theory of dual-comb ranging was introduced，and the architecture of the test system was built.It is theoretically demonstrated that a precision of 100μm in the range of 400m，along with a 1kHz response speed，can be achieved.Further，the key parameters of the ranging system were designed and simulated，and the space environment adaptability of the system was analyzed.The results show that it can achieve high-precision measurement within a maximum speed of 19.5m/s，meeting the mission requirements.The analysis results provide a technical reference for the on-orbit test and aerospace engineering application. Related Articles | Metrics

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Form-finding design of radial rib cable membrane reflector antenna based on force density method DU Xuelin , ZHANG Kang, ZHANG Ruixiang, LIU Anmin, XIA Jie, ZHANG Hong, TU Yu 2024, 44 (3):  136-145.  doi: 10.16708/j.cnki.1000-758X.2024.0047 Abstract ( 96 )   PDF (8067KB) ( 78 )   Save  Aiming at the initial form-finding design of space cable membrane structure，an iterative strategy of antenna form-finding for boundary cable tension design and cable net shape design is proposed based on the force density method and the method of controlling the grid area.Firstly，the membrane reflector is discretized into triangular membrane elements to obtain the equivalent effective density of membrane elements.Combined with the structural characteristics of cable net，the static equilibrium equation of cable net and membrane is obtained.The tension of all internal cable segments of the cable network is equal，and the tension design of boundary cable segments is realized by controlling the size of grid area.In order to design the shape of the front cable net，according to the paraboloid equation of the front cable net，the free node coordinates of the front cable network are updated，the vertical cable tension is readjusted，and the grid area is controlled.Finally，the shape design of the antenna is realized through the iterative process.The example of radial rib cable membrane reflector antenna shows that this method can obtain the design results that meet the shape requirements and tension distribution. Related Articles | Metrics

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Performance analysis of Galileo open service navigation message authentication LIU Weilun, CHEN Xiao, LIU Ting, XU Ying, REN Mingliang 2024, 44 (3):  146-156.  doi: 10.16708/j.cnki.1000-758X.2024.0048 Abstract ( 128 )   PDF (6986KB) ( 112 )   Save  In recent years，frequent spoofing attacks of Global Navigation Satellite System（GNSS）have aroused the attention of many countries on the protection of GNSS signal.As a system-level solution for civil signal，Navigation Message Authentication（NMA）has a good protection effect against spoofing attacks.Galileo first proposed the NMA scheme in 2016 and officially released the Open Service Navigation Message Authentication（OSNMA）test signal in 2021.Aiming at the performance testing for the OSNMA service，the Galileo NMA technique and the authentication process of terminal were described，then the GNSS receiver was used to carry out the technical test and simulation of the key performance indicators.The results show that the OSNMA indicators are in line with expectations and the star selection strategy of cross-authentication is representative.The research results can provide a reference for the design of the future NMA service in BeiDou Navigation Satellite System（BDS）. Related Articles | Metrics

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Image feature matching algorithm based on nonlinear anisotropic filtering LI Hua, YANG Yang, CHEN Yujie 2024, 44 (3):  157-166.  doi: 10.16708/j.cnki.1000-758X.2024.0049 Abstract ( 85 )   PDF (8475KB) ( 59 )   Save  Image matching is the key technology in augmented reality system，and matching accuracy is the key to improving the performance of feature matching.A multi-scale feature matching enhancement algorithm（I-AKAZE） is proposed.By improving the conduction function in the process of nonlinear anisotropic filtering，the nonlinear diffusion speed in the region with large gradient value of the image is slowed down，and the edge features of the matched image are retained to a great extent.At the same time，combined with the improved nonlinear quantization accelerated robust feature descriptor（NLG-SURF），the recognition rate of the descriptor is improved.The experimental results show that the repeatability score of I-AKAZE algorithm on Mikolajczyk data set is greatly improved compared with the current advanced AKAZE algorithm，that the average recognition rate of the corresponding feature descriptors is increased by 8.4%，and that the running speed is about 600ms faster than that of the classic SIFT algorithm.The overall performance of the algorithm is improved in the detection and description stages. Related Articles | Metrics

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Thermal induced disturbance torque of GEO solar sail WANG Jie, YU Ye, ZHANG Tao 2024, 44 (3):  167-173.  doi: 10.16708/j.cnki.1000-758X.2024.0050 Abstract ( 125 )   PDF (5035KB) ( 137 )   Save The solar sail is a complex system composed of large，flexible membranes that are tensioned by light booms.However，when the solar sail experiences high and low temperatures in space due to variations in the environment，the sudden change in temperature field can cause the booms to deform and vibrate.This disturbance torque can affect the attitude of the solar sail，leading to an instability in the control system.To address this issue，an analytical method is proposed for thermal-induced disturbance torque of the solar sail.Firstly，a thermalstructural analysis model is established that considers the transient temperature fields of the structure when the solar sail enters and leaves the shadow.This analysis enables us to better understand how the sudden temperature changes impact the sail′s dynamics.Next，the dynamic responses of the sail under these temperature conditions are calculated，taking into account its deformation and vibration.Finally，the disturbance torque of the dynamic responses towards the central body of the solar sail is obtained.Results show that the thermal-induced deformation and vibration of booms when entering and leaving the earth′s shadow can cause significant disturbances to the central body of the solar sail，with an amplitude of the disturbance torque reaching 10-3N·m.The simulation accurately predicts thermal disturbances in orbit，providing a valuable theoretical method for engineering purposes. Related Articles | Metrics

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A high-precision system level calibration method for spaceborne magnetometers MENG Lifei, XU Chaoqun, XIAO Qi, LIU Chaobo, GENG Xiaolei, CHEN Dexiang, YI Zhong, ZHANG Tielong 2024, 44 (3):  174-179.  doi: 10.16708/j.cnki.1000-758X.2024.0051 Abstract ( 159 )   PDF (1770KB) ( 132 )   Save  Spaceborne three-axis magnetometers are often used for attitude confirmation and correction of satellites in orbit.In order to improve the accuracy of in-orbit magnetic field measurement，a high-precision system level calibration method for spaceborne magnetometers is proposed.Firstly，an optical prism reference is introduced to achieve the orthogonality self-calibration of the reference magnetometer magnetic axis.Subsequently，the coil coefficient calibration of the three-axis zero magnetic environment simulation system is completed using the multiplication method.The magnetic axis orthogonality calibration of the three-axis zero magnetic environment simulation system is completed using a reference magnetometer，thereby obtaining a high-precision space magnetic environment ground simulation system.Finally，the calibration of the spaceborne magnetometer is completed using the orthogonality correspondence between the three-axis zero magnetic environment simulation system and the satellite.The experimental results show that the non orthogonality of the three-axis zero magnetic environment simulation system is better than 0.01°，and that the calibration error of the spaceborne magnetometer is better than 10nT.The research provides a new approach for ground calibration and verification of spaceborne magnetometer systems. Related Articles | Metrics