ppt創(chuàng)意設(shè)計(jì)方案 201491 - indico [home]

1、Preliminary Design of the eXTP SatelliteInstitute of Spacecraft System Engineering , CAST Hong Bin Mar 22th , 2017 , Beijing,,,1. General Description2. Design Evolution3. Basic Parameters4. Preliminary D

2、esign5. Programme Schedule6. Problems7. Conclusions,Outlines,General Description,,eXTP , the enhanced X-ray Timing and Polarimetry mission, is a science mission designed to study the state of matter under extreme cond

3、itions of density , gravity , and magnetism.It’s the next generation of the X-ray detected telescope after HXMT in China.,HXMT,eXTP,2007 The conception of XTP was put forward by IHEP;2008-2012 An advance

4、d research of the XTP was carried out by ISSE;2013-2014 Completed the system analysis and achieved the mission’s basic parameters . The first step design of the XTP was finished;2015-2016 With the LAD and WFM ad

5、ding into the XTP and the parameters of SFA&PFA has changed，redesigned the eXTP satellite;2017 New launch vehicle; new orbit；new payload；So we update the design of the eXTP satellite.,2. Design Evolutio

6、n,3. Basic Parameters,LM-7 launch vehicle ，has a big fairing with diameter of 4200mm a total height of 10300 mm， has maximum capacity for 550km circular orbit at 0 deg. inclination is 4500kg.,4. Preliminary Design,Launch

7、 Vehicle,Telemetry and Control system,The TC system applies the international USB system . Low tilt angle communication is achieved through utilizing relay satellites or building new TC station.,Satellite ground applicat

8、ion system,Data receiving is achieved by stations at Sanya. Or using the ground station at Malindi (3°S Kenya), built by Italian (LOFT team).,The –X axis point to the specific objects in the inertial space ；The sun

9、 vector is controlled in XOZ plane and in a obtuse angle with the +Z axis；The sun vector will perpendicular to the solar array by rotate it； According to the user’s observation plan to carry out attitude maneuver，aimin

10、g at the burst objects to carry on the observation.,4. Preliminary Design,Observation Mode——Pointing Observation,,Objects,,4. Preliminary Design,Flight Procedure,Burst source,Objects,,Configuration,Stowed in fairing,On o

11、rbit,4. Preliminary Design,4. Preliminary Design,Configuration,Service module(SVM): the SVM includes all units required to control and operate the S/C platform. The WFM and GRM are accommodated in the SVM, too. LAD Asse

12、mbly(LADA): the LADA consists of LAD panel(#1~#4), LAD sunshields, deployment mechanisms. The LADA are accomodated on either sides of the SVM.Mirror Assembly Module(MAM): the MAM is located inside the telescope tube , c

13、ontains the SFA & PFA mirror module and star trackers，with the associated supporting platform. Telescope Tube(TT): the TT allows to maintain the SFA&PFA at the required distance from the focal planes.Focal Plan

14、e Assembly (FPA) : the FPA hosts the 13 focal plane cameras, including thermal control hardware.,Configuration,4. Preliminary Design,4. Preliminary Design,Hosts all platform subsystems; -four tanks -six r

15、eaction wheels -two star trackers -four sun acquisition senors -three gyroscopesSupport the LAD，WFM and GRM;Downside of SVM is the interface of the launch vehicle;Inside the SVM there’s a conta

16、mination cover , it’s also the sun-shield of the WFM.,Service module(SVM) :,4. Preliminary Design,SFA and PFA are accomodated in the mirror platform.Conceived as independent unit.Can be later integrated into the telesc

17、ope support structure.Kinematic mounts :Minimising the impact of mechanical and thermal-elastic loads onto the optics alignment.,Mirror Assembly(MA) :,,,,,,LAD Assembly,4. Preliminary Design,Two wings (each wings two pa

18、nels or one panel（TBD）);LAD support platform use the hign thermal conductivity material for the structure;The deployment mechanisms perform the connection between LAD panel and satellite, withstand the launch loads in

19、the stowed condition;On orbit, the DM releases the panel reliably, and then performs the deployment of the LAD payloads, with the automatic latching at the end of its travel;After the latching, the DM maintains the ang

20、ular position and assure the stiffness.,10 modules each panel1973(L)×1212(B)×132(H),20 modules each panel（TBD）2384(L)×1973(B)×132(H),4. Preliminary Design,Maintain the required focal length;Support

21、 the solar array and ka-antenna;Provide the catching interface for on-orbit servicing(TBD);The ICU of the focal detectors are accomodated on top of the TT;,Telescope Tube(TT) :,4. Preliminary Design,Hosts the 13 focal

22、plane cameras;With the sun-shield to protect the detectors from the suns;The shape is designed to minimize the envelope dimesions and fit the fairing;,Focal Plane Assembly(FPA) :,4. Preliminary Design,TCS: Mirror assem

23、bly thermal design,The insulating washers(fiberglass) are used to limit the conductive heat transfer between the MA and MSP.The MA are covered by 15-layer MIL to insulate heat radiation of SVM.The external surface of

24、TT is used for radiator of the MA.,SFA: 20±2℃,PFA: 20±2℃,4. Preliminary Design,TCS: SDD thermal design,The FPA is connected to the TT by insulating washers, to limit the conductive heat transfer between the S

25、DD and FPSP.The SDD are covered by 10-layer MIL. The SDD heat dissipation are firstly collected by the ethane loop heat pipe, then the collected heat dissipation is refrigerated by the pulse-tube refrigerator(5W@180K ,

26、power 120W). Finally, the hot junction heat dissipation of refrigerator is transmitted to the individual radiator by the ethane heat pipe.,SFA-SDD *11： -110℃~-80 ℃,Ethane loop heat pipe,Radiator,,,Pulse-tube Cryocooler,

27、4. Preliminary Design,TCS- LAD thermal design,Extensile sun-shield is used for the LAD, to insulate heat radiation from the sun.The inside of the sunshield, covered by 15-layer MIL to insulate heat radiation.The LAD he

28、at dissipation(5.4W*40=216W) is radiated by itself. Electric heaters(50W power) are applied in LAD for maintaining the -20℃ lower limit.,extensile sunshield,LAD:-20~-10℃,Phase A:2017.01~2017.12, international coordinat

29、ion, feasibility design ~2017.08, Subsystem interface definition document (IDS) ~2017.10, Subsystem requirements document ~2017.12, System feasibility designPhase B:2018.01~2018.12, Prel

30、iminary design~2018.09, Subsystem preliminary design ~2018.12, System preliminary designPhase C:2019.01~2021.12, System critical design~2019.01 SM delivery(30% for special test(TBD))~2019.12 EM delivery~2020.1

31、2 SM and TM delivery~2021.06 QM completedPhase D:2022.01～2024.06, Flight model and launch~2022.06 FM deliveryPhase E:2025.01～2035.10, Science observation,5. Programme Schedule,21,5. Programme Schedule,Payload equip

32、ment requirements,,LAD Assembly,6. Problems,The following key requirements should be confirmed:Panels: ~The interface between panel structure and sun-shield, DM, module, PBEE. ~The requirements for strength,

33、stiffness, alignment, thermo-stability, material, connection style. ~The technical flow about the delivery, assembly, test(How? Where?).LAD sun-shield: ~The requirements for materials, frequency, weight, therm

34、al control. ~Interface of the HDRM.Deployment Mechanisms: ~The interface between DM and the panels. ~Requirements for Frequency, Accuracy, Drive torque, Thermo-stability, Weight. ~AIT process and it

35、ems.,WFM,6. Problems,The requirements for installation accuracy, consistency of direction (for one pair)Can you accept the state that FoV is blocked or change the point angle(decide by the LAD panels and sunshield)？The

36、 URF could meet the launch loads and on-orbit thermal environment？If CAST responsibility for the design of WFM support structure:Can you adjust the position of the three URF？(Insufficient Operation Space)Can you redes

37、ign the position of the electrical connector？(Insufficient Operation Space for 3 pairs),7. Conclusions,We have updated the design of eXTP satellites, which could meet the requirement of the science;Something should be c