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H3 the Development Status of the Rocket

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H3 the Development Status of the Rocket Document 44-3 The Council for Science and Technology Research Planning and Evaluation Subcommittee space development and utilization Group ( The 44 Times) H30.11.29 H3 The development status of the rocket Heisei 30 (2018) Year 11 Moon 29 Japan Aerospace Exploration Agency Director Yasuhiro Funo H3 Project team Tadashi Okada Today's your report • The 40 Times space development and utilization Group ( 2018 Year 1 Moon twenty four In the day), " H3 About migrating "to the detailed design results and fabrication and testing phase of the rocket comprehensive system, I was pleased to report. • This time, we will explain the progress status of the subsequent development. 1. Progress of production and test phase 2. Implementation of the development test 3. The development status of the ground facilities Four. Considerations for future development Five. Future plans 1 1. Progress of production and test phase • To complete the detailed design in the last year the overall system level, compatible with the conclusion to the mission requirements. • Sun-synchronous orbit (altitude 500km ) To launch capability: Four Ton or more ( H3-30S ) • MHI Standard launch price, which is calculated by the gluteal 【note 1 ] : about 50 Billion yen ( H3-30S ) 【note 1 ] Airframe price of production is in a stable steady-state operation phase and under certain conditions • The satellite forecast, the mass of the geostationary orbit satellites 2.5 ~ 6.5t In has been widely distributed, H3 It can cope with rocket launch capacity range (The 40 Times space development and utilization Group ( 2018 Year 1 Moon twenty four Sun) article 40-2-1 More excerpt) • Then, multiplied by the appropriate feedback to the design from the development test, Maintain a design with the latest state . • on the other hand, International launch market The demand by such all-electric satellite and small constellation satellite Diversification By is willing to have a flexible and quick response H3 Improve competitiveness, not loosened the rocket ' But essential. • H3-32 Highly competitive in the form H3-22 Integration in the form (next page) • 2 Introduction into the plurality orbit by multiple ignition stages engine, such as a plurality satellite adapter Development of Under consideration • testing machine For, from the long ones of such procurement period Already embarked on some production . 2 H3-22 Form and H3-32 Form integration of • Geostationary transfer orbit ( GTO Launch capability to) ton H3-32 Launch Satellite mass ( ) capability of (By such means as an adjustment to the input orbit ) H3-22 In 6 2017 Maximum launch H3-22 Launch possible cover) capability of Five Company B 2015, ΔV = 1500m / s It tends to peak of tons has slowed. ( 6 ※ 22 and 32 It is the ability Four fairing size GTO capability to) Tons 3 L in the case of Company B , 3 The expected 2015 Each mass-band satellite demand forecast (research launch capability Company data, B 2 Company A Of year firm: 2017 ※ H3-30S H3-22L H3-32L H3-24L Machine number H3-22 Form of launch capability is higher than expected, H3-32 Form of demand can be covered by adjustment of input trajectories ( next page ), And thereby for advantages production plan is simplified is large, H3-22 It is integrated into the form. [Note] aircraft identification name H3-abc a : LE-9 Radix ( 2, 3 ) b : SRB-3 The number of ( 0, 2, 4 ) c : Fairing size ( S, L ) 3 Response by adjustment of the closing trajectory Example • I turned on the track in the past geostationary satellite missions ( GTO ) Is accelerated amount of satellite side necessary staticization ( ΔV )But 1500m / s 【note 1 ] Be become orbit was the world's de facto standard. • In recent years, even in the case of large satellite that could not launch in the above-mentioned track, without changing the form of a rocket, The introduction orbit customers and the flexibility to adjust 【note 2 ] Tendency to, increase hitting a large satellite performs the burden of the speed increasing amount of satellite side But worldwide progress. 【note 1 It was converted to the launch from the equator <In recent years Falcon9 Of satellite launch track record> Case. 【note 2 For example, the apogee of 7500 the input orbit 7000 Adjust the altitude and orbital inclination, Required to quiescence ΔV The 6500 1500m / s More satellite side is 6000 borne. kg) 5500 So far the world 5000 standard of 4500 Recently, in response to satellite mass, the form of rocket without changing turned 4000 orbit (satellite side ΔV ) Adjusted trend to launch and progress of the Satellite mass during launch ( 3500 Falcon 9 3000 2500 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300 Satellite side needed to quiescence ΔV (m / s) Four Development Plan • 2020 Testing machine to the year 1 The launch schedule Unit. testing machine 2 After evaluation launch Unit, the development will be completed. • The total development costs; about 1,900 Billion yen 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022 △ PQR ▲ ▲ Milestone △ MDR △ SDR △ PDR △ CDR testing machinetesting machine 1 Unit 2 Unit Conceptual Study Conceptual design Basic design detailed design Maintenance design System design and test Electrical systems test 【note 1 ] ▽ the ground comprehensive test BFT CFT Actual production 1 Actual production Actual production 2 Engine propulsion system development LE-X Technology Demonstration design elements test and design Production Actual type-certification type test 1 Stage / 2 Stage engine Flight for manufacturing and AT test Test equipment repair Facility design Equipment work MDR : Mission definition examination SDR : System definition review PDR : Basic design review CDR : Critical Design Review Structural system / electrical system development Element test and design Production Certification test PQR : Development completed examination AT : Acceptance testing BFT : Thick-walled tank stage combustion test (combination test of simulated tank and the engine) Solid booster development Element test, design and sub-size test Actual large combustion test Production CFT : Actual tanks stage combustion test (combination actual exam flight considerable tank and engine) Ground equipment development Conception, research and basic Detailed design Production and site work and coordination test 【note 1 ] BFT for LE-9 It reflects the readiness of the engine, BFT Review of the implementation period Five 2. Implementation of the development test • The following tests were carried out. ① first 1 Stage engine ( LE-9 Actual engine # to verify the functionality and performance of) 2 Combustion test: completion ( P7 ) ② first 1 Stage thick-walled tank stage combustion test ( BFT )for LE-9 Engine combustion test ( 2 formula) • Each 150 Conducted a combustion test of the order of seconds, complete the confirmation of the functions and performance • The 1 Stage BFT Complete the installation of the test equipment ③ SRB-3 Actual large combustion test (for the Engineering Test "actual type motor"): Completed ( P8 ) ④ electrical systems test: Ongoing • Also, it is preparing towards the following test. ⑤ first 1 Stage thick-walled tank stage combustion test ( BFT ) ( P10 ) ⑥ second 2 Stage engine ( LE-5B-3 ) Certified engine # 2 Combustion test (for the final certification) [ 11 Moon Ten Start from the day] ⑦ LE-9 Actual engine # 1-2 Combustion test • Actual engine # 1 To renovate, verification plans the following towards the certified type design • Design reflects by the data obtained in the tests so far 3D An example of the molding • Aimed at the drastic cost reduction 3D modeling process Wide range of applications of process ( LE-9 Injector elements) 6 ① LE-9 Actual engine # 2 The results of the combustion test • 2 Expression of the actual type engine (# 1 , # 2 ) A prototype, carried out combustion test. • So far, Target thrust ( 150 Ton) , The actual flight and the equivalent of burning time (about 270 Sec.) The achievement. • The total burn time, 19 Kai about 1,640 Sec. # 2 In the engine, Demonstration request time of certification type engine (Flight 2 Double + combustion test and the like of the time: 8 Kai 1,078 Achieved in seconds) as a system. • While continuing to get a variety of data in the combustion test, Reflected in the final design plans. 300 Cumulative Actual engine # 2 1,800 seconds at the time of the test in seconds 1,600 250 1,400 200 1,200 1,000 150 During the test in seconds (s) Actual engine # 1 When the cumulative second (s) 100 800 600 50 400 0 0 200 1 3 5 7 9 11 13 15 17 19 Number of tests In the combustion LE-9 engine 7 ③ SRB-3 The results of actual large ground firing test • the purpose • SRB-3 Actual large ground firing test of, Total 3 Times plan It is (actual motor: 1 Times, certification type motor 2 Times. Epsilon rocket first 1 Also serves as a development stage. Both carried out at the Tanegashima Space Center). • In this test, For the Engineering Test "actual type motor." Using, Acquired the characteristics and performance data of the ignition and combustion, etc. And, contribute to the design. In the combustion SRB-3 • result • Planned Achieve the test purpose did. Basic performance are as follows. item Predicted value result Maximum thrust 2,106kN 2,137kN Maximum combustion pressure 10.8MPa 10.7MPa All combustion time 110.6s 110.1s • Based on the evaluation results of the test data, Considering reflect matters to the design of the certification type motor . Actual type motor 8 [Reference] solid rocket booster ( SRB-3 ) basic specifications Forward Breath item SRB-A ( H-IIA ) SRB-3 ( H3 ) ( 2 Book) Solid propellant Composite
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