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37-537: For developing RAISE-3, JAXA selected MHI, the prime contractor of Japan's H-IIA and H3 rockets. MHI also previously developed Z-Sat, a satellite launched in 2021 as part of the Innovative Satellite Technology Demonstration-2 mission. While in orbit, RAISE-3 would have been operated from MHI's Nagoya Guidance & Propulsion Systems Works plant in Komaki, Aichi . The satellite carried 7 of

74-656: A centrifugal pump , where the pumping is done by throwing fluid outward at high speed, or an axial-flow pump , where alternating rotating and static blades progressively raise the pressure of a fluid. Axial-flow pumps have small diameters but give relatively modest pressure increases. Although multiple compression stages are needed, axial flow pumps work well with low-density fluids. Centrifugal pumps are far more powerful for high-density fluids but require large diameters for low-density fluids. High-pressure pumps for larger missiles had been discussed by rocket pioneers such as Hermann Oberth . In mid-1935 Wernher von Braun initiated

111-425: A "turbopump with a rocket attached"–up to 55% of the total cost has been ascribed to this area. Common problems include: In addition, the precise shape of the rotor itself is critical. Steam turbine -powered turbopumps are employed when there is a source of steam, e.g. the boilers of steam ships . Gas turbines are usually used when electricity or steam is not available and place or weight restrictions permit

148-471: A few bars is not uncommon. Their advantage is a much higher volumetric flowrate. For this reason they are common for pumping liquid hydrogen in rocket engines, because of its much lower density than other propellants which usually use centrifugal pump designs. Axial pumps are also commonly used as "inducers" for centrifugal pumps, which raise the inlet pressure of the centrifugal pump enough to prevent excessive cavitation from occurring therein. Turbopumps have

185-474: A fuel pump project at the southwest German firm Klein, Schanzlin & Becker that was experienced in building large fire-fighting pumps. The V-2 rocket design used hydrogen peroxide decomposed through a Walter steam generator to power the uncontrolled turbopump produced at the Heinkel plant at Jenbach , so V-2 turbopumps and combustion chamber were tested and matched to prevent the pump from overpressurizing

222-558: A long fairing, whereas an H3-30S has three engines, no solid rocket boosters, and a short fairing. W-type fairing is similar to L-type except wider 5.4 m diameter. W-type was mentioned in the description of JAXA's web page, but not in the current description as of November 2023 . Manufacturing of W-type fairing is contracted to RUAG Space (now Beyond Gravity ), whereas other types are manufactured by Kawasaki Heavy Industries. As of November 2018 , three configurations are planned: H3-30, H3-22, and H3-24. A previously mentioned variant,

259-420: A low specific impulse but can produce a large thrust for a short time period. On the other hand, the ion thruster is fuel-efficient but cannot produce a large thrust in a short time period. The two types of thrusters are complimentary, and by combining them KIR can provide a wide variety of thrust capabilities. KIR is sized to fit inside a CubeSat. An external camera monitors the operation of the ion thruster. KIR

296-463: A payload capacity of 28,300 kg (62,400 lb) to low Earth orbit . H3 will have a "dual-launch capability, but MHI is focused more on dedicated launches" in order to prioritize schedule assurance for customers. As of 2018, MHI is aiming to price the H3 launch service on par with SpaceX's Falcon 9. Sources: Japanese Cabinet The first launch attempt on 17 February 2023 was aborted just before

333-428: A planned dogleg maneuver in order to achieve sun-synchronous orbit and not in fact a loss of control. Approximately five minutes and twenty-seven seconds after launch, the second stage engine failed to ignite. After continuing to be unable to confirm second stage engine ignition, and with the velocity of the rocket continuing to fall, JAXA sent a self-destruct command to the rocket at around L+ 00:14:50 because there

370-419: A reputation for being extremely hard to design to get optimal performance. Whereas a well engineered and debugged pump can manage 70–90% efficiency, figures less than half that are not uncommon. Low efficiency may be acceptable in some applications, but in rocketry this is a severe problem. Turbopumps in rockets are important and problematic enough that launch vehicles using one have been caustically described as

407-531: Is a propellant pump with two main components: a rotodynamic pump and a driving gas turbine , usually both mounted on the same shaft, or sometimes geared together. They were initially developed in Germany in the early 1940s. The purpose of a turbopump is to produce a high-pressure fluid for feeding a combustion chamber or other use. While other use cases exist, they are most commonly found in liquid rocket engines. There are two common types of pumps used in turbopumps:

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444-464: Is lost. The volute or diffuser turns the high kinetic energy into high pressures (hundreds of bars is not uncommon), and if the outlet backpressure is not too high, high flow rates can be achieved. Axial turbopumps also exist. In this case the axle essentially has propellers attached to the shaft, and the fluid is forced by these parallel with the main axis of the pump. Generally, axial pumps tend to give much lower pressures than centrifugal pumps, and

481-448: Is powered by two or three LE-9 engines which uses an expander bleed cycle design similar to the LE-5B engine. The fuel and oxidizer mass of the first stage is 225 metric tons. The second stage is powered by a single engine which is an improved LE-5B. The propellant mass of the second stage is 23 metric tons. Each H3 booster configuration has a two-digit plus letter designation that indicates

518-534: Is the most important factor in achieving cost reduction, improved safety and increased thrust. The expander bleed cycle used in the LE-9 engine is a highly reliable combustion method that Japan has put into practical use for the LE-5A / B engine. However, it is physically difficult for an expander bleed cycle engine to generate large thrust, so the development of the LE-9 engine with a thrust of 1,471 kN (331,000 lb f )

555-434: The brazed impeller and it flew apart. A new one was made by milling from a solid block of aluminum . The next two runs with the new pump were a great disappointment; the instruments showed no significant flow or pressure rise. The problem was traced to the exit diffuser of the pump, which was too small and insufficiently cooled during the cool-down cycle so that it limited the flow. This was corrected by adding vent holes in

592-557: The 15 themes that will be tested in Innovative Satellite Technology Demonstration-3. Seven technologies would have been tested on board RAISE-3. GEMINI, developed by Mitsubishi Electric (MELCO) is a device that includes a commercial off-the-shelf graphics processing unit (COTS GPU). GEMINI has SAR images preinstalled to replicate a typical Earth observation satellite , and the GPU will format and process

629-549: The H3 was authorized by the Japanese government on 17 May 2013. The H3 Launch Vehicle is being jointly developed by JAXA and Mitsubishi Heavy Industries (MHI) to launch a wide variety of commercial satellites. The H3 was designed with cheaper engines compared to the H-IIA , so that manufacturing the new launch vehicle would be faster, less risky, and more cost-effective. JAXA and Mitsubishi Heavy Industries were in charge of preliminary design,

666-510: The H3-32, was cancelled in late 2018 when the performance of the H3-22 variant, sporting one less engine on the core booster, was found to be greater than anticipated, putting it close to the H3-32's performance. While the H3-32 would have provided greater performance, JAXA cited SpaceX 's experience with their Falcon 9 rocket, which routinely lifted commercial communications satellite payloads to less than

703-591: The SRB-3 boosters ignition, although the main engines were successfully ignited. On the second launch attempt for the H3 Launch Vehicle on 7 March the vehicle launched at 1:37:55 AM UTC (Universal Time Coordinated). Shortly after the SRB-3 boosters separated from the rocket around two minutes into the flight, the rocket appeared to lose control and begin to tumble based on the views from the ground camera; however, based on subsequent analysis, this appears to be part of

740-564: The chamber. The first engine fired successfully in September, and on August 16, 1942, a trial rocket stopped in mid-air and crashed due to a failure in the turbopump. The first successful V-2 launch was on October 3, 1942. The principal engineer for turbopump development at Aerojet was George Bosco . During the second half of 1947, Bosco and his group learned about the pump work of others and made preliminary design studies. Aerojet representatives visited Ohio State University where Florant

777-524: The client had to then load additional propellant onto their satellite for it to reach GEO, than a more expensive H3-32. As of October 2019 , MHI is considering contributing two variants for the Gateway project: an extended second stage variant, and the H3 Heavy variant which would comprise three first-stage liquid-fuel boosters strapped together, similar to Delta IV Heavy and Falcon Heavy . It would have

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814-712: The design, manufacture, and operation of the H3. The H3 is the world's first rocket to use an expander bleed cycle for the first stage engine. As of July 2015 , the minimum configuration is to carry a payload of up to 4,000 kg (8,800 lb) into Sun-synchronous orbit (SSO) for about 5 billion yen , and the maximum configuration is to carry more than 6,500 kg (14,300 lb) into geostationary transfer orbit (GTO). The H3-24 variant will deliver more than 6,000 kg (13,000 lb) of payload to lunar transfer orbit (TLI) and 8,800 kg (19,400 lb) of payload to geostationary transfer orbit (GTO)(∆V=1830 m/s). Mitsubishi Heavy Industries supervised

851-451: The development and manufacture of the H3 rocket's airframe and liquid-fuel engines, while IHI Corporation developed and manufactured the liquid-fuel engine turbopumps and solid-fuel boosters, and Kawasaki Heavy Industries developed and manufactured the payload fairings . The carbon fiber and synthetic resin used for the solid fuel booster motor case and payload fairing were developed and manufactured by Toray . The development of

888-403: The end of 1948, Aerojet had designed, built, and tested a liquid hydrogen pump (15 cm diameter). Initially, it used ball bearings that were run clean and dry, because the low temperature made conventional lubrication impractical. The pump was first operated at low speeds to allow its parts to cool down to operating temperature . When temperature gauges showed that liquid hydrogen had reached

925-439: The engine per second. The Electron Rocket's Rutherford became the first engine to use an electrically-driven pump in flight in 2018. Most turbopumps are centrifugal - the fluid enters the pump near the axis and the rotor accelerates the fluid to high speed. The fluid then passes through a volute or a diffuser, which is a ring with multiple diverging channels. This causes an increase in dynamic pressure as fluid velocity

962-485: The features of that configuration. The first digit represents the number of LE-9 engines on the main stage, either "2" or "3". The second digit indicates the number of SRB-3 solid rocket boosters attached to the base of the rocket and can be "0", "2", or "4". All layouts of the solid boosters are symmetrical. The letter at the end shows the length of the payload fairing, either short, or "S", or long, or "L". For example, an H3-24L has two engines, four solid rocket boosters, and

999-455: The gold standard geostationary transfer orbit (GTO) of 1,500 m/s (4,900 ft/s) of delta-V remaining to get to geostationary orbit , leaving the satellites themselves to make up the difference. As commercial clients were apparently willing to be flexible, JAXA proposed redefining their reference transfer orbit to something lower, believing commercial clients would prefer the less expensive (if slightly less capable) H3-22 rocket, even if

1036-426: The image in orbit before sending it to a ground station . The main goal of GEMINI is to test how a consumer-grade GPU performs in space. During development, recently recruited engineers at MELCO were charged with the designing and testing of the device. KIR is a water based hybrid thruster that consists of four resistojet thrusters and a single ion thruster , fed by the same water tank. The resistojet thrusters have

1073-623: The pump housing; the vents were opened during cool down and closed when the pump was cold. With this fix, two additional runs were made in March 1949 and both were successful. Flow rate and pressure were found to be in approximate agreement with theoretical predictions. The maximum pressure was 26 atmospheres (26 atm (2.6 MPa; 380 psi)) and the flow was 0.25 kilogram per second. The Space Shuttle main engine 's turbopumps spun at over 30,000 rpm, delivering 150 lb (68 kg) of liquid hydrogen and 896 lb (406 kg) of liquid oxygen to

1110-424: The pump, an attempt was made to accelerate from 5000 to 35 000 revolutions per minute. The pump failed and examination of the pieces pointed to a failure of the bearing, as well as the impeller . After some testing, super-precision bearings, lubricated by oil that was atomized and directed by a stream of gaseous nitrogen, were used. On the next run, the bearings worked satisfactorily but the stresses were too great for

1147-550: The readiness of ground facilities, development of new technologies for the H3, and manufacturing. The main emphasis in design is cost reduction, with planned launch costs for customers in the range of around US$ 37 million. In 2015, the first H3 was planned to be launched in fiscal year 2020 in the H3-30 configuration (which lacks solid-rocket boosters), and in a later configuration with boosters in FY2021. The newly developed LE-9 engine

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1184-492: The satellite's deorbiting and entering Earth's atmosphere . D-SAIL was developed by Axelspace Corporation  [ ja ] . H3 (rocket) The H3 Launch Vehicle is a Japanese expendable launch system . H3 launch vehicles are liquid-propellant rockets with strap-on solid rocket boosters and are launched from Tanegashima Space Center in Japan. Mitsubishi Heavy Industries (MHI) and JAXA are responsible for

1221-473: The use of more efficient sources of mechanical energy. One of such cases are rocket engines , which need to pump fuel and oxidizer into their combustion chamber . This is necessary for large liquid rockets , since forcing the fluids or gases to flow by simple pressurizing of the tanks is often not feasible; the high pressure needed for the required flow rates would need strong and thereby heavy tanks. Ramjet motors are also usually fitted with turbopumps,

1258-458: Was "no possibility of achieving the mission". The payload onboard was the ALOS-3 satellite, which was also destroyed with the launch vehicle on the moment of self-destruct. On 17 February 2024, JAXA finally successfully launched the second testing rocket which has the same configuration as the first one, H3-22S, and the second stage reached the desired orbit. Turbopump A turbopump

1295-457: Was developed by Pale Blue, a company that produces a series of thrusters for use in smallsats, all using water as fuel. The company claims that the use of water, instead of toxic alternatives will lead to the sustainable development of space. D-SAIL is a deployable sail that uses its large surface area to generate friction with the atmosphere and decrease the orbital speed of the satellite, which allows it to lower altitude, ultimately leading to

1332-722: Was the most challenging and important development element. Firing tests of the LE-9 first-stage engine began in April 2017, with the first tests of the solid rocket boosters occurring in August 2018. On 21 January 2022, the launch of the first H3 was rescheduled to FY 2022 or later, citing technical problems regarding the first stage LE-9 engine. The H3 Launch Vehicle is a two-stage launch vehicle. The first stage uses liquid oxygen and liquid hydrogen as propellants and carries zero, two or four strap-on solid rocket boosters (SRBs) (derived from SRB-A ) using polybutadiene fuel. The first stage

1369-457: Was working on hydrogen pumps, and consulted Dietrich Singelmann , a German pump expert at Wright Field. Bosco subsequently used Singelmann's data in designing Aerojet's first hydrogen pump. By mid-1948, Aerojet had selected centrifugal pumps for both liquid hydrogen and liquid oxygen . They obtained some German radial-vane pumps from the Navy and tested them during the second half of the year. By

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