Hideshi Kagawa

Endurance Firing Test Results of the Long Life 1N Hydrazine Thruster

Monopropellant Hydrazine Thrusters are widely used in many satellites and explorers propulsion systems and launch vehicle RCSs due to their simple and low cost features. The first generation Japanese 1N thruster design is based on the US TRW 1970s design, with a service life insufficient for modern satellite programs, hence the new 1N thruster, with a long catalyst bed life, is awaited. From 2002, JAXA commenced a study to extend the life of the 1N thruster with BBM (Bread Board Model) and EM (Engineering Model) thruster firing tests. In 2010, four types of PM (Prototype Model) thrusters were constructed and Qualification Tests, including Endurance Firing Tests, were conducted. In 2011, the cumulative impulse of 210kNsec (Hydrazine Throughput exceeded 100kg) and cumulative pulse of 870k were achieved with all PM thrusters. Reports of the new 1N thruster Qualification test as well as the overall development program history are described in this paper.

VISUALIZATION FOR A VOIDED CATALYST BED OF HYDRAZINE THRUSTER IN MICROGRAVITY

Meeting Information: 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit(11-14 July 2004), Fort Lauderdale, Florida

Neutron radiography used on a mono-propellant thruster

Most mono-propellant thruster technologies were developed in the 1960s and the basic principles and fundamental structures, such as the catalyst and propellant, have remained in use without major technical innovation. Conversely, much remains to be identified in terms of the concrete mechanisms and quantitative limitations of the phenomena inside the monopropellant thruster. One of our studies to improve the reliability of propulsion systems involved visualization, facilitating the direct observation of the physical and chemical phenomena occurring within the catalyst bed of the mono-propellant thruster. In this paper, we introduce the visualization test results of the mono-propellant thruster utilizing Neutron Radiography. This paper shows an overview of the non-destructive imaging technique using Neutron Radiography and the visualization hot-firing test result of the mono-propellant thruster through the application of Neutron Radiography.

Visualization of Propellant Behavior inside Catalyst Thruster Using Neutron Radiography

One of our studies to improve the reliability of propulsion systems is the activity of visualization through which we can directly observe the physical and chemical phenomena that occur inside the catalyst thruster. In this paper, we introduce the visualization test results of the catalyst thruster utilizing Neutron Radiography. Neutron Radiography is a non-destructive imaging technique using thermal neutrons. Contrary to X-rays, neutrons are attenuated by some light materials such as hydrogen, but penetrate heavy materials. Using these neutron properties, we have conducted various visualization tests of the propellant behaviors inside the catalyst thruster elements. This paper includes an overview of Neutron Radiography and the preliminary visualization test results of the catalyst thruster elements obtained with Neutron Radiography.

Development of New Composite Propellant Tank for Satellites

Satellite components falling to the ground are a crucial problem, particularly titanium tanks in propulsion systems. Satellite tanks are generally made of titanium alloy because it is light and compatible with propellants used for the satellite. However, it also has a high melting point, which hinders melting on re-entry. To replace the titanium tanks, JAXA has studied as the tank for ground damage prevention on re-entry since 2010 and has started developing a new composite propellant tank since 2013. The tank is targeted; not only due to its demise properties but also its extended propellant storage, cost-effectiveness and a short delivery time. For the first development step, the minimum tank (DM: Development Model #1) which has the shortest cylindrical segment length and a volume of 250L were manufactured to confirm the strength proof of critical portions and the adequacy of production techniques. There are also plans to manufacture a PMD (Propellant Management Device) separately to the tank shell. This paper describes the design, trial productions, and data acquisition tests used when developing the new tank.

Hydrazine decomposition phenomena observed by Neutron radiography at a catalyst bed

Most mono-propellant thruster technologies were developed in the 1960s and the basic principles and fundamental structures, such as the catalyst and propellant, have remained in use without major technical innovation. Conversely, much remains to be identified in terms of the concrete mechanisms and quantitative limitations of the phenomena inside the monopropellant thruster. One of our studies to improve the reliability of propulsion systems involved visualization, facilitating direct observation of the physical and chemical phenomena occurring within the catalyst bed of the mono-propellant thruster. In this paper, we introduce the visualization test results of the mono-propellant thruster utilizing Neutron Radiography. We have also succeeded in shooting movies of hydrazine decomposition phenomena using Neutron Radiography at the Kyoto University Research Reactor.

Experimental Results of a Centrifugal Pump Using Hydrazine and MON-3

A performance evaluation test was conducted on a low Ns pump using real liquids of bipropellant liquid rocket engine. The pump’s low efficiency using water had been previously reported and was attributed to the pump’s small size. However, the pump’s performance using real propellants, hydrazine, and MON-3 remained unknown. To test with real propellants, we considered improving the design of the pump seal mechanism and conducting test operation to measure performance with a rig test model. This report discusses the points of improved design, such as the seal system and test operation. It also discusses the results of the real propellant rig test.

FINAL OPERATION OF KAGUYA

KAGUYA (formerly SELENE) is the second Japanese lunar explorer. It was launched on Sept. 14, 2007 (JST: Japan Standard Time), and was in operation in a circular lunar orbit for approximately 21 months. Finally, we conducted maneuvered falling to

Feasibility testing for high temperatures on SV14 cold gas jet thruster

This paper presents and discusses some fundamental feasibility test results from the Phase-B design activity of the Mercury Magnetospheric Orbiter (MMO) cold-gas thruster, performed in the JAXA Satellite Propulsion Reliability Evaluation Test Stand at the Tsukuba Space Center (TKSC). The tests were dedicated mainly to cycle motion test at the requested temperature, internal leakage, and valve response measurements. The tests apparently complied with the MMO system requirements for the high temperature Mercury orbital environment. As the next step, the MMO project and Marotta UK will develop the MMO Cold Gas thruster systems thruster valve based on SV14 cold thruster design .