| Project/Area Number |
11450374
|
|---|
| Research Category |
Grant-in-Aid for Scientific Research (B)
|
| Allocation Type | Single-year Grants |
|---|
| Section | 一般 |
|---|
| Research Field |
Aerospace engineering
|
|---|
| Research Institution | TOHOKU UNIVERSITY |
|---|
Principal Investigator |
KAMIJO Kenjiro TOHOKU UNIV., INSTI. OF FLUID SCIENCE, PROFESSOR, 流体科学研究所, 教授 (90282003)
|
|---|
| Co-Investigator(Kenkyū-buntansha) |
TUJIMOTO Yoshinobu OSAKA UNIV., DEP. OF ENG. SCIENCE, PROFESSOR, 基礎工学研究科, 教授 (50112024)
TOKUMASU Takashi TOHOKU UNIV., INSTI. OF FLUID SCIENCE, RESEARCH ASSOCIATE, 流体科学研究所, 助手 (10312662)
OIKE Mamoru TOHOKU UNIV., INSTI. OF FLUID SCIENCE, ASSOCIATE PROFESSOR, 流体科学研究所, 助教授 (70292282)
YAMADA Hitoshi NATIONAL AEROSPACE LAB. KAKUDA RESEARCH CE., GROUP LEADER, ロケット部, 室長(研究職)
TAMURA Hiroshi NATIONAL AEROSPACE LAB. KAKUDA RESEARCH CE., GROUP LEADER, ロケット部, 室長(研究職)
|
|---|
| Project Period (FY) |
1999 – 2001
|
| Project Status |
Completed (Fiscal Year 2001)
|
| Budget Amount *help |
¥14,700,000 (Direct Cost: ¥14,700,000)
Fiscal Year 2001: ¥2,200,000 (Direct Cost: ¥2,200,000)
Fiscal Year 2000: ¥7,400,000 (Direct Cost: ¥7,400,000)
Fiscal Year 1999: ¥5,100,000 (Direct Cost: ¥5,100,000)
|
|---|
| Keywords | AIR LIQUEFACATION / ROCKET ENGINE / HEAT EXCHANGER / LIQUID HYDROGEN / TWO-PHASE FLOW / LIQUID AIR |
|---|
| Research Abstract |
Based on the experimental results, an analytical method of estimating a liquefaction (mass of liquefied air cooled by 1 kg of liquid hydrogen), and an outlet temperature of liquid hydrogen of the heat exchanger was established, by which we easily evaluate the performance of the heat exchanger cooled by liquid hydrogen. Using this analytical method, we will be able to easily improve the performance of heat exchanger. The specific impulse of LACE was estimated using the above -mentioned method. More than 1,000 second of the specific impulse was calculated even in a simple LACE system. The higher specific impulse will be able to obtain by improvement of the heat exchanger, selection of the optimum LACE system, the selection of the optimum delivery pressure of liquid hydrogen pump, etc. Judging from the mentioned above performance of the present LACE engine, it will be considered that the LACE engine would be a one of the candidates of a rocket based combined cycle engine for a future reusable launch vehicle. The effect of the flight trajectory on the LACE engine was numerically investigated. The numerical results showed that the specific impulse of the present LACE system was smaller than that expected in the low flight Mach number. Therefore, some means, for instance the use of subcooled liquid hydrogen, will be required which enhance the performance of the LACE engine in the low flight Mach number.
|
