著者

齊藤 健一 太田 裕文

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.46, no.531, pp.247-253, 1998-04-05 (Released:2010-12-16)

参考文献数

8

被引用文献数

2 2

---

Two design considerations to the exact linearization method that yield a robust controller to parameter variations are proposed. The first one is that the feedback gains using exact linearization are determined to be equal to those of the linear approximated design. This means that the closed-loop system has no less robustness than the corresponding linear approximated design. Another design consideration is based on the idea that two vector fields before and after the nonlinear transformation are made to be equal each other near the design point. Thus, the transformed system retains the original stability characteristics. The first consideration is then used to design a nonlinear controller of an aircraft with a jump phenomena due to roll coupling. The equations of motion are examined from viewpoint of exact linearization, and the required ransformation is obtained analytically. The designed controller is examined for the control input magnitude and parameter variations, and the robustness is compared with a linear controller.

著者

小林 繁夫 小島 浩

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.30, no.341, pp.354-363, 1982-06-05 (Released:2009-05-25)

参考文献数

16

---

An analytical study has been carried out to clarify the mechanism of pogo. As a numerical example, the pogo instability of N-Launch Vehicle has been studied. The calculated result is in good agreement with the flight record for the occurrence time of pogo vibration. The following properties have been disclosed. (1) Main factors which govern the pogo occurrence are the mass ratio and the structural damping coefficient. (2) In the case of N-Vehicle, the pogo instability is mainly created at the oxidizer-structure loop with a short feed pipe. (3) The bubble frequency due to cavitation in the oxidizer pump plays an important role.The effectiveness of an accumulator at the pump inlet as a suppression device is also presented analytically.

著者

竹中 幸彦 小川 鉱一 遠藤 修司

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空学会誌 (ISSN:00214663)

巻号頁・発行日

vol.15, no.159, pp.136-140, 1967-04-05 (Released:2009-07-09)

参考文献数

9

著者

黒田 泰弘 大塚 貞吉 秋葉 鐐二郎

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.24, no.265, pp.66-73, 1976-02-05 (Released:2009-05-25)

著者

久田 安正 伊東 康之 井村 信義 谷沢 一雄 尾形 慶照 引間 栄一

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.31, no.355, pp.456-460, 1983-08-05 (Released:2009-05-25)

参考文献数

5

著者

宮沢 与和 ビクラマシンハ ナビィンダ キトマル 原田 明徳 宮本 侑斗

出版者

一般社団法人 日本航空宇宙学会

雑誌

航空宇宙技術 (ISSN:18840477)

巻号頁・発行日

vol.12, pp.31-38, 2013 (Released:2013-03-06)

参考文献数

10

被引用文献数

3 6 2

---

In the future air transportation system, airspace will be efficiently used and each aircraft can optimize its own performance. Due to limited capacity of the airspace like terminal area, however, some sort of adjustment for each aircraft is necessary to maintain separation among multiple aircraft. Fixed arrival time is a basic solution to the problem. This paper studies the effect of arrival time assignment on the performance by assuming that each aircraft generates its own flight plan by minimizing its fuel consumption. Dynamic programming trajectory optimization is used to calculate the optimal flight profile composed of altitude and velocity. The result shows that the arrival time adjustment is efficiently performed in the descent phase, if the required amount of time to be adjusted is not large.

著者

藤田 輝昭

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.19, no.211, pp.378-384, 1971 (Released:2009-05-25)

著者

平川 美晴 中北 正人

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.47, no.546, pp.267-271, 1999-07-05 (Released:2009-07-09)

参考文献数

6

---

The performance of the ion thruster depends on the discharge performance and the beam extraction, the former of which is significantly effected by the electron property such as density and energy, since ions are produced by ionization collisions between neutral atoms and electrons. In the microwave ion thruster, the discharge owes to the electron cyclotron resonance (ECR). Thus, the electron phenomenon in the microwave discharge chamber was numerically investigated by the particle simulation method. In our model, the electromagnetic wave is polarized circularly and propagates in the axial direction and electrons are moved in the microwave and static magnetic fields, colliding with neutral particles. Collision processes are taken into account by the Monte Carlo method. This simulation results show that some electrons can be heated enough to cause ionization collisions and that the density and energy distributions are peculiar to the microwave ion thrusters.

著者

佐藤 昌之 村岡 浩治

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.61, no.4, pp.110-118, 2013 (Released:2013-10-25)

参考文献数

15

被引用文献数

3 5

---

This paper is concerned with the flight controller design of Quad Tilt Wing (QTW) Unmanned Aerial Vehicle (UAV) which has Vertical Take-Off and Landing (VTOL) capability as well as high speed cruise performance. The flight controller is composed of Stability Augmentation System (SAS), which feedbacks angular velocity, and Control Augmentation System (CAS), which feedbacks the difference between attitude commands and current attitude angles. The gains of S/CAS are both scheduled by the tilt angle of the main wings of the QTWUAV since its airspeed and flight dynamics drastically change in accordance with the tilt angle. The S/CAS are designed by three steps; we first select several design points, then design the controller gains at those design points, and finally connect the gains by linear interpolation. In the design process of the controller gains, perturbed models are introduced in addition to the nominal models, and common gains for those models are designed to ensure robust control performance against modeling errors. Full transition flight from vertical take-off to horizontal cruise was successfully accomplished using our controllers.

著者

坂東 俊夫 小林 修

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.31, no.349, pp.66-75, 1983-02-05 (Released:2009-05-25)

参考文献数

6

被引用文献数

1 2

著者

森田 光男 佐々木 誠 高沢 金吾 鳥崎 忠雄

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.32, no.371, pp.731-739, 1984-12-05 (Released:2009-05-25)

参考文献数

12

著者

三浦 安帆

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.33, no.376, pp.251-266, 1985-05-05 (Released:2009-05-25)

参考文献数

14

著者

蒋 理 大森 太加 柴田 寿一 今村 太郎 李家 賢一

出版者

一般社団法人 日本航空宇宙学会

雑誌

航空宇宙技術 (ISSN:18840477)

巻号頁・発行日

vol.14, pp.17-21, 2015 (Released:2015-02-13)

参考文献数

7

被引用文献数

1

---

Modified PARSEC (PARametric SECtion Method) is used as a parameterization method to describe airfoil shapes by few number of parameters, which is suitable for airfoil design optimization. To calculate these parameters, GA (Genetic Algorithm) is usually used. However, it has been observed that for some airfoils, Modified PARSEC method generates irregular shapes when GA is used. To overcome this issue, a new method using Pseudo-Inverse Matrix is developed. The proposed method is applied to various airfoils including the airfoil sections of the CRM (Common Research Model) wing, and a two-dimensional CFD code is used to carry out the aerodynamic analysis. Subsequently, the three-dimensional CRM wing is reproduced using the proposed method and its aerodynamic characteristics are analyzed with Euler equations. The results show that reproduced geometry is almost identical to that of the original CAD data in terms of aerodynamic characteristics, which shows the applicability and usefulness of the method.

著者

江島 重良

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.20, no.219, pp.214-219, 1972 (Released:2009-05-25)

著者

炭田 潤一郎

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.32, no.369, pp.553-561, 1984-10-05 (Released:2009-05-25)

参考文献数

5

著者

金井 喜美雄

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.27, no.308, pp.439-452, 1979-09-05 (Released:2009-05-25)

参考文献数

40

被引用文献数

1

著者

高浜 盛雄 木村 剛 徳田 映 大野 正博

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.41, no.473, pp.324-329, 1993-06-05 (Released:2010-12-16)

参考文献数

16

著者

藤森 篤

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.45, no.523, pp.474-481, 1997-08-05 (Released:2010-12-16)

参考文献数

9

被引用文献数

2 2 2

---

This paper presents a flight control technique using fuzzy gain-scheduling state-feedback. The dynamics of an aircraft considered in this paper is regarded as a linear parameter-varying system in which the altitude and the flight velocity are varying. The system is given by a fuzzy model which consists of linear time-invariant systems at some operating points. The state-feedback gains of the fuzzy gain-scheduling are obtained so as to satisfy multiple linear matrix inequalities. The proposed technique shows better control performance than conventional linear quadratic regulators and a conventional gain scheduling technique in a numerical simulation of a longitudinal flight control problem.

著者

宮沢 与和

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.41, no.473, pp.318-323, 1993-06-05 (Released:2010-12-16)

参考文献数

10

被引用文献数

1 2

著者

ワイスハール テレンスA. 鈴木 真二

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.42, no.487, pp.455-461, 1994-08-05 (Released:2010-12-16)

参考文献数

23