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Journal Article 8

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2020 1

2018 1

2007 1

2006 2

2000 2

1999 1

Keywords

AC position servo system 1

Parameter optimization 1

Pico-satellite 1

Satellite–rocket separation mechanism 1

Separation parameters 1

aircraft 1

child restraint system 1

ground dynamic simulating test 1

heavy lift launch vehicle 1

injury criteria 1

lateral vibration 1

liquid rocket engine 1

manned lunar landing 1

optimal control 1

propulsion having top priority 1

rating program 1

reusable launching vehicles 1

robust control 1

rocket 1

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XB High Accuracy Rocket Sled Test Track

Yang Xingbang

Strategic Study of CAE 2000, Volume 2, Issue 10, Pages 98-104

Abstract:

Rocket sled test track is a large ground dynamic simulating test facility.China has successfully built the world ´s only track —XB high accuracy rocket sled test track

Keywords： rocket sled test track ground dynamic simulating test

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Exploration of the Development Road for Chinese Liquid Rocket Engine in 21st Century

Wang Heng

Strategic Study of CAE 1999, Volume 1, Issue 2, Pages 1-5

Abstract:

Liquid rocket engine is an important member of the space propulsion family and the only propellingMeanwhile, we should begin preliminary researches on rocket spaceplane and aerospike nozzle adopted by

Keywords： propulsion having top priority liquid rocket engine heavy lift launch vehicle rocket spaceplane

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Astronauts Hitch First Ride Aboard Private Rocket to Space Station

Chris Palmer

Engineering 2020, Volume 6, Issue 11, Pages 1207-1209 doi: 10.1016/j.eng.2020.08.007

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Present Situation and Future Prospects of Child Restraint Systems for Vehicles

Fang Yuan,Wu Guangqiang

Strategic Study of CAE 2006, Volume 8, Issue 8, Pages 81-85

Abstract:

Child restraint system(CRS)is a new study field in the world. Especially in China, the CRS research is particularly meaningful with the rapid growth of the number of child passengers. The amendment and optimization on the regulations of CRS are brought out based on the distinction between CRS and occupant safety systems. The application of advanced design theory, the technology of computer simulation and the systematical analysis strategy will bring a new prospect for the development of CRS.

Keywords： child restraint system safety chair sled test injury criteria rating program

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Lateral Vibration Analyses of Flying Vehicle under Thrust and Drag

Song Jian

Strategic Study of CAE 2000, Volume 2, Issue 10, Pages 63-72

Abstract:

In this paper, the influence of thrust and air drag on rocket lateral vibration is studied, and theThe equations of transverse movement when nozzle connected rigidly with rocket and related boundary conditions

Keywords： aircraft rocket lateral vibration thrust and drag vibration mode and frequency

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Optimal Robust Control of AC Position Servo System for Multiple Rockets

Chai Huawei,Ma Dawei,Li Zhigang,Le Guigao,Wang Feng

Strategic Study of CAE 2007, Volume 9, Issue 10, Pages 83-87

Abstract:

In order to realize high speed and high precision position control in an AC servo system, in view of such kinds of uncertainties as moment of inertia and load moment changing widely, and strong impact moment, an optimal robust control tactics is put forward. Experimental results show that this control tactics has strong robustness, and has fairly good dynamic performances and steady-state precision.

Keywords： rocket mortar AC position servo system robust control optimal control

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A composite optimization method for separation parameters of large-eccentricity pico-satellites None

Lai TENG, Zhong-he JIN

Frontiers of Information Technology & Electronic Engineering 2018, Volume 19, Issue 5, Pages 685-698 doi: 10.1631/FITEE.1700416

Abstract: A spacecraft’s separation parameters directly affect its flying trace. If the parameters exceed their limits, it will be difficult to adjust the flying attitude of the spacecraft, and the spacescraft may go off-track or crash. In this paper, we present a composite optimization method, which combines angular velocities with external moments for separation parameters of large-eccentricity pico-satellites. By changing the positions of elastic launch devices, the method effectively controls the popping process under the condition of less change in the separation mechanism. Finally, the reasons for deviation of angular velocities and unreliable optimization results are presented and analyzed. This optimization method is proved through a ground test which offsets the gravity. Simulation and test results show that the optimization method can effectively optimize the separation parameters of large-eccentricity pico-satellites. The proposed method adapts particularly to the fixed and non-stable status elastic parameters, the distribution of all kinds of elastic devices, and large-eccentricity spacecrafts for which attitude corrections are difficult. It is generally applicable and easy to operate in practical applications.

Keywords： Pico-satellite Satellite–rocket separation mechanism Separation parameters Parameter optimization