Simulations of the collection of mesospheric dust particles with rocket instrument
0
Citation
23
Reference
10
Related Paper
Abstract:
Abstract. We investigate the collection of dust from the mesosphere with the MESS instrument that is designed to fly on a sounding rocket. The instrument consists of a collection device with an opening and closure mechanism and an attached conic funnel. Attaching the funnel increases the sampling area in comparison to the collection area. The instrument will collect primary particles that directly hit the collection area and secondary particles that form from mesospheric dust hitting the funnel. We simulate the entry and impact of dust onto the detector considering their trajectories in the airflow and the fragmentation at the funnel. We estimate the collection efficiency of the instrument and the impact energy of particles at the collecting area. The design considered has a sampling area of 5 cm diameter and a collection area of 1.8 cm diameter. We use the results of the calculations to estimate the amount of dust that MESS (MEteoric Smoke Sampler) can collect during a rocket flight. We consider meteoric smoke particles (MSP) based on a model of the MSP distribution. In addition we assume that water ice particles that form close to the mesopause contain a fraction of smaller MSP. The water ice sublimates during the collection or later during rocket flight so that only refactory material remains. Assuming the collected particles contain 3 % volume fraction of MSP, we find that the instrument would collect of the order of 1014 to 1015 amu of refractory MSP particles. The estimate basis on the assumption that the ice components are melting and the flow conditions in the instruments are for typical atmospheric pressures at 85 km. Aside from the instrument conditions that we investigate in this paper, our estimate of the mass that we expect to collect with MESS applies the results from a particle transport model for the meteoric smoke particles and from the description of noctilucent cloud particles based on published model and observational results.Keywords:
Sounding rocket
Funnel
Rocket (weapon)
An S-520 sounding rocket was launched in the summer of 2007 in order to observe magneto electric phenomena in high sky and to verify a new spectroscopic observation method. A Multi-Spectrum Imager (MSI) was developed for the latter aim. The observation device is equipped a spectroscopic camera with a liquid crystal tunable filter and a pointing system to control the pointing direction to take spectroscopic images of a target against the spin of the rocket body. With the successful flight of the sounding rocket, the MSI succeeded in taking and sending approximately 30 pictures and the house keeping data.
Sounding rocket
Rocket (weapon)
Cite
Citations (0)
The De-spun Rocket Borne Imager 2 (DERBI2) was designed for the February 2007 launch of the Rocket Observations of Pulsating Aurora (ROPA) sounding rocket. DERBI2 will obtain large-scale, topside images of pulsating aurora which will be de-spun to minimize the effects of im- age blurring due to spinning of the rocket payload. This de- spinning is achieved via a rotating platform within the imager upon which will be mounted a back-thinned, frame-transfer CCD and supporting electronics. This CCD was chosen for superior gain and transmission characteristics, and as a re- sult, DERBI2 is a more compact imager with a wider field of view than its predecessor.
Rocket (weapon)
Sounding rocket
Payload (computing)
Cite
Citations (0)
사운딩로켓의 고도 극대화를 위한 최적의 분사조건을 결정하기 위한 연구를 수행하였다. 공력저항을 고려한 단순화된 1차원 모멘텀 방정식의 거동을 조사하였다. 해석적 해가 존재하는 경우와 분사 유량이 일정한 경우에 대해 계산을 수행하였으며, 해는 수치 해와 비교하였다. 사운딩로켓의 고도를 최대로 하는 최적의 분사조건이 존재하며, 최적조건은 로켓의 질량비의 함수임을 보였다. A study to determine the optimal jet conditions for maximizing altitude of the sounding rocket is conducted. The behavior of a simplified one-dimensional momentum equation including aerodynamic drag is investigated. The case where an analytic solution exists and the case where the mass flow rate is constant are calculated. The solutions are compared with numerical solutions. It is shown that there are the optimal jet conditions for maximizing altitude of a sounding rocket and the optimal condition is a function of the rocket mass ratio.
Sounding rocket
Rocket (weapon)
Momentum (technical analysis)
Mass flow rate
Cite
Citations (1)
Sounding rocket
Rocket (weapon)
Rocket propellant
Cite
Citations (0)
The second pulsating aurora (PULSAUR 2) rocket was a comprehensively instrumented rocket for the study of the generating mechanisms of pulsating auroras and their related atmospheric and ionospheric effects. It carried instruments to measure electrons and ions over a wide range of energies and pitch angles, optical emissions and X-rays, direct currents and alternating currents, magnetic fields, electron densities and temperatures. The rocket was flown from Andoeya, Norway on 9 February 1994, during good auroral and optical conditions, and reached an altitude of 291.5 km. Coordinated measurements were made from the rocket range by television cameras, photometers, magnetometers, riometers and very low frequency receivers. Ionospheric parameters were measured by the EISCAT radar. The main objectives and performance of the project are discussed, and some of the data obtained are mentioned.
Sounding rocket
Rocket (weapon)
Photometer
Ionospheric sounding
Atmospheric sounding
Airglow
Cite
Citations (1)
The design of a rocket‐borne data transmission system is presented in this article. This data transmission system is used for Meridian Space Weather Monitoring Project II sounding rocket. The major function of this data transmission system is to transmit payload data and rocket telemetry data to ground station. The data transmission system achieves power greater than 4 W (36 dBm). The amplitude unbalance is 1.60% (0.14 dB) and the phase unbalance is 1.74°. Total power consumption of the data transmission system is less than 24 W (28 V power supply). The radiation performance of the data transmission antenna is good. Based on the actual condition of solid rocket, the relevant heat dissipation and vibration reduction measures are designed under the demand of miniaturization. The data transmission system has been tested by performance test, environmental simulation test, system integration test, and other tests; the test results show that it has good working performance, good stability, and high reliability.
Sounding rocket
Rocket (weapon)
Cite
Citations (0)
The temperatures and winds in the upper atmosphere have been measured by means of the Aerobee sounding rocket. The determination of the velocity of sound between grenades ejected from the rocket and exploded at successive heights measures the temperatures. The angles of arrival of the sound waves at the ground are used to determine the winds. The experimental method is outlined and the rocket-borne and ground instrumentations are described. A summary of the rocket firings carried out is also given.
Rocket (weapon)
Sounding rocket
Instrumentation
Atmospheric sounding
Cite
Citations (7)
Cell-cell interactions and the formation of cell aggregates are important events in the mitogen-induced lymphocyte activation. The fact that the formation of cell aggregates is only slightly reduced in microgravity suggests that cells are moving and interacting also in space, but direct evidence was still lacking. Here we report on two experiments carried out on a flight of the sounding rocket MAXUS 1B, launched in November 1992 from the base of Esrange in Sweden. The rocket reached the altitude of 716 km and provided 12.5 min of microgravity conditions.
Sounding rocket
Rocket (weapon)
Atmospheric sounding
Cite
Citations (18)
Local ionospheric electron density irregularities in the scale size of 3m to 300m have been measured on the ascending path from 74km to 93km by a fix biased Langmuir probe on board the S-310-16 sounding rocket. The rocket was launched at 22:40:00 on February 1, 1986 from Kagoshima Space Center in Japan. It is found from frequency analysis of the data that the spectral index of the irregularities is 0.9 to 1.8 and the irregularity amplitude is 1 to 15%. The altitude where the amplitude reaches its maximum is 88km.The generation mechanism of these irregularities is explained by the neutral turbulence theory, which indicates that the spectral index is 5/3 and has been confirmed by a chemical release experiment using rockets over India to be valid up to about 110km.From frequency analysis of the data observed during the descent in the lower E region, we have found that the rocket-wake effect becomes larger when the probe is situated near the edge of the rocket-wake, and that this is also the case even when the rocket-wake effect does not clearly appear in the DC current signal which approximately changes in proportion to the electron density, where the probe is completely situated inside the rocket-wake region.
Sounding rocket
Rocket (weapon)
Ionospheric sounding
Langmuir Probe
Descent (aeronautics)
Cite
Citations (2)
Sounding rocket
Rocket (weapon)
Payload (computing)
Electron gun
Cite
Citations (9)