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981.
Space-time adaptive processing (STAP) and related adaptive array techniques hold tremendous potential for improving sensor performance by exploiting signal diversity. Such methods have important application in radar, sonar, and communication systems. Recent advances in digital signal processing technology now provide the computational means to field STAP-based systems. The objective of this special collection of papers is to examine the current state-of-the art in STAP technology and explore the remaining obstacles, practical issues and novel techniques required to implement STAP-based radar, sonar or communication systems 相似文献
982.
Green J.L. Benson R.F. Fung S.F. Taylor W.W.L. Boardsen S.A. Reinisch B.W. Haines D.M. Bibl K. Cheney G. Galkin I.A. Huang X. Myers S.H. Sales G.S. Bougeret J.-L. Manning R. Meyer-Vernet N. Moncuquet M. Carpenter D.L. Gallagher D.L. Reiff P.H. 《Space Science Reviews》2000,91(1-2):361-389
The Radio Plasma Imager (RPI) will be the first-of-its kind instrument designed to use radio wave sounding techniques to perform repetitive remote sensing measurements of electron number density (N
e) structures and the dynamics of the magnetosphere and plasmasphere. RPI will fly on the Imager for Magnetopause-to-Aurora Global Exploration (IMAGE) mission to be launched early in the year 2000. The design of the RPI is based on recent advances in radio transmitter and receiver design and modern digital processing techniques perfected for ground-based ionospheric sounding over the last two decades. Free-space electromagnetic waves transmitted by the RPI located in the low-density magnetospheric cavity will be reflected at distant plasma cutoffs. The location and characteristics of the plasma at those remote reflection points can then be derived from measurements of the echo amplitude, phase, delay time, frequency, polarization, Doppler shift, and echo direction. The 500 m tip-to-tip X and Y (spin plane) antennas and 20 m Z axis antenna on RPI will be used to measures echoes coming from distances of several R
E. RPI will operate at frequencies between 3 kHz to 3 MHz and will provide quantitative N
e values from 10–1 to 105 cm–3. Ray tracing calculations, combined with specific radio imager instrument characteristics, enables simulations of RPI measurements. These simulations have been performed throughout an IMAGE orbit and under different model magnetospheric conditions. They dramatically show that radio sounding can be used quite successfully to measure a wealth of magnetospheric phenomena such as magnetopause boundary motions and plasmapause dynamics. The radio imaging technique will provide a truly exciting opportunity to study global magnetospheric dynamics in a way that was never before possible. 相似文献
983.
984.
The Radio Plasma Imager investigation on the IMAGE spacecraft 总被引:1,自引:0,他引:1
Reinisch B.W. Haines D.M. Bibl K. Cheney G. Galkin I.A. Huang X. Myers S.H. Sales G.S. Benson R.F. Fung S.F. Green J.L. Boardsen S. Taylor W.W.L. Bougeret J.-L. Manning R. Meyer-Vernet N. Moncuquet M. Carpenter D.L. Gallagher D.L. Reiff P. 《Space Science Reviews》2000,91(1-2):319-359
Radio plasma imaging uses total reflection of electromagnetic waves from plasmas whose plasma frequencies equal the radio sounding frequency and whose electron density gradients are parallel to the wave normals. The Radio Plasma Imager (RPI) has two orthogonal 500-m long dipole antennas in the spin plane for near omni-directional transmission. The third antenna is a 20-m dipole along the spin axis. Echoes from the magnetopause, plasmasphere and cusp will be received with the three orthogonal antennas, allowing the determination of their angle-of-arrival. Thus it will be possible to create image fragments of the reflecting density structures. The instrument can execute a large variety of programmable measuring options at frequencies between 3 kHz and 3 MHz. Tuning of the transmit antennas provides optimum power transfer from the 10 W transmitter to the antennas. The instrument can operate in three active sounding modes: (1) remote sounding to probe magnetospheric boundaries, (2) local (relaxation) sounding to probe the local plasma frequency and scalar magnetic field, and (3) whistler stimulation sounding. In addition, there is a passive mode to record natural emissions, and to determine the local electron density, the scalar magnetic field, and temperature by using a thermal noise spectroscopy technique. 相似文献
985.
Muon observations are complementary to neutron monitor observations but there are some important differences in the two techniques.
Unlike neutron monitors, muon telescope systems use coincidence techniques to obtain directional information about the arriving
particle. Neutron monitor observations require simple corrections for pressure variations to compensate for the varying mass
of atmospheric absorber over a site. In contrast, muon observations require additional corrections for the positive and negative
temperature effects. Muon observations commenced many years before neutron monitors were constructed. Thus, muon data over
a larger number of solar cycles is available to study solar modulation on anisotropies and other cosmic ray variations.
The solar diurnal and semi-diurnal variations have been studied for many years. Using the techniques of Bieber and Chen it
has been possible to derive the radial gradient, parallel mean-free path and symmetric latitude gradient of cosmic rays for
rigidities <200 GV. The radial gradient varies with the 11-year solar activity cycle whereas the parallel mean-free path appears
to vary with the 22-year solar magnetic cycle. The symmetric latitudinal gradient reverses at each solar polarity reversal.
These results are in general agreement with predictions from modulation models. In undertaking these analyses the ratio of
the parallel to perpendicular mean-free path must be assumed. There is strong contention in the literature about the correct
value to employ but the results are sufficiently robust for this to be, at most, a minor problem. An asymmetric latitude gradient
of highly variable nature has been found. These observations do not support current modulation models.
Our view of the sidereal variation has undergone a revolution in recent times. Nagashima, Fujimoto and Jacklyn proposed a
narrow Tail-In source anisotropy and separate Loss-Cone anisotropy as being responsible for the observed variations. A new
analysis technique, more amenable to such structures, was developed by Japanese and Australian researchers. They confirmed
the existence of the two anisotropies. However, they found that the Tail-In anisotropy is asymmetric and that both anisotropies
had different positions from the prediction.
Most 27-day modulations are observed at neutron monitor rigidities but not so readily at higher rigidities. An exception to
this is the Isotropic Intensity Wave modulation observed in the early 1980s and again in 1991. This modulation is very strongly
related to the heliospheric sector structure and implies a significantly different cosmic ray density on either side of the
neutral sheet.
The interpretation of most cosmic ray modulation phenomena requires good latitude coverage in both hemispheres. The closure
of many muon observatories is a matter of concern. In the northern hemisphere a few new instruments are being constructed
and spatial coverage is barely adequate. In the southern hemisphere the situation is far worse with the possibility that within
a decade only the Mawson observatory in Antarctica will still be in operation.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
986.
杨始燕%汪倩%谢择民%徐抗%吕伟 《宇航材料工艺》2000,30(1):42-45
研究了一种新的空间级加成型室温硫化硅橡胶KH—SP—B ,它的特点在于具有低的热真空失重 ,在 12 5℃× 2 4h ,1× 10 - 10 MPa下的热真空失重可小于 0 .3% ;高的粘接强度 ,与金属及聚酰亚胺等的粘结强度可达到 2MPa以上 ;高的热稳定性能 ,分解温度可达 52 4℃ ;优异的低温性能 ,脆性温度为 - 114℃ ;良好的电性能 ,体积电阻率可达 1.3× 10 16 Ω·cm。是一种综合性能优良的空间级室温硫化硅橡胶。 相似文献
987.
988.
双立尾/三角翼布局的立尾抖振研究 总被引:1,自引:0,他引:1
在北航的风洞中进行了双立尾-三角翼布局的立尾抖振实验,目的是研究立尾抖振产生的原因.主要采用了激光测振仪测立尾加速度和动态压力传感器测立尾表面的动态压力的实验方法.实验结果表明在旋涡破裂以后,立尾上就会产生强烈的抖振.抖振是由立尾上表面压力的周期性脉动造成的.对机翼和立尾表面的压力频谱分析表明,立尾上的压力脉动来源于机翼前旋涡破裂流中的螺旋波.对于本实验使用的模型来说,当机翼迎角α=0°~20°范围,由于流动是附着流和涡流,所以立尾没有明显抖振;当机翼迎角在α=20°~56°范围,立尾处在破裂涡流的范围,立尾抖振明显,并且抖振强度在35°~50°之间达到最大.因此,三角翼破裂涡流中的螺旋波正是双立尾产生抖振的主要原因. 相似文献
989.
990.