37 results about "Space Science" patented technology

A frequency-to-voltage converter with low additional noise. The invention adopts phase-locked loop technology to establish the conversion relationship of frequency and voltage, lock the phase of the low-noise voltage-controlled oscillator to the measured signal, and then detect the control of the voltage-controlled oscillator. It realizes low-noise frequency-to-voltage conversion with the frequency range of the measured signal greater than 100 kHz, which can meet the measurement requirements of ultra-stable laser frequency noise spectrum; it can also be used to measure the frequency noise of general narrow-band lasers, which is better than measuring laser line by fiber delay method. The method of wide calibration laser frequency performance is more accurate, and the present invention provides a higher-precision and more scientific measurement method for the frequency noise level of ultra-stable lasers, and directly determines the noise source that affects the laser frequency stability based on the noise spectrum, so as to be targeted Optimizing the laser system and reducing the frequency noise of the laser is of great significance in the application of ultra-stable lasers and narrow linewidth lasers in time-frequency measurement, basic physics research, deep space exploration, space science and many other fields.

The invention discloses a method for driving a nonmetal flyer with laser, which includes the step: enabling the laser generated by a laser device to enter an ablation layer on optical glass, enabling materials on the ablation layer to instantly evaporate, gasify and ionize so that high-temperature and high-pressure plasmas are generated, and under restraint of the optical glass, enabling high-pressure shock waves generated by the plasmas to act on the other face of the ablation layer and be positioned on a nonmetal film in front of an incident area, so that the residual non-metal film is sheared and driven at a high speed, and the high-speed flyer is formed. The method and an implementation device can make up the defect that a current laser-driven flyer can only emit metallic grits so that non-metal grits can be emitted, and can also be applied to the field of high-pressure physics, space science, material micro-forming technology, rapid initiation of explosives and the like. When a space debris environment is simulated in a laser-driven flyer manner in the space science, the debris environment can be efficiently simulated by alternately using various flyer materials.

The invention provides a novel HOM interference theory based gravity instrument. The instrument comprises an entangled source (1), a delayer (2), a first beam splitter (3), a stress sensor (4), a prism (5) to be dropped, a reference prism (6), a second beam splitter (7), a first detector (8), a second detector (9), a coincidence measurement logic calculator (10), an atomic block (11) and a controller; when in use, the delayer (2) is adjusted to delay to enable destructive interference between the idle light and signal light flowing through the initial position, then the prism (5) to be dropped freely falls down to the end position, the free falling time is recorded, the delayer (2) is adjusted to delay again to enable destructive interference between the idle light and the signal light flowing through the end position, and finally the gravity acceleration can be obtained through the controller according to the difference between two delay, and the difference between the initial time and the end time. According to the instrument, the HOM interference theory is utilized to achieve the high precision measurement of the gravity accelerator; the instrument can be widely applied to the fields of metering, surveying and mapping, physical geography, ocean exploration and space science.

The invention relates to a method for measuring the distance of celestial bodies. The method comprises the following steps of setting angle measuring devices for measuring angles of the celestial bodies, selecting a first measuring point and a second measuring point on the same meridian on the surface of the earth, wherein the first measuring point and the second measuring point are respectively provided with the first angle measuring device and the second angle measuring device, and the first measuring point and the second measuring point are separated with a certain latitude; aiming at the same celestial body with the two measuring points, recording measuring angles, and computing angle difference of the two measuring points (the positions of a level point and a vertical point of the celestial body on the Earth take the centre of the earth as a base point, form a diagonal line with the celestial body, and form a triangle having three straight lines and the total degree of three internal angles of 180 DEG, the angle of the centre of the Earth is utilized for computing an radiation angle of the celestial body, and the condition that the angle of the centre of the earth is measurable is utilized for solving the difficult problem that the angle of the celestial body is immeasurable); subtracting latitude distance of the two measuring points from the angle distance of the two measuring points to obtain the radiation angle of the celestial body; and taking the radius of the earth as a radix, extrapolating that the angle distance per one second equals to 1,309,778,457 kilometers, and at last dividing the distance by the radiation angle of the celestial body to obtain the distance from a measured star to the earth's core. The invention is beneficial to the development needs of space science.