6 results about "Orbital speed" patented technology

The invention belongs to the technical field of ocean surface flow velocity remote sensing measurement, and particularly relates to a Luoga No.2 SAR (Synthetic Aperture Radar) flow velocity correction method based on Bragg orbit velocity, which comprises the following steps of: verifying the physical correctness of an orbit velocity mechanism relative to a phase velocity mechanism; under a DopRIM framework, a physically consistent sea wave error correction model is established; calibrating parameters of the sea wave error correction model; applying the calibrated sea wave error correction model to along-orbit interference SAR observation data of the Luoma No. 2 satellite, and calculating the radial surface flow velocity and sea wave error of each resolution unit; comparing an output result with a matched reference truth value to evaluate the effectiveness of the sea wave error correction model; comparing the sea wave error correction model with a KaDOP model, and respectively counting and analyzing simulated sea wave errors under different methods; the sea wave error simulation result is visually displayed, and the improvement effect is quantitatively evaluated through in-situ observation data and a KaDOP simulation result.

The application discloses a high-precision time offset autonomous calculation method and system based on satellite speed v and gravity acceleration g. By establishing a closed correlation between the gravity field strength and the orbital speed, the traditional multi-parameter relativistic time correction model is simplified to a closed-form calculation depending on only two in-orbit measurable physical quantities, without the need for input of orbital radius, universal gravitational constant, earth mass, external ephemeris, etc. The application has outstanding originality, simple calculation, strong autonomy and reliable precision, can realize a daily cumulative time error of less than 1 ns, is suitable for low-orbit satellites, navigation satellites, constellation systems and various high-reliability time service scenarios, has a wide application range and high industrial value, and can significantly improve the autonomous time service capability of a spacecraft and the stability of a time system.

The present application belongs to the technical field of remote sensing measurement of ocean surface current velocity, and in particular to a Lujia-2 SAR current velocity correction method based on Bragg orbital velocity, comprising the following steps: verifying the physical correctness of the orbital velocity mechanism relative to the phase velocity mechanism; and under the DopRIM framework, establishing a physically consistent sea wave error correction model; calibrating the parameters of the sea wave error correction model; applying the calibrated sea wave error correction model to Lujia-2 satellite along-track interferometric SAR observation data to calculate the radial surface current velocity and sea wave error of each resolution unit; comparing the output results with the matched reference true value to evaluate the effectiveness of the sea wave error correction model; comparing the sea wave error correction model with the KaDOP model, respectively, to statistically analyze the simulated sea wave error under different methods; visualizing the sea wave error simulation results, and quantitatively evaluating the improvement effect through in-situ observation data and KaDOP simulation results.

A method is provided for efficient orbital launch trajectories. A payload (e.g., satellite) is launched as high as a first radius with respect to the center of the Earth. The method decreases the payload altitude in response to a gravitational pull of the Earth, and ultimately the payload attains a stable orbit around the Earth at a second radius with respect to the center of the Earth. If the first radius is twice the second radius, the payload acquires a gravitational first potential energy at the first radius, and in the stable orbit the payload has a second (potential and kinetic) energy equal to the gravitational first potential energy, with the second kinetic energy being equal to the energy required to maintain a stable orbital velocity. Advantageously, the stable orbit can potentially be at any orbital inclination angle in the range between 0 and 360 degrees.

A passive landing system for decelerating a payload delivered from orbit or at orbital velocity onto a non-atmospheric celestial body, including a catcher assembly positioned to intercept incoming payloads at orbital speeds, and a deceleration system mechanically coupled to the catcher assembly and extending along a sloped terrain, wherein the system decelerates the payload by exchanging momentum between the descending payload and the extended deceleration system, without the use of propulsion. A landing system for oversized payloads on a non-atmospheric celestial body, which can be used in combination with the passive landing system, including a structure configured to house and secure large-volume cargo during descent and deceleration, a surface interaction mechanism configured to establish frictional contact with regolith of the celestial body, and a dynamic deployment system that controls the extent and duration of surface contact during descent, wherein the landing system decelerates primarily by converting kinetic energy into heat and mechanical resistance through friction with the regolith.

The invention discloses an atomic oxygen generation device for ground simulation of an ultra-low orbit atmospheric environment. The atomic oxygen generation device comprises an atomic oxygen generation module, a speed screening module, a neutralization module, a shell and an electronic gun, the atomic oxygen generation module comprises an ionization source device, one side of the shell is connected with the ionization source device through a flange and a matched nut, and pure oxygen forms high-speed oxygen ions in the ionization source device and then is guided into a cavity of the shell; the speed screening module comprises parallel electrode plates arranged in the cavity and an external magnetic field arranged on the outer side of the shell, and the module realizes high-speed oxygen ion screening and directional transmission; the screened high-speed oxygen ions enter a neutralization module on the right side of the cavity, an electron gun is located at an outlet of the cavity, electrons are injected into the neutralization module, and atomic oxygen with the real orbital velocity and neutral state characteristics is formed. The high-speed atomic oxygen generator can generate high-speed atomic oxygen with the orbit equivalent speed of 7800m / s, improves the atomic state retention capability and the flow field stability, and has the characteristics of modularization and low power consumption.