7 results about "Celestial navigation" patented technology

The invention discloses a low-altitude high-speed flight manned flying saucer, and relates to the technical field of aviation aircrafts, the low-altitude high-speed flight manned flying saucer comprises a saucer-shaped body, a power device and an undercarriage, the saucer-shaped body is composed of a central bearing ball cabin and a peripheral reinforcing ring coaxially sleeved outside the central bearing ball cabin; the central bearing ball cabin is divided into a celestial navigation and communication cabin, a panoramic cockpit and an environment control and life support system cabin from top to bottom; the inner cabin section of the peripheral reinforcing ring forms a passenger cabin; the bearing strength and the space utilization rate of the machine body are effectively improved through the composite structure of the central spherical cabin and the peripheral reinforcing ring; due to the integrated design of the annular duct and the vector engine, the aerodynamic efficiency and the control flexibility in the vertical take-off and landing and high-speed flight states are remarkably improved; an independent environment control system ensures the safety and comfort of passengers in high-altitude flight; the overall layout gives consideration to functionality and maintenance convenience, and has high practical value.

Techniques are disclosed for improving daylight performance of a star tracker. A region of interest (ROI) within a field of view of sky is obtained. The region of interest is divided into sub-ROIs. Sub-ROIs including a candidate celestial object are identified. An angular velocity of each candidate celestial object is determined. The known celestial object is a candidate celestial object identified as having a angular velocity, during a time period, that is within a range of angular velocities about a known angular velocity associated with the known celestial object.

A system for selecting one or more resident space objects from a number of resident space objects for targeting includes a database for storing properties of the resident space objects and one or more processors. The processors are configured to determine, for each resident space object, a utility metric representing a navigation utility of the resident space object. Determining the utility metric includes determining a projected position of the resident space object by projecting a position of the resident space object over time based on ephemeris data and covariance data associated with the resident space object, and computing the utility metric based at least in part on the projected position. The processors rank the resident space objects according to their utility metrics and select the one or more resident space objects for targeting based on the ranking.

The invention relates to a star sensor star measurement probability evaluation method, and belongs to the technical field of airborne celestial navigation. The method comprises the following steps: generating a screening star library according to a limit star magnitude design value of a star sensor; calculating the optical axis direction of the star sensor according to the star measurement time, place and attitude; screening out an observable star set again from the screening star library according to the star sensor design parameters and the optical axis direction; setting satellite measurement time, place and attitude sequences, performing continuous satellite measurement analogue simulation, and recording the number of satellites in an observable satellite set; and counting the satellite measurement probability and the satellite measurement distribution condition, and evaluating the availability of the design parameters. According to the method, the preliminary analogue simulation verification of the airborne star sensor can be realized, a reference is provided for the parameter iterative design of the star sensor, and too much trial and error investment in the aspect of real objects in the earlier stage of the design is avoided.

The application discloses an aerial calibration method of an aviation celestial navigation device, combines a flight route in a flight task of an airplane, integrates aerial calibration work of a celestial navigation system into the flight route, and synchronously carries out tracking and positioning work of a star tracker and a navigation processor in the celestial navigation device after the airplane enters a calibration task area; according to a task route plan, the airplane enters each side of a route path once, and the celestial navigation system completes aerial calibration once under the condition that a heading determination meets a requirement; after completing calibration of the last side, a calibration result is output, and the aerial calibration is completed. The application shifts the environment of calibration work of the celestial navigation device from the ground to the top of the clouds in the air, and synchronously carries out the calibration work with a task, avoids important influence of change of the clouds in the air on a calibration success rate, improves the calibration success rate, saves a large amount of input of manpower and material resources, and can be popularized to the fields of spaceflight and navigation, and has a good guiding role for application, popularization and development of the celestial navigation device.

The application discloses a star sensor, which comprises a detection lens, a star sensor body frame, a rotating mechanism, a circuit board, a heat-conducting pad, a heating film and a PEEK shell; the detection lens is installed on the star sensor body frame; the rotating mechanism is connected with the star sensor body frame to make the star sensor body frame rotate axially; the circuit board is arranged on the star sensor body frame; the heat-conducting pad is arranged between the circuit board and the star sensor body frame to transfer the heat generated by the chip of the circuit board to the star sensor body frame; the outer side of the circuit board is sequentially provided with the heating film and the PEEK shell; the heating film can heat the circuit board; and the PEEK shell can isolate the radiant heat of the high-temperature environment. The application further discloses an astronomical navigation system. The application can adapt to high and low temperatures, strong radiation and other harsh environments, and ensures the reliability of the equipment.

The invention relates to a laboratory simulation satellite measurement navigation device and method, and belongs to the technical field of airborne celestial navigation. The device comprises a target simulation servo table, a star target simulator and an acquisition processing computer, the star target simulator is mounted above the target simulation servo table, the target simulation servo table is provided with a load platform double-degree-of-freedom rotating shaft and a star target simulation single-degree-of-freedom rotating shaft, and the acquisition processing computer is cross-linked with the target simulation servo table. The method comprises the following steps: compiling a servo table transposition program according to requirements; calculating a simulated star vector under each transposition, and storing the simulated star vector into a simulated star library; the target simulation servo table rotates in place, and a simulation star calculation vector under the current transposition is calculated; the simulated star is observed, and the actual measurement direction of the simulated star is calculated; calculating combined navigation measurement; the combined navigation calculation of the current transposition is completed; and traversing all translocations to finish the laboratory simulation satellite measurement navigation task. According to the method, the limitation of weather factors on satellite measurement navigation tests is broken through, most satellite measurement navigation debugging and testing requirements in the research and development process can be met, the product research and development speed is increased, and the research and development period is shortened.