82 results about "Flight space" patented technology

The invention discloses a design method of a cooperative driving aircraft system and the system. Technologies of a manned aircraft and an unmanned aircraft system are combined. Air and ground cooperation driving is constructed. A new technology aircraft system of easy flight and safe flight is provided. Technologies of aerial driving, ground monitoring, air and ground cooperation driving flight, navigation and flight control, data link and navigation monitoring system and the like, and updating and development of a whole industry value chain of a corresponding navigability standard and approval laws and regulations, flight space management laws and regulations, a driver training method, an aircraft design and manufacturing technology, a flight application and business mode and the like are covered. The new aviation technology can be applied to airplanes of commercial transportation, general aviation, military aviation and the like so as to promote development of a new aviation industry. Especially for the airplanes applied to motion of the general aviation, an official business, freight transport and industrial and agricultural usage, an aviation tradition of depending on a professional driver is changed and public flight time in which general public flies a plane is opened.

In the mass spectrometer of the present invention, a flight space is provided before the mass analyzer, and the flight space includes a loop orbit on which ions fly repeatedly. While ions fly on the loop orbit repeatedly, ion selecting electrodes placed on the loop orbit selects object ions having a specific mass to charge ratio in such a manner that, for a limited time period when the object ions are flying through the ion selecting electrodes, an appropriate voltage is applied to the ion selecting electrodes to make them continue to fly on the loop orbit, but otherwise to make or let other ions deflect from the loop orbit. If ions having various mass to charge ratios are introduced in the loop orbit almost at the same time, the object ions having the same mass to charge ratio continue to fly on the loop orbit in a band, but ions having mass to charge ratios different from that are separated from the object ions while flying on the loop orbit repeatedly. Even if the difference in the mass to charge ratio is small, the separation becomes large when the number of turns of the flight becomes large. After such a separation is adequately achieved, the ion selecting electrodes can select the object ions with high selectivity, or at high mass resolution. By adding dissociating means, fragment ions originated only from the selected object ions can be analyzed, which enables the identification and structural analysis of the sample at high accuracy.

The invention discloses an air vehicle with folding arms. The air vehicle comprises a vehicle body (1); the air vehicle further comprises the multiple folding arms (2); each folding arm (2) comprises a first arm (21) connected with the vehicle body (1), a second arm (22) and a rotating mechanism (23) allowing the second arm (22) to rotate relative to the first arm (21); and each first arm (21) is provided with a rotor wing (3), and each second arm (22) is provided with a rotor wing (3). The air vehicle has the beneficial effects that the structure of the first arms and the second arms which can be rotationally connected is adopted in the air vehicle, and when the air vehicle is used, the external dimension of the air vehicle can be changed, so that the air vehicle can be suitable for different flight spaces, and the application area of the air vehicle is further wider.

The present invention relates to a time of flight mass spectrometer (TOFMS) having a flight space in which ions to be analyzed repeatedly fly in a loop orbit or reciprocal path. In an example of the present invention, the TOFMS carries out two rounds of measurement for one sample under two conditions differing in the effective flight distance of the ions to create two flight time spectrums. The data processor of the TOFMS compares the central points of the peaks in the two spectrums to identify peaks that have resulted from the same kind of ion (Step S3). If any peak is found to be unidentifiable (“No” in Step S4), the data processor examines the similarity of the peak shapes (e.g. half-value width) to identify peaks that have resulted from the same kind of ion (Step S5). After the correspondence of all the peaks have been determined, the data processor calculates the approximate mass to charge ratio of each ion from the difference in flight time (Step S6) and determines the number of turns of the ion based on the approximation (Step S7). Finally, it calculates the exact mass to charge ratio, using the number of turns and the flight time (Step S8). Thus, even if the sample contains many components and the spectrums accordingly have many peaks mixed together, the TOFMS can identify all the peaks.

In a time of flight mass spectrometer (TOFMS) having a flight space in which ions fly in a loop orbit formed by a plurality of electric sector fields, the present invention provides a simple structure that creates a spiral path by deflecting the ions in the axial direction of the electric fields at every turn of the ions. In a mode of the present invention, the TOFMS has cylindrical electrodes 11 and 12 for creating electric sector fields E1 and E2, between which a parallel pair of planer magnetic poles 15a and 15b are provided. The planer magnetic poles 15a and 15b create a deflecting magnetic field B1 for shifting the ions in the axial direction (Y-direction) of the electric sector fields. The ions experience a Lorenz force once every turn when they pass through the deflecting magnetic field B1. This construction uses only one pair of magnetic poles facing each other across the ion path P to deflect every ion irrespective of its number of turns. There is no need to provide one deflector for each turn of the ions, as in the case of conventional TOFMSs.

A autonomous navigation system of a navigational satellite based on X radial pulse satellite includes: an X radial detector, an atomic clock group on the satellite, a planet of our solar system parameter database, an X radial pulsar module and a characteristic parameter database, a computer on the satellite, a strap-down inertial navigation system SINS and an autonomous navigation algorithm module library; in the autonomous navigation method, the X radial photons radiated from the pulsar are used as the input of the external information; the pulse arrival time TOA and the angular position information are obtained; data is processed through a autonomous navigation filter; and the navigational parameters such as the position, the speed, the time and the pose of the navigational satellite; the navigational telegraph text and the control command are generated independently, and the independent running of the navigational satellite is realized. The present invention has the advantages of providing a long time and a high degree of accuracy autonomous navigation, and providing the fault-tolerance capacity of the autonomous navigation information processing. The autonomous navigation system is also be adequate for the high degree of accuracy autonomous navigation of the near earth orbit, the deep space, the interplanetary flight space vehicle, the a celestial body lander without thickset atmosphere and the surface peripatetic machine.