31 results about "Orbital flight" patented technology

A turbojet is combined with a co-axially integrated rotary rocket to form a propulsion system called a Rotary Turbo Rocket that can function as a turbojet, as an afterburning turbojet, as an Air Turbo Rocket, or as a rotary rocket. The Rotary Turbo Rocket can operate in any of these propulsion modes singularly, or in any combination of these propulsion modes, and can transition continuously or abruptly between operating modes. The Rotary Turbo Rocket can span the zero to orbital flight velocity speed range and/or operate continuously as it transitions from atmospheric to space flight by transitioning between operating modes.

The invention discloses a super-orbit speed flight technical scheme assisted by aerodynamic force, and belongs to the technical field of aircraft design. According to the basic principle of the technical scheme, aerodynamic lift force pointing to the earth center and generated by the aircraft with the high lift-drag ratio serves as supplement of centripetal force, super-orbital speed flight is achieved without centrifugal motion, meanwhile, thrust is used for offsetting aerodynamic resistance, and continuous flight at the super-orbital speed is maintained. The method specifically comprises thefollowing steps: firstly, establishing a flight dynamics model of a super-orbital-velocity aircraft based on a high-lift-drag-ratio aircraft; secondly, based on equal-height and equal-speed assumptions, calculating a super-orbit flight speed which can be reached by the aircraft; then establishing a burnup calculation method of the super-orbital-velocity aircraft; and finally, solving orbit parameters of the optimal fuel consumption flight scheme by adopting an optimization method. The ultra-high-speed flight technology has important application potential in the fields of global fast arrival,spaceflight emergency rescue and the like.

A satellite data processing method, apparatus, and a satellite backup subsystem belongs to the technical field of satellites. This method is applied to the satellite backup subsystem. The method comprises: receiving a data task, wherein the data task comprises data backup or data restoration; splitting the data task into a plurality of single-orbit tasks; and executing respective single-orbit task in each orbital flight.

The invention belongs to the field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle safety test system and method. The system comprises a central controller, a flight track, a safety connection assembly and an unmanned aerial vehicle. The safety connecting assembly is connected with the unmanned aerial vehicle and the flight track; the flight track is in an activity area limiting the unmanned aerial vehicle; the central controller generates aircraft test parameters; the unmanned aerial vehicle performs a flight test according to the aircraft test parameters to obtain flight test data; and the central controller generates a test result according to the flight test data. According to the scheme, an aircraft safety test track and a closed safety test site are constructed. And it can be ensured that the aircraft completes various key performance tests in an absolutely safe environment. The test safety is improved, the unmanned aerial vehicle cannot fall and be damaged when being out of control, the safety of the unmanned aerial vehicle for testing is guaranteed while the test effect is not hindered, and the potential safety hazard of the test is reduced.

The invention provides a self-adaptive drag-free control method based on a set value identification algorithm, and belongs to the technical field of aerospace, control science and engineering. The method comprises the steps of processing measurement information inside and outside a measurement range of a gravity gradiometer to obtain a set value type measurement value of the gravity gradiometer for residual acceleration, wherein the measurement information is the residual acceleration of a gravity gradient satellite in the flight direction of an orbit; establishing an identification algorithmto estimate the resistance gain coefficient of the gravity gradient satellite along the orbital flight direction according to the obtained set value type measurement value of the gravity gradiometer to the residual acceleration; and according to the estimated resistance gain coefficient, constructing a self-adaptive controller of the gravity gradient satellite along the flight direction of the orbit. According to the invention, drag-free control under saturation constraint measurement can be realized.

The invention provides a detection sensor for spatial atmospheric surface density and a manufacturing method thereof. The detection sensor can realize direct detection of the atmospheric surface density of a spatial fixed point; the resonant sensor is employed for detection of spatial atmospheric surface density, realizes direct measurement of atmospheric surface density via atmospheric substancesadhering onto the surface of a probe of the sensor and better serves research on the resistance of atmospheric surface density to spacecrafts; and the resonant sensor is low in power consumption, canmeet the networking requirements of micro-nano satellite constellations, and realizes spatial large-scale distributed measurement of atmospheric surface density and real-time measurement of orbit atmosphere simultaneously in virtue of the networking micro-nano satellite constellations. According to the invention, the resonant sensor is small in size, light in weight and capable of monitoring atmospheric surface density at different positions and different angles in virtue of a sensor array mode. A data processing unit of the invention can be separated from a gas acquisition module, so distributed measurement can be realized, and the atmospheric surface density of the spacecraft during orbital flight can be accurately determined.

The invention provides a commercial spaceflight and civil aviation operation cooperation system based on digital twinning. The system comprises a physical commercial spaceflight and civil aviation scene module, a virtual commercial spaceflight and civil aviation scene module, a commercial spaceflight and civil aviation twinning big data module and a commercial sub-orbit flight and civil aviation operation cooperation module. The system can be applied to a civil aviation air traffic control department, and aims at verifying the feasibility of a decision-making scheme for a flight to avoid a sub-orbital debris danger area and a cooperation mode of commercial space flight and civil aviation operation by using a digital twin-based commercial space flight and civil aviation operation cooperation system. And under the condition of dynamic change of the sub-orbital debris danger area, designing a civil aircraft avoidance decision scheme in real time, and re-planning an air route which conforms to an air traffic control rule, so that the safety of the civil aviation airspace is improved.

The invention relates to a carrier rocket orbit parameter reconstruction method based on iterative guidance, and belongs to the field of carrier rocket guidance control. The method comprises the following steps of 1, collecting carrier rocket state information; 2, calculating the consumption of a propellant entering a target orbit according to the state information, if the consumption of the propellant is less than the available amount, normally flying to an original target orbit, and if the consumption of the propellant is greater than the available amount, performing orbit parameter reconstruction; 3, searching parameters of a reconstructed orbit on line, and taking the reconstructed orbit obtained by searching as a new target orbit; and 4, controlling a carrier rocket to fly towards the new target orbit. The method is based on iterative guidance, the principle is simple, engineering implementation is convenient, whether the carrier rocket can enter the target orbit or not can be judged according to the state information, orbit parameters are searched for and reconstructed on line when necessary, the carrier rocket has the autonomous orbit reconstruction capacity, economic losses are avoided or reduced under the fault condition, and the launch task performance capacity is improved.

An ultra-low orbit satellite all-electric propulsion orbit maintenance system comprises a GNSS receiver, an atmospheric density measurement unit, a satellite service management unit and an electric propulsion system. The GNSS receiver provides a state vector of the ultra-low orbit satellite in an earth-fixed coordinate system. And the atmospheric density detection unit obtains atmospheric density data and inverts the orbit height of the ultra-low orbit satellite. And the electric propulsion system completes distribution of thrust parameters and generation of a thrust according to an orbit maintenance control law transmitted by the satellite service management unit. The satellite service management unit comprehensively determines orbit information of an ultra-low orbit satellite, generates a satellite space trajectory error after processing, further determines an orbit maintenance control law through an orbit maintenance algorithm according to the satellite space trajectory error, and sends the orbit maintenance control law to the electric propulsion system to complete orbit maintenance control. According to the invention, the problem of rapid attenuation of the satellite in the ultra-low orbit flight is solved, stable flight of the satellite in the ultra-low orbit is realized, and the operation duration of the ultra-low orbit satellite is greatly prolonged.

The invention relates to a ground test method for simultaneously examining inertial navigation and simulated flight. The ground test method comprises the following steps: determining simulated flight initial parameters; acquiring initial navigation parameters of a test site at an initial moment; simulating orbit flight through a thrust curve; according to actual measurement of data output by a master-slave inertial measurement combination in real time, initial speed, position and attitude information of a test point as initial values, and gyro data and table data measured by master-slave inertial navigation equipment in real time, enabling a master inertial measurement unit and a slave inertial measurement unit to respectively use a set of navigation to carry out inertial navigation calculation; and enabling the first set of navigation to obtain a master inertial measurement integrated navigation result, and the second set of navigation to obtain a slave inertial measurement integrated navigation result for checking the navigation precision of the master-slave inertial measurement unit; therefore, three sets of navigation results are obtained, and aircraft thrust curve flight simulation completed by the third set of navigation is used for flight control. Thrust curve simulation is adopted, a real track can be simulated, real inertial measurement unit characteristics are reflected, and a ground test is more real and reliable.

The invention relates to a vehicle, in particular to a rail ultralow-altitude aerial vehicle small in building difficulty and low in pollution. The rail ultralow-altitude aerial vehicle is a full electric driven rail aerial vehicle, and therefore energy is wide in source and clean. By means of the rail aerial vehicle, the problems of long charging time and short travel of common electric vehicles are eliminated; according to the rail ultralow-altitude aerial vehicle, rails need to be built, compared with land vehicles, the influence of the terrain on the rail ultralow-altitude aerial vehicle is small, and therefore the rail ultralow-altitude aerial vehicle is wide in coverage; and damage of rail building of the rail ultralow-altitude aerial vehicle to the environment is quite small, the rails of the rail ultralow-altitude aerial vehicle and highways or railways can be built together, and therefore cost is reduced, and the space utilization rate is increased.