39 results about "Orbital speed" patented technology

A tractor configuration includes a mainframe structure, a control station having a means of controlling the tractor, an undercarriage system having one left side and one right side track assembly, a wheel mechanism containing one or more wheels located forward of the track assemblies, a power train for forcing both track assemblies to travel at the same or different speeds, a controller responsible for exerting force to transfer vertical load back and forth between the front portion of the track assemblies and the wheel mechanism and controlling the amount of weight carried by the wheel mechanism. The controller causes or allows the wheel or wheels of the wheel mechanism to follow the tractor's curved path caused by track speed difference.

A system for determining the directional properties of surface waves or internal waves of a fluid medium includes a sonar system having a plurality of transducers for generating respective, separate acoustic beams and receiving echoes from one or more range cells located substantially within the beams; and a computer program for determining the directional properties associated with the surface waves or internal waves from the received echoes, wherein the computer program determines along-beam velocities along the separate acoustic beams and combines the along-beam velocities to form an equivalent orbital velocity vector. The system is mounted on or in a sub surface buoy that can move or rotate during measurement and includes a motion sensor measuring six degrees of freedom to account for horizontal velocity and vertical displacement in the subsurface buoy mounted sonar system.

The invention relates to a precise measuring method of an earth gravity field, in particular to a satellite gravity inversion method based on an inter-satellite velocity interpolation principle; an inter-satellite velocity interpolation observation equation is established by leading high-precision inter-satellite velocity into a satellite-satellite link component of the relative orbital velocity vector of double satellites, so as to precisely and quickly invert the earth gravity field; the method has high satellite gravity inversion precision, so that the physical meaning of the satellite observation equation is clear, the gravity satellite system sensitivity analysis is easy, the exploration of gravity field signals in medium and short wave is favorable, and the requirement on computer performance is low; and an inter-satellite velocity interpolation method is an effective method for resolving the earth gravity field with high precision and high spatial solution.

Disclosed is a high altitude space launcher system for transferring payloads from surface to orbit at a significantly lower cost than conventional rockets. It comprises a aerostat lifted one stage light gas gun operating in stratosphere that shoots rocket assisted projectiles containing payload at near orbital velocities to a low angle trajectory. Alternatively, to launch acceleration sensitive payloads such as astronauts the light gas gun is replaced with a muzzle loaded conventional gun that shoots a single stage rocket at a much lower velocity. The system is mostly static structure, attached to a tether-elevator that moors it to land or a ship and provided it with electricity and lifts the projectiles to the gun.

A method of measuring and displaying track-type tractor performance in real time calculates both a measure of work performance and a theoretical optimum work performance for a given input state, such as track speed. After estimating soil conditions, the theoretical optimum is estimated using an iterative technique. The optimum and current performance are normalized and displayed using a first bar representing a full range of work performance, a second bar depicting a range of optimum performance for current conditions is presented overlying the first bar, and an indicator line showing the current performance. This allows an operator to adjust speed or load accordingly. A coefficient of traction and a shear modulus adjustment, reflecting soil conditions, are calculated at the tractor during operation and used to offset a table of ideal condition operating points to produce the second bar.

A middle and high layer atmosphere density separation type detector comprises a universal module with a microsatellite platform, and is characterized by further comprising a spherical structural body shell used for simplifying an atmosphere resistance analysis model, an accelerometer, a GPS receiver and an attitude control system, the surface of the special structural body shell is covered with a solar cell, the accelerometer is arranged in the spherical structural body shell, the accelerometer is formed by distributing 4 to 6 static suspension type accelerometers around the axis, the accelerometer is used for measuring the atmosphere resistance, the GPS receiver is arranged in the spherical structural body shell and used for tracking and monitoring the track speed and the position of a microsatellite, the attribute control system is arranged in the spherical structural body shell and used for controlling the attribute of the microsatellite so as to keep the spinning of the satellite stable and ensure the correct directing of a GPS receiver antenna and a data transmission antenna.

An electrically powered launcher is disclosed that can accelerate small payloads to orbital velocities. The invention uses a novel geometry to overcome limitations of other design, and allows full exploitation of existing superconducting materials.

The invention relates to a method for inverting an earth gravity field of a residual inter-star velocity, and the method is characterized in that high-precision residual inter-star velocity observation quantity of a satellite-borne laser interference range finder is introduced into a sight component of a residual track velocity differential vector of a global positioning system (GPS) receiving machine to establish a novel residual inter-star velocity observation equation so as to precisely and rapidly invert the earth gravity field; the precision for calculating the earth gravity field is high, the satellite gravity inversion velocity is fast, requirement on the computer performance is low, the method is sensitive to high-frequency signals in the gravity field, and easiness for analyzing the satellite gravity inversion error is realized; and the residual inter-star velocity method is a key technology for establishing a high-precision and high spatial-resolution global gravity field model.

An electronic control system for a work allows for control of steering despite movement of an implement that may support a load. Control may be based on vehicle position, velocity, acceleration, center of gravity, and heading. A control point is determined despite movement of the load, and may be based upon one or more of roll, yaw, and pitch of the vehicle. The vehicle may be of the type that allows for control only of wheel or track speed and rotational direction. A desired center of gravity is maintained while controlling an error between a desired vehicle trajectory and a determined trajectory in a closed loop manner.

A GPS position calculating apparatus is configured to acquire from navigation data contained in signals transmitted from GPS satellites, orbit information including a position, clock time, orbital speed and altitude of each GPS satellite at a transmission time of each signal from a respective one of the GPS satellites, then calculate a position of each GPS satellite at a reception time of the same signal at a measurement point on the basis of the acquired orbital speed and a time difference between the reception time and the transmission time, further calculate a first angle of the horizon relative to a first line segment connecting the second position of each GPS satellite with a position of the measurement point on the basis of a range of the first line segment and the acquired altitude, subsequently calculate a range of a second line segment connecting the first position of each GPS satellite with the position of the measurement point on the basis of the range of the first line segment, the first angle, and the orbital speed, and finally perform calculation of the position of the measurement point. A GPS position calculating method carried out by the apparatus is also disclosed.

A GPS position calculating apparatus is configured to acquire orbit information from navigation data contained in signals transmitted from GPS satellites, the orbit information including a position, clock time and orbital speed of each GPS satellite at a transmission time of each signal, to calculate a position of each GPS satellite at a reception time of the same signal at a measurement point, from the acquired orbital speed and clock time, to calculate a range of a line segment connecting the calculated position of each GPS satellite with a position of the measurement point using a time difference between the transmission time and the reception time, and to calculate the position of the measurement point using the calculated range of the line segment as a pseudorange. A GPS position calculating method carried out by the apparatus is also disclosed.

The invention relates to a method for guiding the motion of a movable machine part (8) of a numerically controlled or special machine tool on a predetermined trajectory (S) of the machine part (8), wherein the workspace (31) of the machine tool is defined The support points (32) within, wherein the maximum possible orbital impulse () and/or the maximum possible orbital acceleration () and/or the maximum possible orbital velocity (), and the movement of the machine part (8) on the moving orbital (S) at the maximum possible orbital impulse () and/or maximum possible orbital acceleration () and/or maximum possible orbital velocity ( )conduct. Thus, the method provides a simple and inexpensive method of optimal motion guidance of a movable machine part (8) of the numerically controlled machine tool on a predetermined trajectory (S) of motion of the machine part (8).

The invention discloses an aircraft orbit injection control method using space vector matching. The method includes the following steps of initiating state parameters of an aircraft, calculating the root and geocentric radius vector of a current orbit of the aircraft and the rotating angle of the current orbit relative to a standard orbit, obtaining a standard orbit speed vector which a current orbit state should have according to the geocentric radius vector and the rotating angle of the current orbit relative to the standard orbit, calculating the deviation value of the speed vector, the residual flight time DT, the pitching program angel and the yaw program angle according to the standard orbit speed vector and a current actual orbit speed vector, and conducting posture control and shutdown control through the calculated residual flight time DT, pitching program angel and yaw program angle. The invention relates to the technical field of orbit control. The method is high in real-time performance, high in guidance precision and high in orbit adjusting capacity, flight software on the aircraft is simple, and the work requirements for preparing and calculating various elements on the ground are low.

The invention discloses a method for maintaining a regression orbit in a high-precision gravitational field based on monopulse orbit control. The method comprises the steps of constructing high-orderPoincare mapping, solving a multi-objective optimization function of an initial value of the regression orbit, and solving to obtain a first initial value of the regression orbit,performing orbit integration on the first regression orbit initial value to obtain an orbit state quantity,reconstructing the high-order Poincare mapping according to the orbit state quantity, and solving to obtain a nextregression orbit initial value,and determining a monopulse speed increment required by track control according to the speed difference between the track state quantity and the initial value of the next regression track, thereby realizing maintenance of the regression track in the high-precision gravitational field. According to the method, on the basis that the orbit design is used as a nominal value, the orbit speed states in the adjacent regression periods are connected by applying the speed pulse at the ascending node of the equator, so that high-precision orbit control is realized, and the actual sub-satellite point orbit of the satellite deviates from the nominal position by a distance within a threshold range set by a user.

It is an epicyclic gear system for use in speed reducer or overdrive, however using an inner pulley, an external ring and a driving belt or a tire instead of using toothed gears. The system particularity is an inner pulley drivingly coupled to an external ring and the torque transmission between the inner pulley and the external ring is done through a belt or a tire, as either the inner pulley or the external ring has orbital motion.