80 results about "Delta" patented technology

The invention provides a multipurpose pneumatic type ejection airborne landing flight training device, and an ejection method is utilized to eject training personnel to a high altitude, the training personnel utilize the airborne landing flight training devices equipped for the training personnel to perform airborne landing or air the training personnel flight training, or the trainers without any device are ejected to safety protection equipment in a fixed-point mode to perform parachuting basic training. The training device comprises a base seat, a pneumatic ejection device, a saddle-shaped ejection seat, an elevation angle adjuster and safe landing protection facilities, wherein the elevation angle adjuster and the ejection device are arranged on the base seat, the ejection seat is arranged on the ejection device, and the safe landing protection facilities are arranged on a landing point. The airborne landing flight training device comprises a parachute, a delta wing aircraft, a wing outfit aircraft, a fixed wing aircraft or other single pawn airborne landing flight devices, when the airborne landing flight training device is used, geographical environment limitation does not exist, parachuting, delta wing flight, wing outfit flight, fixed flight or pneumatic parachute flight motions can be popularized quickly, and meanwhile, the research and development of the sports equipment can further be driven.

A UAS may use camera-captured ground feature data to iteratively estimate pose change through a Kalman filter. To avoid excessive drift, the UAS may periodically perform a reset by publishing delta pose and covariance as an edge in a global pose graph, by zeroing out the delta pose and covariance. To further improve global pose estimation, two UASs may share range information and associated pose graph information, thereby providing an additional constraint for each UAS to use in its pose graph optimization.

The invention discloses a moon-earth three-pulse return orbit speed increment analysis method, which comprises the following steps: A, obtaining a normal unit vector h1 of a lunar orbit plane, a normal unit vector h2 of a lunar escape orbit plane and positions rA, rB and rC for applying three pulses by taking a moon center as an original point; B, obtaining a conical surface S1 with the lunar escape orbit aiming v infinity out as the axis, wherein the half cone angle of the conical surface S1 is eta; C, enabling the plane where v infinity out and h1 are located to serve as the datum plane, setting the rotating angle sigma of rC around the straight line where v infinity out is located, and determining rC and a lunar escape orbit plane; D, obtaining a conical surface S2 with the straight line where rC is located as the axis, wherein the half cone angle of the conical surface S2 is alpha; E, obtaining the included angle beta between h1 and v infinity out and the different-plane differencexi between the lunar orbit and the lunar escape orbit; F, solving the sizes delta v1, delta v2 and delta v3 of the three pulses; G, solving a total speed increment delta v; and H, changing the independent variable influencing the delta v to obtain a change rule of the delta v. According to the method, the spatial geometrical relationship is utilized, and preliminary approximate analysis can be rapidly, effectively, visually and simply carried out on the speed increment required by the three-pulse maneuvering process.

The invention discloses a spacecraft formation flight method on a small-thrust suspension orbit. Mapping of orbital parameters (hz, k, alpha, delta E, delta r) of a bounded suspension orbit to formation parameters (delta T, delta omega) is established, wherein the following formula is met: f:(hz, k, alpha, delta E, delta r) to (delta T, delta omega); formation conditions of three kinds of formation types are determined; and then suspension orbits of main satellites and salve satellites meeting all formation conditions are searched in a two-dimensional(delta T, delta omega) plane to realize bounded formation flight of the main satellites and salve satellites. Therefore, three different kinds of bounded relative orbits are obtained and the orbit precision is high. The method is suitable forlong-period large-scale formation flight; and implementation of a near-surface mission or a deep-space exploration formation mission is ensured.

A Fiber-fed Pulsed Plasma Thruster (FPPT) will enable enhanced low Earth orbit, cis-lunar, and deep space missions for small satellites. FPPT technology utilizes an electric motor to feed PTFE fiber to its discharge region, enabling high PPT propellant throughput and variable exposed fuel area. An innovative, parallel ceramic capacitor bank dramatically lowers system specific mass. FPPT minimizes range safety concerns by the use of non-pressurized, non-toxic, inert propellant and construction materials. Estimates are that a 1U (10 cm×10 cm×10 cm, or 1 liter) volume FPPT thruster package may provide more than 10,000 N-s total impulse and a delta-V of 1.4 km / s delta-V for an 8 kg CubeSat.