51 results about "Gliding flight" patented technology

The invention discloses a thermal environment design method of space between control rudders of a hypersonic flight vehicle. The method comprises the steps of on account of a simplified appearance of the hypersonic flight vehicle, adopting a prediction method of aerodynamic heat engineering to conduct a prediction for aerodynamic-heat thermal environment and obtain a prediction result of aerodynamic heat engineering; according to the prediction result of aerodynamic heat engineering, confirming flow pattern changes of a rudder shaft section of a control rudder along a trajectory, and conducting numerical calculation of thermal environment of the flight vehicle on multiple groups of typical trajectories under a condition of different flow patterns according to the trajectory time period of flow pattern changes, then obtaining heat flow distribution of the space between the control rudders of the flight vehicle; choosing a laminar flow state to conduct numerical calculation of thermal environment of the space between the control rudders, and modifying the prediction result of aerodynamic heat engineering according to the calculation result; designing the thermal environment of the space between the control rudders along a trajectory according to the modified result. The thermal environment design method of space between control rudders of a hypersonic flight vehicle resolves the problems that the flow patterns of space between control rudders of a hypersonic gliding flight vehicle are too complex to predict under a ballistic condition, and the thermal environment is so tough that a part of heat-proofing risks are hard to be estimated.

A high-altitude long-endurance airship with a top surface that is highly emissive of infrared radiation and a bottom surface that is highly absorptive of infrared radiation. Movable displacer blankets inside the airship separate the upper and lower portions of the airship. Lifting gas in the airship is warmed by radiation from the earth when the displacer blankets are in their upper position. Lifting gas is cooled by radiation to space when the displacer blankets are in their lower position. The whole airship is a heat engine. By expanding the volume of lifting gas when it is relatively warm and compressing the lifting gas when it is relatively cold, net power output can be recovered in the form of electric power. The overall configuration of the preferred airship is a variable-thickness flying wing. If the whole airship is alternately expanded and compressed, imbalance between its weight and buoyancy allow gliding flight.

The invention relates to an aircraft landing monitoring guiding system. According to the aircraft landing monitoring guiding system, firstly, an ideal landing point, a stern line and a runway finishing line are set on a runway; secondly, a camera (6) is selected and is mounted outside the runway at one side of a transverse line of the runway finishing line, a view center of the third camera (6) aligns a far-end point of an ideal glide path; an optical landing assisting system (5) is mounted outside the runway at a same side as the camera (6); a commander (2) and a monitor (3) are at same side of the runway as the camera (6) and the optical landing assisting system (5); the camera (6) is connected with a control computer (4) and a monitor (3) through signal wires; a whole flight process of an aircraft (1) along the ideal glide path is observed by the commander (2), images of the aircraft (1) during gliding flight are acquired from the monitor (3); high-low and left-right deviation of the aircraft (1) is determined by the commander (2), and a pilot is prompted to land the aircraft (1).

A micro aerial vehicle capable of controlled transitory or sustained gliding flight. The vehicle includes a fuselage. A pair of articulated wings are forward of a center of gravity of the vehicle, the wings being articulated and having trailing edge flaps, and having actuators for controlling the dihedral angles of the wings and the flaps for effective yaw control across the flight envelope. The dihedral angles can be varied symmetrically on both wings to control the aircraft speed independently of the angle of attack and flight-path angle, while an asymmetric dihedral setting can be used to control yaw and the actuators control the dihedral settings of each wing independently. The aircraft lacks a vertical tail or other vertical stabilizer.

The invention discloses a troposphere intermittent gliding flight control method and belongs to the flight control technical field. The troposphere intermittent gliding flight control method is particularly applied to an aircraft to increase flight time or range of the aircraft by reasonably using updrafts in a troposphere region. The method includes the following steps that: step one, heat updraft modeling and judgment are carried out; step two, aircraft modeling is carried out, and a control law when updrafts do not exist is designed; and step three, intermittent gliding flight control is carried out. According to the control method of the invention, atmospheric energy is utilized to perform intermittent gliding flight, and therefore, the flight time and range of the aircraft can be improved, and the control method has important significance for the aircraft to realize long-flight time, long-range and attack patrol operational goals. The control method of the invention can be widely applied to small-sized unmanned aerial vehicles and small-sized cruise missiles, and can effectively improve the combat effectiveness of the unmanned aerial vehicles and cruise missiles.

Characterized in that in a first stage are loaded or produced on board in a mother aircraft at least a product or mixed of products to act on forest fires, pests or atmospheric phenomena; in a second stage the said product is stored in a glider container with gliding flight ability and equipped with a precision guidance system; in a third stage the glider container is dropped from the mother aircraft and guided towards the release point of the load; in a fourth stage the glider container releases of its interior the load of product on the release point, and in a fifth stage the glider container is recovered for a following reusing.

A propulsion module configured to launch a craft into space including a recoverable module and a non-recovered part, which is secured to the recoverable module at launch. The recoverable module includes a propulsive system to launch the craft, systems for command and control of the propulsive system, a subsonic flight propulsion motor, airfoils for the subsonic flight, a landing gear, and a braking parachute. The recoverable module is installed in a lower position of the craft when the craft is in the launch position. The non-recovered part includes at least one tank to feed the propulsive system. The recoverable module and the non-recovered part are configured to be separated when the propulsion module reaches a given altitude, and the recoverable module is capable of landing in a controlled fashion after a coasting flight, for example for a return to the launch site.

An auxiliary propeller folding mechanism of a model airplane glider comprises a steering engine and an auxiliary propeller, wherein the steering engine comprises an oscillating arm, the auxiliary propeller is connected with an output shaft of a power element, the power element is connected with a machine body through a parallel four-connection-bar mechanism, the steering engine is fixed in the machine body, and the oscillating arm is connected with any one connection bar in the parallel four-connection-bar mechanism. A position sensor is arranged at the tail end of the stroke of the power element, the first connection bar or the second connection bar and is connected with the control end of a controller or the steering engine through a signal line. The steering engine drives the parallel four-connection-bar mechanism, and the auxiliary propeller and the power element can contract in the machine body or protrude out of the machine body. In the powerless gliding flight process, the auxiliary propeller and the power element contract in the machine body, and accordingly the aerodynamic performance of the machine body can be remarkably improved, resistance can be reduced and the glider hang time can be prolonged.

The invention discloses a hypersonic aircraft airborne trajectory planning method and device, an aircraft and a medium. A reentry gliding section motion equation of a hypersonic aircraft is used as a training environment of a trajectory planning problem of the hypersonic aircraft; constructing a state space, a strategy action space, an environment dynamic transfer function, a reward function and a discount factor of the trajectory planning problem; and training the neural network of the trajectory planning problem by using a deep reinforcement learning algorithm. And inputting the state space obtained in the flight process into the trained Actor network to obtain a strategy action space, so that the hypersonic aircraft flies to a predetermined target area according to the strategy action space to complete the flight task of reentering the gliding section. According to the method, airborne real-time trajectory planning of the hypersonic flight vehicle in the gliding section is realized by using an artificial intelligence algorithm, the task adaptability of the flight vehicle is improved, and the problem that the trajectory of the hypersonic deformation flight vehicle like gliding flight is difficult to plan on line is effectively solved.

This aircraft comprises both thrusters (7, 16, 17) for conventional aircraft flight through the atmosphere and for high-altitude use as a rocket. It is divided into a payload compartment (8) and a compartment (13) chiefly containing the rocket motor propellants. It comprises a long, low-backsweep transverse wing (3) near the rear to provide better wing lift in the dense strata of the atmosphere and allow the aircraft to climb to high altitudes at subsonic speed before the rocket motors are used. Return to earth is in gliding flight or flight controlled in the same way as a conventional aircraft.

The invention discloses a four-stage solid carrier rocket trajectory optimization method based on a particle swarm algorithm, and relates to a trajectory optimization control method of a four-stage solid commercial carrier rocket platform. The method aims at a four-stage solid rocket trajectory flight section. The maximum flight attack angle of the first-stage power flight section, the pitching program angular rate of the second-stage power flight section, the gliding flight time of the rocket after second-stage depletion, the pitching program angular rate of the third-stage power flight section, the pitching program angular rate of the fourth-stage gliding flight section, the pitching program angular rate of the fourth-stage power flight section and the pitching program angular rate of the fourth-stage power flight section are changed into the maximum flight attack angle; the flight time of the four-stage sliding section serves as a trajectory design variable needing to be optimized, global optimization is conducted on the seven variables according to a particle swarm optimization algorithm, and global optimal parameters which can meet the injection conditions of the four-stage solid rocket and have the minimum performance index are sought. After initial values and variation ranges of the seven variables are selected, global optimization is carried out on the seven variables by applying a particle swarm optimization algorithm, and global optimal parameters which can meet four-stage solid rocket orbit injection conditions and have minimum performance indexes are sought.

A rocket-powered spacecraft having a wing which has hinged aft portions which can be elevated about a hinge line. Tail booms extend rearwardly from the outer ends of the aft wing portions, and rudders are mounted at the aft ends of the booms. Each tail boom supports a horizontal tail with an elevon at its trailing edge. In normal flight, the wing aft portions are not elevated, and the wing has a normal airfoil shape. During atmosphere reentry, the wing aft portions are steeply elevated to provide a stable high-drag altitude for the spaceship for speed reduction at low thermal and structural loading. After reentry, the aft wing is returned to an unelevated position which enables gliding flight to a horizontal-runway landing.

The invention belongs to the technical field of helicopter application, and particularly relates to a design method of a helicopter exhaust pipe shaping spoiler aiming at the problems that in a gliding flight state, when wake flow acts on a vertical fin, the vertical tail pneumatic environment is unstable, oscillating transverse force is generated, and tail screening occurs. The shaping spoiler structure meets the requirement that the leeward area of the exhaust pipe is in smooth transition to the machine body or the leeward face is reduced. The method specifically comprises the following steps: S1, establishing a second-order unsteady display flow field solving model and carrying out gliding state simulation, S2, carrying out mechanism analysis, and determining the reason of tail screening, S3, determining a reference state of design scheme evaluation, S4, forming a design scheme, and S5, carrying out design scheme verification. By means of the design method, the effects of stabilizing wake flow and restraining tail screening can be achieved.

The invention discloses a fixed wing and flapping wing composite aircraft. The aircraft is characterized in that a whole aircraft skin adopts a flexible material, wings with an inner wing structure and an outer wing structure are designed, in the takeoff process, the inner section wings provide stable lifting force, and the outer section wings generate all the thrust and partial lifting force through large flapping and chord direction twisting; and in the flight process, gliding flight is mainly used, the lifting force is provided through the inner section wings and the outer section wings, flapping of the outer wings with the lower flapping frequency is adopted for assistance, and the flight stability of the aircraft is improved through tail wings. According to the fixed wing and flappingwing composite aircraft, the flight attitude of the aircraft is adjusted by changing the center of gravity of a suspension object below the airfoil; and in the emergency state, the outer section flapping wings can stop flapping and are locked in the designated positions and are parallel to the fixed wings to form a fixed wing layout and realize gliding flight. The aircraft has higher stability, safety and comfort, and can improve the lifting force characteristic of the whole miniature aircraft.

The present application discloses a method and system for forced landing of a fixed-wing UAV. The method includes: obtaining the current airspeed of the fixed-wing UAV when the fixed-wing UAV enters the forced landing procedure; Adjust the current airspeed to the gliding flight airspeed; obtain the ground terrain information corresponding to the current airspace of the fixed-wing UAV; select the forced landing area to perform the forced landing and glide mission according to the ground terrain information; during the execution of the forced landing and glide mission, collect the area information of the forced landing area , regional ground wetness and softness information, and regional terrain trend information; according to the regional area information, regional ground wetness and softness information, and regional topographic trend information, a landing grounding plan for the fixed-wing UAV is generated; Landing and grounding scheme, control the fixed-wing UAV to land and ground. The application improves the safety of the fixed-wing unmanned aerial vehicle when it is forced to land in the forced landing area, and reduces the damage rate of the fixed-wing unmanned aerial vehicle when it is forced to land.

The invention discloses a multi-flapping-wing micro air vehicle designed by imitating wild goose array formation and gliding flight. The multi-flapping-wing micro air vehicle is in a six-flapping-wing layout form and is composed of a vehicle body and three pairs of flapping wings, the three pairs of flapping wings are in bilateral symmetry and are arranged on the two sides of the vehicle body in a stepped mode, and wing tips of each pair of front flapping wings are flush with the half-span positions of the adjacent rear flapping wings. Wild goose array formation and gliding flight are simulated, and when the aircraft flies at high altitude and high speed, the flapping wing attack angle is fixed for gliding flight; and when high lift force and high thrust are needed, the flapping wings flap obliquely in the same phase to generate lift force and thrust. According to the multi-flapping-wing micro air vehicle imitating wild goose array formation and gliding flight design, the interference effect of wingtip vortexes generated by the front flapping wings on the rear flapping wings is effectively utilized, and the problems that a traditional flapping-wing air vehicle is insufficient in lifting force and low in aerodynamic efficiency are solved.