685 results about "Tailplane" patented technology

The invention discloses a bionic robot with walking, jumping and taking-off functions and a movement method, and belongs to the technical field of robots. The robot comprises a control system, a flapping wing mechanism and two leg mechanisms. Each leg mechanism comprises a driving device I, an execution connecting rod mechanism and a buffer foot part, the buffer foot part is connected with the execution connecting rod mechanism, and the execution connecting rod mechanism is driven by the driving device I; the flapping wing mechanism comprises a driving device II, a transmission mechanism, wings and an empennage; the execution link mechanism is connected with the transmission mechanism, the wings and the empennage are respectively connected with the transmission mechanism, the transmission mechanism is driven by the driving device II, the control system is used for controlling the driving device I and the driving device II, and the motion modes comprise walking, jumping and flying. The multi-mode bird-simulating robot has a multi-mode bird-simulating motion function, can autonomously realize mode switching from land motion to air flight, and remarkably improves the motion performance of the robot.

The invention belongs to the technical field of airplane structure design, and discloses a horizontal tail wing beam connecting structure, an airplane and an assembling method, and the horizontal tail wing beam connecting structure comprises a central rib plate, an upper T-shaped connector, a lower T-shaped connector, a left connecting plate, a right connecting plate and an outer side connecting plate. The upper T-shaped joint comprises a lower edge strip, a first left edge strip and a first right edge strip, the lower T-shaped joint comprises an upper edge strip, a second left edge strip and a second right edge strip, the central rib plate is arranged between the left beam and the right beam, and the left connecting plate, the right connecting plate and the outer side connecting plate are combined for use, so that the bearing capacity of a left beam web plate and a right beam web plate is improved; the first left edge strip and the first right edge strip can increase the contact area between the upper T-shaped connector and the left wing and the contact area between the upper T-shaped connector and the right wing, the second left edge strip and the second right edge strip can increase the contact area between the lower T-shaped connector and the left wing and the contact area between the lower T-shaped connector and the right wing, the connecting strength of the left beam and the right beam in the vertical direction is improved, and the lower edge strip, the upper edge strip and the central rib plate are matched with one another. And the connection strength of the left beam and the right beam in the horizontal direction is improved.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a passive tilting wing unmanned aerial vehicle which comprises a vehicle body, wings, a locking mechanism, a vertical empennage, a thrust power assembly, a posture regulation and control power assembly and a controller, and the thrust power assembly, the posture regulation and control power assembly and the locking mechanism are all electrically connected with the controller. The locking mechanism is responsible for locking angles of the wings in a vertical take-off and landing state and a cruising flight state, the thrust power assembly is arranged on the wings, the wings are rotationally connected with the fuselage, and the thrust power assembly is responsible for generating lift force for vertical take-off and landing and thrust force for cruising flight. The device can also be used for providing underwater thrust during water surface navigation; the passive tilting wing unmanned aerial vehicle can solve the technical problems that an existing tilting wing aircraft is heavy in tilting mechanism, poor in loading capacity, complex in aerodynamic characteristic in the tilting process, large in robustness control difficulty, poor in stability and the like.

The invention belongs to the technical field of electric heating deicing, and particularly relates to a surface heating electric heating film and a preparation method thereof. Comprising an outer surface insulating layer, a heating layer, a power supply electrode and an inner surface insulating layer, the heating layer is prepared from a carbon-based conductor composite polymeric material in a printing or coating mode, and the carbon-based conductor composite polymeric material is formed by mixing polyimide resin and carbon fibers (or one or more of graphene, carbon nanotubes and the like). The surface heating electric heating film provided by the invention has the characteristics of simple and reliable structure, light weight and surface heating performance, can be applied to ice prevention and removal operation of parts such as aircraft wings, empennages, propellers and the like, and has relatively high practical application value.

The invention provides an aircraft overall optimization design method and device and electronic equipment, and relates to the technical field of aircraft overall design. The method comprises the following steps: calculating the weight of each part of an aircraft based on aircraft design parameters, and calculating the maximum takeoff weight and the gravity center of the whole aircraft by integrating the weight and the gravity center of each part; based on airplane design parameters and the gravity center of the whole machine, parametric modeling is conducted on all the components, pneumatic calculation is conducted, and a lift-drag analysis result is output; establishing an engine performance model according to the engine type and the engine performance parameters, and generating a power curve and an oil consumption curve based on the model; calculating a plurality of aircraft performance indexes; and performing multi-objective optimization by taking the shape parameters of the wing empennage as design variables and taking a plurality of aircraft performance indexes as optimization objectives, and generating a Pareto optimal solution set containing an optimal value combination of the shape parameters of the wing empennage. The defects of subject conflict and long research and development period caused by the adoption of a serial design process in the existing aircraft design are overcome.

The invention discloses a large seaplane integrated with a distributed electric propulsion technology and a propulsion method, and relates to the technical field of seaplane. Comprising a fuselage, a left wing and a right wing are arranged on the two sides of the fuselage respectively, and a V-shaped hull is arranged at the lower end of the fuselage; and a T-shaped empennage is arranged at the tail part of the fuselage. Through the synergistic effect of the design of the V-shaped ship body and the distributed propulsion system, the whole ship body makes contact with the water surface to provide sufficient buoyancy at the low speed, only the main sliding face makes contact with the ship body to form an air layer at the high speed, and the air film drag reduction effect of a propeller at the bottom of the ship body is matched, so that the water resistance is reduced by 35%-50%, and the draft is reduced by 40%-60% along with speed increase; the problems that a traditional seaplane is large in water resistance and difficult to leave water are effectively solved, meanwhile, the left buoy and the right buoy are in linkage with the attitude control system, wave disturbance can be counteracted in real time, the transverse inclination angle is controlled within 1 degree, the wave resistance is improved to be capable of coping with waves with the height of 1.5 m, and the defects that a traditional seaplane is poor in wave resistance and has strict requirements for taking-off and landing water areas are overcome.

The application aims to provide a single-motor driven multi-mode ornithopter simulating the flight posture of insects and birds, comprising a fuselage, a foldable wing mechanism, a flapping wing and ground walking mechanism, and a steering tail wing mechanism; the flapping wing and ground walking mechanism is a spatial five-link mechanism; in the flight state, the motor outputs power, the five-link mechanism drives the wing to complete the flapping action; in the ground walking state, the electromagnet connection hole is not electrified, the connecting rod driving wheel and the electromagnet right-angle connecting shaft are disconnected, the wing is in the folded state, and the rotation output of the motor is the rotation movement of the driving connecting rod driving wheel; the application integrates the connecting rod and the wheel, realizes the function of single-motor driving two modes, simplifies the mechanism complexity, reduces the manufacturing difficulty, lightens the ornithopter weight, and has good obstacle crossing ability and can cross narrow space.

The invention discloses a tilt rotor aircraft depending on aerodynamic force, and relates to the technical field of aircrafts. The four-axis unmanned aerial vehicle comprises a fuselage, wing assemblies, four-axis unmanned aerial vehicle modules and empennage assemblies. The wing assembly comprises a left wing, a right wing and a wing cross beam which are all provided with ailerons; the four-axis unmanned aerial vehicle module is I-shaped, is hinged to a wing cross beam through a bearing, and can tilt bidirectionally; the empennage assembly comprises a tail support, a horizontal electric variable pitch propeller, a horizontal empennage with a control surface and a vertical empennage. The four-axis unmanned aerial vehicle module serves as a tilting unit, and the structure is simplified; attitude control is realized by virtue of aerodynamic difference, and the efficiency is improved; the tail horizontal electric variable-pitch propeller realizes rapid pitching adjustment; vertical take-off and landing, low-altitude maneuvering and high-speed cruising capabilities are integrated, the application scene is wide, and safe forced landing can be achieved when faults occur.

An electric vertical take-off and landing aircraft comprises a fuselage and a tilt wing. The tilt wing is tiltable relative to the fuselage in a range of tilt wing angles. Control surfaces are arranged at the tilt wings. The aircraft comprises a horizontal stabilizer with an elevator, in particular a stabilator, a vertical stabilizer with a rudder, in particular a fully movable stabilizer, at least one electric engine for powering main propellers arranged at the tilt wing and at least one software control device. The control device is configured to control at least the control surfaces , the main propellers and the tilt wing angle during hover and transition between hover and cruise flight.

A vertical take-off and landing aircraft includes: a fuselage and 2N tilting rotors. Both sides of the fuselage are provided with a wing symmetrically, a tail of the fuselage is provided with an empennage, and ruddervators are provided at the empennage. 2N tilting rotors are symmetrically provided at both sides of the fuselage, and a part of the 2N tilting rotors are provided on the empennage. N is a natural number greater than or equal to 2; in a vertical take-off and landing state, projections of propellers of the 2N tilting rotors on a horizontal plane are centrally symmetrical about point B, point B and a center of gravity point G of the vertical take-off and landing aircraft are both provided in a symmetry plane of the fuselage.

The invention discloses a turbojet power logistics unmanned aerial vehicle based on a fixed wing structure and a control method. The unmanned aerial vehicle comprises a carbon tube fuselage, cork wood wings, a full-motion horizontal empennage, double vertical empennages, a nose fairing, a storage bin, a turbojet engine, an undercarriage, a flight control system and an emergency parachute. According to the turbojet power logistics unmanned aerial vehicle based on the fixed wing structure and the control method, the fixed wing structure and the turbojet engine are organically combined, short-distance take-off within 50 meters can be achieved, compared with a traditional propeller type fixed wing unmanned aerial vehicle, the take-off distance is shortened by 40% or above, the cruising speed can reach 80 km / h-120 km / h, the unmanned aerial vehicle can be matched with a standard material box of 200 mm * 200 mm * 400 mm, and the unmanned aerial vehicle is suitable for large-scale popularization and application. The flight control system supports two modes of manual remote control and automatic driving, and is equipped with an emergency parachute, so that safe parachute recovery of the unmanned aerial vehicle in an emergency state is realized, and the problem that a traditional unmanned aerial vehicle has obvious limitation when meeting emergency material delivery requirements is effectively solved.

The invention discloses an anti-explosion method and system for a vertical fixed-wing unmanned aerial vehicle, the unmanned aerial vehicle and a medium, and the anti-explosion method comprises the steps: monitoring the operation conditions of motors of all rotor assemblies in real time, and determining a fault motor when an abnormality occurs; performing first stability control on other motors without faults, the control surface of the fixed wing and the control surface of the empennage according to the fault motor; acquiring the current flight height of the unmanned aerial vehicle, and performing landing control on the unmanned aerial vehicle according to the current flight height until the unmanned aerial vehicle lands to the ground; and performing fault detection processing on the unmanned aerial vehicle, and generating a fault processing flow record. The fault motor can be accurately identified and positioned in the landing process of the unmanned aerial vehicle, and corresponding emergency measures are taken according to the position relation of the fault motor, so that the unmanned aerial vehicle can maintain stability in the air and stably land on the ground, the phenomenon of explosion of the unmanned aerial vehicle is effectively avoided, and the safety of the unmanned aerial vehicle is improved. And the landing safety and stability of the unmanned aerial vehicle are ensured.

The invention provides a vertical empennage control surface calibration device and method, and relates to the technical field of vertical empennage control surface calibration, the device comprises a first clamping mechanism, the two ends of the first clamping mechanism are a first clamping end and a first operation end respectively, and the first clamping end is used for clamping a movable wing surface of a vertical empennage; the two ends of the second clamping mechanism are a second clamping end and a second operating end respectively, and the second clamping end is used for clamping the fixed wing surface of the vertical tail wing; the pointer is connected to one side of the first operation end through a sliding adjusting mechanism; the dial plate is connected to one side of the second operation end, angle scales are arranged on the surface of the side, close to the pointer, of the dial plate, and the pointer is matched with the angle scales; the problem that in the prior art, a special vertical empennage control surface calibration tool and technology are lacked is solved.

The empennage device is used for being arranged at the tail of a cargo box and comprises an upper flow guide plate, a lower flow guide plate, a lower flow guide plate and a tail wing device, and the upper flow guide plate is used for being arranged at the top of a box door in an openable and closable mode; one end of the first connecting rod is hinged to the side, close to the box door, of the upper flow guide plate when the upper flow guide plate is unfolded, the other end of the first connecting rod is used for being hinged to the box door, one end of the first supporting rod is hinged to the side, away from the box door, of the upper flow guide plate when the upper flow guide plate is unfolded, and the other end of the first supporting rod is used for being hinged to the box door. The upper flow guide plate is installed on the container door and has a flow disturbing effect in an unfolded state, and by guiding airflow and reducing turbulent flow and vortex at the tail of the container, a vehicle is more stable when running at a high speed and encountering crosswind, and the running safety is improved; the upper flow guide plate is arranged at the top of the container door in an openable and closable mode through the first connecting rod and the first supporting rod; the container door is opened during driving and closed during loading and unloading, the occupied space of the vehicle is reduced, and opening of the container door can be prevented from being hindered.

1. Name of the design product: ship tail wing. 2. Use of the design product: used for reducing the lift generated at the tail of the ship when sailing, thereby stabilizing the ship body. 3. Design points of the design product: in shape. 4. Picture or photo best indicating the design points: perspective view 1.

The invention relates to the technical field of aircrafts, in particular to a telescopic wing type aircraft with a self-adaptive duct and a control method, and the telescopic wing type aircraft comprises a rack, a lifting force assembly, a power assembly and an adjusting assembly; the lifting force assembly comprises a telescopic wing mounted at the top end of the rack and an empennage mounted at the tail end of the rack; the power assembly comprises self-adaptive duct sets installed on the two sides of the rack, and the self-adaptive duct sets are located on the two sides of the bottom ends of the telescopic wings and used for preventing airflow from disturbing the telescopic wings. When the unmanned aerial vehicle ascends and descends vertically, power airflow can be sprayed out vertically and downwards almost and cannot be blocked or turned back by wings above, thrust is utilized to the maximum degree to overcome gravity, the thrust-weight ratio and the hovering efficiency are improved, and attitude control is more direct and accurate; in the cruising state, the positions of the self-adaptive duct sets prevent airflow from directly impacting the surfaces of the wings, smooth airflow on the surfaces of the wings is prevented from being damaged, vortexes are prevented from being generated, the power efficiency is improved, and thrust loss caused by airflow impact is avoided.

1. Name of the designed product: tail wing. 2. Use of the designed product: tail wing of car, for decoration. 3. Design points of the designed product: in shape. 4. Picture or photo showing the design points: perspective view 2.

The invention discloses a multi-layer combined unmanned aerial vehicle and a control method, and relates to the field of high-altitude long-endurance unmanned aerial vehicles, the multi-layer combined unmanned aerial vehicle comprises a plurality of sub-aircrafts, each sub-aircraft comprises a fuselage, an empennage, wings, wingtips and protrusions, the wingtips are arranged at the ends, away from the fuselage, of the left and right wings, and the wingtips can be in butt joint with the wingtips of the other aircraft; protrusions are arranged on the upper surface and the lower surface of each wing, the end faces of the protrusions can be in butt joint with the end faces of the protrusions of another airplane, and the protrusions can be used for containing an aircraft undercarriage at the same time. Through aggregation and recombination of a plurality of small unmanned aerial vehicles, a multi-layer combined unmanned aerial vehicle with a high aspect ratio is formed, and the combined unmanned aerial vehicle can effectively overcome the defect that the rigidity of wings of a traditional unmanned aerial vehicle with a high aspect ratio is insufficient and can carry an oversized radar conformal antenna with long wave bands such as meter waves and the like. And long-time air-hang detection of high-value targets such as stealth aircrafts and the like is realized.

The invention discloses a deformable empennage applied to a bionic aircraft, and relates to the technical field of bionic flying robots. Through efficient cooperation of five-degree-of-freedom motion of the empennage and deformation motion of the wings, the maneuverability and adaptability of the aircraft are remarkably improved. The bionic aircraft comprises a motor, a fuselage, a deformation wing, an empennage and an empennage deformation driving mechanism. And flexible switching among a horizontal tail state, a positive V tail state and an inverted V tail state can be realized. When the state is switched to the positive V tail state, parasitic resistance can be effectively reduced, wingtip vortex interference is reduced, and the aerodynamic efficiency of the cruising stage is improved; when the inverted V-tail state is switched, the influence of wing wake flow can be avoided, the aerodynamic stability is obviously enhanced under the working condition of a large angle of attack, and the stall risk is effectively inhibited; and when the horizontal tail state is switched, aerodynamic lift force distribution in the low-speed stage can be optimized, and the aerodynamic response of take-off and landing control is improved. The flexible switching of the empennage among the three states provides better pneumatic suitability for the aircraft in different flight stages and task scenes.

The present application relates to the field of aircraft technology, and discloses a vertical take-off and landing aircraft, which comprises a wing-body integrated lifting body fuselage, a front wing and a rear wing, and a stabilizing tail, and is composed of a two-degree-of-freedom propulsion Y3 configuration formed by the front wing, the rear wing and the fuselage, and is composed of two fixed lifting propellers installed below the front wing and in the front part of the gravity center and a two-degree-of-freedom tilting thruster installed at the tail to solve the problem that the existing Y3 configuration cannot simultaneously consider the low-speed hovering mode and the cruising mode; the tandem-lifting body aerodynamic configuration is combined with the new Y3 power configuration to solve the problem that the aircraft is difficult to balance the contradiction between high aerodynamic efficiency and large cargo capacity; and finally, the side aerodynamic optimization of the fuselage, the up-down staggered design of the front and rear wing tip ailerons, and the ring wing 21 design are adopted to solve the problem that the existing configuration is prone to generate large aerodynamic resistance.

The utility model discloses an unmanned aerial vehicle with tilting rotors. The unmanned aerial vehicle comprises a fuselage and wings symmetrically arranged on the left side and the right side of the fuselage. A tail supporting rod parallel to the axis of the fuselage is correspondingly mounted in the middle of each wing; the head of the tail supporting rod is hinged to a supporting foot which is arranged outside the tail supporting rod. A front steering engine used for driving the supporting feet to tilt is installed in an inner cavity of the head of the tail supporting rod. The supporting leg is provided with a supporting end and a mounting end which are oppositely arranged, and a front rotor wing is mounted at the mounting end; a rear rotor wing is arranged at the middle rear part of the tail support rod; an empennage is arranged at the tail part of the tail support rod; in the vertical take-off and landing stage, the supporting ends and the empennage form four supporting legs for supporting the fuselage; in the cruising stage, the axial direction of the supporting feet is parallel to the axial direction of the corresponding tail supporting rods. Through the cooperation of the front steering engine, the supporting legs, the front rotor wings and the empennage, the tilting function and the undercarriage function are combined into a whole, an independent undercarriage system is omitted, and therefore the structure is simplified, the weight is reduced, the resistance is reduced, and the space utilization rate is increased.

The present application belongs to the technical field of unmanned sailboat, and particularly relates to a rigid wing sail self-balancing turning sail system of unmanned sailboat, which comprises a main sail skeleton, a main sail shell, a turning sail control box, a tail wing connecting rod assembly, a tail wing main body, a steering engine and a tail wing rope driving assembly. The driving end of the steering engine is controlled to move, and the tail wing main body is driven to rotate through the tail wing rope driving assembly, so as to adjust the deflection angle of the tail wing main body relative to the main sail as a whole, adjust the included angle (attack angle) between the main sail as a whole and the wind, and make the main sail as a whole reach a predetermined attack angle and keep a stable balance state. The mast of the main sail as a whole can rotate freely around the unmanned sailboat body, realizes the rotation decoupling of the rigid wing sail and the ship body, the bow shaking movement of the unmanned sailboat does not affect the attack angle of the rigid wing sail, the tail wing can be regarded as the air rudder of the main sail by adjusting the attack angle of the main sail through the tail wing, and the method makes the main sail attack angle adjustment more efficient and rapid, and reduces the adjustment power consumption.

This utility model discloses an airship control system based on an execution drive encoder board, comprising a flight control computer, an execution drive encoder board, a logic control circuit, and output ports. The flight control computer can output six control signals (PWM0-PWM5). The execution drive encoder board integrates six 2-to-1 analog switches, with the switch inputs connected to the six PWM signals output from the flight control computer and the execution drive board, respectively. The logic control circuit consists of OR gates, XOR gates, and AND gates, with its inputs connected to the control terminals of each analog switch, receiving control authority feedback signals from the execution drive board and control status feedback signals from the flight control computer. The output ports output the six PWM signals selected by the analog switches, respectively driving the servos corresponding to the horizontal tail, vertical tail, duct tilt, duct lock, engine throttle, and engine shutdown. This solution addresses the problems of insufficient control signal switching flexibility, incomplete control logic, and poor system scalability in existing airship control systems.

An aircraft (10) has four or more rotors (20) including a pair of first rotors (20a) and a pair of second rotors (20b, 20c), the pair of first rotors (20a) being disposed bilaterally symmetrically with a center at a position overlapping a center axis (A) of a fuselage (12) when viewed from above at a position forward of a front wing (14), the pair of second rotors (20b, 20c) being disposed bilaterally symmetrically with a center at a position overlapping the center axis (A) of the fuselage (12) when viewed from above at a position between the front wing (14) and a tail wing (16). The distance (Dy, Dz) separating the fuselage (12) and the second rotors (20b, 20c) in a width direction is longer than the distance (Dx) separating the fuselage (12) and the first rotors (20a) in the width direction.

The environment-friendly burner for the cracking furnace comprises a burner box body assembly, an empennage burner block, an external spray gun and an incandescent light, the external spray gun comprises a plurality of branch air guns, the top of the empennage burner block is provided with an ignition inclined face, and ignition holes are evenly distributed in the circumferential direction of the ignition inclined face. Guiding tail wings are further evenly distributed in the circumferential direction of the ignition inclined face, the two adjacent guiding tail wings and the ignition inclined face form a combustion guiding groove, and the branch air guns correspond to the combustion guiding grooves in a one-to-one mode. All the spray guns except the incandescent light are arranged on the outer side of the burner block; part of spray holes in the spray gun on the outer side of the burner block are used for spraying to the burner block, so that the burning root flame is effectively stabilized, and meanwhile, part of flue gas is brought in during high-speed spraying; the guide empennage is arranged on the ignition slope of the burner block and can guide the injection direction of fuel gas, flame interference between the guide empennage and adjacent spray guns is avoided, and peak temperature increase caused by flame superposition is reduced. NOx generation is reduced through the triple action.

The utility model discloses a gliding unmanned aerial vehicle with folding wings. A canard-type middle-single-wing aerodynamic layout is adopted; the full-moving front wing can be folded downwards by 90 degrees; the two main wings are an outer main wing and an inner main wing, the outer main wing can be folded downwards by 180 degrees at the joint of the outer main wing and the inner main wing, and the lower surfaces of the wings are opposite; the inner main wing can be folded upwards by 90 degrees at the joint of the inner main wing and the main wing reinforcing rib; main wing reinforcing ribs on two sides of the fuselage are fixed with main wing rotating shafts and can rotate around the main wing rotating shafts, so that the main wing reinforcing ribs are switched between a horizontal state and a vertical state; when the two sections of main wings are folded and placed in parallel to the fuselage, the front edges of the folded main wings are below; the vertical empennage can be retracted into the fuselage. Compared with a conventional layout, the canard layout has better maneuverability, the canard wings and the main wings generate lift force, and the folded wings have a large aspect ratio after being unfolded, so that the large lift-drag ratio is favorably provided, and gliding flight of the unmanned aerial vehicle is facilitated.

This application discloses a tail wing device, a control method for the tail wing device, and a vehicle. The tail wing device includes a wing body, a base, and a drive mechanism. One end of the base is rotatably connected to the wing body, and the other end of the base is adapted to be connected to a trunk lid. The base has a receiving cavity. The drive mechanism is located within the receiving cavity and is connected to the wing body, wherein the drive mechanism is used to drive the wing body to rotate. Using the technical solution of this application, the angle of the wing body can be flexibly adjusted to ensure effective improvement in vehicle stability during driving.

A tail assembly for a rotorcraft having a fuselage. The tail assembly includes a stabilizer having an aft spar and a forward spar. An aft joint couples the aft spar to the fuselage and defines a pitch axis such that the aft joint allows the stabilizer to pivot about the pitch axis. A forward joint couples the forward spar to the fuselage. The forward joint has an axial stiffness configured to tailor a chordwise pivot mode of the stabilizer and a bending stiffness configured to tailor a beamwise bending mode of the stabilizer. The chordwise pivot mode of the stabilizer is decoupled from the beamwise bending mode of the stabilizer.

The application belongs to the field of aircraft design, and particularly relates to a military transport aircraft. The military transport aircraft comprises a fuselage (1), a ring-shaped wing (2), an engine (3), a vertical tail (4), a canard (5), a landing gear (6) and a rear cargo door (7). The ring-shaped wing (2) extends upwards and upwards from the middle floor of the fuselage, and is connected with the vertical tail (4). The fuselage is surrounded by the ring-shaped wing (2) by 360 degrees. The engine nozzle is shielded from below and from the side by the ring-shaped wing (2). The main landing gear strut is connected to the wing and can be placed in the wing after being retracted. The application improves the cruising efficiency of the military transport aircraft, reduces the structural weight, improves the airport and take-off and landing adaptability, effectively shields and protects the fuselage and the engine, and comprehensively enhances the use efficiency of the transport aircraft.

The forest fire extinguishing bomb comprises an empennage assembly and a full-standby bomb body, the empennage assembly is installed at the tail of the full-standby bomb body and comprises an empennage, turbine generators are installed on the left side and the right side of the top of the empennage, and the output ends of the turbine generators are connected with a radio proximity control mechanism. An isolation insurance ignition device is mounted in the empennage; a hanging ring is mounted at the top of the empennage; the full-standby bomb body comprises a bomb body, the bomb body is filled with a fire extinguishing agent, a center powder pipe is arranged in the center of the bomb body, and the top of the center powder pipe is connected with the isolation safety ignition device. The stability, the accuracy and the directionality of the fire extinguishing bomb can be ensured in the air-drop process, the fire extinguishing bomb is exploded at a fixed height above a fire source, and a polymer gel fire extinguishing agent is impacted at a high speed to cover the fire source, so that a better fire extinguishing effect is achieved, and the environment cannot be damaged.