284 results about "Fuselage" patented technology

The utility model discloses a water area propeller and water area movable equipment. The water propeller is used for connecting a water carrier to propel the water carrier to move in the water. The water area propeller comprises a body and an operation device. A propelling device used for outputting propelling force for propelling the water area carrier to move is arranged at the end of the machine body. The operation device is rotationally connected to the end, away from the propelling device, of the fuselage body through a transverse connecting shaft, can be folded or unfolded with the fuselage body and is used for being operated by a user to control the water area propeller to operate. The operation device is provided with a first locking unit, the machine body is provided with a second locking unit, and when the operation device and the machine body are in a folded state, the first locking unit and the second locking unit lock the operation device and the machine body at the position between the transverse connecting shaft and the propelling device. And a suspension beam capable of loading the fuselage main body is formed between a locking position of the operating device between the first locking unit and the second locking unit and a connecting position of the operating device on the transverse connecting shaft.

The utility model discloses a water area propeller and water area movable equipment. The water area propeller comprises a machine body, an operation device and a locking module. A propelling device used for outputting propelling force for propelling the water area carrier to move is arranged at the end of the machine body. The operation device is rotationally connected to the end, away from the propelling device, of the fuselage body through a transverse connecting shaft, can be folded or unfolded with the fuselage body and is used for being operated by a user to control the water area propeller to operate. The locking module comprises a first locking unit and a second locking unit, and the first locking unit and the second locking unit are arranged in the operation device and the machine body respectively. The locking module locks the operation device and the machine body main body at the position between the transverse connecting shaft and the propelling device through the insertion force between the first locking unit and the second locking unit, and the operation device forms a cantilever beam capable of loading the machine body main body between the transverse connecting shaft and the locking module.

A device to control movement of fluid that is emitted from an aircraft engine that is mounted to a wing of an aircraft. The device includes a support member positioned on an exterior of the aircraft and having an elongated shape with a first end connected to the wing and a second end connected to the fuselage. The support member has a first sectional size. A deflector shield is mounted to the support member and positioned on the exterior of the aircraft. The deflector shield has a larger sectional size than the support member. The deflector shield has an outer edge that extends around the support member and is positioned radially outward from the support member.

The utility model belongs to the technical field of agricultural unmanned aerial vehicles, and particularly relates to a bionic agricultural pesticide spraying aircraft. Comprising a fuselage and n supporting legs evenly distributed around the fuselage, n is an even number larger than or equal to 4, and each supporting leg is provided with a set of propellers driven by a motor; a plurality of independent pesticide bins are arranged in the machine body, an outlet of each pesticide bin is connected with a mixing box in the machine body through a water path, a metering pump is connected into the water path, a stirring device is arranged in the mixing box, a plurality of nozzles are evenly distributed on the periphery of the machine body, an outlet pipeline of the mixing box is divided into branches with the same number as the nozzles, and the branches are connected with the nozzles in a one-to-one mode. A booster pump is mounted on the branch; depth cameras are distributed outside the fuselage and used for acquiring environment images, and the aircraft controls a flight path according to the environment images; the unmanned aerial vehicle adopts a partitioned pesticide bin and octopus bionic eight-rotor design, and has high pesticide mixing capacity and stable flight control performance.

An aerial and preferably marine vehicle intended to operate in its principal mode near the surface of water or land employing the Wing-in-Ground Effect (WIG) and capable to take-off and land vertically (VTOL) by means of thrust vectoring, which vehicle has a wing arranged at the lowermost part of the fuselage, propulsion units comprising four rotatable pylons extending transversely in pairs on both sides of the upper part of the fuselage, four elongated nacelles mounted on the outer tips of said pylons, which nacelles contain electric motors (E) and provided with propellers at their extremities, so that the rotation of the pylons results in turning the nacelles and thrust of propellers from substantially vertical, ensuring take-off and landing, to substantially horizontal providing a flight mode, retractable hydroskis for emergency landing on water, while said propulsion units and said wing are spaced apart vertically and horizontally and do not overlap.

The invention discloses a guide wall for airplane ground test run, which comprises a U-shaped barrier part enclosing an airplane, the barrier part comprises a side guide wall corresponding to the side of the airplane and a rear guide wall corresponding to the tail of the airplane, the side guide wall comprises a windward side and a leeward side, and the leeward side is connected with a fixing frame. The fixing frame is connected with a ground anchor bolt to support the side flow guide wall, and the rear flow guide wall is fixedly connected with ground concrete; the length of the side flow guide wall exceeds the position of the nose during the test run of the airplane, and an air inlet channel is arranged at the side flow guide wall corresponding to the side wing during the test run of the airplane, penetrates through the side flow guide wall and supplements airflow to the engine close to the side wing of the air inlet channel; by arranging the air inlet channel, air flow is introduced from the side face of the aircraft directly facing the engines, the problem that the test is affected by insufficient air suction of the double engines due to the fact that the side face flow guide wall is far longer than the fuselage is solved, the internal and external pressure difference of the flow guide wall is reduced, and test run of the aircraft is facilitated.

The electric hydrofoil watercraft according to the invention provides detachable and hermetic electrical connection via contact pins for cables providing power to underwater propulsion means between above-water platform and one side of the mast and between the fuselage of the hydrofoil and the other side of the mast.

Truss-braced wing aircraft engine mounting and associated systems are disclosed. An example aircraft includes a fuselage including a central structural section, a wing extending from the fuselage, a truss extending from the central structural section and coupled to the wing, a pylon coupled to the central structural section, and an engine coupled to the pylon, wherein the pylon is positioned at an angle substantially 45 degrees from a horizontal plane and a vertical plane.

A connecting rod coupling device for attaching a component to an aircraft fuselage and / or stiffening the fuselage has a first coupler, and a second coupler couplable to the first coupler. The first coupler has an elongate body with a first channel on a lateral surface along a first longitudinal axis. The second coupler has a hollow-cylindrical portion, which, on an inner face along a second longitudinal axis, has a second channel complementing the first channel. The hollow-cylindrical portion has a radial cutout through which the elongate body is radially insertable into the second channel from outside the hollow-cylindrical portion. The second coupler has a closure body, which closes the radial cutout, and can be positioned removably in the cutout to complete the second channel on a radially internal face. The second coupler also has an element, pushable onto the hollow-cylindrical portion to secure the closure body on the hollow-cylindrical portion.

A vertical take-off and landing aircraft includes a fuselage, at least one propulsion system, at least four lift propellers and at least two fixed wing planes. The fixed wing planes which are located behind the most forward lift propellers are located above the lift propellers. The lift propellers are distributed on either side of at least one of the fixed wing planes and on either side of the fuselage such that the lift propellers are longitudinally separated by at least the magnitude of the chord of the fixed wing plane located therebetween, and are laterally separated by at least the width of the fuselage located therebetween. At least one of the fixed wing planes has a variable span and the aircraft includes a control system for varying this span in flight.

The invention belongs to the technical field of aircraft design, and discloses an amphibious aircraft water surface sliding speed reduction, turning and resistance reduction system and method.The system comprises two water baffles, and the two water baffles are arranged on the two sides of a hull structure below an aircraft waterline respectively and located between an aircraft belly fault step and a tail fault step; when the opening angle is small, the two water baffles form an air cavity at the rear portion through the ventilation effect to form the drag reduction effect, when the opening angle is large, the two water baffles reduce the exciting force caused by vortex falling, and the two water baffles are embedded in a groove of the rear fuselage when being forbidden to conform to the overall shape of the aircraft. The water baffles are innovatively arranged on the two sides of the hull structure of the seaplane, resistance or turning torque or a resistance reduction air cavity can be generated by changing the hydrodynamic shape of the seaplane when the seaplane slides on water, and the sliding process of the seaplane is controlled.

The utility model discloses a control surface control mechanism of a V-tail unmanned aerial vehicle, which comprises a pair of control surface main bodies which are arranged in a V shape, and the included angle between the two control surface main bodies is 90 degrees; the main shaft is vertically arranged on the end faces of the ends, close to each other, of the control surface main bodies; and the control assembly is used for controlling the pair of main shafts to rotate synchronously. The utility model has the following advantages and effects: after being assembled, the control mechanism is completely hidden in the fuselage of the aircraft, so that the flight resistance is not additionally increased; differential motion and homodromous motion of the two control surface main bodies are respectively driven by the same motor, so that the deflection consistency of the control surface main bodies on the two sides can be ensured.

The wide-speed-range tailless variable-structure aircraft comprises an aircraft body, the aircraft body comprises an aircraft body-fixed wing fusion body and variable-structure wing rudders, the variable-structure wing rudders are symmetrically arranged on the two sides of the aircraft body-fixed wing fusion body, and a wing body fusion body layout is integrally formed; the fuselage-fixed wing fusion body is connected with the variable-structure wing rudder through a driving mechanism, and the variable-structure wing rudder can deflect in the axial direction of the fuselage; the tail of the fuselage-fixed wing fusion body is provided with a trailing edge rudder, the trailing edge rudder of the fuselage-fixed wing fusion body achieves pitching channel control through same-direction deflection, and under the condition that the channel coupling coefficient is smaller than 1.5, rolling channel control is achieved through differential deflection. The problem that the yaw channel operation stability characteristic is insufficient under the tailless layout condition is solved, and the wide-speed-range operation performance of the aircraft is effectively improved; compared with other variable-structure aircrafts in which additional variables are introduced, the combination of the variable-structure wing rudder and the trailing edge rudder is simple and efficient, and the burden on a control system is small.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a water-land-air triphibian unmanned aerial vehicle which comprises a water-land-air unmanned aerial vehicle body and further comprises a positioning assembly, unmanned aerial vehicle blades are arranged at the top of the water-land-air unmanned aerial vehicle body, an underwater propeller is arranged on the rear side of the bottom of the water-land-air unmanned aerial vehicle body, and propeller blades are arranged on the back face of the underwater propeller. A working box is fixedly connected to the middle of the bottom of the water-land-air unmanned aerial vehicle body, the positioning assembly comprises first supporting springs, the first supporting springs are fixedly connected to the left side and the right side of the bottom in the working box, and a lifting shell is fixedly connected to the top ends of the first supporting springs. When the body of the water-land-air unmanned aerial vehicle makes contact with the water surface, the elastic arc-shaped plates make contact with the water surface and expand outwards, the contact area between the elastic arc-shaped plates and the water surface is increased, the weight of the body is dispersed, the local pressure is remarkably reduced, the unmanned aerial vehicle is prevented from sinking, the expanded elastic connecting plates form a structure similar to a hydrofoil, transverse stability is provided, and the rollover risk caused by waves is effectively resisted.

The invention discloses a multi-mode self-rotating tailstock type vertical take-off and landing aircraft. Multi-mode motion comprises a multi-axis mode, a self-rotating mode and a fixed wing mode. The unmanned aerial vehicle comprises a fuselage, a variable collective pitch structure and four symmetrical wings on the two sides; the wing type of each wing is a symmetrical wing type, the tail end of each wing is a full-moving wing tip, and each wing is provided with a driver; the driver is a propeller driven by a motor; each wing, the driver and each full-motion wingtip can rotate by + / -90 degrees around a rotating shaft in the spanwise direction of the wing, and switching among multiple modes and attitude control are achieved. The aircraft disclosed by the invention has more flexible maneuvering capability, has vertical take-off and landing performance of a multi-axis mode, efficient hovering performance of a spinning mode and high-speed cruising performance of a fixed wing mode, can meet different flight requirements, and has better environment adaptability.

The invention provides a posture adjusting method, system and equipment for a cold regenerator and a medium, and belongs to the technical field of cold regenerator control, the method comprises the following steps: descending four supporting legs of the cold regenerator before construction, enabling the whole machine to be horizontal, enabling a milling hub to be flush with the ground, and recording the heights of the four supporting legs as zero point heights; lowering the milling hub to a target cutting depth, and collecting initial values of a left-right inclination angle, a front-back inclination angle, four support leg oil cylinder pressures and an engine load rate corresponding to the zero point height; in the construction process, the real-time values of the left-right inclination angle, the front-back inclination angle, the pressure of the four supporting leg oil cylinders and the engine load rate are collected in real time; the change of the real-time value relative to the initial value is compared, the state of the corresponding supporting leg is judged to be pressed to the obstacle or the pit, the corresponding supporting leg ascends or descends till the collected real-time value recovers to the initial value, and automatic adjustment of the posture of the cold regenerator is completed. The machine body can be automatically kept horizontal, it is guaranteed that the cutting depth is stable, and construction precision and efficiency are improved.

An aircraft and an aircraft control method. The aircraft comprises: a fuselage (100), a frame (200), front propellers (300) and rear propellers (400), wherein the frame (200) tilts relative to the fuselage (100) about a pitch axis (001), with a tilt angle being adjustable; and the front propellers (300) and the rear propellers (400) are spaced apart along a longitudinal axis (002), and at least one of the front propellers (300) and the rear propellers (400) tilts relative to the fuselage (100) about an axis parallel to the pitch axis (001), with a tilt angle being adjustable. The frame (200) can tilt relative to the fuselage (100) about the pitch axis (001), thereby preventing the fuselage (100) from tilting and improving the stability of the aircraft. In addition, the tilted frame (200) can enable the front propellers (300) and the rear propellers (400) that are tilted to a horizontal state to be offset in a horizontal direction, thereby reducing aerodynamic interference of the front propellers (300), the rear propellers (400) and the fuselage (100), and ensuring the propulsion efficiency of the aircraft.

The application discloses a kind of unmanned aerial vehicle with anti-collision structure, comprising: fuselage, landing gear, rotor, first anti-collision device, second anti-collision device, the fuselage is unmanned aerial vehicle main body, carries unmanned aerial vehicle basic component;The landing gear square distribution is provided with four, is fixed in the four corners of fuselage;The rotor square distribution is provided with four, respectively rotatable fixed in the top of landing gear;The first anti-collision device square distribution is provided with four, and the middle part of each first anti-collision device is respectively fixed in the top of landing gear;The second anti-collision device is provided with four, respectively between adjacent first anti-collision device, and fixed on fuselage.Compared with prior art, the anti-collision device in the application adopts the structure design of mitigation offset, multiple rotating structures, so that the unmanned aerial vehicle is more flexible and variable in response to impact, and reduces the loss of unmanned aerial vehicle main body.

The invention is suitable for the technical field of unmanned aerial vehicle manufacturing, and provides an intelligent remote sensing unmanned aerial vehicle which comprises a fuselage, a landing gear is fixedly connected to the bottom of the fuselage, four connecting rods are connected to the fuselage at equal intervals, a plurality of through air holes are formed in each connecting rod, propellers are fixedly connected to the ends of the connecting rods, and the propellers are connected to the bottom of the fuselage. The propellers are jointly and electrically connected with a battery, the battery is fixed in the fuselage, and a camera is arranged on one side of the battery; and the rotating speed control system comprises a flight speed regulation and control module which can construct a flight speed regulation and control model according to the current flight speed and the flight risk assessment index and output the target flight speed. According to the method, the dynamic amplification effect of the sensor error on the flight risk can be quantified in real time, risk misjudgment caused by sensor precision reduction in a complex meteorological environment or in a takeoff / landing key stage is avoided, and thus the accuracy of flight risk assessment and the reliability of autonomous decision making are improved.

The application relates to a force couple balance and longitudinal array push-pull vertical take-off and landing high-speed aircraft, belonging to the technical field of aircrafts, which comprises a fuselage, a rotor, a fixed wing, a steering controller and a propeller. The rotor is installed at the top of the middle part of the fuselage through a rotor shaft, and a clutch is arranged between the rotor and a power system and / or a transmission system matched with the fuselage, so as to be controlled to be disconnected or to transmit power to the rotor. The steering controller comprises a fixed base and a rotating base, and each of the nose and the tail has a set of the rotating base. The propeller is provided with two propellers which are respectively installed on the rotating bases of the nose and the tail, and are controlled to rotate with the rotating bases relative to the fixed base. The force couple formed by the front and rear thrust vectors is used to balance the reverse torque brought by the rotor. When the propeller is coaxial with the middle axis of the fuselage, the wind area of the single propeller obtains double thrust. The application can improve the energy utilization rate, improve the carrying capacity, improve the flight safety performance and obtain a longer hovering time.

A vertical take-off and landing aircraft (1) comprises a fuselage (2), at least one propulsion system (5), at least four lift propellers (10), and at least two fixed wing planes (20, 30, 40), the fixed wing planes (30, 40) located rearward of the forwardmost lift propellers (10) being located above the lift propellers (10). The lift propellers (10) are distributed on either side of the fixed wing planes (30) and on either side of the fuselage (2) such that the lift propellers (10) are separated in the longitudinal direction by at least the size of the chord (Cl, C2) of the fixed wing planes located between the lift propellers (10) and in the lateral direction by at least the width (L1, L2) of the fuselage (2) located between the lift propellers (10). At least one of the fixed wing planes (30) has a variable wingspan and the aircraft (1) comprises a control system for varying the wingspan in flight.

The application discloses a kind of underwater self-explosion barrier robots in the technical field of underwater robot, including fuselage, propeller, mechanical arm, attachment mechanism, observation instrument and charging mechanism;The propeller includes horizontal propeller and vertical propeller, the horizontal propeller and vertical propeller are symmetrically installed in the left and right sides of fuselage, the observation instrument is installed in the grabbing surface of fuselage, the attachment mechanism is installed in one end of horizontal propeller, and with the grabbing surface same direction;The mechanical arm is symmetrically installed in the upper and lower sides of fuselage, the mechanical arm has at least three degrees of freedom, the free end of the mechanical arm is provided with mechanical claw, the mechanical arm can be gripped with pincer type;The charging mechanism is installed in the non-grabbing surface of fuselage.The underwater self-explosion barrier robot provided by the application can be closely adsorbed on the surface of barrier, suitable for a variety of complex shape barriers, high applicability range and high stability, high barrier efficiency and low manufacturing cost.

This invention discloses a hybrid configuration high-payload unmanned helicopter, belonging to the field of unmanned aerial vehicle (UAV) technology. It includes a fuselage with symmetrically detachable wings on both sides. Two rotor systems are mounted on the top of the fuselage along its longitudinal axis, a tail thrust system is mounted at the rear, and landing gear is mounted at the bottom. Internally, the fuselage houses a synchronous transmission system, a power system, and a control system. The power system provides power and transmits it to the two rotor systems and the tail thrust system via the synchronous transmission system. The control system controls flight attitude, transmits and receives commands, and processes data. This invention utilizes tandem rotors to provide primary lift, combined with the auxiliary lift from the detachable wings to reduce cruise power consumption. The tail thrust system enhances forward speed and attitude control. The modular, quick-release structure significantly improves transportation and maintenance convenience, effectively addressing the limitations of existing single-configuration UAV helicopters in simultaneously achieving high payload, long endurance, and high maneuverability.

The invention belongs to the technical field of aircraft landing gear ship surface load analysis and test, and particularly relates to an aircraft full-aircraft ejection dynamic simulation test device which comprises a fuselage fake part, a balance weight, a main engine wheel tire, a nose landing gear test part and an ejection restraining mechanism. The multiple groups of counterweights are horizontally arranged on the fuselage false part at intervals, the tire is connected to the tail end of the bottom of the fuselage false part, the nose landing gear test piece can be connected to the front end of the fuselage false part, and the ejection restraining mechanism is connected with the nose landing gear test piece and can perform ejection control on the fuselage false part; the ejection restraining mechanism comprises an ejection rod, an ejection reciprocating vehicle and a restraining rod. The mass distribution and rigidity of the airplane can be truly simulated; engine pulling force (pushing force) can be effectively simulated; compared with an existing catapult pulley test, the catapult buffering, tensioning and releasing process can be truly simulated; the ground course ejection sliding capacity is achieved; the elastic design of the fuselage fake part and the balance weight can simulate the dynamic response of the fuselage in the catapulting sliding process.

This invention relates to the field of aviation technology, and more particularly to a tiltrotor aircraft configuration capable of flipping over on water and a method for controlling rollover recovery on water. The invention includes: a fuselage structure, a wing, a rotor structure, and a drainage structure; the wing is fixedly mounted in the middle of the fuselage structure; the rotor structure is mounted on the fuselage structure and the wing; and the drainage structure is provided on the fuselage structure and the wing. When the aircraft operates on water, the one-way drain can prevent water from entering the fuselage and wing interior, and when there is water inside, it can drain to the outside. When the aircraft rolls over on the water, the rotor is adjusted to provide a tilting moment until it returns to right. After the aircraft returns to right, its attitude is adjusted so that the water inside the aircraft flows out through the one-way drain, achieving the ability to continue operating after a rollover.

A fixed-wing unmanned aerial vehicle propeller starting test device is characterized in that the fixed-wing unmanned aerial vehicle comprises a nose, a fuselage and blades at the tail, the test device comprises a test bed and a protective cover, a limiting plate, a first supporting seat and a second supporting seat are sequentially fixed on the surface of the test bed from left to right, a first half hoop is arranged above the first supporting seat, and a second half hoop is arranged above the second supporting seat. A second half hoop is arranged above the second supporting seat; the fixed-wing unmanned aerial vehicle is horizontally placed on the first supporting seat and the second supporting seat, the machine head is fixed to the first supporting seat through a first half hoop, the machine body is fixed to the second supporting seat through a second half hoop, the front end face of the machine head abuts against a limiting plate, and the paddles are suspended; and the protective cover covers the periphery of the test bed and the fixed-wing unmanned aerial vehicle.

A vertical take-off and landing (VTOL) aircraft is disclosed, including a fuselage having an elevated front section configured to accommodate antennas for obstruction- free communication and a rear section configured to hold an engine, fuel storage, battery, and payload with easy and ergonomic access for loading, unloading, and maintenance A pair of wings extends laterally from fuselage to generate lift during flight, while a pair of canards are positioned forward of the wings to improve stability. The fuselage, the wings and canards are shaped to provide a significant nose-up pitching moment, enabling longitudinal stability at positive angles of attack. A pair of booms interconnect fuselage, wings, and canards to form an interconnected box-like structure that uniformly distributes loads across the aircraft. The aircraft includes VTOL rotors for vertical thrust, concealed landing gears for reduced air drag, and a cowling system with air inlets and outlets that provide efficient engine cooling.

The invention discloses a cross-medium variable tilt rotor aircraft and a control method thereof, and relates to the technical field of cross-medium aircrafts. Comprising a fuselage, front rotor units, a tail tilting rotor assembly, main wing units and wing unfolding and folding mechanisms, wherein the front rotor units are arranged on high-position mounting platforms on the two sides of the fuselage and are in bilateral symmetry; the tail tilting rotor assembly is arranged at the tail end of the fuselage and can rotate around a transverse tilting shaft; the main wing units are in bilateral symmetry and can be folded; the buoyancy adjusting unit and the control system are arranged in the fuselage. Through collaborative design of fuselage bionic integration, the composite rotors, the variable main wings, active buoyancy adjustment and closed-loop control, the traditional single propulsion bottleneck is broken through, cross-medium adaptation, consideration of take-off and landing and cruising efficiency and smooth transition are achieved, multi-scene adaptation is achieved, and breakthrough support is provided for engineering application.

A landing gear is connected to the lower portion of a fuselage, a right front middle large rotor and a right front end small rotor are sequentially connected to the middle section and the front end of a forward-swept right front arm on the lower layer of the fuselage, and a left front middle large rotor and a left front end small rotor are sequentially connected to the middle section and the front end of a forward-swept left front arm on the lower layer of the fuselage. The right rear middle large rotor and the right rear end small rotor are sequentially connected to the middle section and the rear end of a sweepback right rear arm in the middle layer of the fuselage, and the left rear middle large rotor and the left rear end small rotor are sequentially connected to the middle section and the rear end of a sweepback left rear arm in the middle layer of the fuselage. The near-tail small rotor and the tail-end small rotor are sequentially connected to the middle section and the rear end of a longitudinal backward tail engine arm on the rear side of the upper layer of the fuselage; in the process of controlling rolling, pitching and heading, the lift force of the right front middle large rotor wing, the left front middle large rotor wing, the right rear middle large rotor wing and the left rear middle large rotor wing is kept in the original state, the variable-speed power loss of motors for driving the rotor wings is reduced, and the vertical lifting flight platform has the advantage of being long in endurance time and becomes a universal vertical lifting flight platform.

This invention discloses a fire-fighting drone, comprising a fuselage and multiple aircraft mounted on the fuselage, including a probe head disposed on the fuselage; a magazine located on the fuselage for storing fire extinguishing bombs, with a bomb-dropping hole at the bottom of the magazine; a mounting slot located at the bottom of the fuselage; and a bomb-dropping mechanism disposed within the mounting slot. This fire-fighting drone provides high bomb-dropping accuracy and excellent fire-fighting effect. It employs a partially engaged gear and rack drive system combined with a spring energy storage mechanism to achieve catapult-style deployment of fire extinguishing bombs. The moment the partially engaged gear and rack disengage, the bomb-dropping tube rapidly resets under the elastic potential energy of the spring, using inertia to project the fire extinguishing bomb. This catapult method imparts a certain initial velocity to the fire extinguishing bomb, enabling it to fly along a specific trajectory towards the target fire point, effectively shortening the flight time of the fire extinguishing bomb.