CN206502045U - Mobile launch formula autogyro - Google Patents

Abstract

The utility model discloses a mobile launch type autorotary rotorcraft, which comprises a fuselage, a fairing, a restraint package, first to second V-shaped flat tails, a vertical tail, a folding rotor, a rotating shaft, a bracket spring, a motor, a propeller, and a propeller installation. Axis, 1st to 4th servos, ESC, receiver and power module. The utility model can launch to reach the target airspace through artillery launch, submarine launch, and airdrop carried by fighter planes. During this period, it does not rely on its own power to fly, and at the same time, it has faster flight speed, more concealed launch, and stronger penetration capabilities; and the structure It is compact and has two modes: launch flight mode and cruise mode. In the two modes, the structure is different and the aerodynamic shape is different; in addition, when the engine is stopped, it can rely on the advantage of converting the potential energy of its own gravity into rotor maneuvering energy, which improves the ability to resist drought and crash .

Description

mobile launch autogyro

technical field

The utility model relates to the field of unmanned aerial vehicles, in particular to a mobile launching type autogyro.

Background technique

Conventional UAVs mainly take off by taxiing, hand-throwing or ejection. The aircraft needs to fly to the target area by itself, and has certain requirements for time and place.

Generally speaking, conventional UAVs rely on their own power to fly to their destinations. They are slow, have weak penetration capabilities, and require high venues for takeoff. After the engine is stopped, they are prone to crashes.

Utility model content

The technical problem to be solved by the utility model is to provide a mobile launching type autogyro for the defects involved in the background technology.

The utility model adopts the following technical solutions for solving the above-mentioned technical problems:

Motor launch type autogyro, including fuselage, fairing, restraint package, first to second V-shaped horizontal tail, vertical tail, folding rotor, rotating shaft, bracket spring, motor, propeller, propeller installation shaft, first to fourth Servo, ESC, receiver and power module;

The motor is arranged at the head end of the fuselage; the first to second V-shaped horizontal tails and vertical tails are correspondingly arranged at the tail of the fuselage; inside the body;

One end of the propeller installation shaft is fixedly connected to the output shaft of the motor, and the other end is used to install the propeller; the blades of the propeller can be folded around the propeller installation axis on the bullet head of the fuselage;

The folding rotor comprises a folding hub, first to third rotor blades, a universal joint and a hub bracket;

The foldable hub includes a hub body, a hub axis, bearings and first to third deployment mechanisms;

One end of the hub axis is connected to the hub body through a bearing, so that the hub body can freely rotate around the hub axis;

The first to third deployment mechanisms all include a paddle clamp, a gantry, a rotor spring and a locking structure, wherein the paddle clamp is hinged to the hub body through a screw shaft and can rotate up and down around the hub body; The gantry is fixedly connected to the paddle hub body; one end of the rotor spring is fixedly connected to the gantry, and the other end is fixedly connected to the paddle clip, and the plane of the rotor spring and the paddle clip when they rotate are in the same plane, and in a stretched state; the locking structure is used to lock the paddle clip when the paddle clip rotates to be on the same plane as the propeller hub body so that it cannot rotate any more;

The first to third rotor blades are respectively fixedly connected to the paddle clips of the first to third deployment mechanisms;

The fuselage is provided with a bracket folding groove for accommodating the hub bracket and corresponding rotor folding grooves for accommodating the first to third rotor blades;

One end of the hub bracket is connected to the other end of the hub axis through a universal joint, and the other end is hinged at a predetermined distance from the end through the rotating shaft and the two side walls of the folding groove of the bracket, The propeller hub bracket can be folded into the bracket folding groove around the rotating shaft, and when the propeller hub bracket is folded into the bracket folding groove, the first to third rotor blades can be folded into the bracket folding groove respectively. in the first to third rotor folding slots;

One end of the bracket spring is connected to the end of the hub bracket away from the hub, and the other end is connected to the fuselage in a stretched state for pulling the hub bracket up from the folding groove of the bracket so that the folded rotor is in the expanded state;

The third steering gear and the fourth steering gear are both arranged on the propeller hub bracket, and are respectively connected to the universal joints through pull rods, and are respectively used to control the universal joints to perform forward and backward pitching and left and right tilting, and then Control the pitch and tilt of the hub plane;

The restraint bag includes a circular restraint ring and two restraint straps; the blades of the propeller are in a folded state, the fairing is covered on the propeller; the restraint ring is fixed on the fuselage, It is used to bind the hub bracket in the bracket folding groove, and bind the first to third rotor blades in the first to third rotor folding grooves respectively; The fairing is connected, and the other end is connected with the fairing, and the fairing is fixed on the head end of the fuselage;

The first steering gear is arranged in the fuselage, and its output end is connected with a blade through the rocker arm, which is used to cut off the bound ring after receiving the control current, and the fuselage is provided with a blade for cutting the bound ring. through holes;

The second steering gear is arranged on the fuselage and is used to control the vertical tail and then control the yaw of the rotorcraft;

The universal joint is electrically connected to the ESC through the steering gear, and the ESC is also electrically connected to the motor, receiver, and power supply module, wherein the receiver is used to receive instructions and convert instructions into control The signal is transmitted to the ESC; the ESC distributes current to the motor and the first to fourth servos according to the received control signal; the motor is used to control the speed of the propeller according to the received current and then Controls the speed at which the rotorcraft flies forward.

As a further optimization scheme for the mobile launching autogyro of the utility model, the locking structure includes a hook and a spring piece, wherein the end of the hook is hinged to the hub body, and the hook can wrap around the hub body Rotation; one end of the spring piece is against the propeller hub body, and the other end is against the end of the hook, which is used to push the spring piece when the paddle clip is rotated to be in the same plane as the propeller hub body The hook portion of the hook locks the paddle clamp.

As a further optimization scheme of the mobile launching autogyro of the utility model, the fuselage is streamlined.

As a further optimization solution for the mobile launching autogyro of the present invention, the power supply module adopts a lithium battery.

Compared with the prior art by adopting the above technical scheme, the utility model has the following technical effects:

1. It reaches the target airspace by means of artillery launch, submarine launch, and airdrop carried by fighter jets. During this period, it does not rely on its own power to fly, and at the same time, it flies faster, launches more concealed, and has stronger penetration capabilities;

2. The utility model has a compact structure and has two modes: launch flight mode and cruise mode. The structures and aerodynamic shapes are different in the two modes;

3. When the engine is stopped, the utility model can rely on the advantage of its own gravity potential energy to be converted into rotor motor energy, which improves the ability to resist drought and crash.

Description of drawings

Fig. 1 is the structural representation of the utility model;

Fig. 2 is a schematic diagram of the folded structure of the propeller hub bracket in the utility model;

Fig. 3 is the structural representation that motor is connected with propeller in the utility model;

Fig. 4 is the structural representation of folding rotor in the utility model;

Fig. 5 is a schematic diagram of the structure of the folding propeller hub in the utility model when it is unfolded;

Fig. 6 is a structural schematic diagram of the foldable propeller hub in the utility model when it is folded;

Fig. 7 is a structural schematic diagram of the restraint bag in the utility model;

Fig. 8 is a structural schematic diagram of the utility model in the launch mode;

Fig. 9 is a schematic structural view of the utility model in the unfolded mode;

Fig. 10 is a schematic structural diagram of the utility model in cruise mode.

In the figure, 1- fairing, 2-propeller, 3-rotor folding groove, 4-bracket folding groove, 5-vertical tail, 6-V-shaped flat tail, 7-propeller hub bracket, 8-rotating shaft, 9-propeller hub bracket Spring connection hole on the top, 10-power module, 11-motor, 12-first servo, 13-spring connection hole in the fuselage, 14-ESC, 15-second servo, 16-receiver, 17 -propeller, 18-propeller installation shaft, 19-bullet, 20-rotor blade, 21-folding hub, 22-universal joint, 23-third steering gear, 24-fourth steering gear, 25-propeller hub bracket , 26-spring mounting hole on paddle clip, 27-spring mounting hole on gantry, 28-gantry, 29-bearing, 30-propeller hub shaft, 31-screw shaft, 32-hook, 33-spring leaf, 34--paddle clamp, 35-restraint belt, 36-restraint ring.

detailed description

Below in conjunction with accompanying drawing, the technical scheme of the utility model is described in further detail:

The utility model discloses a mobile launch type autorotary rotorcraft, which comprises a fuselage, a fairing, a restraint bag, first to second V-shaped flat tails, a vertical tail, a folding rotor, a rotating shaft, a bracket spring, a motor, a propeller, and a propeller installation. Axis, 1st to 4th servos, ESC, receiver and power module.

As shown in Figure 1, the motor is arranged at the head end of the fuselage; the first to second V-shaped horizontal tails and vertical tails are correspondingly arranged at the tail of the fuselage.

As shown in Figure 2, the motor, ESC, receiver, and power module are all arranged in the fuselage.

As shown in Figure 3, one end of the propeller installation shaft is fixedly connected to the output shaft of the motor, and the other end is used to install the propeller;

The blades of the propeller can be folded about the fuselage around the propeller mounting axis on its bullet.

As shown in FIG. 4 , the folding rotor includes a folding hub, first to third rotor blades, a universal joint and a hub bracket.

As shown in Figure 5, the foldable propeller hub includes a propeller hub body, a propeller hub central shaft, bearings and first to third deployment mechanisms;

One end of the central axis of the hub is connected to the hub body through a bearing, so that the hub body can freely rotate around the central axis of the hub.

The first to third deployment mechanisms all include a paddle clamp, a gantry, a rotor spring and a locking structure, wherein the paddle clamp is hinged to the hub body through a screw shaft and can rotate up and down around the hub body; The gantry is fixedly connected to the paddle hub body; one end of the rotor spring is fixedly connected to the gantry, and the other end is fixedly connected to the paddle clip, and the plane of the rotor spring and the paddle clip when they rotate are in the same plane, and in a stretched state; the locking structure is used to lock the paddle clip when the paddle clip rotates to be on the same plane as the propeller hub body so that it cannot rotate any more;

The first to third rotor blades are correspondingly and fixedly connected to the paddle clips of the first to third deployment mechanisms.

The locking structure includes a hook and a spring, wherein the end of the hook is hinged to the hub body, and the hook can rotate around the hub body; one end of the spring is against the hub body, and the other end Abut against the end of the hook, the spring leaf pushes the hook portion of the hook to lock the paddle clip when the paddle clip rotates to be on the same plane as the propeller hub body.

The fuselage is provided with bracket folding grooves for accommodating the hub bracket and corresponding rotor folding grooves for accommodating the first to third rotor blades.

As shown in Figure 4, one end of the propeller hub bracket is connected to the other end of the propeller hub central axis through a universal joint, and the other end is at a preset distance from the end through the hinge between the rotating shaft and the folding groove of the bracket. The two side walls are hinged so that the propeller hub bracket can rotate around the shaft and be folded into the bracket folding groove, and when the propeller hub bracket is folded into the bracket folding groove, the first to third rotors The sheets can be folded into the first to third rotor folding grooves, respectively.

One end of the bracket spring is connected to the end of the hub bracket away from the hub, and the other end is connected to the fuselage in a stretched state for pulling the hub bracket up from the folding groove of the bracket so that the folded rotor is in the expanded state.

The third steering gear and the fourth steering gear are both arranged on the propeller hub bracket, and are respectively connected to the universal joints through pull rods, and are respectively used to control the universal joints to perform forward and backward pitching and left and right tilting, and then Controls the pitch and roll of the hub plane.

As shown in FIG. 7 , the restraint pack includes a circular restraint ring and two restraint belts.

As shown in Figure 8, the blades of the propeller are in a folded state, and the fairing covers the propeller;

The binding ring is fixed on the fuselage, and is used to bind the hub bracket in the bracket folding groove, and bind the first to third rotor blades in the first to third rotor folding grooves respectively ;

One end of the two tie straps is connected to the fairing, and the other end is connected to the fairing, so as to fix the fairing on the head end of the fuselage.

As shown in Figure 2, the first steering gear is arranged in the fuselage, and its output end is connected with a blade through the rocker arm, which is used to cut off the binding circle after receiving the control current. The blade cuts the through hole of the tie ring.

The second steering gear is arranged on the fuselage and is used to control the vertical tail and further control the yaw of the rotorcraft.

The universal joint is electrically connected to the ESC through the steering gear, and the ESC is also electrically connected to the motor, receiver, and power supply module, wherein the receiver is used to receive instructions and convert instructions into control The signal is transmitted to the ESC; the ESC distributes current to the motor and the first to fourth servos according to the received control signal; the motor is used to control the speed of the propeller according to the received current and then Controls the speed at which the rotorcraft flies forward.

As shown in Figure 6, when the folding rotor is folded, the hooks in the first to third unfolding mechanisms are slightly turned backwards, and the hooks cannot hook the end of the paddle clip. Rotate, first fold the propeller hub bracket into the slot of the fuselage, and then fold the rotor blades close to the fuselage.

The fuselage is preferentially designed to be streamlined.

The power module preferably adopts a lithium battery.

This law also discloses a control method based on the maneuverable launch type autogyro, comprising the following steps:

Step 1), launching the maneuverable launch autogyro;

Step 2), sending a deployment command to the maneuverable launch autogyro;

Step 3), the receiver distributes current to the first steering gear after receiving the unfolding command;

Step 4), after the first steering gear receives the control current, it controls the blade on the rocker arm at its output end to cut off the binding ring;

Step 5), the fairing comes off with the restraint bag;

Step 6), the rotor springs in the first to third deployment mechanisms respectively pull the first to third rotor blades to spring up from the first to third rotor folding grooves, so that the paddle clips in the first to third deployment mechanisms rotate to be on the same plane as the propeller hub body, at this time, the locking structures in the first to third deployment mechanisms lock their corresponding propeller clips;

Step 7), the bracket spring pulls the propeller hub bracket to spring up from the bracket folding slot, so that the folded rotor is in the unfolded state;

Step 8), as the rotorcraft falls, the first to third rotor blades are blown by the airflow and rotate around the central axis of the propeller hub, the gravitational potential energy of the rotorcraft is converted into the kinetic energy of the rotor, and the rotorcraft decelerates and falls;

Step 9), when the lift generated by the rotor blades rotates stably and the gravity balances, and the rotorcraft falls at a constant speed, the receiver distributes current to the motor;

Step 10), the motor rotates, and the folded propeller propeller is thrown away under the action of centrifugal force, and the propeller rotates to generate pulling force, which drives the rotorcraft forward, and the rotorcraft enters the cruising state.

The remote controller transmits the signal, the receiver receives the signal, the lithium battery supplies power to the ESC, the ESC distributes the current to the motor and the steering gear, the receiver transmits the signal to the ESC, and controls the ESC to the motor and the first to fourth steering gear The distribution of current, and then control the UAV.

After the rotorcraft is deployed in the air, the remote controller on the ground sends out a signal, and the receiver inside the fuselage receives the signal. By controlling the current distributed to the motor by the ESC to control the speed of the motor, the purpose of adjusting the flight speed of the rotorcraft is achieved. The receiver also controls the steering gear of the folding rotor to control the pitch of the rotor. The receiver controls the yaw of the rotorcraft by controlling the vertical tail servo of the fuselage.

The utility model can be launched by a cannon or equipped with a fighter plane to fly to the destination without relying on its own power, and realize air deployment over the destination, and enter the cruising state.

As shown in Fig. 8, Fig. 9 and Fig. 10, the utility model includes three working modes, the maneuvering launch mode, the unfolding mode, and the cruising mode. The utility model is researched through design and calculation, and breaks through the key technologies such as the automatic launch control technology of the mobile launch and the integrated design of the whole machine with aerodynamics. Find a technical way for the autogyro to achieve maneuvering launch, and lay a theoretical and technical foundation for the flexible application of the new unmanned rotorcraft.

Those skilled in the art can understand that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meanings as commonly understood by those of ordinary skill in the art to which the present invention belongs. It should also be understood that terms such as those defined in commonly used dictionaries should be understood to have a meaning consistent with the meaning in the context of the prior art, and will not be interpreted in an idealized or overly formal sense unless defined as herein Explanation.

The specific embodiments described above further describe the purpose, technical solutions and beneficial effects of the present utility model in detail. For the utility model, any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the utility model shall be included in the protection scope of the utility model.

Claims (4)

1. The mobile launch type autogyro is characterized in that it includes a fuselage, a fairing, a restraint package, first to second V-shaped flat tails, a vertical tail, a folding rotor, a rotating shaft, a bracket spring, a motor, a propeller, and a propeller installation shaft , the first to fourth steering gear, ESC, receiver and power module; The motor is arranged at the head end of the fuselage; the first to second V-shaped horizontal tails and vertical tails are correspondingly arranged at the tail of the fuselage; inside the body; One end of the propeller installation shaft is fixedly connected to the output shaft of the motor, and the other end is used to install the propeller; the blades of the propeller can be folded around the propeller installation axis on the bullet head of the fuselage; The folding rotor comprises a folding hub, first to third rotor blades, a universal joint and a hub bracket; The foldable hub includes a hub body, a hub axis, bearings and first to third deployment mechanisms; One end of the hub axis is connected to the hub body through a bearing, so that the hub body can freely rotate around the hub axis; The first to third deployment mechanisms all include a paddle clamp, a gantry, a rotor spring and a locking structure, wherein the paddle clamp is hinged to the hub body through a screw shaft and can rotate up and down around the hub body; The gantry is fixedly connected to the paddle hub body; one end of the rotor spring is fixedly connected to the gantry, and the other end is fixedly connected to the paddle clip, and the plane of the rotor spring and the paddle clip when they rotate are in the same plane, and in a stretched state; the locking structure is used to lock the paddle clip when the paddle clip rotates to be on the same plane as the propeller hub body so that it cannot rotate any more; The first to third rotor blades are respectively fixedly connected to the paddle clips of the first to third deployment mechanisms; The fuselage is provided with a bracket folding groove for accommodating the hub bracket and corresponding rotor folding grooves for accommodating the first to third rotor blades; One end of the hub bracket is connected to the other end of the hub axis through a universal joint, and the other end is hinged at a predetermined distance from the end through the rotating shaft and the two side walls of the folding groove of the bracket, The propeller hub bracket can be folded into the bracket folding groove around the rotating shaft, and when the propeller hub bracket is folded into the bracket folding groove, the first to third rotor blades can be folded into the bracket folding groove respectively. in the first to third rotor folding slots; One end of the bracket spring is connected to the end of the hub bracket away from the hub, and the other end is connected to the fuselage in a stretched state for pulling the hub bracket up from the folding groove of the bracket so that the folded rotor is in the expanded state; The third steering gear and the fourth steering gear are both arranged on the propeller hub bracket, and are respectively connected to the universal joints through pull rods, and are respectively used to control the universal joints to pitch forward and backward and tilt left and right, and then Control the pitch and tilt of the hub plane; The restraint bag includes a circular restraint ring and two restraint straps; the blades of the propeller are in a folded state, the fairing is covered on the propeller; the restraint ring is fixed on the fuselage, It is used to bind the hub bracket in the bracket folding groove, and bind the first to third rotor blades in the first to third rotor folding grooves respectively; The fairing is connected, and the other end is connected with the fairing, and the fairing is fixed on the head end of the fuselage; The first steering gear is arranged in the fuselage, and its output end is connected with a blade through the rocker arm, which is used to cut off the bound ring after receiving the control current, and the fuselage is provided with a blade for cutting the bound ring. through holes; The second steering gear is arranged on the fuselage and is used to control the vertical tail and then control the yaw of the rotorcraft; The universal joint is electrically connected to the ESC through the steering gear, and the ESC is also electrically connected to the motor, receiver, and power supply module, wherein the receiver is used to receive instructions and convert instructions into control The signal is transmitted to the ESC; the ESC distributes current to the motor and the first to fourth servos according to the received control signal; the motor is used to control the speed of the propeller according to the received current and then Controls the speed at which the rotorcraft flies forward. 2. The mobile launching autogyro according to claim 1, wherein the locking structure includes a hook and a spring leaf, wherein the end of the hook is hinged to the hub body, and the hook can rotate around The propeller hub body rotates; one end of the spring piece is against the propeller hub body, and the other end is against the end of the hook, so that when the propeller clip rotates to be on the same plane as the propeller hub body, the spring Push the hook part of the hook to lock the oar clip. 3. The mobile launching autogyro according to claim 1, wherein the fuselage is streamlined. 4. The mobile launching autogyro according to claim 1, wherein the power supply module is a lithium battery.