CN115465454A - Design method of omnidirectional missile rack of scouting and batting airplane and omnidirectional missile rack - Google Patents

Abstract

The invention discloses a design method of an omnidirectional missile rack of a scouting and beating airplane and the omnidirectional missile rack, wherein a support which can rotate relative to a fuselage within a certain range is designed to serve as a bearing structure of the omnidirectional missile rack; designing a loading mechanism of the omnidirectional bullet rack on a turntable mechanism, and designing the loading mechanism to rotate together with the turntable mechanism; meanwhile, the turntable mechanism is designed to be connected to the support through the rotating mechanism, and the servo motor drives the turntable mechanism to rotate relative to the support, so that the emission angle of the loading mechanism in the plane and the three-dimensional direction is adjusted. The invention provides newly developed space omnidirectional scouting and batting, effectively solves the general design of inside installation and outside installation, effectively solves the air defense integrated design, comprehensively solves the technology of scouting and batting immediately and space omnidirectional emission, and supports the application of increasing equipment and weapon loading capacity or loading large weapons in the inside installation, thereby perfecting and improving the capability of omnidirectional scouting and batting integrated airplanes.

Description

Design method of omnidirectional bullet rack of scouting and shooting airplane and omnidirectional bullet rack

Technical Field

The invention belongs to the technical field of airplane general design and electromechanical engineering, in particular to an integrated unmanned aerial vehicle.

Background

To check and hit a whole airplane, or to have been present for some time. The hit objects of the existing combat integrated unmanned aerial vehicle are limited to the anti-terrorism mode, and are not suitable for the new requirements of high-strength combat of strong enemy confrontation scenes. In connection with the problem to be solved by the present invention, the following main aspects were selected and listed. Firstly, how to adapt to the requirement of quick response of side-to-side inspection and striking of flying routes such as side-to-side inspection and sea-to-side inspection; secondly, the method is suitable for strong enemy confrontation and is suitable for continuously striking and pressing enemy cluster targets; thirdly, how to increase the remote striking capability against strong enemies, such as adding remote reconnaissance equipment and loading remote ammunition, in particular to a low-price air-jet reconnaissance unmanned aerial vehicle; fourthly, as the firepower of the aircraft is increased by striking on the ground and in the air, how to have the corresponding omnidirectional observing and striking integrated air defense capability; fifthly, how equipment and ammunition adopt built-in space is increased, and aerodynamic resistance influencing the performance of the aircraft is reduced; and sixthly, the applicability and the use selectivity of the new mechanism are improved by adopting a universal design, and the cost is reduced. The solution of above problem is applicable to the investigation and play integrative aircraft, especially unmanned aerial vehicle.

Some possibilities are presented in the patents of the prior art in the above part of the solution. For example, the application document with publication number CN107985605A entitled control method and system for surrounding scouting and batting integrated aircraft discloses in detail the technical constitution of surrounding or omnidirectional scouting and batting integrated aircraft, in the technical solution, the control system for surrounding scouting and batting integrated aircraft is composed of an aircraft, an onboard weapon system, an onboard detection system and a ground monitoring station; the aircrafts in all states are respectively provided with an abdomen hanging scaffold, weapons can be arranged on the abdomen hanging scaffold, the photoelectric pod is arranged, the lifting height of the pod can be adjusted to avoid the interference of the launching with the weapons, and other weapons can be hung under the wing or on the fuselage while the abdomen hanging scaffold is arranged. The design scheme of the observing and shooting airplane provided by the scheme solves the problem of limited emission angle of the weapon, and allows the guided missiles mounted on the hanging scaffold to be consistent with the direction of the observing and aiming device at any time through designing the ventral hanging scaffold, but synchronous alignment is not needed, and the guided missiles can be directed to the target at any time in the same direction or along with the observing and aiming device, so that the condition of emission at any time is established.

The invention patent application with the publication number of CN109387113A discloses a transmission elastic chain system of an omnidirectional scouting and hitting airplane, which comprises an airborne weapon, wherein the airborne weapon is arranged on the wing or the belly of the airplane body or the inside of an airplane cabin by adopting a built-in or external structure; the onboard weapons are either chain transferred or carousel transferred by transfer chain mechanisms or suspended spindles to adjust the firing orientation for firing outside the aircraft cabin. In the scheme, the weapon striking of the omnidirectional scouting and batting integrated airplane is based on striking of a flying omnidirectional target, the carried weapon can be omnidirectionally launched from the belly of a body or other parts through the coordinate binding of a rotating mechanism or the target, and can strike targets in all directions at any time, particularly, the airplane can continuously strike one specific target or one group of targets in a circling flight with an 8-shaped flight path, and the omnidirectional scouting and batting integrated airplane is suitable for loading various weapons and various guidance in a mixed mode, is suitable for high-strength battlefield countermeasures and is also suitable for general-strength battlefield countermeasures or anti-terrorism battles. Meanwhile, the airborne weapon of the omnidirectional scouting and hitting airplane can be stored in the cabin in normal times, and the airplane decelerates and flies before hitting the target and releases the weapon out of the cabin, so that the influence on the flight performance is reduced. In addition, when weapons are not installed in the cabin of the omnidirectional scout airplane, the unmanned plane can be used for loading other goods or passengers, becomes a multipurpose airplane, and improves the economy of the airplane.

However, the prior art is still not ideal, the solutions disclosed in the above sections mainly relate to plane surrounding scouting, but creative improvements on the above prior art are still needed to realize space omnidirectional scouting and solve the problems of general design of interior installation and exterior installation and air defense integrated design.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides a design method of an omnidirectional missile rack of a scouting and hitting airplane and an omnidirectional missile rack structure.

The invention is realized by the following steps:

the invention firstly provides a design method of an omnidirectional missile shelf of a scouting and batting airplane, which comprises the following steps: the support which can rotate in a certain range relative to the machine body is designed to serve as a bearing structure of the omnidirectional bullet rack; designing a loading mechanism of the omnidirectional bullet rack on a turntable mechanism, and designing the loading mechanism to rotate together with the turntable mechanism; meanwhile, the turntable mechanism is designed to be connected to the support through the rotating mechanism, and the servo motor drives the turntable mechanism to rotate relative to the support, so that the emission angle of the loading mechanism in the plane and the three-dimensional direction is adjusted. The loading mechanism is used for mounting a weapon. The loading mechanism is connected to the turntable mechanism and rotates together. The loader is a function of the loading mechanism, the launching mode of the cartridge mechanism is preferably selected, different types of weapons can be designed into a mixed installation scheme, and the overlapping installation mode of multiple layers of cartridge mechanisms.

In some embodiments, the cradle is designed to be attached to the fuselage structure using a hinge mechanism that incorporates a drive component and a servo motor, as well as a hinge mount attached to the fuselage structure. The supports are generally symmetrically arranged at the left side and the right side of the fuselage structure, can rotate relative to the fuselage in a certain range through the hinge mechanism, can be arranged in the fuselage, can be unfolded outside the fuselage or often arranged outside the side wall of the fuselage,

in some embodiments, control of the omnidirectional cartridge rack is achieved by designing a controller; the controller comprises control assembly and a plurality of sensor, includes at least: 1) The control component of the omnidirectional bullet rack can be operated in time according to the target information; 2) And the limiting sensor is used for limiting the rotation range of the bracket or the turntable mechanism. The controller can be specially designed, and corresponding functions can be implemented by a navigation flight control system of the aircraft.

The controller is installed on the organism and is connected with the control object through the pencil, and the connection and control mode includes: 1) A servo motor connected with the support hinge mechanism to control the support to rotate a certain angle relative to the machine body; 2) A servo motor connected with the turntable mechanism is used for controlling the turntable mechanism to rotate a certain angle relative to the bracket; 3) Connecting a loading mechanism to control omnidirectional firing of the weapon; 4) The video device on the turntable mechanism is connected to push the information of the target to be hit; 5) The controller controls the process of unfolding or collecting the omnidirectional missile rack according to the action process of aiming at the target position.

In some embodiments, the reduction of aerodynamic drag is achieved by the design of the hatch; the design method of the cabin door comprises the following steps: 1) Is connected to the bracket; 2) Is designed integrally with the support structure; 3) The cabin door is independently designed into a sliding cabin door, is connected with a sliding chute corresponding to the structure of the fuselage and can slide back and forth along the course of the fuselage to open the cabin door; 4) Sliding cabin doors are designed corresponding to a plurality of groups of omnidirectional bullet racks and are installed according to the height difference of upper parts and lower parts, the sliding cabin doors can respectively move forwards or backwards relatively, and the omnidirectional bullet racks are opened sequentially according to the unfolding sequence of the omnidirectional bullet racks.

In some embodiments, the attachment scheme of the omnidirectional ammunition carriage's support to the fuselage structure is not limited to a hinge mechanism. The applicability of the omnidirectional cartridge frame can be extended by several general designs. 1) Multiple sets of omnidirectional bullet racks can be arranged inside or outside the machine body in front of and behind the center of gravity of the whole machine by the omnidirectional bullet racks, so that the design requirement of the center of gravity of the whole machine is met. 2) The design can be simplified, and the fuselage pylon and the wing pylon are respectively adopted and can be externally connected with the belly structure and the wing structure of the fuselage. 3) Two-dimensional directional two-dimensional weapon stores pylon design proposals suitable for wing installation. The wing padlock and the wing upper hanging rack are combined and connected with the wing, the wing padlock and the wing upper hanging rack can be designed separately or integrally, and a motor is arranged in the upper hanging rack to drive the omnidirectional cartridge rack to rotate so as to provide the direction of a weapon; a motor is arranged in the lower hanging frame to drive the omnidirectional bullet frame to rotate so as to provide the direction of the weapon; the geometric shape of the side fairing is that the two ends and the middle part of the fairing are wide along the airflow direction, and the cross section of the fairing along the airflow is wedge-shaped. The structure is made of a selectable hard composite material. 4) The other simplified design is that a cylinder mechanism is selected, a hinge mechanism is cancelled for the bracket part, and the bracket part is directly connected with the machine body; a further simplified design can eliminate the turntable mechanism and simplify the built-in mounting structure of the weapon by adopting a triangular mounting mode, for example. 4) The hinge mechanism is eliminated for the support of the omnidirectional bullet rack, and a combined mechanism with a plurality of sets of omnidirectional bullet racks is arranged in the machine body. The combined mechanism can realize the control of rotating and converting the bullets and lifting and taking out of the cabin by using a lifting and rotating mechanism, and the lifting and rotating mechanism and the combined mechanism can be arranged on a frame partition structure of the machine body in a coordinated manner.

Based on the method, the invention provides an omnidirectional bullet rack of a scouting and batting airplane, which is arranged on a navigation airplane or an unmanned aerial vehicle and comprises one or the combination of more than two mechanisms of a bracket, a turntable mechanism, a bullet loading mechanism, a controller, a video device and a cabin door; the support is connected to the machine body structure through a hinge mechanism, and the hinge mechanism of the support comprises a transmission part, a servo motor and a hinge seat connected to the machine body structure; the rotary table mechanism is connected to the bracket through the rotating mechanism, and the loading mechanism is connected to the rotary table mechanism; the controller is arranged on the machine body and is connected with a control object through a wire harness; the video device is connected with the turntable mechanism, moves synchronously with the turntable mechanism, is not shielded in view angle and points to a target; the door is attached to the bracket or is integral with the bracket structure.

Compared with the prior art, the invention provides newly developed space omnidirectional scouting and batting, effectively solves the general design of interior installation and exterior installation, effectively solves the air defense integrated design, comprehensively solves the technology of scouting and batting and space omnidirectional launching, and supports the application of increasing equipment and weapon loading capacity in interior installation or loading large weapons, thereby perfecting and improving the capability of omnidirectional scouting and batting integrated airplanes.

Drawings

FIG. 1 shows the loading mechanism built into the body and deployed outside the body; other weapons can be mixed in the fuselage (reverse course view);

FIG. 2 shows that the turret mechanism and the loading mechanism can adjust the firing angle (0-360) of the weapon;

FIG. 3 shows that the omnidirectional missile bay is outboard (single or double sided) in the body, and may be tilted at launch angle (reverse heading view);

FIG. 4 shows the omnidirectional missile bay with the full fuselage center of gravity connected fore and aft on the fuselage (shown retracted against the side wall of the fuselage), with the upper single wing;

FIG. 5 shows the omnidirectional missile bay with the full hull center of gravity connected fore and aft on the hull (shown retracted against the side wall of the hull), with the lower single wing;

figure 6 shows a general design of an omnidirectional cartridge rack and a schematic of the connections on the body (under the fuselage);

figure 7 shows a general design of an omnidirectional missile bay and a schematic of the connections on the airframe (under the wing);

FIG. 8 illustrates one of the wing two-dimensional pointing weapon pylons;

FIG. 9 shows a second inboard wing two-dimensional pointing weapon pylon;

FIG. 10 shows a schematic view of directional cross-section four quadrant angular omnidirectional emission (I and III, II and IV);

FIG. 11 shows a simplified design result schematic of an omnidirectional ammunition carrier (mounted horizontally relative to the fuselage);

FIG. 12 shows a simplified design result schematic of an omnidirectional cartridge rack (mounted vertically with respect to the fuselage);

fig. 13 shows a simplified design result diagram of an omnidirectional ammunition holder (a triangular mounting schematic diagram of a simple bracket for mounting a cartridge mechanism);

figure 14 shows a schematic view of the omnidirectional missile mount built into the fuselage and the lifting and rotating pylon (details of the mechanism of the lifting and rotating pylon are not shown);

fig. 15 shows an omnidirectional missile rack installation on a compound wing drone (the diameter of the take-off and landing motor propeller indicates the projected length associated with the take-off and landing mechanism, the upper right dotted line indicates the actual diameter);

FIG. 16 shows a weapon firing orientation diagram for an omnidirectional carrier; the landing gear mechanism is not shown.

The labels in the figures are: 1-omnidirectional cartridge holder, 11-combined mechanism, 12-lifting and rotating mechanism, 13-machine body, 14-simple support, 15-lifting and rotating hanger, 16-lifting and landing mechanism, 17-lifting and landing wheel, 18-lifting and landing mechanism servo mechanism wheel, 2-support, 21-hinge mechanism, 22-fuselage, 23-hinge seat, 24-fuselage hanger, 25-wing hanger, 26-wing, 27-wing padlock, 28-upper hanger, 29-built-in throwing object, 3-turntable mechanism, 31-rotating mechanism, 32-lower hanger, 33-side fairing, 4-loading mechanism, 41-cartridge mechanism, 42-cartridge, 5-controller, 6-video player and 7-cabin door. The method comprises the following steps of a-mechanism outer section indication, b-omnidirectional missile frame retraction position, c-take-off and landing mechanism lowering position, d-take-off and landing mechanism retraction position, e-take-off and landing motor rotor wing actual diameter indication, f-loading mechanism vertical position, g-loading mechanism horizontal position, h-air launching angle and i-launching quadrant indication (along course left weapon launching III quadrant and right weapon launching II quadrant, not shown).

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the description of the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Please refer to fig. 1-16. In the invention, the omnidirectional bullet rack 1 mainly comprises a bracket 2, a turntable mechanism 3, a bullet loading mechanism 4, a controller 5, a video player 6 and a cabin door 7. Wherein in many cases the carriage 2 and the hatch 7 are of an integrated design, as illustrated in figure 1.

Wherein the lower arrows in fig. 1 and 3 indicate the emission angle schematic. The lower two figures in fig. 2 show the loader and its axial rotation schematic. In fig. 1, the omnidirectional bullet rack 1 on the upper left is obliquely arranged, the omnidirectional bullet rack 1 on the lower left is externally arranged, the omnidirectional bullet rack 1 on the right is externally arranged, and the two layers of omnidirectional bullet racks 1 in the middle are internally arranged. In fig. 3, the omnidirectional bullet rack 1 on the upper left is obliquely arranged, the omnidirectional bullet rack 1 on the lower left is externally arranged, and the omnidirectional bullet rack 1 on the right is externally arranged. Figure 14 shows an omnidirectional magazine 1 in the out-of-compartment view.

The figures show different placing modes and taking-out modes of the omnidirectional bullet rack 1.

In most embodiments, the cradle 2 is mounted to the fuselage 22 structure, typically the belly compartment structure, by a hinge mechanism 21. The hinge mechanism 21 of the bracket 2 comprises a transmission part, a servo motor and a hinge seat 23 connected to the structure of the machine body 22, and can be used for manufacturing a composite material structure or a mixed material structure of the composite material and a metal material selected by the bracket 2. The transmission component can be selected from a rack, a chain, a steel cable and a belt.

The support 2 is preferentially symmetrically arranged on the left side and the right side of the machine body 22 structure, the lateral gravity center and the inertia moment balance of the whole machine are considered, and reasonable gaps are designed on the upper layer support 2 and the lower layer support 2 of the built-in omnidirectional bullet rack 1. The stand 1 is rotated relative to the body 22 by a hinge mechanism 21, and is deployed outside the body 22, as shown in fig. 1.

Alternatively, the support 2 is mounted on the structure of the body 22 by the hinge mechanism 21, and the support 2 is externally arranged on the body 22, i.e. is stored on the outer side wall of the body 22 and is not stored in the body 22. The support 2 may be deployed over a range of angles, such as from vertical to horizontal. The advantage of external installation is that the internal height of fuselage 22 can be reduced, reduces full quick-witted aerodynamic resistance, and the shortcoming is that the local aerodynamic resistance that omnidirectional bullet frame 1 produced is great, and the aircraft appearance is not pleasing to the eye.

The hinge seat 23 of the hinge mechanism 21 is structurally connected to the body 22 in such a manner that the bracket 2 is properly protruded from the outer sidewall of the body 22 to prevent the sidewall from being crushed, as shown in fig. 3.

The turntable mechanism 3 is connected to the support 2 through a rotating mechanism 31, the rotating mechanism 31 comprises a servo motor and a mounting structure and is connected to the support 2, and the rotating mechanism 31 can drive the turntable mechanism 3 to rotate 0-180 degrees or 0-360 degrees relative to the support 2. The omnidirectional bullet rack 1 is selectively arranged in the machine body 22, the cabin door 7 on the belly of the machine body 22 can be selected to be designed integrally with the turntable mechanism 3, and when the omnidirectional bullet rack 1 is stored in the machine body 22, the cabin door 7 is in a closed position, as shown in figure 1. The video camera 6 may be mounted on a turntable mechanism as shown in fig. 2. The turntable mechanism 3 can be made of composite materials or a mixed material structure of the composite materials and metal materials.

The loading mechanism 4 is used for mounting a weapon. The loading mechanism 4 is connected to the turntable mechanism 3 to rotate together. The loader is a function of the loading mechanism 4, and is designed in detail according to the mounting structure of the selected weapon, including the mounting design of the barrel mechanism 41, or the hook structure, or the slide rail structure, and the launch lock design, which is a function of the loading mechanism 4, for locking or releasing the weapon. The weapon may be selected from the group consisting of a round, a projectile, a weapon-grade laser, a non-lethal weapon, and a target signal, suitable for the loading mechanism 4. The weapon is arranged on the loading mechanism 4, the design scheme is determined according to the specific weapon when the weapon is launched, and the weapon is generally provided with an electric control interface; it is recommended to select the firing pattern of the barrel mechanism 41 so as to be connected to the loading mechanism 4 in a compact arrangement and so that the barrel mechanism 41 may not be thrown after the weapon is fired. Different weapons may be designed with a hybrid mounting scheme and with overlapping multi-tier barrel mechanisms 41, including top-to-bottom overlapping and coplanar tail-to-tail overlapping, as shown in fig. 2. The loading mechanism 4, in particular the cartridge mechanism 41, may be made of a composite material or a composite material/metal material mixture.

The controller 5 is composed of a control component and a plurality of sensors, and comprises:

1) The control component of the omnidirectional bullet rack 1 can be operated in time according to target information provided by a navigation flight control system or a reconnaissance system to which the aircraft belongs;

2) And a limit sensor for limiting the rotation range of the bracket 2 or the turntable mechanism 3.

The controller 5 can be specially designed, and the navigation flight control system of the aircraft can also implement corresponding functions. The controller 5 is mounted on the machine body and connected to a control object through a wire harness:

1) A servo motor connected to the hinge mechanism 21 of the stand 2 to control the stand 2 to rotate relative to the body 22;

2) A servo motor connected with the turntable mechanism (3) to control the turntable mechanism to rotate relative to the bracket (2);

3) The loading mechanism (4) is connected to control the omnidirectional firing of the weapon. The omnidirectional emission direction covers the forward direction and the backward direction of the heading direction and basically covers four quadrants on the periphery from forward heading view, so that a space omnidirectional emission condition is formed, as shown in figures 15-16;

4) The video camera 6 on the turntable mechanism 3 is connected to push information of the target to be hit, wherein the technical scout positioning function of the scout system can guide the photoelectric pod of the scout system towards the target instead of manual search. The controller 5 performs flow control of unfolding the omnidirectional bullet rack 1 or reverse flow control of collection according to the action flow of aiming at the target position.

The video device 6 is connected with the turntable mechanism 3, moves synchronously with the turntable mechanism 3, has an unobstructed view angle and points to a target. The video unit 6 may be selected from visible light or low light, infrared or short wave infrared video and installed according to user selection, as shown in fig. 2.

The hatch 7 is intended to reduce aerodynamic drag, and the hatch 7 may be optionally designed to be attached to the carriage 2 and preferably designed to be structurally integrated with the carriage 2, as shown in fig. 1. Or the cabin door 7 is independently designed, is not connected with the bracket 2, is designed into a sliding cabin door 7, is connected with a sliding chute corresponding to the structure of the machine body 22, and can slide back and forth along the course of the machine body 22 to open the cabin door 7 when being opened; if two sets of built-in omnidirectional ammunition carriers 1 are installed in front of and behind the center of gravity of the whole machine body 22, the sliding doors 7 corresponding to the omnidirectional ammunition carriers 1 are installed according to the height difference of one over the other, can move forwards or backwards relatively, and are opened sequentially according to the unfolding sequence of the omnidirectional ammunition carriers 1. The material for making the door 7 is preferably compatible with the material for making the fuselage 22, and may be selected individually, such as a composite material or a composite material and metal material mixed material structure.

The connection scheme of the support 2 and the body 22 structure of the omnidirectional bullet rack 1 is not limited to the hinge mechanism 21, as shown in fig. 1 and 3. The application range of the omnidirectional bullet rack 1 can be expanded by adopting several general designs:

1) A plurality of sets of omnidirectional bullet racks 1 can be arranged inside or outside a machine body 22 in front of and behind the center of gravity of the whole machine by using the support 2 of the omnidirectional bullet rack 1, are installed close to the center of gravity of the whole machine as much as possible and are symmetrical with the center of gravity as far as possible, and meet the design requirement of the center of gravity of the whole machine, as shown in figures 4-7.

2) The general design can be simplified by using a fuselage pylon 24 and a wing pylon 25, which can be connected to the belly structure of the fuselage 22 and the under-wing outboard portion of the wing 26, respectively, as shown in fig. 8-9.

3) Two-dimensional directional, two-dimensional weapon pylon designs suitable for wing 26 mounting are shown in fig. 11-14. In fig. 11-13, a wing padlock 27 and an upper hanging rack 28 are combined to connect with a wing 26, which can be designed separately or integrally, and a motor is arranged in the upper hanging rack 28 to drive the omnidirectional missile frame 1 to rotate so as to provide the yaw orientation of the weapon; the lower hanging rack 32 is internally provided with a motor to drive the omnidirectional missile rack 1 to rotate so as to provide the pitching direction of the weapon; the side cowling 33 has a geometry that is tapered along the airflow direction with both ends and the middle wide, and has a tapered cross section along the airflow direction. The structure is made of optional hard composite materials. The pitch angle of the weapon in fig. 11-13 should be limited to a small angular range in order to limit the aerodynamic drag increase to too great an extent, for example, to within 30. In fig. 14, the upper rack 28 is internally provided with a motor to drive the omnidirectional ammunition carrier 1 to rotate left or right to provide weapon direction; the lower suspension 32 has a built-in motor to drive the omnidirectional missile shelf 1 to rotate to provide heading or pitch. The weapon pointing angle in fig. 14 may be relatively large.

4) Another simplified design of the general design is that a bullet tube mechanism 41 is selected, the hinge mechanism 21 of the support 2 is omitted, and the support is directly connected with the machine body 22, so that the built-in bullet loading amount can be increased; a further simplified design can be achieved by eliminating the turntable mechanism 3 and adopting a triangular mounting manner of a simple bracket, wherein two ends of two fixed parts are connected to the internal structure of the machine body, one locking rod moving part is used for assembling and disassembling the barrel mechanism 41, and the launching direction of the installed barrel mechanism 41 cannot rotate in use, as shown in fig. 11-13; the built-in mounting structure of the weapon is simplified, and the loading capacity is increased; therefore, in use, the target information management of the weapon is matched to meet the launching condition, and the launched weapon is associated with the guidance of the airborne reconnaissance system.

5) The support 2 of the omnidirectional bullet rack 1 is designed to be provided with a plurality of sets of combination mechanisms 11 of the omnidirectional bullet rack 1 in a combined mode in a machine body 22 without a hinge mechanism 21. The combined mechanism 11 can realize the control of rotating and converting the bullets and lifting and taking out of the cabin by using the lifting and rotating mechanism 12, wherein the lifting and rotating mechanism 12 can select several mature transmission mechanisms and is arranged on a frame partition structure of the machine body 22 in coordination with the combined mechanism 11; the transmission mechanism adopts a scheme of selecting a motor and a rack transmission scheme or an electric cylinder transmission scheme with a motor. Fig. 14, example 4.

The design method of the omnidirectional missile frame 1 is suitable for being used on general aviation airplanes and various unmanned planes including multi-axis gyroplanes.

Several specific examples are given below to further illustrate the technical solution of the present invention.

Embodiment 1, to the air to ground scouting and beat integrative unmanned aerial vehicle.

The omnidirectional scouting and batting is developed from planar surrounding scouting and batting to spatial omnidirectional scouting and batting, and the adaptability of weapon emission is improved, as shown in fig. 10. The omnidirectional bullet rack 1 provides favorable emission conditions for realizing space omnidirectional batting. The design requirement is that the omnidirectional ammunition holder 1 is stored in the fuselage 22 as much as possible, and when the omnidirectional ammunition holder 1 is deployed from the fuselage 22 or the wall of the fuselage 22, the increased aerodynamic drag will reduce the flight speed moderately, but will facilitate the reduced speed flight required during the scout stage. Therefore, the design scheme of the omnidirectional bullet rack 1 is that the omnidirectional bullet rack is selectively stored in the fuselage 22 to reduce aerodynamic drag in the flight phase, and is released to be unfolded outside the fuselage 22 in the launching phase, but the safety requirement that the flight speed of the aircraft is far greater than the stall speed is met.

The controller 5 is used for carrying out the process control of the unfolding and weapon launching on the control object on the connected omnidirectional bullet rack 1. The control signal of controller 5 comes from the flight control system of airborne navigation, reconnaissance equipment and weapon sighting system that contains, and after the target signal transmits controller 5, automatic control flow that starts includes but not limited to: the method comprises the steps of determining a launching azimuth angle, automatically avoiding a launching blind area shielded by a machine body, controlling a hinge mechanism 21 of a support 2 to rotate relative to a machine body 22 and reach the azimuth angle within the range of a limit sensor, controlling a turntable mechanism 3 to rotate relative to the support 2 to build a launching condition, automatically or online selecting weapon types, binding target information including coordinates or images for the weapons, switching target images of optional reconnaissance equipment to a tracking state of a video device 6 on the support 2, waiting for launching instructions online or automatically launching the weapons immediately, completing a retracting process of the turntable mechanism and the support through an automatic or online reverse flow, and storing the turntable mechanism and the support in place. But the target position appears in the forward direction or the backward direction of the aircraft and can not be aligned to the target by only adjusting the azimuth angle of the omnidirectional missile frame 1, the navigation flight control system of the aircraft can control the aircraft to align to the target by the maneuvering flight matched turntable mechanism 3 or the loading mechanism 4.

In the aspect of weaponry, in an automatic or online mode, three typical seeker weapons and applicable scenarios can be selected:

1) Laser guidance is suitable for the condition that a target is single, and the mode of the notebook computer is adopted.

2) The infrared target is suitable for the situation that the target has a heat source and is not influenced after being transmitted, in particular to an aerial target.

3) And video guidance is suitable for the situation of cluster targets and visible images, and is not needed to be found after transmission.

Embodiment 2, remotely observe and beat integrative unmanned aerial vehicle.

The remote reconnaissance equipment is configured through the machine, and a remotely launched weapon is loaded, so that the requirement of beyond-visual-range remote combat is met. The photoelectric reconnaissance range of the traditional reconnaissance and hitting integrated unmanned aerial vehicle is within 15 kilometers, the radar reconnaissance range is within 50 kilometers, and the corresponding weapon launching distance is relatively short. There are many ways for the machine to realize remote reconnaissance and attack.

Firstly, airborne configuration technique reconnaissance equipment, reconnaissance distance generally is greater than 200 kilometers, and the small-size long-range reconnaissance of the optional low-cost air-drop of weapon hits integrative unmanned aerial vehicle, and the transmission distance generally selects near 100 kilometers, requires built-in unmanned aerial vehicle of carrier and nimble transmission, and typical cartridge-packed small-size aerial emission unmanned aerial vehicle is if "flick sword" unmanned aerial vehicle increases the journey, can make up many framves and install on omnidirectional bullet frame 1. The combat process comprises the steps that the ground station controls the machine, the airborne control system selects information of the technical reconnaissance system, the target position is bound and transmitted for the air-launched unmanned aerial vehicle, the target position can be bound again in the process, targets can be selected through online instructions and attacked through the instructions, and the air-ground online reconnaissance and combat integrated mode is achieved.

And secondly, the robot observes the shooting according to the book, namely the robot is used as an ammunition carrier or an information relay platform and is matched with a small unmanned aerial vehicle which is out of the air to fight. The ground station controls the small unmanned aerial vehicle to be used as an ammunition carrier, and the small unmanned aerial vehicle is suitable for carrying ammunition by the omnidirectional ammunition rack 1 to implement a near target launching mode according to target information of a small unmanned aerial vehicle, so that the cost of the ammunition for short-range launching is low. Especially in the urban lane fighting mode, the low-cost unmanned aerial vehicle which comes out provides a target position, and the machine launches weapons to strike. The structural remote investigation and combat modes all require the machine to have the instant launching condition of flexibly launching weapons, and the omnidirectional bullet rack 1 is more applicable.

Example 3, direct application of the general design.

An omnidirectional missile frame 1 applied to a composite wing unmanned aerial vehicle is selected, and the omnidirectional missile frame is similar to the application of a helicopter. As shown in fig. 15 and 16.

Main technical data of a typical composite wing drone: the maximum takeoff weight is 180 kilograms, the net load is more than 50 kilograms, the endurance time is 6 hours, the cruising speed is 120 kilometers per hour, the cruising height is 1000 meters, the length of the airplane body is 2.5 meters, the width of the airplane body is 0.3 meter, the height of the airplane body is 0.35 meter, and the ground clearance height of the belly is 0.3 meter; the diameter of the cylinder is 0.055 meter, the length of the cylinder is 0.8 meter, the total weight of the cylinder is 3.5 kilograms, the maximum firing range is 8 kilometers, the shooting height is more than 4 kilometers, and the launching unlocking force is 100N; 2 axles of support are 0.2 meters apart from the belly, and 3 axles of carousel mechanism are 0.15 meters apart from 2 axles of support (can merge 4 bullet barrels of installation), and the skew 0.15 meters of bullet barrel half-length center and 3 axles of carousel mechanism, its terminal surface of support 2 outer end both sides outstanding skeleton respectively apart from 0.4 meters and mountable minor diameter wheel of axis. 4-8 pieces of the whole machine can be loaded, and the machine is suitable for hitting targets such as light armor, no armor and the like.

The cartridge is one of the loading mechanisms 4, and is convenient to assemble, disassemble and launch. The omnidirectional bullet frame 1 is made of metal and composite materials.

The composite wing unmanned aerial vehicle is a fixed wing aircraft combined electric rotorcraft, and has the advantage of optimized performance of vertical take-off and landing and cruise of fixable wings compared with a single fixed wing unmanned aerial vehicle or electric rotorcraft. The time of sailing can be increased to 4-6 hours, and the loading weight is increased to 20-50 kg. The fixed wing organism of compound wing unmanned aerial vehicle adopts the overall arrangement of single wing usually, installs electronic gyroplane on the cooperation wing, and when the little condition of compound wing unmanned aerial vehicle load-carrying capacity, the slewing mechanism that can install and release can not be installed to the vaulting pole structure of motor screw. A large amount of batteries, fuel oil and task equipment are arranged in a small-size body of the composite-wing unmanned aerial vehicle, and the omnidirectional missile frame 1 is generally not suitable for being used in the body.

The omnidirectional missile frame 1 is installed near the center of gravity of a fixed wing body of the compound wing unmanned aerial vehicle and is external, an upward launching channel of a weapon can be shielded by an upper single wing and an electric gyroplane, therefore, an integrated omnidirectional missile frame mechanism is designed and observed outside the center of gravity of the compound wing unmanned aerial vehicle body, III and II quadrants on the left and right sides in the forward navigation are generally adopted to launch the weapon, and the forward and backward launching channel in the course is not limited. The unfolding angle of the support 2 of the external omnidirectional missile frame 1 relative to the fuselage can be in a range from vertical to horizontal, and II-III quadrant weapon launching is realized through the turntable mechanism, wherein the omnidirectional missile frame 1 on the left side of the forward flight heading can launch the weapon to the II quadrant, and the right side can launch the weapon to the III quadrant, so that the rotation of the support 2 or the turntable mechanism 3 enables the loading mechanism 4 to form a launching condition, namely, aim at a target. The special design may partially satisfy the emission in quadrants I and IV as shown in fig. 10.

The composite wing unmanned aerial vehicle is suitable for being applied by using the omnidirectional missile frame 1 to load small ammunition externally, and meets the low-cost requirement required by short-range accompanying combat. The omnidirectional missile frame 1 is applied to a helicopter, and the installation and launching conditions of the omnidirectional missile frame are similar to those of a composite wing unmanned aerial vehicle.

Example 4 Combined mechanism of Universal design

The universal design scheme can expand the application range of the omnidirectional missile rack 1 or increase the missile loading capacity. The combination mechanism 11 for increasing the number of the omnidirectional ammunition frames 1 in the machine body 22 is an optimized scheme for the inside installation of the omnidirectional ammunition frames 1, as shown in fig. 14. Comparing design schemes:

1) Inside fuselage 22 near the square to three sets of omnidirectional bullet racks 1 of equilateral triangle combination constitute combined mechanism 11, and the loading quantity is one set more than the horizontal closed assembly, and is more reasonable to the utilization ratio in fuselage 22 space to, for reducing the pneumatic resistance of fuselage 22, the inside width X height dimension proportion of fuselage 22 is optional: 1x0.9. The rotation of the combined mechanism 11 in the machine body 22 and the lifting in and out of the machine body 22 can be realized by designing a set of control of the lifting and rotating mechanism 12. The lifting and rotating mechanism 12 can be connected with the combined mechanism 11 by using a plurality of mature transmission mechanisms, is arranged on the frame structure of the machine body in a coordinated way with the combined mechanism 11, and comprises a transmission mechanism of a motor and a rack or an electric cylinder transmission mechanism with a motor.

2) Four sets of omnidirectional ammunition racks 1 can be combined in a square shape in the machine body 22, and the height of the machine body 22 can be reduced by 30 percent. But the amount of loading is reduced to achieve rotation of four sets of omnidirectional ammunition carriers 1. This scheme is not preferable.

3) The circular combined loading mechanism is designed in the machine body 22, the loading amount is large, but the turntable mechanism 3 cannot be reserved for each weapon, the cost is high, the structure weight is heavy, and the omnidirectional launching condition cannot be realized after the turntable mechanism 3 is cancelled. This scheme is not preferable.

The above embodiments are merely illustrative of the technical idea of the present invention, and it is apparent to those skilled in the art that the present invention is not limited to the details of the above embodiments, and the present invention can be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Claims (10)

1. A design method of an omnidirectional missile frame of a scouting and hitting airplane is characterized by comprising the following steps: the support (2) which can rotate a certain range relative to the machine body (22) is designed to be used as a bearing structure of the omnidirectional bullet rack (1); the loading mechanism (4) of the omnidirectional bullet rack (1) is designed on a turntable mechanism (3), and the loading mechanism (4) is designed to rotate together with the turntable mechanism (3); meanwhile, the turntable mechanism (3) is designed to be connected to the support (2) through the rotating mechanism (31), and the servo motor drives the turntable mechanism (3) to rotate relative to the support (2), so that the launching angle adjustment of the loading mechanism (4) in the plane and three-dimensional directions is realized.

2. The design method of the omnidirectional missile frame of the scout and attack aircraft as claimed in claim 1, wherein the method comprises the following steps: support (2) design is for adopting hinge mechanism (21) to connect at fuselage (22) structurally, and support (2) can be installed in the left and right sides of fuselage (22) structure symmetrically, rotates certain extent for fuselage (22) through hinge mechanism (21) to the design includes following arrangement mode:

1) Is arranged in the machine body (22);

2) Is unfolded outside the fuselage (22);

3) Often externally located to the side walls of the fuselage (22).

3. The design method of the omnidirectional missile rack of the scout and attack aircraft as claimed in claim 1, wherein the design method comprises the following steps: the omnidirectional bullet rack (1) is controlled by designing a controller (5); the controller (5) is composed of a control component and a plurality of sensors, and at least comprises:

1) The control component of the omnidirectional bullet rack (1) can be operated in time according to the target information;

2) And the limiting sensor is used for limiting the rotation range of the bracket (2) or the turntable mechanism (3).

4. The design method of the omnidirectional missile frame of the scout and attack aircraft as claimed in claim 3, wherein the method comprises the following steps: the controller (5) is installed on the machine body (13) and is connected with a control object through a wire harness, and the connection and control mode comprises the following steps:

1) A servo motor connected with a hinge mechanism (21) of the bracket (2) to control the bracket (2) to rotate a certain angle relative to the machine body (22);

2) A servo motor connected with the turntable mechanism (3) is used for controlling the turntable mechanism to rotate a certain angle relative to the bracket (2);

3) Connecting a loading mechanism (4) to control omnidirectional firing of the weapon;

4) A video device (6) connected with the turntable mechanism (3) is used for pushing information of the target to be hit;

5) The controller (5) controls the flow of unfolding or collecting the omnidirectional bullet rack (1) according to the action flow of aiming at the target position.

5. The design method of the omnidirectional missile frame of the scout and attack aircraft as claimed in claim 1, wherein the method comprises the following steps: the pneumatic resistance is reduced by the design of the cabin door (7); the design method of the hatch (7) comprises the following steps:

1) Is connected to the bracket (2);

2) Is designed integrally with the structure of the bracket (2);

3) The cabin door (7) is independently designed into a sliding cabin door (7) and is connected with a sliding chute corresponding to the structure of the fuselage (2), and the cabin door (7) can slide back and forth along the course of the fuselage (2) to be opened;

4) Sliding cabin doors (7) are designed corresponding to a plurality of groups of omnidirectional bullet racks (1), are installed according to the height difference of upper and lower parts, can move forwards or backwards relatively, and are opened sequentially according to the unfolding sequence of the omnidirectional bullet racks (1).

6. The utility model provides a scouting and beating aircraft qxcomm technology bullet frame which characterized in that: the omnidirectional bullet rack (1) is arranged on a navigation airplane or an unmanned aerial vehicle and comprises a support (2), a turntable mechanism (3), a bullet loading mechanism (4), a controller (5), one or the combination of more than two mechanisms of a video device (6) and a cabin door (7); wherein, the bracket (2) is connected to the structure of the machine body (22) through a hinge mechanism (21), the hinge mechanism (21) of the bracket (2) comprises a transmission component, a servo motor and a hinge seat (23) connected to the structure of the machine body (22); the turntable mechanism (3) is connected to the support (2) through a rotating mechanism (31), and the loading mechanism (4) is connected to the turntable mechanism (3); the controller (5) is arranged on the machine body (13) and is connected with a control object through a wire harness; the video device (6) is connected with the turntable mechanism (3), synchronously moves with the turntable mechanism (3), has an unobstructed view angle and points to a target; the hatch (7) is connected to the bracket (2) or is structurally integrated with the bracket (2).

7. The omnidirectional cupped missile rack of claim 6, wherein: the support (2) rotates relative to the fuselage (22) through a hinge mechanism (21) and is unfolded outside the fuselage (22), or the support (2) is installed on the structure of the fuselage (22) through the hinge mechanism (21), and the support (2) is externally arranged on the fuselage (22), namely, is collected on the outer side wall of the fuselage (22) and is not collected in the fuselage (22).

8. The omnidirectional missile rack of a scout and attack aircraft of claim 6, wherein: the rotating mechanism (31) comprises a servo motor and a mounting structure and is connected with the bracket (2), and the rotating mechanism (31) drives the turntable mechanism (3) to rotate 0-180 degrees or 0-360 degrees relative to the bracket (2).

9. The omnidirectional missile rack of a scout and attack aircraft of claim 6, wherein: the wing padlock (27) and the upper hanging rack (28) are combined and connected with the wing (26), the two are designed separately or integrally, and the upper hanging rack (28) is internally provided with a motor to drive the omnidirectional missile frame (1) to rotate so as to provide the yaw orientation of the weapon; the lower hanging rack (32) is internally provided with a motor to drive the omnidirectional missile rack (1) to rotate so as to provide the pitching direction of the weapon.

10. The omnidirectional missile rack of a scout and attack aircraft of claim 6, wherein: the side fairing (33) is geometrically wedge-shaped along the airflow direction with two sharp ends and a wide middle.

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