CN110329515A - It is a kind of to examine the design method and system for making integrated aircraft - Google Patents

Abstract

The invention discloses a design method and system for an integrated reconnaissance and attack aircraft. The integrated reconnaissance and strike aircraft is designed to introduce long-range and day-and-night reconnaissance equipment including technical reconnaissance and radar reconnaissance in addition to photoelectric reconnaissance, and interact with various weapons. All-round attack; the aircraft route is designed to continuously attack one or a group of air or ground and sea targets in a specific direction by using a figure-of-eight circling flight; the airborne weapons are designed to be built into the cabin at ordinary times. The salient feature of the present invention is that the omnidirectional launch of the launching type weapon is realized by installing the weapon hanger. The reconnaissance and strike aircraft adopt the circling flight of the figure-of-eight route, and the airborne weapons are continuously pointed at the target, which can realize the basic combat pattern of continuous omnidirectional reconnaissance and strike. A larger launch angle, such as 135 degrees or even larger, supports the aircraft to turn around in time to implement a shorter figure-of-eight route, which can win greater combat effectiveness.

Description

A design method and system for a reconnaissance-strike integrated aircraft

technical field

The invention belongs to the technical field of multi-mission aircraft for reconnaissance and combat in the aviation field, in particular to the technical field of manned aircraft, unmanned aerial vehicle systems and co-pilot aircraft with the integrated purpose of reconnaissance and strike.

Background technique

The omnidirectional reconnaissance and strike integrated aircraft is referred to as the omnidirectional reconnaissance and strike aircraft, including unmanned aerial vehicles and manned aircraft or others. The weapon attack of the traditional surveillance and strike integrated UAV is based on the attack on the flying forward target. No matter how many weapons are hung, the occupying time for the forward target attack is relatively small, which is suitable for low-intensity battlefield confrontation or anti-terrorism operations. At the same time, the reconnaissance and strike efficiency of traditional reconnaissance and strike aircraft is low. The photoelectric reconnaissance distance is about 10km, and all-weather operations are limited. Hanging under the wing or under the fuselage will affect the aerodynamic performance of the UAV. This design is only suitable for UAVs with relatively low ceiling and speed.

In the application document submitted by the applicant on November 30, 2017, the application number is 201711241305.1, and the title of the invention is a control method and system for an integrated aircraft for surveillance and strike, which discloses in detail the technical composition of the surround or omnidirectional surveillance and strike aircraft , similarly, another invention-creation submitted by the applicant, the application number is 201811107991.8, and the name of the invention-creation is an omni-directional reconnaissance and strike aircraft transmission ammunition chain system. The content mainly proposes the technical method of the weapon transmission ammunition chain system. The technical solution for omnidirectional reconnaissance and strike does not include targets in the air. These two patent applications do not involve the design method of omnidirectional reconnaissance and strike aircraft weapon pylons, and do not introduce the application of reconnaissance and strike technology for technical reconnaissance and radar reconnaissance. It provides a technical solution for simultaneous reconnaissance and strikes against multiple different targets in the air. Therefore, it is necessary to further creatively expand and improve the technical solutions involved in these two patent applications, in order to form a relatively complete new type of omnidirectional reconnaissance and strike aircraft system for omnidirectional reconnaissance and strikes against the air and simultaneous strikes against multiple targets. It can further significantly improve the combat effectiveness of the omnidirectional reconnaissance and strike aircraft.

Contents of the invention

The object of the present invention is to propose a design method and system for an integrated aircraft of reconnaissance and attack, so as to overcome the deficiencies in the prior art.

Detailed technical description:

The design method of the integrated reconnaissance and strike aircraft of the present invention is to design the reconnaissance and strike integrated aircraft to introduce long-range and day and night reconnaissance equipment including technical reconnaissance and radar reconnaissance in addition to photoelectric reconnaissance, and interact with various weapons to carry out all-round strikes; The flight path of the aircraft is designed to continuously attack one or a group of air or ground and sea targets in a specific direction by circling flight in a figure-of-eight flight path; the airborne weapons are designed to be built into the cabin at ordinary times.

The omnidirectional reconnaissance and strike integrated aircraft system designed according to the above method includes an aircraft structure, a weapon pylon installed on the aircraft structure, an airborne weapon installed on the weapon pylon, a reconnaissance load and an airborne system installed on the aircraft structure, And the ground monitoring station supporting the airborne system.

The aircraft structure is divided into the fuselage cabin, the front cabin of the nose, the lower cabin of the belly and the upper cabin of the back. The design scheme can divide the structure of the fuselage compartment participating in the force transmission into front, middle and rear fuselages, wings and empennage; the front cabin of the nose is connected to the front end of the front fuselage; The bottom of the fuselage; The lower cabin of the belly can be changed to other purposes, such as cargo cabin, pesticide cabin, and target drone cabin.

The weapon pylon can be installed on the aircraft structure, including the front compartment of the nose, the lower compartment of the belly and the upper compartment of the back of the fuselage, and under the wings of the fuselage compartment.

The design of the weapon pylon includes: the pylon structure, on which multiple weapons can be installed, and can be installed in layers, especially the mixed installation of various types of weapons; the fairing installed on the pylon structure, inside the fairing can be installed Self-contained aiming illuminator or electronic control unit; mounting lugs for installing airborne weapons; lifting mechanism for connecting the weapon hanger to the aircraft structure; electric control box and servo servo mechanism. The weapon pylon can be designed with its own sighting illuminator and electronic control unit. The weapon pylon can perform dual drive: one is to accept the reconnaissance load and transfer the target parameters to the electronic control unit to follow the target to lock the target, and then control the weapon pylon The observation and aiming illuminator can continuously lock and track the target, which constitutes a double drive for the weapon pylon; secondly, the self-contained observation and aiming illuminator and the electronic control unit of the weapon pylon can independently guide and drive the weapon pylon to track and stabilize the target, realizing Multiple target tracking.

In the installation scheme of the weapon pylon on the aircraft structure, the general design is to install the weapon pylon near the center of gravity of the aircraft structure, or design a design scheme that can adjust the center of gravity of the aircraft structure to adapt to the launch of airborne weapons, or to adjust the center of gravity of the aircraft structure. Mounted weapons are fired managed to ensure center of gravity balance. Similarly, flame deflectors can be designed for the tail flame generated by the launch of airborne weapons.

The airborne weapons are installed on the weapon pylon and arranged in one or more parts of the aircraft structure, including the front compartment of the nose, the lower compartment of the belly and the upper compartment of the back of the aircraft, and under the wings of the fuselage compartment; Equipped with three types of main airborne weapons suitable for omnidirectional launch, one is launch-type missiles that can be launched with the weapon pylon, such as laser irradiation or radar-guided missiles, aviation machine guns, and the other is that the antenna can be installed in the front cabin of the nose electromagnetic disruptors.

The design scheme of each part is: small missiles or electromagnetic jammer antennas can be installed in the upper space of the front cabin of the nose; launchable missiles, guided or unguided bombs, aviation Machine guns and air-dropped drones, where the installation of aviation machine guns can choose a weapon pylon with a two-dimensional follow-up servo mechanism. In addition, when the weapon pylon in the lower compartment of the belly is used for forward launch, laser-guided or stapled Guided bombs with target coordinates, as well as drop-type weapons; in the interior and exterior spaces of the upper compartment on the back of the aircraft, a weapon pylon with a two-dimensional follow-up servo mechanism can be selected; in the inner space of the upper compartment on the back of the aircraft, a weapon pylon can be optionally installed The simplification mechanism of the structure is the combination of vertically launched missiles and their launch boxes, which are launched out of the cabin through opening or membrane rupture; the weapon pylons are connected under the wings of the fuselage compartment, and the same type of airborne missiles as the belly compartment can be installed. arms.

The reconnaissance load can be optoelectronic load; technical reconnaissance load; radar load; choose one or a combination of the three to install on the aircraft structure.

Each control unit of the reconnaissance load supports the control of the aforementioned weapon pylons, that is, it supports omnidirectional attack on one target or multiple targets at the same time and avoids hitting the same target. Among them, the control units for photoelectric load, technical reconnaissance load and radar load for signal processing and servo control are respectively connected to the electronic control box of the weapon pylon with cables. When the control unit of each reconnaissance load is selected After the locking parameters of the target are transmitted to the electronic control box, the electronic control box guides the direct drive weapon pylon to align with the target according to the coordinates of the selected target and is in a follow-up launch state, waiting for the execution of the airborne system command to launch the weapon; or guide the observation and aiming irradiation The device continues to track and stabilize the target, controls the weapon pylon to keep aiming at the target and is in a follow-up launch state, waiting for the execution of the airborne system command to launch the weapon, while the sighting illuminator and electronic control unit on different weapon pylons can Continuously lock and track the selected target independently, so as to realize the stable aiming and launching state of multiple targets at the same time; therefore, the associated action of a reconnaissance load and the electronic control unit can constitute a double drive for the weapon pylon; the above directly Both the driving and dual driving processes transmit the target information back to the subsystems of the airborne system, such as the flight control subsystem, and then distribute it to the ground monitoring station, thus closing and completing the "human online" launch of weapons against the target.

The design scheme of a launch procedure for the launch process is divided into: 1) The flight control subsystem of the airborne system follows the scheduled launch process and according to the target information received by the ground monitoring station, the "human online" determines the launch timing and issues instructions and sends to the electronic control box of the weapon pylon for launch, or according to the target information of the reconnaissance payload, "human off-line" automatically generates launch instructions and sends them to the electronic control box of the weapon pylon for launch, so that one or more targets can be targeted separately or Simultaneously launch strikes in all directions independently; and set the necessary launch conditions to avoid launch obstacles; 2) The electronic control box of the weapon pylon sends the information to the flight control subsystem of the airborne system according to the information on target tracking and forwards it to the ground monitoring The station obtains the "person-on-line" launch command and then the electric control box controls the launch strike; or directly generates the launch command and executes the launch according to the predetermined launch criteria of the electric control box; and also sets the necessary launch conditions to avoid launch obstacles.

The flight control subsystem of the airborne system is connected with the electronic control box of the reconnaissance load and the weapon pylon through cables, forming the information and command connection of the aforementioned direct drive and dual drive. The weapon management subsystem connected to the flight control subsystem is connected to the electronic control box of the reconnaissance load and the weapon pylon through cables to form an information and command connection.

For the flight control subsystem, navigation subsystem and data link subsystem of the airborne system, the design changes shall be carried out according to this article:

1) For the flight control subsystem, regardless of whether its original computer module is a single-redundancy system structure or a redundancy system structure, this article introduces a new scheme of a dual-module redundancy system structure of the flight management module + flight control module. Among them, the flight The design scheme of the management module and the flight control module can adopt the hot backup of the prefabricated functions of flight control and emergency response; the flight management module focuses on the man-machine interface and the auxiliary monitoring flight and the process management and monitoring of task execution; The flight control module focuses on flight control and acceptance of flight management module instructions or parameter adjustments; at the same time, the detection software covering the same airborne sensors is introduced to jointly build a redundant system structure in which the two modules communicate with each other and detection software assists in judgment.

2) To adapt to the change of the flight control subsystem, for the navigation subsystem, the navigation data information is introduced into the flight management module and the flight control module, and the navigation data information is deeply coupled and applied in the flight management module; The calculation time delay of the data improves the calculation accuracy, and it can be applied as a flight management module with the help of a high-performance navigation computer.

3) For the airborne data link, parallel data links are used so that the parallel data links can work in division or alternately; support the general data link of one station with multiple machines or one machine with multiple stations, and time-division or frequency-division coding to support one station with multiple machine data link.

The parallel data link installed at the ground monitoring station is consistent with the data link subsystem used in the above-mentioned changes of the airborne system; the operation interface supports manual command control, or authorizes the airborne system "human off-line" automatic control process monitoring and emergency control operation , supports the application of one station with multiple machines or one machine with multiple stations; it can be configured to support the ADS-B ground base station used in non-military operations for daily training.

The above design scheme is applied to the UAV system, and the manned aircraft becomes a special aircraft by adding and modifying weapon pylons and applicable airborne systems. It is suitable for anti-terrorism or combat in the army, armed police, border and coastal defense.

The present invention proposes a design method and system suitable for carrying out reconnaissance and attack on the surrounding space of the aircraft or all-round targets. In addition to photoelectric reconnaissance, long-range and day-and-night reconnaissance equipment such as technical reconnaissance and radar reconnaissance are introduced to interact with various weapons for all-round blow. In particular, the aircraft can continuously strike one or a group of air or ground and sea targets in a specific direction by adopting a 8-shaped circling flight, and can strike multiple different targets at the same time. It is suitable for high-intensity battlefield confrontation, and is also suitable for general-intensity battlefield confrontation or anti-terrorism operations. The airborne weapons can usually be built in the lower cabin of the belly, so that the impact on flight performance is reduced.

Description of drawings

Figure 1 is a schematic diagram of a weapon pylon with a horizontally rotating servo mechanism, a single-layer missile, and a front view;

Fig. 2 is a schematic diagram of the weapon pylon of the horizontal rotation servo mechanism, single-layer missile, attached view;

Fig. 3 is a schematic diagram of the weapon pylon of the horizontally rotating follow-up servo mechanism, a double-layer rail missile, and a front view;

Fig. 4 is a schematic diagram of the weapon pylon of the horizontally rotating follow-up servo mechanism, a double-layer rail missile, and attached view;

Figure 5 is a diagram of a weapon pylon with a horizontally rotating horizontal servo mechanism, a double-layer barreled missile, and a front view;

Fig. 6 is a schematic diagram of the weapon pylon of the horizontally rotating horizontal servo mechanism, double-layer barreled missiles, and attached view;

Fig. 7 is the weapon pylon illustration of horizontal and pitching rotation follow-up servomechanism, front view, (the rotating shaft of pitching rotation mechanism is near the center of gravity section of weapon pylon);

Fig. 8 is the weapon pylon illustration of horizontal and pitching rotation follow-up servomechanism, attached view, (the rotating shaft of pitching and rotatable mechanism is near the center of gravity section of weapon pylon);

Fig. 9 is a schematic view of the weapon pylon of the horizontal and pitch rotation servo mechanism, the front view, (the rotating shaft of the pitch rotation mechanism is at the front end of the center of gravity section of the weapon pylon);

Fig. 10 is the weapon pylon diagram of horizontal and pitching rotation follow-up servomechanism, attached view, (the rotating shaft of pitching and rotating mechanism is at the front end of the center of gravity section of weapon pylon);

Fig. 11 is the installation diagram of the weapon pylon on the aircraft wing;

Figure 12 is a schematic illustration of the center of gravity position of a plurality of weapon pylons installed outside the belly of the mid-wing aircraft;

Figure 13 is a schematic diagram of the installation position of the upper and lower weapon pylons/vertical cabins/photoelectric loads;

Fig. 14 is a divided diagram of various parts of the aircraft structure.

The marks in the accompanying drawings are: 1-lifting mechanism, 2-following servo mechanism, 3-horizontal rotation pylon and pylon structure, 4-fairing, 5-airborne weapon, 6-observation and aiming illuminator, 7- Pitching rotation mechanism and pylon structure, 8-Electronic control unit, 9-Drive hinge of pitching rotation mechanism, 10-Weapon pylon transmission chain, 11-Transmission chain control mechanism, 12-Cabin on the back of the machine and weapon pylon, 13- Fuselage compartment, 14-vertical launch missile and vertical launch cabin, 15-photoelectric load, 16-weapon pylon, 17-flame deflector, 18-hanging lug, 19-electric control box, 20-front cabin of the nose, 21-back upper cabin, 22-fuselage lower cabin, 23-wing, 24-tail.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

In the description of the present invention, it should be noted that, unless otherwise specified and limited, the terms "installed", "set with", "sleeved/connected", "connected", etc. should be understood in a broad sense, such as " Connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediary, and it can be an internal connection between two components. connectivity. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

Embodiments of the invention:

As shown in Figure 1-13: a design method and system for an omnidirectional reconnaissance and strike integrated aircraft include an aircraft structure; a weapon pylon 16 installed on the aircraft structure, and an airborne weapon 5 installed on the weapon pylon 16. Reconnaissance payloads and on-board systems installed on the aircraft structure, and ground monitoring stations adapted to the on-board systems. The airborne system is other functional systems installed on the aircraft structure except the weapon pylon 16, the airborne weapon 5 and the reconnaissance load, including but not limited to navigation and flight control subsystems, sensor subsystems, data link subsystems, power subsystem.

Aircraft structure is divided into fuselage cabin 13, nose front cabin, belly lower cabin and aircraft back upper cabin. The design scheme can divide the structure of the fuselage cabin 13 participating in the force transmission into front, middle and rear fuselages, wings and empennages, wherein the front, middle and rear fuselages can be designed according to the overall structure, and the middle fuselage includes the fuselage cabin 13, The lower compartment under the belly and the upper compartment on the back of the aircraft can be collectively referred to as the fuselage compartment 13. The main molecular system of the airborne system is installed on the fuselage compartment 13, the layout design of the wings meets the installation of the weapon pylon 16 and the launch of the airborne weapon 5 minimizes the blocking of structural parts; the front cabin of the nose is connected to the front fuselage At the front end of the heading, the reconnaissance equipment is installed in the front cabin of the nose half-buried to reduce the shielding of the launch of the airborne weapon 5 protruding downward from the lower cabin of the belly, and the upper space of the front cabin of the nose can be attached. The lower cabin of the belly is connected to the bottom of the front, middle and rear fuselage, and is not designed to bear the force transmission of the fuselage compartment 13, so as to facilitate the change of the structural space, and is mainly used for installing the weapon pylon 16 and the rail type and the barrel type Launch missiles, guide and coordinate bombs, and technical reconnaissance and radar reconnaissance loads; Reserving a suitable space is mainly used to install two-dimensionally rotated weapon pylons 16 and anti-aircraft weapons, and vertically launching missiles and vertically launching cabins 14 are installed. The lower cabin of the belly can be changed to other purposes, such as cargo cabin, pesticide cabin, and target drone cabin.

The weapon pylon 16 is installed on the aircraft structure, including the front compartment of the nose, the lower compartment of the belly and the upper compartment on the back of the aircraft, and under the wing of the fuselage compartment 13.

The weapon pylon 16 design includes:

The hanger structure is mainly made of light materials and structures. Multiple weapons can be installed on it, and it can be installed in layers, especially the mixed installation of various types of weapons, such as the installation of multiple weapons in a single layer or multiple layers in two layers, such as irradiation Type or guided type mixed, the option of the weapon to be launched is completed by the command of the weapon management subsystem of the airborne system;

The fairing 4 that cooperates with the hanger structure can be installed in the fairing 4 with a self-contained aiming illuminator 6 or an electronic control unit 8; as shown in accompanying drawings 7-10.

Install the weapon hanger 18 of the airborne weapon 5, which can be designed as a fast loading and unloading structure;

The hoisting mechanism 1 that weapon hanger 16 is connected with aircraft structure can drive weapon hanger 16 relative to the plane of fuselage compartment 13 horizontal datum lines to carry out horizontal and vertical lifting by electric mechanism, and vertical lifting function can be used for the collection of weapon hanger 16 to reduce Aerodynamic resistance can also be used for airborne weapon hanger 16; there are many design schemes for optional lifting mechanism 1, which can adopt parallelogram plus power cylinder mechanism, electric cylinder moving mechanism, electric gear worm screw mechanism, hydraulic electric moving mechanism, electric Steel rope mechanism; shown in accompanying drawing 1-2.

The electric control box 19 receives the instruction parameters of the reconnaissance load by the electric control box 19 and instructs the electric mechanism to control the follow-up servo mechanism 2 to drive the weapon pylon 16 to rotate at a horizontal angle or a pitch angle, and the horizontal angle rotation is relative to the horizontal reference of the fuselage cabin 13 The plane of the line is rotated parallel to 360 degrees to provide the azimuth angle of the omnidirectional launch of the airborne weapon 5, which is performed by the horizontal rotation mechanism 2 and the horizontal rotation pylon 3 connected to the lifting mechanism 1; the pitch angle rotation is relative to the fuselage cabin 13 The plane of the horizontal reference line is used for pitch angle rotation, and the general pitch angle range is about 45 degrees upward or downward, which is performed by the pitch rotation mechanism and the hanger structure 7 installed on the horizontal rotation hanger and the hanger structure 3; the pitch rotation mechanism And the design scheme of pylon structure 7 can be divided into two kinds, one is that the pitching rotation axis is arranged near the section of the center of gravity of the weapon pylon 16, and the driving design scheme is such as a motor, as shown in accompanying drawings 7-8; the other is that the pitching rotation axis is arranged At the front end of the section of the center of gravity of the weapon hanger 16, the driving design scheme is like an electric cylinder, as shown in accompanying drawings 9-10; there are many driving design schemes for the optional follow-up servo mechanism, and various types of motors, rack and pinion chains can be used, Rocker arm type driven by electric cylinder or hydraulic pressure, electromagnetic drive;

An auxiliary sighting system for photoelectric sighting and laser irradiation can be designed on the weapon rack 16, and an electronic control unit 8 that can control the target tracking and sighting can be provided. As shown in accompanying drawings 7-10.

Therefore, the weapon pylon 16 can execute two driving modes to aim at the target and launch the weapon: one is the dual driving mode, that is, accepting the reconnaissance load and handing over the target parameters to the electronic control unit 8 to follow and lock the target, and then controlling the observation of the weapon pylon 16. The aiming illuminator 6 continues to lock and track the target, forming a double drive to align the weapon pylon 16; the second is a direct drive method, that is, accepting the reconnaissance load and handing over the target parameters to the electronic control unit 8 to follow the target, or by The self-contained aiming illuminator 6 and the electronic control unit 8 of the weapon pylon 16 can independently guide and drive the weapon pylon 16 to track and aim at the target.

Weapon pylon 16 is installed on the aircraft structure in the scheme, to control the center of gravity of the aircraft structure after the launch of the airborne weapon 5. The general design is that the weapon pylon 16 is installed near the center of gravity of the aircraft structure (1) so as not to be affected or reduced. The center of gravity of the airborne weapon 5 is changed after launch; accompanying drawing 12 designs a kind of design scheme that adapts to the launch of the airborne weapon 5 and adjusts the center of gravity of the aircraft structure: The weight changes and can automatically move forward and backward to adjust the center of gravity of the aircraft. The movement of the center of gravity of the weapon pylon 16 is designed as a separate or interconnected automatic movable mode; The launch sequence and quantity of the launcher are managed by the center of gravity balance; or the weapon pylon 16 after launching the airborne weapon 5 can be dropped by the center of gravity principle driver, which can reduce the weight or reduce the aerodynamic resistance. Similarly, the tail flame produced by the launch of the airborne weapon 5 can be solved by designing the flame deflector 17, and the installation position of the flame deflector 17 is shown in Figure 13 for illustration. In a word, the installation of the weapon pylon 16 on the aircraft structure should meet the technical requirements of peripheral vision, balanced center of gravity, non-destructive impact and harmless tail flame.

The airborne weapon 5 is installed on the weapon pylon 16 and can be arranged on one or more positions of the aircraft structure together with the weapon pylon 16 (according to the use characteristics), including the front cabin of the nose, the lower cabin of the belly and the upper cabin on the back of the aircraft. , and under the wing of the fuselage compartment 13; for the weapon pylon 16, three types of main airborne weapons 5 that are suitable for omnidirectional launch are selected, and the one is an irradiation type or guided missile that can be launched with the weapon pylon 16. Aiming aviation machine guns, laser irradiators, anti-radiation missiles or air-launched drones, the second is the simplified mechanism of the weapon pylon structure, that is, vertically launching missiles, warning fireworks or infrared decoy bombs, and the third is that the antenna can be installed on the nose Forward-facing electromagnetic jammer.

The design scheme of each part is, can install the small-sized missile of launch distance 2-5km in the airborne weapon 5, or the antenna of the electromagnetic jammer in the upper space of the front compartment of the nose; Rail-type or barrel-mounted missiles launched in the airborne weapon 5, guided or unguided bombs, aviation machine guns and air-dropped drones, wherein the weapon pylon 16 with a two-dimensional follow-up servo mechanism 2 can be selected for installing the aviation machine gun and The fairing 4 can be designed to reduce aerodynamic resistance. In addition, when the weapon hanger 16 in the lower compartment of the belly is used for forward launch, guided bombs with laser guidance or binding target coordinates can be added, as well as drop-type weapons; on the back of the machine In the interior and exterior spaces of the cabin, the weapon pylon 16 of the two-dimensional follow-up servo mechanism 2 can be preferably selected and barreled missiles or aviation machine guns can be installed to perform omnidirectional launch with horizontal azimuth rotation and a certain pitch angle. The two-dimensional weapon pylon 16 or the airborne weapon 5 can use the fairing 4 to reduce the aerodynamic resistance; in the cabin interior space on the back of the machine, the combination of vertically launched missiles and their launch boxes can also be selected, and the combination can be achieved by opening the combined hatch. Open the cabin, or puncture the dust-proof and water-discharging film and rupture the membrane, and then launch the missile out of the cabin. The launch distance of the anti-aircraft missile used for small targets is not less than 2km; the weapon pylon 16 is connected under the wing of the fuselage cabin 13, which can be installed Onboard weapons of the same type as in the underbelly compartment5.

The reconnaissance load can choose the photoelectric load 15, through the mechanical movement of the photoelectric servo mechanism, it can identify, track and lock the target, and cooperate with laser ranging and irradiation to generate target parameters; the technical reconnaissance load, through the active or passive detection of the antenna and the processing of the target signal , to generate target parameters; radar load, active detection of the target through the direction of the antenna and signal processing, to generate target parameters; choose one or a combination of three to install on the aircraft structure; optional other suitable for installation on the aircraft structure type of reconnaissance payload.

Each control unit of the reconnaissance load supports the control of the aforementioned weapon pylon 16 (i.e., it supports omnidirectional attack on one target or multiple targets at the same time and avoids hitting the same target), wherein the signal processing of the photoelectric load 15 The photoelectric control unit with servo control, the signal processing and servo control technical detection control unit of the technical reconnaissance load, the radar control unit with the signal processing and servo control of the radar load are respectively connected with the electric control box 19 of the weapon pylon 16 by cables After each control unit of the reconnaissance load transmits the locking parameters of target selection to the electric control box 19, the electric control box 19 can directly drive the weapon pylon 16 to align with the target and be in the firing state, or the observation and aiming illuminator 6 The secondary drive continues to be in the launch state for the target tracking control; and the target information is transmitted back to the subsystems of the airborne system such as the flight control subsystem, and then distributed to the ground monitoring station; wherein, the photoelectric load 15 and the technical detection load can be The pitch angle of the locked target is handed over to the electronic control box 19, so that the space targets above and below the horizontal reference line of the fuselage compartment 13 can be launched and attacked. The radar load only hands over the parameter information to the electric control box 19 for the pitch angle of the locked target. information, thus only launch strikes on space targets below the horizontal reference line of the fuselage compartment 13; for space targets near the horizontal reference line of the fuselage compartment 13, the aircraft structure can be controlled to circle the target or leave the target with a small slope to launch strikes .

A design of the launch process is divided into: 1) The flight control subsystem of the airborne system follows the scheduled launch process and according to the target information received by the ground monitoring station, the "human online" determines the launch timing and issues instructions and sends them to the weapon pylon 16 of the electronic control box 19 to execute the launch, or according to the target information of the reconnaissance payload, "human off-line" automatically generates a launch command and sends it to the electronic control box 19 of the weapon pylon 16 to perform launch, so that one or more targets can be targeted, respectively or Simultaneously launch strikes independently in all directions; among them, set the necessary launch conditions to avoid launch obstacles, such as the vertical tail or landing gear of the fuselage compartment 13; It is sent to the flight control subsystem of the airborne system and forwarded to the ground monitoring station to obtain the "man-on-line" launch command, and then the electronic control box controls the launch strike; or it is directly generated according to the predetermined launch criteria of the airborne system or the electronic control box 19 The launch instruction is executed and the launch is executed; wherein, necessary launch conditions are also set to avoid launch obstacles.

The direct drive and dual drive of the reconnaissance load and the electronic control box 19, especially the dual drive provided by the technical reconnaissance load and the radar load, have changed the strike mode of the traditional reconnaissance and strike integrated UAV single forward aiming launch, providing rich A striking pattern suitable for omnidirectional launch.

Connect the reconnaissance load and the electric control box 19 of the weapon pylon 16 through the flight control subsystem cable of the airborne system to form the information and command connection of the aforementioned direct drive and dual drive, and digitally transmit the target position or orientation of the weapon pylon 16. guide. Connect the reconnaissance load and the electric control box 19 of the weapon pylon 16 through the weapon management subsystem cable in the airborne system to form an information and command connection, select and dispatch each weapon and perform power-on and power-off and launch management, and provide The location coordinates or attack course of the weapon striking the stapled target.

For the flight control subsystem, navigation subsystem and data link subsystem of the airborne system, the design changes shall be carried out according to this article, and other molecular systems shall be adjusted according to the principle of interface adaptation with these molecular systems, and the interfaces shall remain unchanged.

1) For the flight control subsystem, regardless of whether its original computer module is a single-redundancy system structure or a redundancy system structure, this article introduces a new scheme of a dual-module redundancy system structure of the flight management module + flight control module. The flight management module focuses on man-machine interface and auxiliary flight control, including navigation hot backup, route reckoning and new route binding, flight airspace restriction, route attitude monitoring and control, and task execution, including route task switch, load interface adaptation and switch , load action area, load data distribution, weapon control instructions and support for dual-drive process management and monitoring; the flight control module focuses on flight control and accepts flight management module instructions or parameter adjustment; at the same time, the introduction of coverage The same The detection software of the airborne sensor jointly builds a redundant system structure in which two modules communicate with each other + detection software assists in judgment.

2) To adapt to the change of the flight control subsystem, for the navigation subsystem, the navigation data information is introduced into the flight management module and the flight control module, and the navigation data information is deeply coupled and applied in the flight management module; The calculation time delay of the data improves the calculation accuracy, and it can be applied as a flight management module with the help of a high-performance navigation computer.

3) For the airborne data link, a set of long-range line-of-sight and beyond-line-of-sight data links of the original UAV is used, and a set of short-range line-of-sight broadband ad hoc networks that support one station for multiple machines or one machine for multiple stations is used. Data link or 4/5G communication link, you can choose to add another set of laser communication links, and design a switch device to form a parallel data link that can work in division or alternately; and time-division or frequency-division coding supports data links for multiple machines at one station . The ground monitoring station is also changed accordingly. The so-called long-range refers to greater than 100km, and short-range refers to about 30km.

It can be used as an optional configuration for the original technical solution of the flight control subsystem and navigation subsystem, as well as the narrowband data link subsystem.

The parallel data link installed in the ground monitoring station is consistent with the data link subsystem used in the above-mentioned modification of the airborne system, and is connected by radio; the operation interface supports the manual control of the weapon pylon 16 and the airborne weapon 5, or sends an authorization machine The process monitoring and emergency control operation of the automatic generation of control commands by the manned system offline supports the application of one station with multiple machines or one machine with multiple stations; ADS-B ground base stations for non-military operations that support daily training can be configured.

The salient feature of the present invention is that by installing the weapon hanger 16, the omnidirectional emission of the launching type weapon is realized. The reconnaissance and strike aircraft adopt the circling flight of the figure-of-eight route, and the airborne weapons 5 continue to point to the target, which can realize the basic combat pattern of continuous omnidirectional reconnaissance and strike. A larger launch angle, such as 135 degrees or even larger, supports the aircraft to turn around in time to implement a shorter figure-of-eight route, which can win greater combat effectiveness.

The present invention has the advantage of mixing weapons: the mixing of airborne weapons 5 is a difficult point, but also a bright spot. One is the mixed installation of ground-to-air weapons, the second is the mixed installation of barrel-launched and non-barrel-launched weapons, and the third is the mixed installation of weapons of similar length.

Implementation case 1:

An omnidirectional reconnaissance and strike integrated unmanned aerial vehicle system, as shown in Figure 12, and only two front and rear weapon racks 16 are installed in the lower cabin of the belly. Two sets of weapon racks 16 are installed at the front and rear of the belly, a total of 4×2 laser-guided missiles, with an effective range of 12km; a radiation-proof UAV is installed in the middle; a set of weapon racks 16 and 4 small missiles are installed in the upper compartment of the aircraft back Infrared-guided missiles have an effective range of 5km (the combination of weapons in the front cabin of the nose and vertical launch on the back of the aircraft is ignored in the figure), the weight of the weapon is about 320kg; the maximum take-off weight is 1800kg, and the flight speed is about 180km/h. A set of photoelectric load 15 is installed in the front cabin of the nose, and a set of technical reconnaissance load (not shown) is installed in the fuselage compartment 13 . After taking off, the UAV flew at an altitude of 5000km. The technical reconnaissance load first found the target position at 2 o'clock, with a distance of 200km. It was initially identified as an armored convoy and command post, and it was undergoing training. 1 hour to reach the target. It is known that there is a command post near the armored convoy, and there is an opponent's airport about 400km behind. After identification and confirmation, the target is a convoy of 8 armored personnel carriers, and it is identified that the accompanying small drones in the air are multi-rotor aircraft, about 3 of which are flying at an altitude of 500m. The ground monitoring station decides that the UAV is at a safe distance of 15km from the convoy, and actively flies around the front and side of the convoy at about 20 degrees to avoid the multi-directional attack of surface-to-air missiles. At the same time, the UAV rises to an altitude of 6000m, and the figure-eight hovers horizontally at a distance of about 8km from the target to launch a strike. The photoelectric load 15 locks the vehicle in front, and the front weapon hanger 16 in the lower compartment of the fuselage launches the first laser-guided missile and is tracked and irradiated by the stabilizer of the hanger. The rear weapon hanger 16 of the lower cabin is tracked and irradiated by the stabilizer of the hanger. The first shot was hit, the convoy was evacuated, and the photoelectric stabilizer continued to lock on one of the vehicles and continued to irradiate and strike. The photoelectric load 15 locks on another vehicle tracking from the dispersed convoy. The second vehicle was hit, and the target activities of the command post were frequently located by the technical reconnaissance payload, and the anti-radiation drone was launched. The figure-of-eight circle lasted for about 5 minutes, hitting 5 vehicles one by one, and the rest of the vehicles retreated. The signal from the command post was weakened, but there was no close reconnaissance assessment for the retreat.

If traditional forward strike, expect each attack to exceed 5 minutes. During this period, many opponents left the armored vehicle and used shoulder-fired missiles to attack the UAV. The distance and height ensured the safety of the UAV. The flying height of the unmanned aerial vehicle that the other side goes out is lower, and the machine back weapon pylon 16 of unmanned aerial vehicle cannot be aimed at. Since the target was small and not very threatening, the photoelectric load 15 in the front cabin did not leave the armored vehicle and aimed at it deliberately, and did not launch a missile attack on it. During the battle, the technical reconnaissance payload found that the opponent took off and estimated that two manned combat aircraft were expected to arrive at the scene in 30 minutes. The UAV withdraws from the battlefield and returns to the airspace protected by its own surface-to-air missiles. It avoids the possibility that drones may chase armored vehicles and be attacked by shoulder-launched missiles at close range.

Implementation case 2:

Same as the UAV in Case 1, the weapon load is reduced and fuel is added, and the battery life is 24 hours. The lower cabin of the belly is refitted with low-light video, laser camera and digital camera combined surveying and mapping payload to provide maritime search and rescue applications. With the help of the space under the belly of the aircraft, add some life jackets and life-saving smoke generators, etc., weighing about 200kg. After receiving the position and information of the merchant ship through the UAV-borne AIS system, the aircraft flew to the target area and circled at an altitude of 2000m to search, and confirmed a suspended cargo ship. It is known that the cargo ship was unable to sail due to an oil leakage failure, and no serious situation has occurred. The drone took pictures of the cargo ship to collect evidence and sent it back to the shore-based headquarters to complete the mission and return to the voyage, and other ships went to rescue. In case of a rescue situation in Hainan, the drone will approach the target and drop life-saving equipment at ultra-low altitude.

Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments, or perform equivalent replacements for some of the technical features. Within the spirit and principles of the present invention, any modifications, equivalent replacements, improvements, etc., shall be included in the protection scope of the present invention.

Claims (8)

1. A method for designing an integrated aircraft for reconnaissance and attack, characterized in that: the integrated aircraft for reconnaissance and attack is designed to introduce long-range and day-and-night reconnaissance equipment including technical reconnaissance and radar reconnaissance in addition to photoelectric reconnaissance, and interact with multiple weapons to carry out comprehensive Azimuth strike; Aircraft route is designed to continuously strike one or a group of air or ground sea targets in a specific direction by adopting figure-eight route circling flight; Airborne weapon (5) is designed to be built into the cabin interior at ordinary times. 2. An integrated aircraft system for reconnaissance and attack is characterized in that: it comprises an aircraft structure, a weapon pylon (16) installed on the aircraft structure, an airborne weapon (5) installed on the weapon pylon (16), and an airborne weapon (5) installed on the aircraft structure. The structure is equipped with reconnaissance payloads and airborne systems, as well as ground monitoring stations supporting the airborne systems. 3. the inspection and strike integrated aircraft system according to claim 2, is characterized in that: the aircraft structure is divided into fuselage compartment (13), the nose front compartment, the belly lower compartment and the upper compartment on the back of the aircraft; The fuselage cabin (13) structure of power is divided into front, middle and rear fuselage, wing and empennage; The front compartment of the nose is connected at the front end of the course of the front fuselage; The upper cabin is connected above the front, middle and rear fuselages. 4. the integrated aircraft system of observing and striking according to claim 2 is characterized in that: the weapon pylon (16) is installed on the aircraft structure, and the installation position comprises the front cabin of the nose, the cabin under the belly and the cabin on the back of the aircraft, and Under the wing of the fuselage compartment (13); The weapon pylon (16) comprises: a pylon structure on which a plurality of weapons are installed, and is installed in layers or mixed with various types of weapons; the fairing (4) installed on the pylon structure, the fairing (4) A self-contained aiming illuminator (6) or an electronic control unit (8) is installed inside; mounting ears (18) for installing airborne weapons (5); a lifting mechanism (1) for connecting the weapon hanger (16) to the aircraft structure; Electric control box (19) and follow-up servomechanism (2). 5. The reconnaissance and strike integrated aircraft system according to claim 2, characterized in that: the airborne weapon (5) is installed on the weapon pylon (16) and is arranged in one or more positions of the aircraft structure, including the front of the nose cabin, under the cabin of the belly and the upper cabin on the back of the fuselage, and under the wing of the fuselage compartment (13); for the weapon pylon (16) is selected three types of airborne weapons (5) that are suitable for omnidirectional launch, one can be used with Weapon pylon (16) is followed by the launching type missile of launching such as laser irradiation type or radar guidance type missile, or aviation machine gun, and the 2nd, antenna can be installed in the small-sized missile or electromagnetic disruptor of head forward; The design of each part is: install small missiles or electromagnetic disruptor antennas in the upper space of the front cabin of the nose; install launching missiles, guided or unguided bombs, aviation machine guns and Airdrop unmanned aerial vehicles, wherein the installation of aviation machine guns selects the weapon pylon (16) with two-dimensional follow-up servo mechanism (2). Laser irradiation or the guided bomb of binding target coordinates, and drop type weapon; In the interior and exterior space of cabin on the back of the machine, select the weapon hanger (16) of two-dimensional follow-up servomechanism (2) for use; On the cabin on the back of the machine The internal space of the weapon pylon (16) can be selected to install a simplified mechanism that is a combination of a vertically launched missile and its launch box, which is launched out of the cabin through opening or rupture of the membrane; the weapon is connected under the wing of the fuselage compartment (13). Pylon (16), is installed with the airborne weapon (5) of the same type of cabin under the belly of the fuselage. 6. The integrated aircraft system of reconnaissance and attack according to claim 2 is characterized in that: the photoelectric load (15) is selected for the reconnaissance load; the technical reconnaissance load; the radar load; therefrom, one or three combinations are selected to be installed in the aircraft structure Each control unit of the reconnaissance load supports the follow-up control of the weapon pylon (16) and points to the selected target; wherein, the photoelectric load (15), the signal processing of the technical reconnaissance load and the radar load and The control unit of the servo control function is respectively connected with the electric control box (19) of the weapon pylon (16) with a cable. ), the electric control box (19) guides the direct drive weapon pylon (16) to aim at the target according to the selected target coordinates; ) continuously aiming at the target is in the follow-up launch state; and the sighting illuminator (6) and the electronic control unit (8) on different weapon pylons (16) can independently carry out continuous locking and tracking of the selected target, thereby realizing the Simultaneous steady aiming and launch status of multiple targets; therefore, a reconnaissance load and the associated action of the electronic control unit (8) can constitute a dual drive to the weapon pylon (16); the above direct drive and dual drive processes will The target information is transmitted back to the subsystems of the airborne system, such as the flight control subsystem, and then distributed to the ground monitoring station, so as to complete the online launch of weapons against the target. 7. The integrated aircraft system of reconnaissance and attack according to claim 2 is characterized in that: the flight control subsystem of the airborne system is connected with the electric control box (19) of the reconnaissance load and the weapon pylon (16) by cables to form a Direct drive and dual drive information and command connection; the weapon management subsystem connected to the flight control subsystem is connected with the reconnaissance load and the electric control box (19) of the weapon pylon (16) through cables to form an information and command connection. 8. The integrated aircraft system according to claim 2, characterized in that: the parallel data link installed at the ground monitoring station is consistent with the data link subsystem adopted by the airborne system; the operation interface supports manual command control, or the authorized machine The process monitoring and emergency control operation of the off-line automatic control of the carrier system supports the application of one station with multiple machines or one machine with multiple stations; it is equipped with ADS-B ground base stations for non-military operations that support daily training.