CN112429236B - An integrated reconnaissance platform based on ICBMs - Google Patents

Abstract

An integrated reconnaissance platform carried by intercontinental missiles can be widely applied to the fields of military reconnaissance, attack, anti-terrorism, scientific and technological exploration and the like and the fields of entry deceleration and landing of celestial bodies in the aerospace field. The system is placed at the head of a missile and comprises a load catapult, a grid wing aircraft and a detection robot system, the integrated formation of air and ground is released through remote launching, deceleration landing and arrangement in an observation area, real-time information is obtained, electronic countermeasure and accurate striking are carried out by combining a load, the monitoring and deterrence of an enemy to a target are formed, and an effective means is provided for remote battlefield situation control.

Description

An integrated reconnaissance platform based on ICBM

technical field

The invention relates to an integrated reconnaissance platform carried by an intercontinental missile, which can be widely used in the fields of military reconnaissance, attack, anti-terrorism, scientific and technological exploration, and the fields of entry deceleration and landing of celestial bodies in the aerospace field.

Background technique

As the form of warfare accelerates to transform into information-based warfare, information-based combat operations such as "point-pointing" attacks that employ technological surprises will become an important method of future combat. In order to realize the "point-point" attack, it is necessary to carry out precise reconnaissance and detection of the target.

Traditional reconnaissance platforms, such as military satellites and military radars, all have blind spots for observation. Due to the limitation of time and space, they cannot achieve global deployment and lack real-time monitoring and effectiveness.

SUMMARY OF THE INVENTION

The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, an integrated reconnaissance platform based on intercontinental missiles is provided. Acquired, combined with the payload to conduct electronic countermeasures and precise strikes, form monitoring and deterrence on hostile targets, and provide effective means for remote battlefield situational control. In order to ensure that the dynamic indicators such as attitude and speed before landing of the platform are controlled, the stability of the ultra-high-speed re-entry structure, ultra-high-speed deceleration technology, and aero-thermal ablation resistance technology have been overcome; through theoretical calculations and experiments, the use of fluid mechanics The landing speed and launch overload of the robot are quantified; the impact dynamic principle is used to analyze the landing impact process of the robot, and the robot's motion mechanism is protected by combining emerging material technologies such as mechanical metamaterials and anti-buffer transmission structure Design, using potting, multi-stage vibration isolation and other design methods to protect the robot's electrical system, power supply, cameras and other detection sensors, warheads, antennas, etc. for overload shock protection.

The technical solution of the present invention is: an integrated reconnaissance platform carried by an intercontinental missile, including a payload catapult, a grid-wing aircraft and a reconnaissance robot system;

The payload catapult is used for catapulting the grid-wing aircraft out of the missile parent body at high speed;

The grid-wing aircraft includes a grid controller and a parachute system, on which a reconnaissance robot system is carried; it is initially installed on a payload catapult, and is ejected and released after reaching a preset target point, and the attitude is continuously adjusted during the landing process to achieve stability flying; the parachute system is installed on the top of the reconnaissance robot system to realize the deceleration and landing of the grid-wing aircraft; the reconnaissance robot system is used for reconnaissance of the target point after landing.

Further, the grid wing controller includes a grid wing, a turbine worm drive mechanism, and a hydraulic actuator; the grid wing is located at the outermost side of the grid wing aircraft, and is connected with the grid wing aircraft through a mechanical interface; its movement is controlled by hydraulic pressure. The actuator drives the turbine worm drive mechanism to act, and the motion pitch angle is ±20°.

Further, the parachute system includes a catapult, a stabilization parachute, a deceleration parachute, and a parachute bag.

Further, the reconnaissance robot system includes a spherical rolling robot, a rotorcraft and a spherical combined aircraft.

An integrated reconnaissance method based on the carrying of an intercontinental missile, comprising the following steps:

When the preset distance from the target observation area is reached, the high-altitude launch of the reconnaissance platform is completed according to the predetermined procedure, and the grid wing controller is used to open the grid wing to control the reconnaissance platform to land stably; when the estimated landing speed of the reconnaissance platform is greater than 20m/ At s, the parachute system works, opening the stabilizing parachute and pulling out the deceleration parachute in turn to achieve deceleration;

After reaching the preset effective reconnaissance height, the parachute system is thrown, the reconnaissance robot system is released, and the reconnaissance robot system moves to the preset target point for reconnaissance.

Further, the rotorcraft flies in the air for detection, the spherical combined aircraft has a variable topology configuration for landing or flight reconnaissance, and the spherical rolling robot relies on two-wheel drive for reconnaissance.

Further, the rotorcraft flies in the air and relies on its own power to realize flight reconnaissance.

Further, in the landing state, the spherical combined aircraft uses the rotor fan provided with each aircraft to provide the sphere with power to roll in the target direction.

Further, the spherical combined aircraft is decomposed into 12 pentagonal quadrotors to fly individually or in formation.

Further, when the spherical rolling robot reaches the ground, it uses its built-in buffer material and metamaterial configuration to absorb energy for landing; after landing, the internal mechanism is driven to realize two-wheel drive, autonomous or controllable walking and reconnaissance.

The advantages of the present invention compared with the prior art are:

This reconnaissance platform makes up for the observation blind spots of military satellites and military radars. It is not limited by time and space, and can be deployed globally. Its monitoring is real-time and effective. At present, the relatively mature military robots cannot be delivered at ultra-high speed and can work reliably; their volume is generally large in order to match the battlefield situation; the distance between the drive and control is short, and the effective distance between the operator and the robot cannot be too large. Therefore, the concept of this reconnaissance platform is proposed, which expands the scope of military monitoring and strikes, and facilitates the improvement of the accuracy of global strikes. This robot adopts deceleration technology and buffer technology to improve its own survival rate. At the same time, it carries a launch load, which is also of great practical significance for improving the combat effectiveness of the parent body.

At the same time, this invention can be extended to military-civilian integration. In some critical, complex and harsh scenes such as natural disasters, nuclear leaks or drug leaks, and man-made terrorist incidents, timely detection of first-hand information on the scene plays an important role in rescue and dispatch. It meets the needs of fast and accurate access to effective disaster information in dangerous environments.

A variety of different sensors can be installed on the robot body carried by the reconnaissance platform. Whether it is military or civilian, it is used for reconnaissance and detection, and it can detect important targets in sensitive areas such as buildings, bunkers, warships, and ships. Implement active detection, effectively obtain target information, and even identify, track and attack the target, so as to help decision makers take quick and decisive countermeasures, which has broad application prospects.

Description of drawings

Fig. 1 is the implementation flow chart of the integrated investigation platform of the present invention;

Fig. 2 is the schematic diagram of the load catapult of the present invention;

FIG. 3 is a schematic diagram of the structure of the grid-wing aircraft and the internal reconnaissance robot of the present invention.

Detailed ways

In order to better understand the above technical solutions, the technical solutions of the present application will be described in detail below through the accompanying drawings and specific embodiments. It is not a limitation on the technical solutions of the present application, and the embodiments of the present application and the technical features in the embodiments may be combined with each other under the condition of no conflict.

An integrated reconnaissance platform based on ICBMs provided by the embodiments of the present application will be described in further detail below with reference to the accompanying drawings. Wing aircraft, reconnaissance robot system. This platform is placed on the missile head.

Based on the integrated reconnaissance platform carried by the ICBM, when approaching the target observation area, the load catapult ejects the grid-wing aircraft according to the predetermined procedure to complete the high-altitude launch of the reconnaissance platform. The grid-wing controller and the aerodynamic control characteristics of the parachute are used to slow down At the same time of its falling speed, the stability of the reconnaissance platform is improved. Control its speed and landing area within an acceptable range.

After reaching the effective reconnaissance altitude, the reconnaissance loads such as spherical rotorcraft, spherical combined aircraft, and spherical rolling robots are released for air-ground integrated reconnaissance.

When reaching the ground, the spherical rolling robot uses its built-in buffer material and metamaterial configuration to absorb the landing energy, release the landing impact in the form of deformation energy, etc., to ensure the safety of internal equipment components. After a safe landing, the internal mechanism drives, enabling two-wheel drive, autonomous or controlled walking. The coupling of the three realizes large-scale reconnaissance and observation of air-ground integration.

The solution provided by the embodiment of the present application includes a payload catapult, a grid-wing aircraft, and a reconnaissance robot system; the payload catapult is used to eject the grid-wing aircraft out of the missile parent body at high speed; the grid-wing aircraft The aircraft is composed of a grid wing controller and a parachute system, which is used to carry the reconnaissance robot system. It is initially installed on the load catapult, and after reaching the preset target point, it is ejected and released, and the attitude is continuously adjusted during the landing process to achieve stable flight; the The grid-wing controller controls the grid-wing attitude grid-wing aircraft; the parachute system is installed on the top of the reconnaissance robot to realize the deceleration and landing of the grid-wing aircraft; the reconnaissance robot is used to detect the target point after the grid-wing has landed.

Further, the load catapult is composed of an inner tube cover, a separation plug, a data recording cable, an inner tube instrument board, an outer tube, an outer tube base, a catapult pill box, an inner tube end, and a travel switch assembly.

Further, in a possible implementation manner, the grid-wing aircraft includes a grid-wing controller and a parachute system. The grid wing controller is composed of grid wings, a turbine worm drive mechanism and a hydraulic actuator. The grid wing is located at the outermost side of the grid wing aircraft, and is connected with the aircraft through a mechanical interface; its movement is realized by the hydraulic actuator driving the turbine worm transmission mechanism. The motion pitch angle is ±20°.

In one possible implementation, the parachute system includes a catapult, a stabilizing parachute, a deceleration parachute, and a parachute bag.

Further, in a possible implementation manner, the reconnaissance robot system is composed of a spherical rolling robot, a rotorcraft and a spherical combined aircraft, and is equipped with a corresponding reconnaissance load according to actual reconnaissance requirements.

In a possible implementation, when approaching the target observation area, according to a predetermined procedure, the load catapult ejects the grid-wing aircraft to complete the high-altitude launch of the reconnaissance platform, and the grid-wing controller is used to open the grid-wing. The aerodynamic control characteristics of the wing can slow down its falling speed and improve the stability of the reconnaissance platform. When the load weight of the reconnaissance platform is large, the overall attitude and speed are controlled based on the coupled deceleration scheme of parachute + grid wing, and its speed and landing area are controlled within an acceptable range.

In a possible way, after reaching the effective reconnaissance height, release the reconnaissance load such as spherical rotorcraft, spherical combined aircraft, spherical rolling robot, etc., and the rotorcraft can fly in the air; the spherical combined aircraft has two operating conditions, one is In the landing state, the spherical combined aircraft can use the rotor fan provided by each aircraft to provide the sphere with power to roll in the target direction, which can reduce the energy consumption during the movement process; secondly, when passing through complex terrain, the entire sphere can be decomposed into 12 pentagonal quadrotors achieve high maneuvering flight.

In a possible way, when reaching the ground, the spherical rolling robot uses its built-in buffer material and metamaterial configuration to absorb the landing energy, release the landing impact in the form of deformation energy, etc., to ensure the safety of internal equipment components . After a safe landing, the internal mechanism drives, enabling two-wheel drive, autonomous or controlled walking. The coupling of the three realizes large-scale reconnaissance and observation of air-ground integration.

Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims (7)

1. An integrated investigation platform based on intercontinental missile carrying is characterized in that: the system comprises a load catapult, a grid wing aircraft and a reconnaissance robot system;

the load catapult is used for ejecting the grid wing aircraft out of the missile parent body at an ultra-high speed;

the grid wing aircraft comprises a grid wing controller and a parachute system, and the detection robot system is carried on the grid wing aircraft; the grid wing aircraft is installed on the load catapult at an initial moment, is catapulted and released after reaching a preset target point, and continuously adjusts the posture in the landing process to realize stable flight; the parachute system is arranged at the top of the investigation robot system to realize the deceleration landing of the grid wing aircraft; the investigation robot system is used for investigating a target point after descending;

the grid wing controller comprises grid wings, a turbine worm transmission mechanism and a hydraulic actuator; the grid wings are positioned on the outermost sides of the grid wing aircrafts and are connected with the grid wing aircrafts through mechanical interfaces; the movement is realized by driving a worm gear and worm transmission mechanism to actuate by a hydraulic actuator, and the movement pitch angle is +/-20 degrees;

the parachute system comprises a catapult, a stabilizing parachute, a speed reducing parachute and a parachute bag;

the investigation robot system comprises a spherical rolling robot, a rotor aircraft and a spherical combined aircraft.

2. The integrated detection method based on intercontinental missile carrying based on the integrated detection platform based on intercontinental missile carrying of claim 1 is characterized by comprising the following steps of:

when the preset distance between the target observation area and the target observation area is reached, completing high-altitude throwing of the detection platform according to a preset program, and utilizing a grid wing controller to open the grid wings to control the detection platform to stably land; when the estimated detection platform landing speed is more than 20 m/s, the parachute system works, and the stabilizing parachute is opened and the deceleration parachute is pulled out in sequence to realize deceleration;

and after the preset effective detection height is reached, the parachute system is thrown, the detection robot system is released, and the detection robot system moves to a preset target point for detection.

3. The integrated detection method carried by an intercontinental missile according to claim 2, wherein: the rotary wing aircraft flies in the air for investigation, the spherical combined aircraft lands or flies for investigation with variable topological structure, and the spherical rolling robot is investigated by means of double-wheel drive.

4. The integrated detection method carried by an intercontinental missile according to claim 3, wherein the detection method comprises the following steps: the rotor craft flies in the air, and the flight investigation is realized by the aid of the power of the rotor craft.

5. The integrated detection method carried by an intercontinental missile according to claim 3, wherein the detection method comprises the following steps: the spherical combined aircraft utilizes the self-contained rotor fan of each aircraft to provide power for rolling the sphere towards the target direction in the landing state.

6. The integrated detection method carried by an intercontinental missile according to claim 3, wherein the detection method comprises the following steps: the spherical combined aircraft is decomposed into 12 pentagonal quadrotor aircraft to realize respective flight or formation flight.

7. The integrated detection method carried by an intercontinental missile according to claim 3, wherein the detection method comprises the following steps: when the spherical rolling robot reaches the ground, the spherical rolling robot performs landing energy absorption by utilizing a built-in buffer material and metamaterial structure; after landing, the internal mechanism drives to realize double-wheel driving and autonomous or controllable walking investigation.

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