CN112429236A - Integrated investigation platform based on intercontinental missile carrying - Google Patents
Integrated investigation platform based on intercontinental missile carrying Download PDFInfo
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- 238000011835 investigation Methods 0.000 title claims abstract description 39
- 238000001514 detection method Methods 0.000 claims abstract description 47
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 4
- 238000005096 rolling process Methods 0.000 claims description 17
- 230000007246 mechanism Effects 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 claims description 6
- 230000033001 locomotion Effects 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 5
- 230000000087 stabilizing effect Effects 0.000 claims description 4
- 238000010521 absorption reaction Methods 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 abstract description 5
- 230000009467 reduction Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 5
- 230000010354 integration Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 239000003814 drug Substances 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 238000005538 encapsulation Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
- B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/80—Transport or storage specially adapted for UAVs by vehicles
- B64U80/82—Airborne vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Transportation (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
An integrated investigation 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 speed reduction 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
Technical Field
The invention relates to an integrated investigation platform carried by intercontinental missiles, which can be widely applied to the fields of military reconnaissance, attack, anti-terrorism, scientific and technological exploration and the like and the fields of speed reduction and landing of celestial bodies in the aerospace field.
Background
With the change from the acceleration of the war form to the information war, "point-hitting" type attacks and the like, which adopt the information combat action of technical assault, will become an important way for future combat. In order to realize the 'point-hitting' type attack, the target needs to be accurately detected and detected.
Traditional investigation platforms such as military satellites and military radars all have observation blind areas, are limited by space and time, cannot realize global arrangement, and lack real-time performance and effectiveness of monitoring.
Disclosure of Invention
The technical problem solved by the invention is as follows: the integrated detection platform is carried by intercontinental missiles, 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 loads, monitoring and fright of an enemy to a target are formed, and an effective means is provided for remote battlefield situation control. In order to ensure that the dynamic indexes of the platform such as attitude, speed and the like before landing are controlled, the stability of an ultrahigh-speed reentry structure, an ultrahigh-speed deceleration technology and an aerodynamic heat ablation resistance technology are overcome; through theoretical calculation and experiments, the landing speed and the launching overload of the robot are quantified by adopting fluid mechanics, explosion mechanics and the like; the impact dynamics principle is adopted to analyze the landing impact process of the robot, the protection design is carried out on the moving mechanism of the robot by combining the technology of emerging materials such as mechanical metamaterials and the like and the anti-buffer type transmission structure, and the overload impact protection is carried out on the detection sensors such as the electrical system, the power supply, the camera and the like, the warhead, the antenna and the like of the robot by adopting the design means such as encapsulation, multistage vibration isolation and the like.
The technical solution of the invention is as follows: an integrated investigation platform carried by intercontinental missiles comprises a load catapult, a grid wing aircraft and an investigation robot system;
the load catapult is used for ejecting the grid wing aircraft out of the missile parent body at high over-speed;
the grid wing aircraft comprises a grid controller and a parachute system, and a detection robot system is carried on the grid controller and the parachute system; the device is installed on a 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 the detection robot system falls.
Further, the grid wing controller comprises a grid wing, 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 of the worm gear 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.
Further, the parachute system comprises an ejector, a stabilizing umbrella, a speed reducing umbrella and an umbrella bag.
Further, the investigation robot system comprises a spherical rolling robot, a rotorcraft and a spherical combined aircraft.
An integrated investigation method based on intercontinental missile carrying comprises the following steps:
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.
Further, the rotary wing aircraft flies in the air for investigation, the spherical combined aircraft lands or flies for investigation in a variable topological configuration, and the spherical rolling robot is investigated by means of double-wheel drive.
Furthermore, the rotor craft flies in the air, and the flight investigation is realized by means of the power of the rotor craft.
Further, 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.
Further, the spherical combined aircraft is decomposed into 12 pentagonal quadrotor aircraft to realize respective flight or formation flight.
Further, when the spherical rolling robot reaches the ground, the spherical rolling robot is landed and absorbed with energy by utilizing a built-in buffer material and metamaterial structure; after landing, the internal mechanism drives to realize double-wheel drive and autonomous or controllable walking investigation.
Compared with the prior art, the invention has the advantages that:
the investigation platform makes up observation blind areas such as military satellites and military radars, is not limited by time and space, can realize global arrangement, and has real-time and effective monitoring. At present, a mature military robot cannot be put in after ultrahigh-speed transportation and reliably work; the volume of the device is generally larger in order to match the battlefield situation; the driving control distance is short, and the effective distance between the operator and the robot cannot be too large. Therefore, the investigation platform concept expands the scope of military monitoring attack and is convenient for improving the accuracy of global attack. The robot adopts a deceleration technology and a buffering technology, improves the survival rate, simultaneously carries the launching load, and has great practical significance for improving the striking efficiency of the parent body.
Meanwhile, the invention can be popularized to the aspect of military and civil integration. In some critical, complex and severe fields such as natural disasters, nuclear leakage or drug leakage, artificial terrorism and the like, the first-hand information of the field is detected in time, so that the first-hand information plays an important role in rescue and scheduling. The requirement of rapidly and accurately acquiring effective disaster information in a dangerous environment is met.
The robot body carried by the investigation platform can be provided with a plurality of different sensors, whether military or civil, the sensors are used for investigation and detection, and can actively detect important targets in sensitive areas such as buildings, ground forts, battleships, ships and the like, so that target information is effectively obtained, and even the targets are identified, tracked and attacked, thereby helping decision-making personnel to take rapid and decisive countermeasures and having wide application prospect.
Drawings
FIG. 1 is a flow chart of an embodiment of the integrated investigation platform of the present invention;
FIG. 2 is a schematic view of the load catapult of the present invention;
FIG. 3 is a schematic view of the structure of the grid wing aircraft and the internal inspection robot according to the present invention.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
An integrated detection platform carried by an intercontinental missile provided by the embodiment of the application is further described in detail in the following drawings, and specific implementation manners can include (as shown in fig. 1-3): load catapult, grid wing aircraft, investigation robot system. The platform is placed at the head of the missile.
Based on an intercontinental missile carrying integrated detection platform, when approaching a target observation area, a load catapult catapults a grid wing aircraft according to a preset program to finish high-altitude launching of the detection platform, and the stability of the detection platform is improved while the falling speed of the detection platform is reduced by utilizing the pneumatic control characteristics of a grid wing controller and a parachute. The speed and landing area are controlled within an acceptable range.
After the effective detection height is reached, the detection loads of the spherical rotor aircraft, the spherical combined aircraft, the spherical rolling robot and the like are released to carry out air-ground integrated detection.
When the spherical rolling robot reaches the ground, the spherical rolling robot utilizes the built-in buffer material and metamaterial structure to carry out landing energy absorption, the landing impact is released in the form of deformation energy and the like, and the safety of internal equipment components is ensured. After safe landing, the internal mechanism drives, thereby realizing double-wheel driving and autonomous or controllable walking. The three parts are coupled to realize large-range investigation and observation of air-ground integration.
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 high over-speed; the grid wing aircraft consists of a grid wing controller and a parachute system, is used for bearing a detection robot system, is installed on a 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 grid wing controller controls a grid wing attitude grid wing aircraft; the parachute system is arranged at the top of the investigation robot to realize the deceleration landing of the grid wing aircraft; the investigation robot is used for investigating a target point after the grid wing falls.
Furthermore, the load catapult consists of an inner cylinder cover plate, a separation plug, a data recording cable, an inner cylinder instrument plate, an outer cylinder base, a catapult medicine box, an inner cylinder end and a travel switch component.
Further, in a possible implementation manner, the grid wing aircraft comprises a grid wing controller and a parachute system. The grid wing controller consists of grid wings, a worm and gear 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 aircrafts through mechanical interfaces; the movement of the worm gear is realized by driving the worm gear drive mechanism to actuate by the hydraulic actuator. The motion pitch angle is +/-20 degrees.
In one possible implementation, the parachute system comprises an ejector, a stabilizer, a drogue, a parachute pack.
Further, in a possible implementation mode, the investigation robot system is composed of a spherical rolling robot, a rotor aircraft and a spherical combined aircraft, and carries corresponding investigation loads according to actual investigation requirements.
In a possible implementation mode, when approaching a target observation area, the load catapult catapults the grid wing aircraft according to a preset program to finish high-altitude throwing of the investigation platform, the grid wings are opened by utilizing the grid wing controller, and the stability of the investigation platform is improved while the falling speed of the grid wings is reduced based on the pneumatic control characteristic of the grid wings. When the load weight of the detection platform is large, the overall attitude and the speed are controlled based on a parachute + grid wing coupling speed reduction scheme, and the speed and the landing area are controlled within an acceptable range.
In a possible implementation mode, after the effective detection height is reached, detection loads such as a spherical rotor aircraft, a spherical combined aircraft, a spherical rolling robot and the like are released, and the rotor aircraft can fly in the air; the spherical combined aircraft has two use working conditions, one of the two working conditions is that the spherical combined aircraft can provide power for the sphere to roll towards a target direction by using a rotor fan carried by each aircraft in a landing state, and the energy consumption in the moving process can be reduced; and secondly, when the spherical aircraft passes through a complex terrain, the whole sphere can be decomposed into 12 pentagonal quadrotor aircrafts to realize high-maneuverability flight.
In a possible implementation mode, when the spherical rolling robot reaches the ground, the spherical rolling robot utilizes the built-in buffer material and metamaterial structure to carry out landing energy absorption, the landing impact is released in the form of deformation energy and the like, and the safety of internal equipment components is ensured. After safe landing, the internal mechanism drives, thereby realizing double-wheel driving and autonomous or controllable walking. The three parts are coupled to realize large-range investigation and observation of air-ground integration.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such 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 intended to include such modifications and variations as well.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
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 high over-speed;
the grid wing aircraft comprises a grid controller and a parachute system, and a detection robot system is carried on the grid controller and the parachute system; the device is installed on a 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 the detection robot system falls.
2. The integrated detection platform carried by intercontinental missile according to claim 1, wherein: 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 of the worm gear 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.
3. The integrated detection platform carried by intercontinental missile according to claim 1, wherein: the parachute system comprises an ejector, a stabilizing parachute, a speed reducing parachute and a parachute package.
4. The integrated detection platform carried by intercontinental missile according to claim 1, wherein: the investigation robot system comprises a spherical rolling robot, a rotor aircraft and a spherical combined aircraft.
5. An integrated investigation method carried by an intercontinental missile is characterized by comprising the following steps:
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.
6. The integrated detection method carried by an intercontinental missile according to claim 5, wherein the detection method comprises the following steps: 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.
7. The integrated detection method carried by an intercontinental missile according to claim 6, 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.
8. The integrated detection method carried by an intercontinental missile according to claim 6, 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.
9. The integrated detection method carried by an intercontinental missile according to claim 6, 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.
10. The integrated detection method carried by an intercontinental missile according to claim 6, 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 drive and autonomous or controllable walking investigation.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011457983.3A CN112429236B (en) | 2020-12-10 | 2020-12-10 | Integrated investigation platform based on intercontinental missile carrying |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011457983.3A CN112429236B (en) | 2020-12-10 | 2020-12-10 | Integrated investigation platform based on intercontinental missile carrying |
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| CN112429236A true CN112429236A (en) | 2021-03-02 |
| CN112429236B CN112429236B (en) | 2022-09-27 |
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|---|---|---|---|---|
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-
2020
- 2020-12-10 CN CN202011457983.3A patent/CN112429236B/en active Active
Patent Citations (9)
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|---|---|---|---|---|
| DE19626075C1 (en) * | 1996-06-28 | 1998-01-15 | Buck Chem Tech Werke | Missiles to combat moving targets |
| JP2002147996A (en) * | 2000-11-14 | 2002-05-22 | Mitsubishi Electric Corp | Missile system |
| DE102006019758A1 (en) * | 2006-04-28 | 2007-11-08 | Deutsch Französisches Forschungsinstitut Saint Louis | Reconnaissance arrangement for carrier projectile, missiles or aircraft, comprises falling body with sensor unit and with an unit for delaying the fall having rotor blades arranged over articulations at a rotationally mounted rotor head |
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