CN111824386B - Aircraft launching device and method - Google Patents
Aircraft launching device and method Download PDFInfo
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- CN111824386B CN111824386B CN202010576131.XA CN202010576131A CN111824386B CN 111824386 B CN111824386 B CN 111824386B CN 202010576131 A CN202010576131 A CN 202010576131A CN 111824386 B CN111824386 B CN 111824386B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/40—Balloons
Abstract
The embodiment of the invention provides an aircraft launching device and method, wherein the device comprises a near space floating platform and an aircraft launching cabin body; the near space floating platform is used for carrying an aircraft to put a cabin body to a target position; the aircraft launching cabin comprises a plurality of unit cabins, the unit cabins are used for loading a plurality of aircrafts, and the opening and closing states of the cabin doors of any one unit cabin are determined based on launching control signals corresponding to the aircrafts in the unit cabin. According to the aircraft launching device and method provided by the embodiment of the invention, a plurality of aircraft unit cabin bodies for loading a plurality of aircraft are arranged, the opening and closing states of the cabin doors of the unit cabin bodies are determined based on launching control signals corresponding to the aircraft in any unit cabin body, the aircraft is launched in different target positions in batches by independently controlling different unit cabin bodies, and the launching tasks of the aircraft in a plurality of areas can be executed.
Description
Technical Field
The invention relates to the technical field of aircraft air-based launching, in particular to an aircraft launching device and method.
Background
In an information battlefield, information becomes a key element for leading and controlling the battlefield, and an aircraft is one of main channels for acquiring information in wartime. The method comprises the steps of taking a near space floating platform as a mother platform, carrying out broadcast type throwing at a position far away from an enemy occupation area after an aircraft is lifted off, carrying out information acquisition work after the aircraft submerges behind an enemy, and finally realizing information transmission through communication with a satellite.
Fig. 1 is a schematic structural diagram of an existing aircraft launching device, and as shown in fig. 1, in the existing aircraft launching device, an unmanned aerial vehicle to be launched is loaded in a cabin, and during launching, the unmanned aerial vehicle can only launch in one region in a one-time mode, and launching tasks in a plurality of different regions cannot be completed.
Disclosure of Invention
The embodiment of the invention provides an aircraft launching device and method, which are used for solving the technical problem that the existing aircraft launching device cannot complete launching tasks in a plurality of different areas.
In a first aspect, an embodiment of the present invention provides an aircraft launching device, including a near space floating platform and an aircraft launching cabin;
the near space floating platform is used for carrying the aircraft launching cabin to a target position;
the aircraft launching cabin comprises a plurality of unit cabins, the unit cabins are used for loading a plurality of aircraft, and the opening and closing state of a cabin door of any unit cabin is determined based on a launching control signal corresponding to the aircraft in any unit cabin.
Optionally, an aircraft launching mechanism fixedly connected with any unit cabin body is arranged in any unit cabin body;
aircraft input mechanism includes mounting and a plurality of restraint piece, the mounting links to each other with each restraint piece respectively, the mounting with arbitrary unit cabin body links to each other, a plurality of restraint piece with the internal a plurality of aircraft in arbitrary unit cabin can dismantle the connection.
Optionally, the aircraft release mechanism further includes a relay control element, each constraint piece is magnetically connected to a connecting member on each aircraft in any unit cabin, and the relay control element is configured to control connection and release of the constraint piece and the corresponding connecting member based on a release control signal corresponding to the aircraft in any unit cabin.
Optionally, the plurality of constraining members are arranged at equal intervals, the plurality of constraining members include a first constraining member and a second constraining member which are equal in quantity, and the first constraining member is opposite to the second constraining member in the mounting surface direction.
Optionally, the system further comprises an azimuth adjusting mechanism, the azimuth adjusting mechanism is respectively connected with the near space floating platform and the aircraft launching cabin, and the azimuth adjusting mechanism is used for adjusting an initial launching azimuth angle of the aircraft.
Optionally, a temperature adjusting mechanism is arranged in the unit cabin body or a heat insulating material is covered in the unit cabin body.
In a second aspect, an embodiment of the present invention provides an aircraft launching method, including:
when the aircraft launching device reaches the current target point, controlling the cabin door of the unit cabin body loaded with the aircraft in the current batch in the aircraft launching device to open, and launching the aircraft in the current batch;
and updating the current target point to be the next target point.
Optionally, the launching the current batch of aircraft specifically includes:
and controlling an aircraft throwing mechanism in a unit cabin loaded with the aircrafts in the current batch to sequentially release the connection between each restraint piece and the connecting piece of the corresponding aircraft according to a preset time interval.
Optionally, the launching the current batch of aircraft specifically includes:
and sending a release request to the aircraft in the current batch, so that the aircraft in the current batch is controlled to sequentially release the connection with the corresponding restraint parts according to a preset time interval after receiving the release request.
According to the aircraft launching device and method provided by the embodiment of the invention, a plurality of unit cabin bodies for loading a plurality of aircraft are arranged, the opening and closing states of the cabin doors of the unit cabin bodies are determined based on launching control signals corresponding to the aircraft in any unit cabin body, the aircraft are launched in different target positions in batches by independently controlling different unit cabin bodies, and the launching tasks of the aircraft in a plurality of areas can be executed.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural diagram of a conventional aircraft launching device;
fig. 2 is a schematic structural diagram of an aircraft launching device provided in an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an aircraft launching mechanism provided in an embodiment of the present invention;
fig. 4 is a schematic structural diagram of an aircraft launching device according to another embodiment of the present invention;
FIG. 5 is a schematic flow chart of an aircraft launching method according to an embodiment of the present invention;
reference numerals:
210-an adjacent space floating platform; 220-launching the cabin by the aircraft; 230-unit cabin;
240-an orientation adjustment mechanism; 310-a fixture; 320-a restraint;
330-a connector; 340-relay control element.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 2 is a schematic structural diagram of an aircraft launching device provided in an embodiment of the present invention, and as shown in fig. 2, the device includes a near space floating platform 210 and an aircraft launching cabin 220; the near space floating platform 210 is used for carrying the aircraft launching cabin 220 to a target position; the aircraft launching cabin 220 includes a plurality of unit cabins 230, each unit cabin 230 is used for loading a plurality of aircraft, and the opening and closing state of a door of any unit cabin 230 is determined based on a launching control signal corresponding to the aircraft in the unit cabin.
Specifically, the aircraft launching device provided in the embodiment of the present invention includes an adjacent space floating platform 210 and an aircraft launching cabin 220, which are sequentially connected, where the adjacent space floating platform 210 is used to carry the aircraft launching cabin 220 to a target position, and the adjacent space floating platform 210 may be a high-pressure balloon, a super-pressure balloon, a stratospheric airship, and the like, which is not specifically limited in this embodiment of the present invention.
Different from the existing aircraft launching device, in the embodiment of the present invention, the aircraft launching cabin 220 includes a plurality of unit cabins 230, wherein the unit cabins 230 are used for loading a plurality of aircraft. The unit cabin bodies 230 may be arranged in an array or at intervals, which is not specifically limited in this embodiment of the present invention. The loaded aircraft may be an unmanned aerial vehicle, and may also be other aircraft for executing an information acquisition task, which is not specifically limited in this embodiment of the present invention.
The plurality of unit cabins 230 in the aircraft launching cabin 220 can be independently controlled, and the opening and closing states of the doors of any unit cabin 230 are determined based on corresponding launching control signals of the aircraft in the unit cabin, wherein the launching control signals are used for indicating whether the aircraft needs to be launched. The control method of the opening and closing state of the cabin door of any unit cabin 230 may be that when the aircraft launching device reaches the target position, the ground control system sends a launching request to the aircraft launching device, the launching request includes information of the aircraft to be launched at the target position, and after the aircraft launching device receives the launching request, the aircraft launching device controls the cabin door of the unit cabin to open through a launching control signal corresponding to the aircraft in any unit cabin, and launches the corresponding aircraft. The doors of the unit cabin 230 may be opened sequentially or simultaneously, which is not limited in this embodiment of the present invention.
The control method of the opening and closing state of the cabin door of any unit cabin 230 may also be that a Positioning mechanism, such as a GPS (Global Positioning System) positioner, is arranged on the aircraft launching device, information of a target position and information of an aircraft to be launched at the target position are stored in the Positioning mechanism in advance, and when a real-time position acquired by the Positioning mechanism in the aircraft launching device matches the stored target position, the cabin door of the unit cabin is controlled to open by a launching control signal corresponding to the aircraft in any unit cabin, and the corresponding aircraft is launched.
According to the aircraft launching device provided by the embodiment of the invention, a plurality of aircraft unit cabin bodies used for loading a plurality of aircraft are arranged, the opening and closing states of the cabin doors of the unit cabin bodies are determined based on the launching control signals corresponding to the aircraft in any unit cabin body, the aircraft are launched in different target positions in batches by independently controlling different unit cabin bodies, and the launching tasks of the aircraft in a plurality of areas can be executed.
Based on any one of the embodiments, in the device, an aircraft throwing mechanism fixedly connected with the unit cabin is arranged in any unit cabin; the aircraft release mechanism comprises a fixing part and a plurality of restraining parts, the fixing part is respectively connected with each restraining part, the fixing part is connected with the unit cabin body, and the plurality of restraining parts are detachably connected with the plurality of aircrafts in the unit cabin body.
Specifically, in the aircraft launching device, an aircraft launching mechanism is arranged in any unit cabin body and used for loading and launching the aircraft. The aircraft release mechanism comprises a fixing piece and a plurality of restraining pieces, wherein the fixing piece is used for fixing the aircraft release mechanism, and the restraining pieces are used for fixing and releasing the aircraft. The fixing element is connected with each constraint element respectively, and the fixing element and each constraint element can be connected in a fixed manner or a detachable manner, which is not specifically limited in the implementation of the invention. The plurality of constraining members are arranged on the fixing member at intervals, the arrangement mode of the plurality of constraining members on the fixing member can be equal interval arrangement or unequal interval arrangement, and the comparison of the embodiment of the invention is not particularly limited. When the plurality of restraining pieces are detachably connected with the fixing piece, aircrafts with different sizes can be loaded by adjusting the spacing distance between the plurality of restraining pieces.
Aircraft input mechanism can load a plurality of aircraft with the structure of slicing type through setting up mounting and a plurality of about beam of restricting piece for the space of the unit cabin body obtains make full use of, can guarantee the stable initial gesture of aircraft simultaneously, is favorable to puting in the back aircraft and gets into fast and stabilize the state of gliding, and can load not unidimensional aircraft through the spacing distance between the adjustment a plurality of about beam of restricting piece, makes loading of aircraft more nimble.
The aircraft release mechanism is fixedly connected with the unit cabin body through the fixing part, detachably connected with the plurality of aircrafts through the plurality of constraint parts, the plurality of constraint parts correspond to the plurality of aircrafts one by one, and the detachable connection mode of the plurality of constraint parts and the plurality of aircrafts in the corresponding unit cabin body can be mechanical connection or magnetic connection. Before the flying throwing device executes a throwing task, fixing an aircraft to be thrown on the flying throwing mechanism through a restraint piece; when the flying throwing device reaches the target position, the restraining part in the flying throwing mechanism in the unit cabin body is controlled to release the aircraft connected with the restraining part, so that the aircraft is thrown.
According to the aircraft release device provided by the embodiment of the invention, the aircraft release mechanism comprising the fixing part and the plurality of restraining parts is arranged in any unit cabin body, and the plurality of restraining parts are detachably connected with the plurality of aircrafts in the unit cabin body, so that the space of the unit cabin body is fully utilized, the stable initial posture of the aircrafts is ensured, and the aircraft can rapidly enter a stable gliding state after being released.
Based on any one of the embodiments, fig. 3 is a schematic structural diagram of the aircraft release mechanism provided in the embodiment of the present invention, and as shown in fig. 3, the aircraft release mechanism further includes a relay control element 340, each constraint component 320 is magnetically connected to the connection component 330 on each aircraft in the unit cabin, and the relay control element 340 is configured to control connection and release of the constraint component 320 and the corresponding connection component 330 based on a release control signal corresponding to the aircraft in the unit cabin.
Specifically, the aircraft release mechanism includes a fixing member 310, a plurality of restraining members 320, and a relay control element 340, each restraining member 320 in the aircraft release mechanism is magnetically connected to each aircraft in the corresponding unit cabin 230, and each aircraft is provided with a connecting member 330 correspondingly connected to the restraining member 320. When the aircraft releasing device reaches the target position, the aircraft releasing device controls the cabin door of the corresponding unit cabin to open through a releasing control signal corresponding to the aircraft in the unit cabin, and the relay control element 340 controls the connection release of the constraint component 320 and the corresponding connecting component 330 in the aircraft releasing mechanism based on the releasing control signal.
Because the plurality of constraining members 320 are independent from each other, the plurality of constraining members 320 can be controlled to release the connection with the corresponding connecting member 330, so that the plurality of aircrafts in the unit cabin can be separately launched; the connection between the plurality of constraint 320 pieces and the corresponding connecting piece 330 can also be released in sequence by controlling the plurality of constraint 320 pieces, so that the plurality of aircrafts in the unit cabin can be thrown in sequence at preset time intervals.
According to the aircraft release device provided by the embodiment of the invention, each constraint piece is in magnetic connection with the connecting piece on each aircraft in the unit cabin body, so that the aircraft release mechanism is quickly released when the aircraft is released, the relay control element controls the signal to control the connection and release of the constraint piece and the corresponding connecting piece, the situations of mutual collision and mutual interference after the aircraft is released are effectively avoided, and the survival rate of the aircraft and the success rate of an information acquisition task are improved.
According to any one of the above embodiments, in the device, the plurality of constraining members are arranged at equal intervals, the plurality of constraining members include equal amounts of a first constraining member and a second constraining member, and the first constraining member is opposite to the second constraining member in the mounting surface direction.
Particularly, as the front and back structures of the aircraft are often asymmetric, the front and back masses of the aircraft are not equal, and if a plurality of aircraft are loaded in the same direction, the gravity center of a unit cabin body for loading the aircraft is unstable, so that the flight state of the aircraft launching device and the safety of the loaded aircraft are affected.
In order to ensure the mass balance of a unit cabin body for loading a plurality of aircrafts, a plurality of constraining pieces are arranged on the fixing piece at equal intervals, and the plurality of constraining pieces comprise a first constraining piece and a second constraining piece which are equal in number, the first constraining piece and the second constraining piece are identical in structure, but opposite in installation surface, wherein the installation surface is the surface of the constraining piece in sliding connection with the connecting piece of the aircraft.
The arrangement mode of the first restraint parts and the second restraint parts can be that all the first restraint parts are arranged on one side of the fixing part, and all the second restraint parts are arranged on the other side of the fixing part; the first constraining member and the second constraining member may also be arranged on the whole fixing member in a staggered manner, which is not specifically limited in the embodiment of the present invention. By arranging the first constraint part and the second constraint part in the above manner, the mass balance of the unit cabin body for loading the aircraft in the horizontal direction can be ensured, and the mass balance of the unit cabin body in the vertical direction can also be ensured.
According to the aircraft releasing device provided by the embodiment of the invention, the plurality of restraining parts are arranged at equal intervals, the plurality of restraining parts comprise the first restraining part and the second restraining part which are equal in quantity, the mounting directions of the first restraining part and the second restraining part are opposite, the mass balance of the unit cabin body is ensured, the stable flight of the aircraft releasing device is further ensured, and the potential safety hazard to the aircraft caused by the unstable gravity center of the unit cabin body is reduced.
Based on any one of the above embodiments, fig. 4 is a schematic structural diagram of the aircraft launching device provided by the embodiment of the present invention, and as shown in fig. 4, the device further includes an azimuth adjusting mechanism 240, the azimuth adjusting mechanism is respectively connected to the near space floating platform 210 and the aircraft launching capsule 220, and the azimuth adjusting mechanism 240 is configured to adjust an initial launching azimuth angle of the aircraft.
Specifically, the aircraft launching device provided in the embodiment of the present invention is provided with an orientation adjusting mechanism 240 between the near space floating platform 210 and the aircraft launching capsule 220, and the orientation adjusting mechanism 240 is configured to adjust an initial azimuth angle of the aircraft, where the initial azimuth angle is used to represent an initial direction after the aircraft is launched. Before the launching task is performed, the aircraft may be adjusted to a desired launching orientation by the orientation adjustment mechanism 240 so that the aircraft flies straight to a designated location after launching.
According to the aircraft launching device provided by the embodiment of the invention, the initial azimuth angle of the aircraft is adjusted by arranging the azimuth adjusting mechanism, so that the aircraft directly flies to the specified position after being launched, and the success rate of the information acquisition task is improved.
Based on any one of the embodiments, in the device, a temperature adjusting mechanism is arranged in the unit cabin body or the unit cabin body is covered with a heat insulating material.
In particular, since the electronic components on the aircraft are sensitive to temperature, the electronic components are prone to failure when the temperature is too low. In order to ensure the normal operation of the electronic components of the aircraft, the unit cabin body can be covered with heat insulation materials, so that the electronic components of the aircraft are in an ideal environment temperature. When the aircraft is provided with precise components or electronic components of the aircraft have high requirements on the environmental temperature, a temperature adjusting mechanism can be arranged in the unit cabin body and used for keeping the environmental temperature of the unit cabin body within a specific temperature range, and when the environmental temperature is low, the temperature adjusting mechanism can heat up the unit cabin body through the heating sheet. Because a plurality of unit cabin bodies in the aircraft throwing cabin body are mutually independent, the temperature of each unit cabin body cannot influence each other, and even if the electronic element of the aircraft in a certain unit cabin body fails due to low temperature, the aircraft of other unit cabin bodies cannot be influenced.
Based on any of the above embodiments, the aircraft launching device provided by the embodiments of the present invention is described below by using a specific use method, before an aircraft launching task is performed, an aircraft to be launched is installed in an aircraft launching cabin, a fixed number of aircraft are installed in each unit cabin, and the fixed number is determined according to the number of restraints of an aircraft launching mechanism. During installation, the connecting piece of the aircraft is matched and connected with the mounting surface of the restraint piece, so that the aircraft is ensured to be stably connected. The aircraft throwing cabin body is stably connected with the direction adjusting mechanism, and the aircraft throwing cabin body is stably connected with the near space floating platform. After the loading of the aircraft is completed, the aircraft launching device is lifted off.
After the aircraft launching device reaches the target position, the orientation adjusting mechanism adjusts the initial azimuth angle of the aircraft, the aircraft launching device controls the cabin door of the corresponding unit cabin to be opened through launching control signals of the aircraft corresponding to any unit cabin, based on the launching control signals, the relay control element controls the connection and release of the restraint piece and the connecting piece of the aircraft connected with the restraint piece, and the aircraft directly flies to the designated position according to the initial azimuth angle and continues to execute the information acquisition task.
Based on any one of the above embodiments, fig. 5 is a schematic flow chart of an aircraft launching method provided by an embodiment of the present invention, and as shown in fig. 5, the method includes:
Specifically, the aircraft launching tasks may include a plurality of target point launching tasks, each target point launching task may include position information of a target point and launching information corresponding to each target point, the launching information of each target point may include the number of aircraft that need to be launched by each target point, and the aircraft launching tasks may be set according to an actual application scenario, which is not specifically limited in the embodiment of the present invention. When the aircraft launching device reaches the current target point, the ground control system controls the cabin door of the unit cabin body loaded with the aircrafts in the current batch in the aircraft launching device to be opened, and launches the aircrafts in the current batch, wherein the aircrafts in the current batch are the aircrafts needing to be launched at the current target point. And after the aircraft launching device finishes the current target point launching task, moving to the next target point, and executing the next target point launching task until all target point launching tasks are finished.
The embodiment of the invention takes a near space floating platform as a high-altitude balloon and an aircraft as an unmanned aerial vehicle for example description, and assumes that 300 unmanned aerial vehicles are loaded by an aircraft launching device in total, and a launching task comprises three target points: the unmanned aerial vehicle system comprises a first target point, a second target point and a third target point, wherein the first target point launches a first batch of 100 unmanned aerial vehicles, the second target point launches a second batch of 80 unmanned aerial vehicles, and the third target point launches a third batch of 120 unmanned aerial vehicles.
After 300 unmanned aerial vehicles finish loading, fill helium to high-altitude balloon inside to release through ground infrastructure, make high-altitude balloon carry the aircraft and put in the cabin and go up to the air. According to the principle that wind directions at different heights are different, the weight of ballast on the high-altitude balloon platform is adjusted to enable the high-altitude balloon to be stabilized at the height favorable for the wind direction, the high-altitude balloon flies to a first target point, after the high-altitude balloon reaches the first target point, the ground control system controls the cabin door of a unit cabin body loaded with a first batch of aircrafts to be opened, and 100 unmanned aerial vehicles in a first batch are thrown in; after the first batch of 100 unmanned aerial vehicles are put in, the weight of ballast on the high-altitude balloon platform is adjusted to enable the high-altitude balloons to be stabilized at the wind direction favorable height and fly to a second target point, after the high-altitude balloons reach the second target point, the ground control system controls the cabin doors of unit cabin bodies loaded with second batches of aircrafts to be opened, and a second batch of 80 unmanned aerial vehicles are put in; and repeating the steps to launch 120 unmanned aerial vehicles in the third batch.
According to the aircraft launching method provided by the embodiment of the invention, when the aircraft launching device reaches the current target point, the cabin door of the unit cabin body loaded with the aircrafts in the current batch in the aircraft launching device is controlled to be opened, the aircrafts in the current batch are launched, and after the aircrafts in the current batch are launched, the current target point is updated to be the next target point, so that the aircraft launching tasks in multiple areas can be executed, and the flexibility of launching task design is enhanced.
Based on any of the above embodiments, in this method, step 510 specifically includes:
and controlling an aircraft release mechanism in a unit cabin body loaded with the current batch of aircraft to sequentially release the connection between each restraint part and the connecting part of the corresponding aircraft according to a preset time interval.
Specifically, the launching information of each target point further includes the number of the unit cabin body loaded with the aircraft to be launched, and when the aircraft launching device reaches the current target point, the ground control system controls the aircraft launching mechanism in the unit cabin body loaded with the aircraft in the current batch to sequentially release the connection between each constraint piece and the corresponding aircraft connection piece according to a preset time interval.
For example, there are 100 aircrafts in the current batch, each unit cabin is loaded with 4 aircrafts, the preset time interval is 5 seconds, when the aircraft launching device reaches the current target point, the ground control system controls 25 cabin doors of the unit cabins loaded with 100 aircrafts in the current batch to be opened, each unit cabin successively launches 4 aircrafts according to the sequence of numbers, each unit cabin releases a connection piece between a restraint piece and a connecting piece of the corresponding aircraft every 5 seconds through a relay control element, so that the 4 aircrafts corresponding to each unit cabin are launched successively at intervals of 5 seconds, the situations of mutual collision and mutual interference after the aircrafts are launched are effectively avoided, and the survival rate of the aircrafts and the success rate of information acquisition tasks are improved.
Based on any of the above embodiments, in this method, step 510 specifically includes:
and sending a release request to the aircraft in the current batch, so that the aircraft in the current batch receives the release request, and then controlling the connecting piece of the aircraft in the current batch to sequentially release the connection with the corresponding restraint piece according to a preset time interval.
Specifically, the release information of each target point further comprises a serial number of a unit cabin body loaded with an aircraft to be released and a serial number of the aircraft to be released, when the aircraft release device reaches the current target point, the ground control system controls the release request to be sent to the aircraft in the current batch, so that after the aircraft in the current batch receives the release request, the connecting parts of the aircraft in the current batch are controlled to sequentially release the connection with the corresponding constraint parts according to a preset time interval.
For example, 50 aircrafts are loaded in the current batch, each unit cabin is loaded with 4 aircrafts, the preset time interval is 5 seconds, when the aircraft launching device reaches the current target point, the ground control system sends a launching request to the 50 aircrafts in the current batch, the cabin doors of the 13 unit cabins loaded with the 50 aircrafts in the current batch are opened, the 50 aircrafts in the current batch are sequentially released to be connected with corresponding restraints every 5 seconds according to the sequence of numbering, only two aircrafts are launched in the last unit cabin, and the other two aircrafts do not participate in the current target point launching task.
The difference is that the execution main body for controlling connection and release in the previous embodiment is an aircraft launching mechanism, and the aircraft launching task is implemented by taking a unit cabin as a unit. The aircraft launching method provided by the embodiment of the invention not only effectively avoids the conditions of mutual collision and mutual interference after the aircrafts are launched, but also realizes the independent control of launching of each aircraft and enhances the flexibility of launching task design.
The above-described embodiments of the apparatus are merely illustrative, and the units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (7)
1. An aircraft launching device is characterized by comprising a near space floating platform and an aircraft launching cabin body;
the near space floating platform is used for carrying the aircraft launching cabin to a target position;
the aircraft launching cabin comprises a plurality of unit cabins, the unit cabins are used for loading a plurality of aircrafts, and the opening and closing states of the cabin doors of any one unit cabin are determined based on launching control signals corresponding to the aircrafts in any one unit cabin;
an aircraft throwing mechanism fixedly connected with any unit cabin body is arranged in any unit cabin body;
the aircraft release mechanism comprises a fixing piece and a plurality of restraining pieces, the fixing piece is connected with each restraining piece, the fixing piece is connected with any unit cabin body, and the plurality of restraining pieces are detachably connected with a plurality of aircrafts in any unit cabin body; the aircraft launching mechanism is of a slicing structure;
the aircraft releasing mechanism further comprises a relay control element, each constraint piece is magnetically connected with a connecting piece on each aircraft in any unit cabin, and the relay control element is used for controlling connection and release of the constraint pieces and the corresponding connecting pieces based on release control signals corresponding to the aircraft in any unit cabin.
2. The aircraft delivery apparatus of claim 1, wherein the plurality of restraints are equally spaced apart, and wherein the plurality of restraints comprises a first restraint and a second restraint that are equal in amount, and wherein the first restraint is opposite in direction from a mounting surface of the second restraint.
3. The aircraft launching device according to any one of claims 1-2, further comprising an orientation adjustment mechanism, the orientation adjustment mechanism being connected to the near space floating platform and the aircraft launching cabin, respectively, the orientation adjustment mechanism being configured to adjust an initial launching azimuth angle of the aircraft.
4. The aircraft launch apparatus according to any one of claims 1-2 wherein a temperature adjustment mechanism is provided inside the unit cabin or the unit cabin is covered with insulation.
5. An aircraft delivery method based on the aircraft delivery device according to any one of claims 1 to 4, characterized in that it comprises:
when the aircraft launching device reaches the current target point, controlling the cabin door of the unit cabin body loaded with the aircraft in the current batch in the aircraft launching device to open, and launching the aircraft in the current batch;
and updating the current target point to be the next target point.
6. The aircraft launching method according to claim 5, wherein launching the current batch of aircraft specifically comprises:
and controlling an aircraft release mechanism in a unit cabin body loaded with the current batch of aircraft to sequentially release the connection between each restraint part and the connecting part of the corresponding aircraft according to a preset time interval.
7. The aircraft launching method according to claim 5, wherein launching the current batch of aircraft specifically comprises:
sending a release request to the aircraft in the current batch, so that the aircraft in the current batch is controlled to sequentially release the connection with the corresponding restraint members according to a preset time interval after receiving the release request.
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| GB395568A (en) * | 1931-11-24 | 1933-07-20 | Curt Heber | Improvements in bomb dropping devices for aircraft |
| CN108045543B (en) * | 2017-12-12 | 2021-08-24 | 中国科学院工程热物理研究所 | Unmanned aerial vehicle's dispensing system |
| CN210634740U (en) * | 2019-03-21 | 2020-05-29 | 天津天航智远科技有限公司 | Carry polymorphic type unmanned aerial vehicle's dirigible |
| CN110937111B (en) * | 2019-11-29 | 2022-09-02 | 西北工业大学 | Small-size cluster unmanned aerial vehicle dispensing system of gliding style |
| CN110920892A (en) * | 2019-11-29 | 2020-03-27 | 西北工业大学 | Device is scattered to whole small-size cluster unmanned aerial vehicle of puting in |
| CN110816839A (en) * | 2019-12-17 | 2020-02-21 | 淮安航空产业研究院有限公司 | Unmanned aerial vehicle and system for putting in emergency rescue equipment and people-in-loop putting method thereof |
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2020
- 2020-06-22 CN CN202010576131.XA patent/CN111824386B/en active Active
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