CN113306720A - A device is laid to warhead fixed point for miniature unmanned aerial vehicle - Google Patents
A device is laid to warhead fixed point for miniature unmanned aerial vehicle Download PDFInfo
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- CN113306720A CN113306720A CN202110493777.6A CN202110493777A CN113306720A CN 113306720 A CN113306720 A CN 113306720A CN 202110493777 A CN202110493777 A CN 202110493777A CN 113306720 A CN113306720 A CN 113306720A
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- 230000009471 action Effects 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 9
- 210000001015 abdomen Anatomy 0.000 claims description 7
- 239000003292 glue Substances 0.000 claims description 4
- 208000028804 PERCHING syndrome Diseases 0.000 claims description 3
- 241000269799 Perca fluviatilis Species 0.000 claims 1
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 4
- 238000000926 separation method Methods 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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- 238000011835 investigation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
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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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
- B64D1/06—Bomb releasing; Bombs doors
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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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Abstract
The invention discloses a fixed-point placing device for a warhead of a micro unmanned aerial vehicle, which comprises a top seat, a first steering engine, a second steering engine and a warhead base, wherein the first steering engine is arranged on the top seat; the top seat is provided with a first steering engine and a second steering engine; the first steering engine and the second steering engine are both provided with rocker arms; a rocker arm of the second steering engine is provided with a pin, the base of the warhead is provided with a clamping part, and the second steering engine is clamped with the clamping part of the base of the warhead through the pin; before the base of the warhead is separated, the first steering engine and the second steering engine control the rocker arm to enable the base of the warhead to be close to the lower part of the top seat; when the base of the warhead breaks away from, the second steering engine control rocker arm takes out the pin from the joint of the base of the warhead, so that the base of the warhead is separated from the unmanned aerial vehicle, and the fixed point placement of the warhead is realized. The fixed-point placing device for the warhead is high in placing precision and strong in environmental adaptability, and the using efficiency of the unmanned aerial vehicle is improved.
Description
Technical Field
The invention relates to the technical field of micro unmanned aerial vehicles, in particular to a fixed-point warhead placement device for a micro unmanned aerial vehicle, which can realize accurate fixed-point delivery of various warheads.
Background
The micro unmanned aerial vehicle can provide combat information and execute a striking task at the hidden investigation of the position which is difficult to be perceived by people.
For a long time, the micro unmanned aerial vehicle is often used as a whole machine for fighting, needs to be stagnated for a long time, and is easy to be found by enemies; but often only the combat unit is available for its combat effectiveness. If the miniature unmanned aerial vehicle can accurately deliver the effective combat part to the designated position of the battlefield, and then quickly leave the battlefield; so that the battlefield does not need to be retained for a long time and the battle effect can be achieved.
The traditional warhead release mechanism is mainly based on throwing, can only fall on the ground in an open area, cannot be used in closed environments such as indoor environment and the like, and cannot be arranged on a vertical wall surface; and the precision position precision is low. Therefore, the fixed point placing device which can adapt to the complex battlefield environment is designed, the miniature unmanned aerial vehicle is enabled to accurately place the battlefield part to the designated position of the battlefield, and the design method is a research direction with very high demand.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a fixed-point warhead placing device for a micro unmanned aerial vehicle, so that the unmanned aerial vehicle can accurately place a warhead to a specified position and can meet the installation requirements of a curved plane belly and a plane belly.
The technical scheme of the invention is as follows:
the utility model provides a device is laid to warhead fixed point for miniature unmanned aerial vehicle which characterized in that: the device comprises a top seat, a first steering engine, a second steering engine and a warhead base; the top of the top seat is provided with an interface which is mechanically and electrically connected with the unmanned aerial vehicle, and the top seat is of a semi-closed box-shaped structure and is provided with a first steering engine and a second steering engine; the first steering engine and the second steering engine are both provided with rocker arms; a pin is installed on a rocker arm of the second steering engine, a clamping part is arranged on the base of the warhead, and the second steering engine is clamped with the clamping part of the base of the warhead through the pin; before the base of the warhead is separated, the first steering engine and the second steering engine control the rocker arm to enable the base of the warhead to be close to the lower part of the top seat; when the base of the warhead breaks away from, the second steering engine controls the rocker arm to pull out the pin from the clamping part of the base of the warhead, so that the base of the warhead is separated from the unmanned aerial vehicle, and the fixed-point placement of the warhead is realized.
Preferably, the warhead fixed point placing device for the micro unmanned aerial vehicle is further provided with a support rod, a connecting sleeve and a sleeve-steering engine integrated piece; the rocker arm of the first steering engine is fixedly connected with the support rod through a connecting sleeve; the other end of the supporting rod is fixedly connected with a sleeve part of the sleeve-steering engine integrated piece; the sleeve-steering engine integrated piece is of a semi-closed box type structure and is provided with a second steering engine; and a pin on the second steering engine rocker arm penetrates through the sleeve of the sleeve-steering engine integrated piece and the clamping part at the top of the base of the warhead to connect the sleeve and the base.
Preferably, the device is laid to warhead fixed point for miniature unmanned aerial vehicle can also fix first steering wheel, second steering wheel symmetry installation on the footstock, also install the pin on the rocking arm of first steering wheel, first steering wheel and second steering wheel respectively through the pin with the joint portion block of warhead base, when the warhead base breaks away from, first steering wheel and second steering wheel control rocking arm respectively take the pin out from the joint portion of warhead base for the separation of warhead base and unmanned aerial vehicle.
Preferably, the front ends of the two sides of the top seat are provided with protruding limiting baffles, so that the clamping portion is limited from moving forwards, and the base of the warhead is prevented from being accidentally separated.
Preferably, the clamping portion is a clamping hole or a clamping hook.
Preferably, dry glue is adhered to the lower part of the base of the warhead.
The technical scheme of the invention also relates to a curved-surface ventral unmanned aerial vehicle provided with a warhead fixed-point placing device for the micro unmanned aerial vehicle and a perching method of the curved-surface ventral unmanned aerial vehicle on a vertical wall surface, which are characterized by comprising the following steps of:
the method comprises the following steps that firstly, in a flying state, a support rod is retracted by a first steering engine;
secondly, the unmanned aerial vehicle flies to the vertical wall surface of a stopped building, and a first steering engine in the top seat drives a rocker arm to enable a support rod to be perpendicular to the wall surface;
thirdly, the unmanned aerial vehicle flies to the wall surface at a certain initial speed, under the action of inertia, the pre-tightening force generated by the collision action enables the base of the warhead to be tightly adhered to the wall surface, and the base of the warhead is placed to a specified position;
fourthly, the second steering engine controls the rocker arm to pull out the pin from the sleeve of the sleeve-steering engine integrated piece and the clamping part at the top of the base of the warhead;
fifthly, separating the unmanned aerial vehicle from the base of the warhead to complete fixed-point placement of the warhead;
and sixthly, driving the rocker arm by a first steering engine in the top seat to enable the supporting rod to rotate around the rotating shaft, and withdrawing the supporting rod.
The technical scheme of the invention also relates to a plane ventral unmanned aerial vehicle provided with a warhead fixed-point placing device for the micro unmanned aerial vehicle and a perching method of the plane ventral unmanned aerial vehicle on a vertical wall surface, which are characterized by comprising the following steps:
firstly, the unmanned aerial vehicle flies to the vertical wall surface of a stopped building, and the first steering engine and the second steering engine respectively control the rocker arm to enable the base of the warhead to be tightly attached to the lower part of the footstock;
secondly, the unmanned aerial vehicle flies to the wall surface at a certain initial speed, under the action of inertia, the pre-tightening force generated by the collision action enables the base of the warhead to be tightly adhered to the wall surface, the base of the warhead is placed to a specified position, and the unmanned aerial vehicle is hung on the clamping part at the moment;
thirdly, the first steering engine and the second steering engine respectively control the rocker arm to rotate outwards, so that the unmanned aerial vehicle body is lifted from the clamping part; meanwhile, under the power pushing of the propeller, pins of the first steering engine and the second steering engine move out of the opening of the clamping part, so that the unmanned aerial vehicle is separated from the base of the warhead part;
and fourthly, the first steering engine and the second steering engine drive the rocker arm to retract to the initial position, and the unmanned aerial vehicle flies away from the battlefield.
Compared with the prior art, the fixed-point warhead placing device for the micro unmanned aerial vehicle has the advantages that:
1. the warhead fixed-point placing device for the micro unmanned aerial vehicle ensures that the micro unmanned aerial vehicle only needs to put the warhead with the combat efficiency into a battlefield, and the main body of the unmanned aerial vehicle does not need to stay in the battlefield for a long time, so that the discovery probability of enemies is reduced, and the survival rate of the battlefield is greatly improved.
2. The fixed-point placing device for the warhead of the micro unmanned aerial vehicle can realize point-to-point placing of the warhead, and compared with a release mode of throwing, the precision is greatly improved.
3. The fixed-point warhead placing device for the micro unmanned aerial vehicle adopts a dry adhesive adsorption mode to place the warhead, can adapt to most surfaces, particularly can place the warhead on a vertical wall surface, and has strong environmental adaptability.
4. The fixed-point warhead placing device for the micro unmanned aerial vehicle adopts a modular design, different warheads can be replaced according to different combat requirements, and the use efficiency of the unmanned aerial vehicle is improved.
5. The warhead fixed-point placing device for the micro unmanned aerial vehicle can be assembled for unmanned aerial vehicles with different belly shapes, and the adaptability of the device is improved.
Drawings
Fig. 1 is a schematic view of the overall structure of a warhead fixed-point placement device for a curved-surface ventral micro unmanned aerial vehicle;
FIG. 2 is a schematic view of the placement of the fixed-point warhead placement device for a curved-surface belly micro-unmanned aerial vehicle;
fig. 3 is a schematic overall structure diagram of a warhead fixed-point placement device for a planar ventral micro unmanned aerial vehicle;
fig. 4 is a schematic view of a mounting mode of a warhead fixed-point mounting device for a plane ventral micro unmanned aerial vehicle.
Description of the attached table designations:
1-footstock 1-1-limit baffle 2-first steering engine
3-support rod 4-connecting sleeve 4-1-clamping hook
5-second steering engine 5-1-rocker arm 6-sleeve-steering engine integrated piece
7-pin 8-warhead base 9-wing leading edge locking mechanism
Detailed Description
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 only illustrative and are not intended to limit the present invention.
The invention provides a warhead fixed-point placing device for a micro unmanned aerial vehicle, which is characterized in that: the device comprises a top seat 1, a first steering engine 2, a second steering engine 5 and a warhead base 8; the top of the top seat 1 is provided with an interface which is mechanically and electrically connected with the unmanned aerial vehicle, and the top seat 1 is of a semi-closed box-shaped structure and is provided with a first steering engine 2 and a second steering engine 5; the first steering engine 2 and the second steering engine 5 are both provided with rocker arms; a pin 7 is mounted on a rocker arm of the second steering engine 5, a clamping part is arranged on the base 8 of the warhead, and the second steering engine 5 is clamped with the clamping part of the base 8 of the warhead through the pin 7; before the base 8 of the warhead is separated, the first steering engine 2 and the second steering engine 5 control the rocker arms to enable the base 8 of the warhead to be close to the lower part of the top seat 2; when the warhead base 8 breaks away from, the second steering wheel 5 control rocking arm is taken pin 7 out from the joint of warhead base 8 for warhead base 8 and unmanned aerial vehicle separation realize that the warhead fixed point is laid.
The specific implementation of the warhead fixed-point placement device for the micro unmanned aerial vehicle of the invention is described in detail through specific embodiments.
Example 1
As shown in fig. 1, the warhead fixed point placing device structure for the curved-surface belly micro unmanned aerial vehicle comprises a top seat 1, a first steering engine 2, a support rod 3, a connecting sleeve 4, a second steering engine 5, a sleeve-steering engine integrated piece 6, a pin 7 and a warhead base 8.
Footstock 1 is half closed box structure, and the installation is fixed with first steering wheel 2, and there is the interface simultaneously at the top, carries out mechanical connection with unmanned aerial vehicle, is connected first steering wheel 2 and the electric circuit of second steering wheel 5 with unmanned aerial vehicle simultaneously. The first steering engine 2 is provided with a rocker arm which is fixedly connected with the support rod 3 through a connecting sleeve 4. The other end of the support rod 3 is fixedly connected with the sleeve part of the sleeve-steering engine integrated piece 6. The sleeve-steering engine integrated piece 6 is of a semi-closed box-shaped structure, and a second steering engine 5 is installed in the hollow part of the sleeve-steering engine integrated piece. A rocker arm 5-1 is arranged on the second steering engine 5, and the rocker arm 5-1 is connected with one end of a pin 7. The pin 7 passes through the sleeve of the sleeve-steering engine integrated piece 6 and the opening at the top of the base 8 of the warhead to connect the sleeve and the steering engine.
As shown in figure 2, when unmanned aerial vehicle was in flight state, first steering wheel 2 packed up bracing piece 3, and this air resistance when effectively having reduced the flight, and pin 7 was in all the time and inserts sleeve trompil and 8 top trompils of warhead base this moment. When the warhead breaks away from, the pin 7 is taken out from the trompil at the sleeve of sleeve-steering wheel integrated piece 6 and 8 tops of warhead base to second steering wheel 5 control rocking arm 5-1 for warhead base 8 and unmanned aerial vehicle separation realize that the warhead fixed point is laid.
The inhabitation method of the unmanned aerial vehicle on the vertical wall surface comprises the following specific steps:
firstly, in a flight state, a first steering engine 2 retracts a support rod 3;
secondly, the unmanned aerial vehicle flies to the vertical wall surface of a stopped building, and the first steering engine 2 in the top seat 1 drives the rocker arm to enable the support rod 3 to be perpendicular to the wall surface;
thirdly, the unmanned aerial vehicle flies to the wall surface at a certain initial speed, under the action of inertia, the base of the warhead base 8 is tightly adhered to the wall surface by the pretightening force generated by the collision action, and the base of the warhead is placed to a specified position;
fourthly, the second steering engine 2 controls the rocker arm 5-1 to pull out the pin 7 from the sleeve of the sleeve-steering engine integrated piece 6 and a clamping hole at the top of the base 8 of the warhead;
fifthly, separating the unmanned aerial vehicle from the base 8 of the warhead to complete fixed-point placement of the warhead;
and sixthly, driving the rocker arm by the first steering engine 2 in the top seat 1 to enable the support rod 3 to rotate around the rotating shaft, and withdrawing the support rod 3.
Example 2
As shown in figure 1, the warhead fixed point placing device structure for the plane ventral micro unmanned aerial vehicle comprises a top seat 1, a first steering engine 2, a second steering engine 5 and a warhead base 8.
The footstock 1 is of a semi-closed box-shaped structure, two symmetrical first steering engines 2 and two symmetrical second steering engines 5 are fixedly arranged, and pins 7 at the tail sections of the two steering engine rocker arms are clamped in clamping hooks 4-1 at the left side and the right side of the top of a warhead base 8. The top seat 1 can be embedded into a plane belly for installation, and the front ends of the two sides of the top seat 1 are provided with protruding limit baffles 1-1. When the base 8 of the warhead clings to the top seat 1, the limiting baffle 1-1 limits the hook 4-1 to move forwards, and the base 8 of the warhead is prevented from being accidentally separated from the front end. The warhead base 8 is provided with adhesive dry glue which has strong viscosity, can be adhered to various surfaces, particularly vertical wall surfaces, and can support the weight of the whole machine; the platform has the characteristic of modularization and universalization, and the warhead can be replaced according to different task requirements.
As shown in fig. 4, before the base 8 of the warhead part is separated from the unmanned aerial vehicle, the first steering engine 2 and the second steering engine 5 control the rocker arm to tightly attach the base 8 of the warhead part to the footstock 1. After the base 8 of the warhead is adsorbed on the wall surface, the unmanned aerial vehicle is suspended on the hook 4-1 through the pin 7, and the pin 7 and the hook 4-1 bear the weight of the unmanned aerial vehicle. When the base 8 of the warhead part is separated from the unmanned aerial vehicle, the first steering engine 2 and the second steering engine 5 control the rocker arm to rotate outwards, so that the body is lifted from the clamping hook 4-1; meanwhile, under the power pushing of the propeller, the pin 7 is moved out from the opening of the hook 4-1, so that the unmanned aerial vehicle is separated from the warhead.
The inhabitation method of the unmanned aerial vehicle on the vertical wall surface comprises the following specific steps:
firstly, the unmanned aerial vehicle flies to the vertical wall surface of a stopped building, and a first steering engine 2 and a second steering engine 5 respectively control a rocker arm to enable a warhead base 8 to be tightly attached to the lower portion of a top seat 1;
secondly, the unmanned aerial vehicle flies to the wall surface at a certain initial speed, under the action of inertia, the pretightening force generated by the collision action enables the warhead base 8 to adhere to the dry glue and tightly adhere to the wall surface, the warhead base 8 is placed to a specified position, and the unmanned aerial vehicle is hung on the hook 4-1;
thirdly, the first steering engine 2 and the second steering engine 5 respectively control the rocker arms to rotate outwards, so that the unmanned aerial vehicle body is lifted from the clamping hook 4-1 by taking the pin 7 as a fulcrum; meanwhile, under the power pushing of the propeller, the pin 7 of the first steering engine and the pin 7 of the second steering engine move out of the opening of the hook 4-1, so that the unmanned aerial vehicle is separated from the base 8 of the warhead;
and fourthly, the first steering engine 2 and the second steering engine 5 drive the rocker arm to retract to the initial position, and the unmanned aerial vehicle flies away from the battlefield.
The above-described embodiments are merely preferred embodiments of the present invention, which is not intended to limit the present invention in any way. Those skilled in the art can make many changes, modifications, and equivalents to the embodiments of the invention without departing from the scope of the invention as set forth in the claims below. Therefore, equivalent variations made according to the idea of the present invention should be covered within the protection scope of the present invention without departing from the contents of the technical solution of the present invention.
Claims (10)
1. The utility model provides a device is laid to warhead fixed point for miniature unmanned aerial vehicle which characterized in that: the device comprises a top seat, a first steering engine, a second steering engine and a warhead base; the top of the top seat is provided with an interface which is mechanically and electrically connected with the unmanned aerial vehicle, and the top seat is of a semi-closed box-shaped structure and is provided with a first steering engine and a second steering engine; the first steering engine and the second steering engine are both provided with rocker arms; a pin is installed on a rocker arm of the second steering engine, a clamping part is arranged on the base of the warhead, and the second steering engine is clamped with the clamping part of the base of the warhead through the pin; before the base of the warhead is separated, the first steering engine and the second steering engine control the rocker arm to enable the base of the warhead to be close to the lower part of the top seat; when the base of the warhead breaks away from, the second steering engine controls the rocker arm to pull out the pin from the clamping part of the base of the warhead, so that the base of the warhead is separated from the unmanned aerial vehicle, and the fixed-point placement of the warhead is realized.
2. The warhead fixed point placement device for the micro unmanned aerial vehicle as claimed in claim 1, further comprising a support rod, a connecting sleeve, and a sleeve-steering engine integrated piece; the rocker arm of the first steering engine is fixedly connected with the support rod through a connecting sleeve; the other end of the supporting rod is fixedly connected with a sleeve part of the sleeve-steering engine integrated piece; the sleeve-steering engine integrated piece is of a semi-closed box type structure and is provided with a second steering engine; and a pin on the second steering engine rocker arm penetrates through the sleeve of the sleeve-steering engine integrated piece and the clamping part at the top of the base of the warhead to connect the sleeve and the base.
3. The warhead fixed point placing device for the micro unmanned aerial vehicle is characterized in that a first steering engine and a second steering engine are symmetrically installed and fixed on a top seat, a pin is also installed on a rocker arm of the first steering engine, the first steering engine and the second steering engine are respectively clamped with a clamping part of a base of the warhead through the pin, when the base of the warhead is separated, the first steering engine and the second steering engine respectively control the rocker arm to pull out the pin from the clamping part of the base of the warhead, and therefore the base of the warhead is separated from the unmanned aerial vehicle.
4. The warhead fixed point placing device for the micro unmanned aerial vehicle as claimed in claim 3, wherein the front ends of the two sides of the top seat are provided with protruding limit baffles, which limit the forward movement of the clamping part and prevent the base of the warhead from accidentally disengaging.
5. The device for placing the warhead fixed point of the unmanned aerial vehicle as claimed in any one of claims 1-4, wherein the clip portion is a clip hole or a clip hook.
6. The device for placing the warhead fixed point of the unmanned aerial vehicle as claimed in any one of claims 1-4, wherein the lower part of the base of the warhead is adhered with dry glue.
7. A curved ventral drone provided with a warhead fixed-point placement device for a drone according to any one of claims 2, 5, 6.
8. The perch method of the curved belly drone provided with the warhead fixed-point placement device for the micro drone according to claim 7, characterized by the following steps:
the method comprises the following steps that firstly, in a flying state, a support rod is retracted by a first steering engine;
secondly, the unmanned aerial vehicle flies to the vertical wall surface of a stopped building, and a first steering engine in the top seat drives a rocker arm to enable a support rod to be perpendicular to the wall surface;
thirdly, the unmanned aerial vehicle flies to the wall surface at a certain initial speed, under the action of inertia, the pre-tightening force generated by the collision action enables the base of the warhead to be tightly adhered to the wall surface, and the base of the warhead is placed to a specified position;
fourthly, the second steering engine controls the rocker arm to pull out the pin from the sleeve of the sleeve-steering engine integrated piece and the clamping part at the top of the base of the warhead;
fifthly, separating the unmanned aerial vehicle from the base of the warhead to complete fixed-point placement of the warhead;
and sixthly, driving the rocker arm by a first steering engine in the top seat to enable the supporting rod to rotate around the rotating shaft, and withdrawing the supporting rod.
9. A planar ventral drone provided with a warhead pointing placement device for a drone according to any one of claims 3-6.
10. A method for perching a planar ventral drone, provided with a warhead fixed-point placement device for a micro drone, on a vertical wall, according to claim 9, characterized by the following steps:
firstly, the unmanned aerial vehicle flies to the vertical wall surface of a stopped building, and the first steering engine and the second steering engine respectively control the rocker arm to enable the base of the warhead to be tightly attached to the lower part of the footstock;
secondly, the unmanned aerial vehicle flies to the wall surface at a certain initial speed, under the action of inertia, the pre-tightening force generated by the collision action enables the base of the warhead to be tightly adhered to the wall surface, the base of the warhead is placed to a specified position, and the unmanned aerial vehicle is hung on the clamping part at the moment;
thirdly, the first steering engine and the second steering engine respectively control the rocker arm to rotate outwards, so that the unmanned aerial vehicle body is lifted from the clamping part; meanwhile, under the power pushing of the propeller, pins of the first steering engine and the second steering engine move out of the opening of the clamping part, so that the unmanned aerial vehicle is separated from the base of the warhead part;
and fourthly, the first steering engine and the second steering engine drive the rocker arm to retract to the initial position, and the unmanned aerial vehicle flies away from the battlefield.
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| CN109178315A (en) * | 2018-10-30 | 2019-01-11 | 北京航空航天大学 | A kind of scouting operation miniature drone of absorption type |
| WO2020152665A1 (en) * | 2019-01-22 | 2020-07-30 | Pearls Of Wisdom Advanced Technologies Ltd | A system and method for a sensor wall placing uav |
| CN110203397A (en) * | 2019-06-10 | 2019-09-06 | 华南农业大学 | Detachable high-altitude fixed operation platform and operation recovery method based on UAV flight |
| CN110466743A (en) * | 2019-07-12 | 2019-11-19 | 南京航空航天大学 | Unmanned plane and non-horizontal surface landing takeoff method based on bionical dry pasting material |
| CN111024011A (en) * | 2019-12-06 | 2020-04-17 | 北京理工大学 | Measuring system and method for determining explosive core position of warhead by wireless sensor network |
| CN111532428A (en) * | 2020-04-28 | 2020-08-14 | 北京航空航天大学 | Tilting power micro fixed wing unmanned aerial vehicle capable of freely taking off and landing |
| CN111532429A (en) * | 2020-05-09 | 2020-08-14 | 北京航空航天大学 | Miniature fixed wing unmanned aerial vehicle capable of being adsorbed on plane |
| CN111559502A (en) * | 2020-05-26 | 2020-08-21 | 中国人民解放军32181部队 | Unmanned aerial vehicle throwing type energy-gathering destroying equipment and destroying method |
| CN111874217A (en) * | 2020-06-16 | 2020-11-03 | 北京航空航天大学 | Unmanned aerial vehicle adsorption equipment with jack |
| CN112224412A (en) * | 2020-09-30 | 2021-01-15 | 北京理工大学 | Onboard anti-armor adsorbable warhead |
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