CN116105550A - Inflatable unfolding patrol projectile with multiple modes - Google Patents
Inflatable unfolding patrol projectile with multiple modes Download PDFInfo
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- CN116105550A CN116105550A CN202111327010.2A CN202111327010A CN116105550A CN 116105550 A CN116105550 A CN 116105550A CN 202111327010 A CN202111327010 A CN 202111327010A CN 116105550 A CN116105550 A CN 116105550A
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- 230000007246 mechanism Effects 0.000 claims abstract description 7
- 238000000034 method Methods 0.000 claims description 5
- 239000007788 liquid Substances 0.000 claims description 4
- 239000000446 fuel Substances 0.000 description 3
- 238000005457 optimization Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000035484 reaction time Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
- F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
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- Professional, Industrial, Or Sporting Protective Garments (AREA)
Abstract
The invention discloses an inflatable unfolding fly-round projectile with multiple modes, which is characterized in that an unfolding flexible wing (2) and a wing disengaging mechanism are arranged on a fuselage (1), the wing disengaging mechanism is used for disengaging the flexible wing (2) from the fuselage (1), and a rocket engine is arranged at the tail of the fuselage (1). The multi-mode inflatable unfolding patrol projectile disclosed by the invention has the advantages of flexible operation, high precision, low cost, long cruising time and the like.
Description
Technical Field
The invention relates to an inflatable unfolding patrol projectile with multiple modes, and belongs to the technical field of aircrafts.
Background
The patrol missile is an intelligent missile weapon between the cruise missile and the unmanned aerial vehicle, the missile can patrol and fly for a period of time in a target area to search for a target and attack after positioning the target, and the patrol missile can shorten the attack reaction time, prevent enemies from hiding the target in a short time, does not need to place a high-value launching platform near the target area, and can realize more selective attack and the like, so that the intelligent missile weapon is widely used.
The cruise control is optimized for constant speed remote flight in both propulsion system and wing or lift fuselage designs, and is generally unable to cruise at low fuel efficiency speeds, which significantly reduces the potential cruise time and reduces its cruising ability.
Moreover, the launching mode of the patrol projectile is not flexible enough, so that the adaptability to the environment is poor.
Accordingly, intensive research into the patrol projectile is necessary to solve the above problems.
Disclosure of Invention
In order to overcome the problems, the inventor conducts intensive research, designs an inflatable unfolding patrol projectile with multiple modes, can effectively improve the load capacity and the cruising time of the patrol projectile, optimizes the unit cost, realizes various flexible emission forms such as individual shoulder lever type emission or vertical take-off and landing emission, and has the effects of hiding cruise monitoring targets for a long time, being capable of returning quickly and the like.
In particular, the invention discloses an inflatable unfolding patrol projectile with multiple modes, an unfolding flexible wing 2 is arranged on a fuselage 1,
on the fuselage 1 is provided a wing release mechanism for releasing the flexible wing 2 from the fuselage 1
A rocket engine is arranged at the tail part of the machine body 1.
In a preferred embodiment, the flexible wing 2 is an inflatable wing with an air chamber inside.
In a preferred embodiment, a rotor 21 is provided at the front end of the flexible wing 2.
In a preferred embodiment, the flexible wing 2 is an flying wing configuration.
In a preferred embodiment, the flexible airfoil 2 after deployment is a NACA4418 airfoil.
In a preferred embodiment, the air chamber of the flexible wing 2 is divided into a plurality of air chambers by air beams.
In a preferred embodiment, wing connecting grooves 11 corresponding to the shape of the flexible wing 2 are symmetrically provided in the middle of the fuselage 1 to mount the flexible wing 2.
In a preferred embodiment, the rocket engine is a two-component liquid rocket engine.
In a preferred embodiment, the flying patrol has a landing gear 3, the landing gear 3 being mounted on the fuselage 1, the landing gear 3 being used to erect the fuselage 1 to the ground.
In a preferred embodiment, the landing gear 3 includes a plurality of support rods 31 and a plurality of links 32, the plurality of support rods 31 are uniformly disposed in the circumferential direction of the fuselage 1, the links 32 are telescopic rods or rods capable of swinging, and the links 32 connect the middle portions of the support rods 31 with the fuselage 1.
On the other hand, the invention also provides a method for controlling the patrol projectile, which is realized by adopting the patrol projectile and comprises the following steps:
s1, starting a rocket engine and launching patrol missiles
S2, unfolding the flexible wings, and carrying out patrol flight by the patrol projectile;
s3, the flexible wings are separated from the flying following projectile, and the flying following projectile strikes or returns.
The invention has the beneficial effects that:
(1) The control is flexible, various flight tasks can be completed, the precision is high, and the cost is low;
(2) The wing is inflatable, so that the weight is light, and the occupied volume is small when the wing is not used;
(3) The cruising time of the patrol projectile can be greatly increased, and the recovery and the utilization of the patrol projectile are realized.
Drawings
FIG. 1 illustrates a schematic top view of an inflatable deployed patrol projectile having multiple modes according to a preferred embodiment of the invention;
FIG. 2 illustrates a schematic side view of an inflatable deployed patrol projectile having multiple modes according to a preferred embodiment of the invention;
FIG. 3 illustrates a schematic cross-sectional view of an inflatable deployed patrol projectile airfoil having multiple modes according to a preferred embodiment of the invention;
FIG. 4 is a graph of lift coefficient versus angle of attack for an inflatable deployed cruise ship airfoil having multiple modes according to a preferred embodiment of the invention;
FIG. 5 is a graph of lift-drag ratio versus angle of attack for an inflatable deployed cruise ship airfoil having multiple modes according to a preferred embodiment of the invention;
FIG. 6 illustrates a flexible wing air chamber optimization schematic of an inflatable deployed cruise ship having multiple modes according to a preferred embodiment of the invention;
FIG. 7 illustrates a schematic view of a flexible wing air chamber after optimization of an inflatable deployed cruise ship having multiple modes according to a preferred embodiment of the present invention;
FIG. 8 illustrates a schematic view of an inflatable deployed patrol projectile fuselage structure having multiple modes according to a preferred embodiment of the invention;
FIG. 9 illustrates a schematic view of an inflatable deployed cruise ship landing gear with multiple modes according to a preferred embodiment of the present invention;
FIG. 10 illustrates a schematic diagram of a method of using an inflatable deployed patrol projectile having multiple modes according to a preferred embodiment of the invention.
Description of the reference numerals
1-a fuselage;
2-flexible wings;
3-landing gear;
11-wing attachment grooves;
21-rotor;
22-control surface;
31-supporting rods;
32-connecting rod.
Detailed Description
The invention is further described in detail below by means of the figures and examples. The features and advantages of the present invention will become more apparent from the description.
The word "exemplary" is used herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are illustrated in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
According to the inflatable unfolding fly-round with multiple modes disclosed by the invention, the unfolding flexible wings 2 are arranged on the fuselage 1, as shown in figures 1 and 2, in the cruising stage, the flexible wings 2 are unfolded, so that the energy consumption in the cruising stage is reduced, and the cruising time is prolonged.
The expandable flexible wing is folded in the fuselage or outside in advance, can be rapidly expanded when needed, provides lift for the aircraft, and has the characteristics of small volume, light weight, rapid expansion and the like after being folded.
In the invention, the flexible wings 2 are symmetrically arranged at two sides of the middle part of the airframe.
Further preferably, in the invention, the flexible wing is an inflatable wing, the air chamber is arranged in the flexible wing, when the patrol projectile is launched, the flexible wing is in a folded state, after launching and taking off, the air chamber of the flexible wing is inflated, so that the flexible wing is unfolded for cruising, and the unfolded flexible wing can provide larger lifting force, thereby reducing the fuel consumption of the patrol projectile and effectively improving the cruising capability of the patrol projectile.
In a preferred embodiment, the deployment of the flexible wings is effected by inflation of high pressure air stored in the fuselage.
In a preferred embodiment, the flexible wing employs an flying wing configuration that allows the wing to be relatively bulky so that it has a large enough space to accommodate the exhaust chamber for the fill gas, thereby achieving high load carrying efficiency.
In a more preferred embodiment, NACA4418 airfoil is selected as the airfoil after the flexible airfoil is deployed, as shown in FIG. 3, the NACA4418 airfoil has a greater thickness, which provides a large interior space and facilitates post-processing, and the thick airfoil also has better bending load bearing capability.
The inventor discovers that the ratio coefficient of the lifting force of the patrol flying projectile to the attack angle is 0.9-1.1, and the ratio coefficient of the lifting resistance to the attack angle is 1:5 to 1: and 7, the cruising energy efficiency is highest, namely the fuel consumption is lower under the same cruising distance, the lift coefficient and the lift-drag ratio of the NACA4418 airfoil are suitable for cruising of the fly bomb, the relation between the lift coefficient and the attack angle is shown in figure 4, and the relation between the lift-drag ratio and the attack angle is shown in figure 5.
In a preferred embodiment, the air chamber of the flexible wing is optimized to improve the performance of the wing.
The optimization refers to dividing the air chamber of the flexible wing into a plurality of air chambers through the air beam.
Specifically, a first inscribed circle is arranged at the front end of the airfoil section, and the inscribed circle is tangent to the front end of the airfoil section, the upper end of the airfoil section and the lower end of the airfoil section respectively, as shown in fig. 6;
further, a second inscribed circle is arranged at the rear end of the first inscribed circle, passes through the center of the first inscribed circle and is tangent to the upper end and the lower end of the wing section respectively; repeating the above process, setting a plurality of inscribed circles, wherein the next inscribed circle passes through the center of the last inscribed circle and is tangent to the upper end of the wing section and the lower end of the wing section respectively;
and taking the common chord of the inscribed circles as a dividing line of the air chamber, taking the contour line formed by the circular arcs as the upper end curve and the lower end curve of the approximate wing profile, and transversely expanding to obtain the optimized flexible wing.
The optimized flexible wing is provided with a plurality of air beams, the cross sections of the air beams are shown in fig. 7, the air beams have the advantages of good integrity and strong bearing capacity, and the air beams have better bearing deformation resistance, and the bending resistance and the torsion resistance of the air beams are close to those of the rigid wing.
In a more preferred embodiment, 14 gas beams are arranged to divide the wing section into 15 gas chambers, the last gas chamber has the same tail structure as the original wing section, and experiments prove that the division can furthest improve the bearing deformation resistance of the flexible wing when the projection area of the wing section is 1.2-1.8 square meters.
According to the invention, the flexible wing 2 is in a folded state in the launching stage of the patrol projectile, and the flexible wing 2 is separated from the fuselage 1 in the striking stage of the patrol projectile, namely, the patrol projectile flies at a high speed, and the flexible wing does not bring larger resistance and does not generate excessive negative influence on the patrol projectile flying at a high altitude.
According to the invention, in order to facilitate the retraction and the multipurpose use, the middle part of the body 1 of the flying patrol is a cylinder, as shown in fig. 8, the head of the body 1 is a semi-rotational ellipsoid, and a radar detector component and a control component are arranged inside the semi-rotational ellipsoid of the body 1.
In a preferred embodiment, the head part of the body 1 is made of transparent materials, so that a visual detector such as a high-definition camera or the like is conveniently arranged inside the head part of the body 1.
In a preferred embodiment, wing connecting grooves 11 corresponding to the shape of the flexible wing 2 are symmetrically provided in the middle of the fuselage 1 to mount the flexible wing 2.
Further preferably, a wing detachment mechanism is provided on the fuselage 1 so that detachment of the flexible wing 2 from the fuselage 1 is controllable, and in the present invention, the specific structure of the wing detachment mechanism is not particularly limited as long as detachment controllability of the flexible wing can be achieved, for example, the fuselage and the flexible wing are connected by explosion bolts.
Further preferably, the front end of the airframe 1 is also provided with a folded fairing, the fairing is an annular thin wall after being unfolded and can be clung to the middle part of the airframe 1, and when the flexible wing 2 is not separated from the airframe 1, the fairing is blocked by the flexible wing 2 to be in a folded state; after the flexible wing 2 is separated from the fuselage 1, the fairing is rapidly unfolded along the fuselage 1 under the influence of flight windage, so that the connection groove 11 of the fuselage is covered, and the overall aerodynamic performance of the patrol projectile is ensured.
In a preferred embodiment, the total length of the flying patrol projectile is 1200-1500mm, the head of the fuselage 1 is 100-250mm, the middle of the fuselage 1 is 800-1000mm, and after the flexible wings are unfolded, the maximum thickness position of the wing profile is 200-250mm, preferably 232mm; the maximum relative thickness of the wing profile at the average geometrical chord of the wing is 120-160mm, preferably 144.72mm; the wing infiltration area is 3.5-4 square meters, preferably 3.777 square meters; the projected area of the wing is 1.2-1.8 square meters, preferably 1.584 square meters; the wing volume is 0.15-0.3 cubic meters, preferably 0.214 cubic meters;
under the above-mentioned size, the interior space size of the patrol projectile can realize the loading of traditional patrol projectile module, and the lift that flexible wing provided can support the uniform velocity flat flight of patrol projectile.
In a preferred embodiment, at the front end of the flexible wing 2, a rotor 21 is further provided, the rotor 21 being of a foldable structure, and when the flexible wing 2 is folded, the rotor 21 is in a folded state; when flexible wing 2 is deployed, rotor 21 is deployed, as shown in fig. 1 and 2, and rotor 21 provides the flight power of the cruise projectile during cruise phase.
In the present invention, the specific structure of the foldable structure of the rotor 21 is not particularly limited, and any conventional foldable structure, such as the same structure as a foldable propeller, may be adopted by those skilled in the art.
According to the aircraft, the control surfaces 22 are symmetrically arranged on two sides of the tail of the aircraft body, and the two control surfaces 22 are respectively controlled by one steering engine to realize deflection angle swing so as to control the flight direction of the patrol projectile.
Furthermore, a rocket engine is arranged at the tail part of the machine body 1 to provide power for the stage of launching and rapid striking of the patrol projectile, so as to realize the requirements of light weight, high-speed cruising, striking and the like.
In a preferred embodiment, the rocket engine is a two-component liquid rocket engine, and compared with a conventional engine, the two-component liquid rocket engine has the advantages of simple structure, light weight, high leak-free thrust-mass ratio, low cost and the like.
The patrol projectile with the preferable mode is subjected to software analysis and simulation prediction, and under the condition that the total weight of the patrol projectile is 6kg, the range of 80km and the cruising time of 2 hours can be realized; under the condition of the total weight of 7-50kg, the traditional cruise bomb can only realize the range of 20-70 km and the cruise time of 0.5-1 hour, adopts an expandable flexible wing scheme, particularly adopts an optimized NACA4418 wing profile as a wing profile after the flexible wing is expanded, and has the advantages that the ratio coefficient of lift force to attack angle can reach 1, and the ratio coefficient of lift resistance to attack angle can reach 1: and 6, the effective range of the patrol projectile can be greatly improved, and the cruising time of the patrol projectile can be greatly prolonged. In a preferred embodiment, the flying patrol bullet further has a landing gear 3, the landing gear 3 is mounted on the body 1, and the landing gear 3 is used for erecting the body 1 on the ground, so that the flying patrol bullet can be launched without auxiliary launching equipment and can be stably dropped during flying patrol and return voyage.
In a preferred embodiment, the landing gear 3 includes a plurality of support rods 31, preferably 4 support rods 31, where the plurality of support rods 31 are uniformly disposed in the circumferential direction of the fuselage 1, and the landing gear 3 further includes a plurality of links 32, where the links 32 are telescopic rods or rods capable of swinging, and the links 32 connect the middle part of the support rods 31 with the fuselage 1, and expansion and contraction of the support rods 31 are achieved by telescopic or swinging of the links 32.
Preferably, the connecting rod 32 controls the telescopic or swinging motion of the connecting rod through a steering engine.
When the support bar 31 is contracted, the support bar 31 is parallel to the axis of the body 1; when the supporting rods 31 are unfolded, the supporting rods 31 form an included angle with the axis of the machine body 1, so that the machine body 1 can be supported to stand under the combined action of the supporting rods 31.
The invention also discloses a method for controlling the patrol projectile, which is realized by adopting the multi-mode inflatable unfolding patrol projectile, as shown in fig. 10, and comprises the following steps:
s1, starting a rocket engine and launching patrol missiles
S2, unfolding the flexible wings, and carrying out patrol flight by the patrol projectile;
s3, the flexible wings are separated from the flying following projectile, and the flying following projectile strikes or returns.
In S1, the patrol projectile can have various emission modes, including single-soldier lever type emission and vertical take-off and landing emission.
The single-soldier lever type emission refers to that the patrol projectile is emitted by virtue of an emission barrel;
the vertical take-off and landing launching refers to the launching of a patrol projectile by means of power generated by a rocket engine when a fuselage is vertical under the support of a landing gear.
Preferably, the landing gear support rod contracts after the flying round is launched and lifted.
In S2, when the patrol projectile adopts a single-soldier lever type launching mode, after the patrol projectile enters the air, the flexible wings are inflated and unfolded, the rotor wings are unfolded, the rotor wings start to work under the driving of the motor, after the patrol projectile reaches a preset height, the patrol projectile provides flight power by virtue of the flexible wings and the rotor wings, and the cruise is started to enter a patrol mode.
Preferably, the flexible wings are inflated and deployed by high pressure air stored in the fuselage.
When the patrol projectile directly and vertically takes off by means of the landing gear, the flexible wings are unfolded before launching, and the rotor starts to work under the drive of the motor, so that the rocket engine and the rotor jointly provide power when the patrol projectile launches, the launching speed of the patrol projectile is improved, after the patrol projectile reaches a preset height, the patrol projectile provides flight power by means of the flexible wings and the rotor, and the patrol projectile starts to fly flat and cruises, and enters a patrol flight mode.
Further, in the cruise mode, the target area is searched, and because the cruise mode provides flight power by the flexible wings and the rotor wings, the cruise control system has low energy consumption and low noise, and can realize long-time stealth cruising or monitoring of the target.
In S3, when the patrol projectile needs to be hit or returned, the flexible wings are separated from the patrol projectile, and the patrol projectile can hit or return quickly and accurately to the target under the control of the pushing of the rocket engine and the control surface.
Preferably, when the patrol projectile is sailed back, after reaching the sailing place, the landing gear supporting rod is unfolded, so that the patrol projectile can vertically land, and the recovery and the reutilization of the patrol projectile are realized.
In the description of the present invention, it should be noted that the positional or positional relationship indicated by the terms such as "upper", "lower", "inner", "outer", "front", "rear", etc. are based on the positional or positional relationship in the operation state of the present invention, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," "fourth," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected in common; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
The invention has been described above in connection with preferred embodiments, which are, however, exemplary only and for illustrative purposes. On this basis, the invention can be subjected to various substitutions and improvements, and all fall within the protection scope of the invention.
Claims (10)
1. An inflatable unfolding fly-round with multiple modes is characterized in that an unfolding flexible wing (2) and a wing detaching mechanism are arranged on a fuselage (1), the wing detaching mechanism is used for detaching the flexible wing (2) from the fuselage (1),
a rocket engine is arranged at the tail part of the machine body (1).
2. The inflatable deployed cruise ship projectile having multiple modes according to claim 1,
the flexible wing (2) is an inflatable wing, and an air chamber is arranged in the flexible wing.
3. The inflatable deployed cruise ship projectile having multiple modes according to claim 1,
a rotor (21) is provided at the front end of the flexible wing (2).
4. The inflatable deployed cruise ship projectile having multiple modes according to claim 1,
the flexible wings (2) are in an all-wing layout.
5. The inflatable deployed flying projectile having multiple modes according to claim 2,
the air chamber of the flexible wing (2) is divided into a plurality of air chambers by the air beam.
6. The inflatable deployed flying projectile having multiple modes according to any one of claims 1-5,
wing connecting grooves (11) corresponding to the shape of the flexible wings (2) are symmetrically arranged in the middle of the fuselage (1) so as to install the flexible wings (2).
7. The inflatable deployed flying projectile having multiple modes according to any one of claims 1-5,
the rocket engine is a double-component liquid rocket engine.
8. The inflatable deployed flying projectile having multiple modes according to any one of claims 1-5,
the fly-by-wire has a landing gear (3), the landing gear (3) is mounted on the fuselage (1), and the landing gear (3) is used for erecting the fuselage (1) on the ground.
9. The inflatable deployed flying projectile having multiple modes according to claim 8,
the landing gear (3) comprises a plurality of supporting rods (31) and a plurality of connecting rods (32), the supporting rods (31) are uniformly arranged on the circumference of the machine body (1), the connecting rods (32) are telescopic rods or rod bodies capable of swinging, and the middle parts of the supporting rods (31) are connected with the machine body (1) through the connecting rods (32).
10. A method of controlling a patrol projectile using an inflatable deployed patrol projectile having multiple modes according to any one of claims 1-9, comprising the steps of:
s1, starting a rocket engine and launching patrol missiles
S2, unfolding the flexible wings, and carrying out patrol flight by the patrol projectile;
s3, the flexible wings are separated from the flying following projectile, and the flying following projectile strikes or returns.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111327010.2A CN116105550A (en) | 2021-11-10 | 2021-11-10 | Inflatable unfolding patrol projectile with multiple modes |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111327010.2A CN116105550A (en) | 2021-11-10 | 2021-11-10 | Inflatable unfolding patrol projectile with multiple modes |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120097801A1 (en) * | 2010-10-24 | 2012-04-26 | Barrett Ronald M | Supersonic hovering air vehicle |
| US20160096613A1 (en) * | 2014-09-10 | 2016-04-07 | Jonathon Thomas Johnson | Vtol symmetric airfoil fuselage of fixed wing design |
| CN105865271A (en) * | 2016-05-27 | 2016-08-17 | 中国人民解放军国防科学技术大学 | Portable missile adopting fast inflatable missile wings |
| CN108482635A (en) * | 2018-03-16 | 2018-09-04 | 中国人民解放军国防科技大学 | Inflator wing type aircraft capable of being parked |
| CN109269363A (en) * | 2018-11-16 | 2019-01-25 | 湖南省军合科技有限公司 | A kind of Flying-wing individual soldier hand-thrown type scout missile |
| CN110371283A (en) * | 2019-07-08 | 2019-10-25 | 中国人民解放军国防科技大学 | Intelligent flexible inflatable wing unmanned aerial vehicle structure |
| US10676172B1 (en) * | 2018-04-20 | 2020-06-09 | Northrop Grumman Systems Corporation | Deployable wing for an aircraft |
-
2021
- 2021-11-10 CN CN202111327010.2A patent/CN116105550A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120097801A1 (en) * | 2010-10-24 | 2012-04-26 | Barrett Ronald M | Supersonic hovering air vehicle |
| US20160096613A1 (en) * | 2014-09-10 | 2016-04-07 | Jonathon Thomas Johnson | Vtol symmetric airfoil fuselage of fixed wing design |
| CN105865271A (en) * | 2016-05-27 | 2016-08-17 | 中国人民解放军国防科学技术大学 | Portable missile adopting fast inflatable missile wings |
| CN108482635A (en) * | 2018-03-16 | 2018-09-04 | 中国人民解放军国防科技大学 | Inflator wing type aircraft capable of being parked |
| US10676172B1 (en) * | 2018-04-20 | 2020-06-09 | Northrop Grumman Systems Corporation | Deployable wing for an aircraft |
| CN109269363A (en) * | 2018-11-16 | 2019-01-25 | 湖南省军合科技有限公司 | A kind of Flying-wing individual soldier hand-thrown type scout missile |
| CN110371283A (en) * | 2019-07-08 | 2019-10-25 | 中国人民解放军国防科技大学 | Intelligent flexible inflatable wing unmanned aerial vehicle structure |
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