CN105865271B - A kind of portable missile of use fast aeration missile wing - Google Patents
A kind of portable missile of use fast aeration missile wing Download PDFInfo
- Publication number
- CN105865271B CN105865271B CN201610367199.0A CN201610367199A CN105865271B CN 105865271 B CN105865271 B CN 105865271B CN 201610367199 A CN201610367199 A CN 201610367199A CN 105865271 B CN105865271 B CN 105865271B
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- China
- Prior art keywords
- missile
- missile wing
- inflation
- wing
- portable
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Classifications
-
- 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
-
- 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
-
- 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
Abstract
A kind of portable missile of use fast aeration missile wing, inflation missile wing is symmetrical arranged including body and be arranged on the left and right sides in the middle part of body a pair, the aerating device being connected with inflation missile wing is provided with the body, the inflation missile wing is flexible gas-filled missile wing, it is inflating expanded by aerating device after stored collapsed left and right sides in the middle part of body, MISSILE LAUNCHING before MISSILE LAUNCHING.Stored collapsed and setting missile wing protective cover before missile wing transmitting are inflated, reduces the largest cross-sectional sized of guided missile before transmitting, reduces the requirement to flat pad caliber size, simplify transmitting flow, shorten launch time, control design cost, be convenient for carrying and shift.Present invention employs flexible gas-filled missile wing, stored collapsed before transmitting is easy to rapid fire；There is provided larger lift-drag ratio for rapid deployment after transmitting；Explode and abandon when striking target, improve battlefield flexibility.
Description
Technical field
The invention belongs to portable missile technical field, and in particular to a kind of to have the portable missile for inflating missile wing.
Background technology
Guided missile, as a kind of precision strike weapon, plays more and more important effect in modern war.And conventional pilot
Play that bulky, complicated, launch preparation time length, hang time be shorter, use cost is higher.On the other hand, volume compared with
Small guided cartridge is mostly using without tail fin design, and mobility shortcoming, penetration ability is poor, it is difficult to perform diversified military
Business.Therefore, can rapid fire enter the theater of war, the Miniaturized portable with stronger penetration ability and longer hang time and lead
Bullet turns into the development trend in following guided missile field.
One kind is disclosed in Publication No. 103808212A patent document quickly continuously to launch low cost using artillery
The big gun hair small missile of wide range miniature missile.Guided missile propulsion gunpowder is needs oxygenation fuel, and big gun hair guided missile is anury flyer lead bullet, big gun hair
The transmitting artillery of guided missile is fixedly mounted.It launches miniature missile using artillery, enable guided missile obtained in transmitting it is larger just
Speed, so that guided missile carries less fuel in flight accelerator and can obtain larger acceleration again, gets after bore
Guided missile part is done along guided missile portion central axes and is rotationally advancing at a high speed, and then can greatly increase the range of this miniature missile.But
It is that this big gun hair small missile has following defect：It is that the hang time is short without tail fin design, mobility shortcoming, penetration ability
Difference；The transmitting artillery of big gun hair guided missile uses fixedly mounted, very flexible, it is difficult to deal with complex battlefield surroundings, entirely
Systems bulky, is not suitable for carrying or shifts；Guided missile rotates at a high speed around central shaft in flight course, produces larger inertia
Square, increase system control difficulty.
Therefore design one kind can improve maneuverability, extend the hang time, increase scope, be convenient for carrying and shift
Guided missile be required.
The content of the invention
In order to overcome the deficiencies in the prior art, the present invention provides a kind of portable missile of use fast aeration missile wing.
The technical scheme is that：
A kind of portable missile of use fast aeration missile wing, including body, it is characterised in that：Also include being arranged on body
A pair of the middle part left and right sides are symmetrical arranged the aerating device for being provided with and being connected with inflation missile wing in inflation missile wing, the body,
The inflation missile wing is flexible gas-filled missile wing, before MISSILE LAUNCHING after stored collapsed left and right sides in the middle part of body, MISSILE LAUNCHING
It is inflating expanded by aerating device.
Further, inflation missile wing of the present invention is designed using high aspect ratio.Specifically, inflation missile wing uses aspect ratio
For 7~10 high aspect ratio RECTANGULAR WINGS, the aerofoil profile for the inflation missile wing being fully deployed after inflation is plano-convex aerofoil profile, relative thickness of airfoil
10%~11%.Inflation missile wing is made up of PVC material, and whole inflation missile wing is divided into 10~16 air chambers communicated.Inflate bullet
The be internally provided with dividing plate and flexible tie rod of the wing are used to disperse the load that internal pressure is produced, so as to keep certain wing
Type.
Further, present invention additionally comprises missile wing protective cover, missile wing protective cover is arranged on bullet by protective cover locking bolt
On body, protective cover locking bolt can realize discarding missile wing protective cover after starting, and the inflation missile wing uses Z-shaped folding mode
Cavity of the stored collapsed between body and missile wing protective cover.
Further, the afterbody of body of the present invention is provided with tail vane, and the engine of tail vane is arranged at the afterbody of body.
Further, the empennage of tail vane of the present invention is cruciform tail.
Further, aerating device of the present invention includes being provided with gas cylinder, high pressure gas inside gas cylinder, body
The missile wing inflation that the main gas circuit of bottle is divided into the inflation missile wing that two branch gas circuits are connected respectively to the left and right sides by three-way connection connects
On head.
Further, be provided with the main gas circuit of gas cylinder of the present invention can remote control switch air valve, pass through
The beginning and end of the switch controls gas replenishment process of air valve.
Further, both sides are installed and missile wing installation base are provided with the position of inflation missile wing in the middle part of body of the present invention
Seat, the wing root of inflation missile wing is fixed in installation pedestal, and missile wing installation pedestal is connected by blasting bolt with body, quick-fried
Fried bolt can be realized when striking target, and blast abandons inflation missile wing.
Further, spring assembly is provided between installation pedestal of the invention and body, spring assembly can be realized
Inflation missile wing is quickly separated with body after blasting bolt starts.
The advantage of the invention is that：
Present invention employs flexible gas-filled missile wing, stored collapsed before transmitting is easy to rapid fire；Rapid deployment after transmitting,
Larger lift-drag ratio is provided；Explode and abandon when striking target, improve battlefield flexibility.
Compared with big gun hair small missile, present invention employs cruciform tail and with larger lift-drag ratio and larger length
Missile wing is inflated, the maneuverability of guided missile is improved, extends the hang time；
The missile wing attachment structure that the present invention is abandoned using explosibility, abandons larger-size inflation missile wing in strike, makes
Missile attitude is still accurately controlled with afterbody cross-shape layout tail vane, the flexibility of strike process is improved；
The present invention folds and set missile wing protective cover by inflating missile wing Z-shaped, and the maximum for reducing guided missile before transmitting is cut
Face size, reduces the requirement to flat pad caliber size, simplifies transmitting flow, shorten launch time, control design
Cost, is convenient for carrying and shifts；
The present invention quickly can have found and attack various concealed targets, complete intelligence reconnaissance, precision strike and target Damage and comment
The combat duty such as estimate, the arms and services can be allotted as individual combat equipment, with wide application prospect.
Brief description of the drawings
Fig. 1 is structural representation of the invention.(inflation missile wing folded state)
Fig. 2 is structural representation of the invention.(inflation missile wing deployed condition)
Fig. 3 is structural representation of the invention.(inflation missile wing is separated with body)
Fig. 4 is working condition timing diagram of the invention：(a) it is missile wing folded state；(b) gas replenishment process missile wing state；(c)
Missile wing inflation completes deployed condition；(d) blasting bolt startup missile wing separates moment state with body.
Fig. 5 is the structural representation of inflation missile wing.
Label declaration in figure：
1st, missile wing is inflated；2nd, missile wing protective cover；3rd, protective cover locking bolt；4th, gas circuit；5th, tail vane；6th, engine；7th, send out
Motivation air intake duct；8th, missile wing installation pedestal；9th, blasting bolt；10th, body；11st, missile wing gas-charging connection；12nd, spring assembly；13、
Gas cylinder；14th, air valve；15th, three-way connection.
Embodiment
In order that technical problem solved by the invention, technical scheme and beneficial effect are more clearly understood, below in conjunction with
Drawings and Examples, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein is only used to
The present invention is explained, is not intended to limit the present invention.
Referring to figs. 1 to Fig. 3, the invention provides a kind of portable missile of use fast aeration missile wing, including body 10,
Inflate missile wing 1, tail vane 5, engine 6, missile wing protective cover 2, aerating device.Inflation missile wing 1 in the present invention is flexible gas-filled bullet
The wing, a pair of inflation missile wings 1 being symmetrical set are separately mounted in the left and right sides of the medium position of body 10, the body 10
Be provided with and inflate the aerating device that be connected of missile wing 1, inflate missile wing 1 before MISSILE LAUNCHING stored collapsed in body medium position
It is inflating expanded by aerating device after the left and right sides, MISSILE LAUNCHING.
Reference picture 1, Fig. 2 and Fig. 3, the afterbody of body 10 are provided with tail vane 5, and the engine 6 of tail vane 5 is arranged at body 10
Afterbody, engine inlets 7 are positioned close on the downside of the body of afterbody position.The empennage of tail vane is cross in the present invention
Empennage.Whole tail vane is symmetrical above and below and symmetrical symmetrical structure, and tail vane is coaxially set with body.Missile wing is inflated to use
High aspect ratio is designed, with larger lift-drag ratio, and inside sets dividing plate and flexible tie rod to disperse the load that internal pressure is produced, so that
Certain aerofoil profile can be kept.Using the inflation missile wing with larger lift-drag ratio and larger length, can be provided for missile flight compared with
Lift, improves guided missile maneuverability；
Reference picture 5, for structural representation of the inflation missile wing after inflating expanded, inflation missile wing 1 uses aspect ratio for 7~10
What is be fully deployed after high aspect ratio RECTANGULAR WINGS, inflation inflates the aerofoil profile of missile wing for plano-convex aerofoil profile, and relative thickness of airfoil 10%~
11%.Inflation missile wing is made up of PVC material, and whole inflation missile wing is divided into 10~16 air chambers communicated.Inflate the interior of missile wing
Portion, which is provided with dividing plate and flexible tie rod, to be used to disperse the load that internal pressure is produced, so as to keep certain aerofoil profile.
Structural representation when reference picture 1 is present invention inflation missile wing folded state, inflation is installed in the middle part both sides of body 10
Missile wing installation pedestal 8 is provided with the position of missile wing 1, the wing root of inflation missile wing 1 is fixed in missile wing installation pedestal 8,
Inflation missile wing 1 at the link position of missile wing installation pedestal 8 with making encapsulation process, it is ensured that whole inflation missile wing is sealed.Missile wing is pacified
Dress pedestal 8 is connected by blasting bolt 9 with body 1, and blast discarding that blasting bolt 9 can be realized when striking target is inflating expanded
Inflation missile wing.Missile wing protective cover 2 is additionally provided with the outside of the inflation missile wing of folded state.Missile wing protective cover 2 is locked by protective cover
Only bolt 3 is arranged on body 10, and protective cover locking bolt 3 can realize discarding missile wing protective cover 2 after starting.The present embodiment
In, cavity of the inflation missile wing 1 using Z-shaped folding mode stored collapsed between body 10 and missile wing protective cover 2.Pass through inflation
Missile wing Z-shaped folds and set missile wing protective cover, reduces the largest cross-sectional sized of guided missile before transmitting, reduction is to flat pad mouthful
The requirement of footpath size, can be convenient for carrying and shift using cartridge type transmitting.The missile wing folding mode of the present invention is not limited to Z-shaped folding
Folded mode.
Aerating device in structural representation of the reference picture 2 for the present invention inflation missile wing when inflating expanded, body 10 includes
Gas circuit 4 between gas cylinder 13 and the inflation missile wing 1 of gas cylinder 14 and two.Gas cylinder 14 is arranged on the inside of body 1,
The main gas circuit of gas cylinder 14 passes through inflation missile wing 1 that 15 points of three-way connection is that two branch gas circuits are connected respectively to the left and right sides
On missile wing gas-charging connection 11.Be provided with the main gas circuit of gas cylinder 14 can remote control switch air valve 14, pass through air valve 14
Switch controls gas replenishment process beginning and end.To ensure that gas cylinder inflates the gas replenishment process of missile wing, inflation to both sides
Amount is synchronous consistent, and two branch air paths are symmetrical.Connected using carrying gas cylinder on bullet and by three-way connection
The aerating device of both sides missile wing, can be completed in flight course missile wing fast aeration expansion, while both sides missile wing have it is identical
Air pressure, so as to ensure the accurate symmetrical structure of guided missile.
Structural representation when reference picture 3 separates for present invention inflation missile wing with body, blasting bolt 9 can realize strike
Blast abandons inflation missile wing during target.After attack instruction is received, it can start what inflation missile wing installation pedestal 8 was connected with body 10
Blasting bolt 9, abandons inflation missile wing 1.Spring assembly 12, spring assembly 12 are provided between missile wing installation pedestal 8 and body 10
It can realize that inflation missile wing is quickly separated with body after blasting bolt startup.Spring assembly 12 is to be arranged on missile wing installation pedestal
One group of spring between 8 and body 10.After quick-fried photograph bolt 9 starts, the elastic deformation of spring assembly 12 quickly will inflation missile wing ejection
Realize inflation missile wing and body quick separating.And cross-shape layout's tail vane of the afterbody of body 10 accurately controls Missile Motion appearance
State, fast and flexible is implemented to hit to target.Attachment structure and afterbody cross the tail vane layout abandoned using explosibility, the former
May be implemented in flight course can abandon larger-size missile wing protective cover or inflation missile wing as needed, and the latter can ensure blast
Simplification body after discarding still can accurately control athletic posture, improve the attack precision of target.
In use, can carry out rapid fire to guided missile using emitter, guided missile produces one by the ejection of emitter
Fixed speed, while opening the engine 6 of tail end, thrust, adjustment tail vane deflection, it is ensured that guided missile has phase are provided for missile flight
To stable flight attitude.The protective cover locking bolt for then starting missile wing protective cover abandons missile wing protective cover, while opening master
Air valve on path, starts to inflate the fast aeration process of missile wing.After the completion of inflation, primary path air valve is closed.Now, big length
Than the lift that the inflation missile wing with big lift-drag ratio provides missile flight, it is ensured that the quick target region of aircraft, carry out
Patrol aviation.After attack instruction is received, the blasting bolt that inflation missile wing installation pedestal is connected with body can be started, inflation is abandoned
Missile wing, cross-shape layout's tail vane of afterbody accurately controls Missile Motion posture, and fast and flexible is implemented to hit to target.
After MISSILE LAUNCHING, the working condition of guided missile can be divided into following 4 according to the order at flight moment：Missile wing rugosity
State (Fig. 4 a), gas replenishment process missile wing state (Fig. 4 b), missile wing inflation complete deployed condition (Fig. 4 c), blasting bolt and start inflation bullet
The wing separates moment state (Fig. 4 d) with body.Working condition timing diagram is as shown in Figure 4：
Described above is only the preferred embodiment of the present invention, and protection scope of the present invention is not limited merely to above-mentioned implementation
Example, all technical schemes belonged under thinking of the present invention belong to protection scope of the present invention.It should propose, for the art
Those of ordinary skill for, improvements and modifications without departing from the principles of the present invention, these improvements and modifications should also be regarded
For protection scope of the present invention.
Claims (7)
1. a kind of portable missile of use fast aeration missile wing, including body, it is characterised in that：Also include being arranged in body
A pair of the portion left and right sides are symmetrical arranged the aerating device for being provided with and being connected with inflation missile wing in inflation missile wing, the body, institute
It is flexible gas-filled missile wing to state inflation missile wing, is led to before MISSILE LAUNCHING after stored collapsed left and right sides in the middle part of body, MISSILE LAUNCHING
Overcharge device of air inflating expanded；The inflation missile wing uses aspect ratio for 7~10 high aspect ratio RECTANGULAR WINGS, is opened up completely after inflation
The aerofoil profile for the inflation missile wing opened is plano-convex aerofoil profile, and relative thickness of airfoil 10%~11%, inflation missile wing is provided for missile flight and risen
Power；The aerating device includes being provided with gas cylinder inside gas cylinder, body, and the main gas circuit of gas cylinder is connected by three
Head is divided into two branch gas circuits and is connected respectively on the missile wing gas-charging connection of inflation missile wing of the left and right sides, and two branch air paths are pair
Claim, it is synchronous consistent that gas cylinder, which inflates the gas replenishment process of missile wing, aeration quantity to both sides, and both sides inflation missile wing has identical
Air pressure；The afterbody of the body is provided with tail vane, and the afterbody that the engine of tail vane is arranged at body is provided for missile flight and pushed away
Power, engine inlets are positioned close on the downside of the body of afterbody position.
2. the portable missile of use fast aeration missile wing according to claim 1, it is characterised in that：The inflation missile wing
It is made up of PVC material, whole inflation missile wing is divided into 10~16 air chambers communicated；Inflation missile wing be internally provided with dividing plate and
Flexible tie rod is used for the load for disperseing internal pressure generation.
3. the portable missile of use fast aeration missile wing according to claim 1 or 2, it is characterised in that：Also include bullet
Wing protective cover, missile wing protective cover is arranged on body by protective cover locking bolt, and protective cover locking bolt can be real after starting
Missile wing protective cover is now abandoned, the inflation missile wing is using Z-shaped folding mode stored collapsed between body and missile wing protective cover
Cavity.
4. the portable missile of use fast aeration missile wing according to claim 3, it is characterised in that：The tail of the tail vane
The wing is cruciform tail.
5. the portable missile of use fast aeration missile wing according to claim 1, it is characterised in that：The gas cylinder
Main gas circuit on be provided with can remote control switch air valve, beginning and knot by the switch controls gas replenishment process of air valve
Beam.
6. the portable missile of use fast aeration missile wing according to claim 1, it is characterised in that：In the middle part of the body
Both sides are installed and missile wing installation pedestal are provided with the position of inflation missile wing, and the wing root of inflation missile wing is fixed on installed in installation pedestal
On, missile wing installation pedestal is connected by blasting bolt with body, and blasting bolt can be realized when striking target, and blast abandons inflation
Missile wing.
7. the portable missile of use fast aeration missile wing according to claim 6, it is characterised in that installation pedestal and bullet
Spring assembly is provided between body, spring assembly can realize that inflation missile wing is quickly separated with body after blasting bolt startup.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610367199.0A CN105865271B (en) | 2016-05-27 | 2016-05-27 | A kind of portable missile of use fast aeration missile wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610367199.0A CN105865271B (en) | 2016-05-27 | 2016-05-27 | A kind of portable missile of use fast aeration missile wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105865271A CN105865271A (en) | 2016-08-17 |
| CN105865271B true CN105865271B (en) | 2017-09-05 |
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ID=56642526
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610367199.0A Active CN105865271B (en) | 2016-05-27 | 2016-05-27 | A kind of portable missile of use fast aeration missile wing |
Country Status (1)
| Country | Link |
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| CN (1) | CN105865271B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113091523A (en) * | 2021-04-13 | 2021-07-09 | 西安航天动力技术研究所 | Firer throwing-off type anti-stabilizer wing |
| CN113443145B (en) * | 2021-05-31 | 2023-02-07 | 中航(成都)无人机系统股份有限公司 | Military unmanned aerial vehicle |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU524255B2 (en) * | 1978-12-29 | 1982-09-09 | Commonwealth Of Australia, The | Deployable wing |
| CN1052084A (en) * | 1990-05-31 | 1991-06-12 | 邢麟祥 | Separate driving type wing shape double vertical tails |
| JPH08226798A (en) * | 1995-02-23 | 1996-09-03 | Mitsubishi Electric Corp | Guided air frame |
| CN1523318A (en) * | 2003-02-19 | 2004-08-25 | 姜淑君 | Air-actuated cross rotor and ring form tail wing for ball ammunition and aircraft |
| RU2309087C2 (en) * | 2005-02-08 | 2007-10-27 | Алексей Николаевич Кочетков | Missile carrier "vityaz" for horizontal takeoff without takeoff run at low-temperature gliding in atmosphere and soft landing |
| CN102717887B (en) * | 2012-05-23 | 2015-11-25 | 北京航空航天大学 | A kind of inflatable wing and can the near space dirigible of tilted propeller of adopting |
| CN104089546B (en) * | 2014-04-29 | 2015-09-30 | 北京理工大学 | The variable aerodynamic arrangement structure of body |
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2016
- 2016-05-27 CN CN201610367199.0A patent/CN105865271B/en active Active
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| CN105865271A (en) | 2016-08-17 |
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