CN102226671A

CN102226671A - Redundant locking type longitudinal expansion mechanism of folding wing

Info

Publication number: CN102226671A
Application number: CN2011101385224A
Authority: CN
Inventors: 胡明; 张苗苗; 陈文华; 金永平; 徐国民; 钱萍; 周健; 潘骏; 刘东旭; 张尧
Original assignee: Zhejiang University of Technology ZJUT
Current assignee: Zhejiang University of Technology ZJUT
Priority date: 2011-05-26
Filing date: 2011-05-26
Publication date: 2011-10-26
Anticipated expiration: 2031-05-26
Also published as: CN102226671B

Abstract

The invention relates to a redundant locking type longitudinal expansion mechanism of a folding wing. The existing missile folding wing has the once expansion locking function and has the defects of extremely short expansion time, great expansion locking impact and great posture interference on a missile in flight. The longitudinal expansion mechanism provided by the invention adopts the design idea that a worm mechanism and a ball nut are combined, wherein the mechanism can realize the once reliable locking of the folding wing; the power of a gas actuator cylinder drives the nut to move; a screw shaft is linked with a worm, thereby driving a worm gear to rotate around a wing shaft; and the locking of the folding wing is realized by utilizing the self-locking action of the worm. The longitudinal expansion mechanism provided by the invention realizes the minimization of the enveloping space of the folding wing, has the advantage of compact structure and is easy to realize the folding, the expansion and the locking with high accuracy and high reliability.

Description

The vertical development mechanism of redundant latch fixed pattern folding wings

Technical field

The present invention relates to a kind of folding wings development mechanism, be used for the expansion locking of tactical missile, cruise missile folding wings with auto-lock function.

Background technology

The guided missile missile wing is the important component part of body, and simple and convenient for guided missile launcher miniaturization, transportation are stored, tactical missile extensively adopts folding wings.The development mechanism of folding wings is used to realize the folding and expanding of missile wing.The present domestic Missile Folding wing all has disposable expansion lock function, its duration of run is very short, and it is bigger to launch the locking impact, to the interference of body attitude is bigger in-flight, launch locking and impact even may cause locking pin to be cut off, missile wing can't be locked and cause catastrophic failure.

Summary of the invention

The objective of the invention is to reduce the impact acceleration that body is caused, avoid locking pin to cut off inefficacy, with fast reserve that improves guided missile and the accuracy that strikes target in order to solve the Missile Folding wing in the disposable locking problem of launching extreme position.

Main design of the present invention: for reducing the enveloping space of the Missile Folding wing, adopt worm mechanism and ball nut Combination Design thought, this mechanism can realize the disposable positive lock of folding wings.Power is moved by combustion gas pressurized strut drive nut, and screw shaft connects with worm screw, rotates (worm gear and missile wing connect firmly) thereby drive worm gear around the missile wing axle, utilizes the locking of the self-locking action realization folding wings of worm screw.Locking pin on the body support contacts with missile wing in whole expansion process, and when missile wing launched fully, locking pin cooperated with pin-and-hole on the missile wing, has realized the missile wing positive lock.

The technical solution adopted in the present invention is as follows:

The vertical development mechanism of redundant latch fixed pattern folding wings comprises combustion gas pressurized strut, push rod, ball nut, worm screw, goes up worm gear, following worm gear and support.

Slide block in the combustion gas pressurized strut is fixedlyed connected with push rod, the ball nut that push rod promotes on the worm screw moves, the mobile drive worm screw of ball nut is rotated, worm screw is provided with worm gear, following worm gear away from a side of ball nut, describedly go up worm gear and following worm gear is symmetrical arranged along worm screw, last worm gear, descend worm gear respectively with worm engaging.

On the last worm gear missile wing is housed, the top of last worm gear has the missile wing pin-and-hole; On the following worm gear missile wing is housed down, the bottom of following worm gear has down the missile wing pin-and-hole.

Support is provided with locking pin, following locking pin corresponding to last worm gear, following worm gear place; The centre of support is provided with and is used for carrying the bearing that worm screw is rotated; The rotation of worm screw drives upward, and worm gear rotates around last missile wing axle and following missile wing axle respectively with following worm gear, the last locking pin that last worm gear rotates counterclockwise on 90 ° of after-poppets is gone up worm gear by last missile wing pin-and-hole locking, and the following locking pin that following worm gear clockwise rotates on 90 ° of after-poppets passes through the worm gear down of missile wing pin-and-hole locking down.

The present invention compared with prior art has following beneficial effect: 1, worm mechanism and ball nut applied in any combination have made full use of the joint space of folding wings, satisfy envelope minimized in size principle.2, the input of development mechanism, output are coaxial, and accurate positioning, load are good, can reach fast, stable, expansion promptly and accurately; 3, the application of worm screw has reduced shock loading, stable drive, thus reduced the missile wing disturbance.4, the locking pin on the self-locking performance of worm screw, the body support cooperates accurate location and the reliable locking that has guaranteed after missile wing forwards predetermined angular to the missile wing pin-and-hole, and is little to the bomb body interference, helps keeping folding wings attitude stability in the missile flight process; 5, adopt the longitudinal folding mode of double-vane symmetric arrangement, realized the maximization of folding wings developed area, improved missile flight lift.5, applied range.The present invention also may be used in space development mechanisms such as the collapsible sun wing, deployable antenna and the relevant ground mechanism except can being installed in folding wings folding exhibition joint.

Description of drawings

Fig. 1 is a folded state schematic diagram of the present invention;

Fig. 2 is a deployed condition schematic diagram of the present invention.

The specific embodiment

The invention will be further described below in conjunction with accompanying drawing.

The vertical development mechanism of redundant latch fixed pattern folding wings comprises that combustion gas pressurized strut 1(provides power source); Missile wing 2,13; Worm screw 3; Worm gear 4,12(and missile wing connect firmly); Missile wing pin-and-hole 5,11(cooperates with locking pin, is used for location, the locking of folding and expanding position); Missile wing rotating shaft 6,10; Locking pin 7, location, the locking of 9(missile wing folding and expanding position); Body support 8; Ball nut 14; Push rod 15.Slide block in the combustion gas pressurized strut 1 is fixedlyed connected with push rod 15, the ball nut 14 that push rod 15 promotes on the worm screw 3 moves, the mobile drive worm screw 3 of ball nut 14 is rotated, worm screw 3 is provided with worm gear 12, following worm gear 4 away from a side of ball nut 14, the described worm gear 12 of going up is symmetrical arranged along worm screw 3 with following worm gear 4, and last worm gear 12, following worm gear 4 mesh with worm screw 3 respectively.

On the last worm gear 12 missile wing 13 is housed, the top of last worm gear 12 has missile wing pin-and-hole 11; On the following worm gear 4 missile wing 2 is housed down, the bottom of following worm gear 4 has down missile wing pin-and-hole 5.

Support 8 is provided with locking pin 9, following locking pin 7 corresponding to last worm gear 12, following worm gear 4 places; The centre of support 8 is provided with and is used for carrying the bearing that worm screw 3 is rotated.

Combustion gas pressurized strut 1 straight line moves, driving ball nut 14 by push rod 15 moves, thereby rectilinear motion is converted into the rotation of worm screw 3, the rotation of worm screw 3 drives upward, and worm gear 12 rotates around last missile wing axle 10 and following missile wing axle 6 respectively with following worm gear 4, the last locking pin 9 that last worm gear 12 rotates counterclockwise on 90 ° of after-poppets 8 is gone up worm gear 12 with last missile wing pin-and-hole 11 lockings, thereby has realized the locking of last missile wing 13; The following locking pin 7 that following worm gear 4 clockwise rotates on 90 ° of after-poppets 8 cooperates locking worm gear down with following missile wing pin-and-hole 5, thereby realized the locking of time missile wing 2. accurately put in place for guaranteeing folding and expanding mechanism, wherein utilize the latching characteristics of worm screw 3, folding wings 13 in the assurance, folding wings 2 reliable redundant lockings down, thus finished last missile wing 13 and following missile wing 2 from folded state (as Fig. 1) to deployed condition (as Fig. 2).

Operation principle of the present invention is: have input, output coaxial worm mechanism and ball wire rod mechanism and be used in combination the disposable expansion locking that realizes folding wings, concrete principle is: the mobile rotation that is converted into screw shaft that the combustion gas pressurized strut will be imported by ball nut, screw shaft connects with worm screw, thereby drive missile wing (worm gear and missile wing one) around the rotation of missile wing axle, promptly realize the folding of folding wings and launch function.Locking pin is located with safe, reliable, the redundancy folding, that launch extreme position that realize folding wings cooperating of missile wing pin-and-hole on the self-locking performance of worm screw, the body support.Redundant latch fixed pattern folding and expanding mechanism structure is simple, the missile wing vibration is separated reliably, reduced in accurate positioning, lock, bomb body is disturbed little, helps keeping missile attitude stability in the flight course, satisfy quick, stablize, launch timely requirement.

Claims

1. the vertical development mechanism of redundant latch fixed pattern folding wings comprises combustion gas pressurized strut, push rod, ball nut, worm screw, goes up worm gear, following worm gear and support, it is characterized in that:

Slide block in the combustion gas pressurized strut is fixedlyed connected with push rod, the ball nut that push rod promotes on the worm screw moves, the mobile drive worm screw of ball nut is rotated, worm screw is provided with worm gear, following worm gear away from a side of ball nut, describedly go up worm gear and following worm gear is symmetrical arranged along worm screw, last worm gear, descend worm gear respectively with worm engaging;

On the last worm gear missile wing is housed, the top of last worm gear has the missile wing pin-and-hole; On the following worm gear missile wing is housed down, the bottom of following worm gear has down the missile wing pin-and-hole;