CN215098305U - Locking and unlocking device for aircraft - Google Patents

Abstract

The utility model provides a locking unlocking device for aircraft, including pin puller and drive circuit, the pin puller includes insulating bottom plate, a supporting seat, the axostylus axostyle, insulating terminal, can fuse the stay rope and fix a position the copper post, supporting seat and location copper post are fixed on insulating bottom plate, the one end and the insulating terminal fixed connection of axostylus axostyle, the other end setting of axostylus axostyle is on the supporting seat, be provided with pretensioning mechanism between axostylus axostyle and the supporting seat, the both ends of can fuse the stay rope are fixed on fixing the copper post, can fuse the stay rope and connect in drive circuit, under the locking state, drive circuit opens a circuit, there is the pretightning force between axostylus axostyle and the supporting seat, when unblocking, drive circuit switches on, can fuse the stay rope circular telegram and fuse, the axostylus axostyle slides on the supporting seat under the effect of pretightening force, accomplish the unblock action; the unlocking process has no impact, the unlocking time can be accurately controlled, and the unlocking time can be repeatedly utilized.

Description

Locking and unlocking device for aircraft

Technical Field

The utility model relates to a locking unlocking device of no impact especially is used for locking and the unblock of cutting umbrella protection and goods and materials input of aircraft.

Background

All need use locking and unlocking device to equipment such as aviation aircraft, guided missile, underwater equipment, for example unmanned aerial vehicle express delivery is put in, is cut umbrella protection, deep sea test and equip put in, deep sea does not have the mechanism unblock of taking the sampler etc..

Along with the rapid development of unmanned aerial vehicle technique, unmanned aerial vehicle's application area constantly expands, and fixed wing unmanned aerial vehicle is difficult to guarantee usually in practical application to have suitable runway and take off and land the landing point, consequently, fixed wing unmanned aerial vehicle adopts the takeoff and landing mode that launches the takeoff and landing parachute landing usually, and the phenomenon that the unmanned aerial vehicle slided is dragged to the parachute easy to take place after unmanned aerial vehicle contacts to earth, threatens unmanned aerial vehicle's organism safety. In addition, when the unmanned aerial vehicle is used for throwing materials or sending missiles, the unmanned aerial vehicle flies above a target area and throws materials in the air, and the ground fixing and space unlocking functions are realized between the materials or the missiles and the unmanned aerial vehicle through the locking and unlocking device.

At present, locking unlocking device is mostly the initiating explosive device, like initiating explosive device pin puller, though it can satisfy the basic demand of separation unblock, nevertheless has shortcomings such as inflammable and explosive, impact nature are great, and can only use once, and its application receives very big restriction.

SUMMERY OF THE UTILITY MODEL

The utility model provides a problem provide a locking unlocking device of non-explosive device of non-impact, but accurate control unblock time to but reuse.

A locking and unlocking device for an aircraft comprises a pin puller and a driving circuit, wherein the pin puller comprises an insulating base plate, a supporting seat, a shaft rod, an insulating terminal, a fusible tension rope and a positioning copper column, the supporting seat and the positioning copper column are fixed on the insulating base plate, one end of the shaft rod is fixedly connected with the insulating terminal, the other end of the shaft rod is arranged on the supporting seat, a pre-tightening mechanism is arranged between the shaft rod and the supporting seat, two ends of the fusible tension rope are fixed on the positioning copper column, the fusible tension rope is connected in the driving circuit, the driving circuit is broken in a locking state, a pre-tightening force exists between the shaft rod and the supporting seat, the driving circuit is switched on when unlocking, the fusible tension rope is switched on and fused, and the shaft rod slides on the supporting seat under the action of the pre-tightening force, and completing the unlocking action.

Further, the positioning copper column is fixed on the insulating bottom plate through the positioning screw.

Furthermore, two ends of the fusible tensioning rope are fixed on the positioning copper column through the locking screws.

Furthermore, the pre-tightening mechanism is a spring, the spring is arranged between the insulating terminal and the supporting seat, the spring is sleeved outside the shaft rod, and the spring provides pre-tightening force for the shaft rod in a locking state.

Furthermore, the pre-tightening mechanism is a spring, a positioning pin is fixedly arranged on the shaft rod, the spring is sleeved outside the shaft rod, and the spring is arranged between the positioning pin and the supporting seat.

Further, the supporting seat comprises a first supporting end and a second supporting end, the insulating terminal is arranged on one side, away from the second supporting end, of the first supporting end, and the positioning pin is located between the first supporting end and the second supporting end.

Furthermore, the locking device also comprises a locking seat, wherein the locking seat is fixedly connected with the insulating bottom plate or integrally formed, and the free end of the shaft rod penetrates through the locking seat.

Furthermore, the driving circuit provides fusing current in a capacitive energy storage-instantaneous discharge mode.

Further, the driving circuit is equivalent to an RLC series circuit in principle.

Further, the driving circuit comprises an energy storage capacitor, and the capacity of the energy storage capacitor is inversely proportional to the voltage.

The beneficial effects of the utility model, the utility model discloses a locking unlocking device adopts the pin puller of the non-explosive device of no impact, through the design to structure and drive circuit, makes fusible tensioning rope can circular telegram fuse, but accurate control unblock time to unblock in-process does not have the impact, recoverable used repeatedly of pin puller, and the range of application is wide, and the practicality is strong.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.

FIG. 1 is a first three-dimensional perspective view of an embodiment of a locking and unlocking device;

FIG. 2 is a second three-dimensional perspective view of an embodiment of a locking and unlocking device;

FIG. 3 is a schematic diagram of a driving circuit according to a first embodiment;

FIG. 4 is an equivalent schematic diagram of a driving circuit according to the first embodiment;

FIG. 5 is a simplified equivalent circuit principle of the driving circuit according to the first embodiment;

fig. 6 is a three-dimensional perspective view of a second locking and unlocking device according to the embodiment.

Description of reference numerals:

100-pin puller; 101-an insulating base plate; 102-a support base; 1021-a first support end; 1022-a second support end; 103-shaft rod; 104-a locating pin; 105-a spring; 106-insulated terminals; 107-fusible tensile cords; 108-positioning copper columns; 109-set screws; 110-locking screws; 111-locking seat.

Detailed Description

In order to make the aforementioned objects, features and advantages of the present invention more comprehensible, embodiments accompanied with figures are described in detail below. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Example one

As shown in fig. 1-2, a locking and unlocking device for an aircraft includes a pin puller 100 and a driving circuit, the pin puller 100 includes an insulating base plate 101, a supporting seat 102, a shaft rod 103, an insulating terminal 106, a fusible tension rope 107, and a positioning copper column 108, the supporting seat 102 and the positioning copper column 108 are fixed on the insulating base plate 101, one end of the shaft rod 103 is fixedly connected with the insulating terminal 106, the other end of the shaft rod 103 is disposed on the supporting seat 102, both ends of the fusible tension rope 107 are fixed on the positioning copper column 108, the fusible tension rope 107 is connected in the driving circuit, in a locked state, the driving circuit is broken, a pre-tightening mechanism is disposed between the shaft rod 103 and the supporting seat 102, and when the driving circuit is turned on and the fusible tension rope 107 is electrically fused, the shaft rod 103 slides on the supporting seat 102 under the action of the pre-tightening force, thereby completing an unlocking action.

The pin puller 100 is fixed on the aircraft body and can be used for automatic umbrella opening, umbrella cutting protection, target drone launching, material launching and the like.

The positioning copper column 108 is fixed on the insulating base plate 101 by a positioning screw 109.

The fusible tension cord 107 is secured at both ends to the positioning copper posts 108 by locking screws 110.

Optionally, the pre-tightening mechanism is a spring, the spring is disposed between the insulating terminal 106 and the supporting seat 102, the spring is sleeved outside the shaft rod 103, and the spring provides a pre-tightening force for the shaft rod 103 in the locked state.

Optionally, the pre-tightening mechanism is a spring 105, a positioning pin 104 is fixedly disposed on the shaft 103, the spring 105 is sleeved outside the shaft 103, and the spring 105 is disposed between the positioning pin 104 and the support seat 102.

Optionally, the supporting base 102 includes a first supporting end 1021 and a second supporting end 1022, the insulating terminal 106 is disposed at a side of the first supporting end 1021 away from the second supporting end 1022, and the positioning pin 104 is located between the first supporting end 1021 and the second supporting end 1022.

The fusible tension rope 107 is preferably made of stainless steel, and the rest of the structure of the pin puller is preferably made of high-strength aluminum alloy material.

When the fuse-type tension rope is used, the driving circuit is electrified, a large amount of heat is generated in the fuse-type tension rope 107 through current, and therefore the fuse-type tension rope 107 reaches the fracture temperature and is fused and unlocked. The used pin puller 100 can be recycled, and a new fusible tension rope 107 can be installed and fixed for reuse.

In order to reduce the impact on the power supply, the driving circuit provides the fusing current by using a capacitive energy storage-instantaneous discharge mode, and a schematic diagram of the circuit is shown in fig. 3.

The whole driving circuit can be equivalent to an RLC series circuit in principle, as shown in FIG. 4.

The loop equations are listed according to kirchhoff's voltage law as:

in the formula: c is an energy storage capacitor; l is the total inductance of the loop, including the inductance of the energy storage capacitor, the transmission line and the like; r is the total resistance of the loop, including the resistances of the load, the energy storage capacitor, the transmission line and the like; v0 is the initial voltage value of the energy storage capacitor.

Solving equation (1) can give

In the formula:

δ — R/(2L) is an attenuation coefficient expressed as a natural logarithm of the ratio of the amplitude of the attenuated sinusoidal quantity to the amplitude after the elapse of unit time, that is:

δ＝ln(I_imax/I_jmax)/(t_i-t_j)

as can be seen from equation (2), the result of the increase in the parasitic inductance of the discharge circuit is a decrease in the current amplitude and an increase in the power generation period, which are detrimental to the reliable fusing of the fuse. Therefore, when a circuit is designed, the loop inductance is reduced as much as possible, a low-inductance capacitor and a low-inductance output cable are adopted, the circuit structure is optimized, and the length of the output cable is shortened.

The parasitic inductance of the discharging loop is reduced to a negligible degree on the premise of meeting the requirements, and then the equivalent circuit can be simplified into a form of fig. 5.

The preferred stainless steel wire rope of fusible tensioning rope 107, stainless steel wire rope's quality is M, and fusing temperature is T, and stainless steel wire rope's specific heat capacity is c, and the temperature before the stainless steel wire rope circular telegram is T, the absorptive heat when stainless steel wire rope breaks:

Q_{absorption of}＝cM(T-t)；

Capacitor energy storage formula W ═ CU²/2＝Q_{Absorption of}；

Energy storage capacitor C2Q_{Absorption of}/U²；

The capacity and volume of the storage capacitor can be reduced if boosting to higher voltages is allowed.

Example two

Referring to fig. 6, the pin extractor 100 of the second embodiment includes all the structures of the first embodiment, and further includes a locking seat 111, and the locking seat 111 is fixedly connected to the insulating base plate 101, or integrally formed. The free end of the shaft 103 passes through the locking seat 111.

Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (9)

1. A locking and unlocking device for an aircraft is characterized by comprising a pin puller and a driving circuit, wherein the pin puller comprises an insulating base plate, a supporting seat, a shaft lever, an insulating terminal, a fusible tension rope and a positioning copper column, the supporting seat and the positioning copper column are fixed on the insulating base plate, one end of the shaft lever is fixedly connected with the insulating terminal, the other end of the shaft lever is arranged on the supporting seat, a pre-tightening mechanism is arranged between the shaft lever and the supporting seat, two ends of the fusible tension rope are fixed on the positioning copper column, the fusible tension rope is connected in the driving circuit, the driving circuit is broken in a locking state, pre-tightening force exists between the shaft lever and the supporting seat, the driving circuit is conducted during unlocking, the fusible tension rope is electrified and fused, and the shaft lever slides on the supporting seat under the action of the pre-tightening force, completing the unlocking action; the driving circuit provides fusing current in a capacitive energy storage-instantaneous discharge mode.

2. The locking and unlocking device for the aircraft according to claim 1, wherein said positioning copper cylinder is fixed on said insulating base plate by a positioning screw.

3. The locking and unlocking device for aircraft according to claim 1, wherein both ends of said fusible tension rope are fixed to said positioning copper pillar by means of locking screws.

4. The locking and unlocking device for the aircraft according to claim 1, wherein the pre-tightening mechanism is a spring, the spring is arranged between the insulated terminal and the supporting seat, the spring is sleeved outside the shaft rod, and the spring provides pre-tightening force for the shaft rod in a locking state.

5. The locking and unlocking device for the aircraft according to claim 1, wherein the pre-tightening mechanism is a spring, a positioning pin is fixedly arranged on the shaft, the spring is sleeved outside the shaft, and the spring is arranged between the positioning pin and the supporting seat.

6. The locking and unlocking device for aircraft according to claim 5, wherein said support base includes a first support end and a second support end, said insulated terminal is provided on a side of said first support end remote from said second support end, and said positioning pin is located between said first support end and said second support end.

7. The locking and unlocking device for the aircraft according to claim 1, further comprising a locking seat fixedly connected with the insulating base plate or integrally formed, wherein the free end of the shaft rod penetrates through the locking seat.

8. The locking and unlocking device for aircraft according to claim 1, wherein said drive circuit is in principle equivalent to an RLC series circuit.

9. The locking and unlocking device for the aircraft according to claim 1, wherein the driving circuit includes an energy storage capacitor, and a capacity of the energy storage capacitor is inversely proportional to the voltage.

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