CN112498700A - Locking and unlocking device for aircraft - Google Patents
Locking and unlocking device for aircraft Download PDFInfo
- Publication number
- CN112498700A CN112498700A CN202011500473.XA CN202011500473A CN112498700A CN 112498700 A CN112498700 A CN 112498700A CN 202011500473 A CN202011500473 A CN 202011500473A CN 112498700 A CN112498700 A CN 112498700A
- Authority
- CN
- China
- Prior art keywords
- locking
- supporting seat
- unlocking device
- driving circuit
- fusible
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 19
- 229910052802 copper Inorganic materials 0.000 claims abstract description 19
- 239000010949 copper Substances 0.000 claims abstract description 19
- 230000007246 mechanism Effects 0.000 claims abstract description 11
- 230000009471 action Effects 0.000 claims abstract description 9
- 239000003990 capacitor Substances 0.000 claims description 12
- 238000004146 energy storage Methods 0.000 claims description 10
- 238000000034 method Methods 0.000 abstract description 10
- 230000008569 process Effects 0.000 abstract description 5
- 229910001220 stainless steel Inorganic materials 0.000 description 6
- 239000002360 explosive Substances 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 238000010521 absorption reaction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000000977 initiatory effect Effects 0.000 description 2
- 230000003071 parasitic effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
Classifications
-
- 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
- B64D17/00—Parachutes
- B64D17/22—Load suspension
- B64D17/38—Releasable fastening devices between parachute and load or pack
-
- 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
-
- 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
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/12—Releasing
-
- 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
- B64D17/00—Parachutes
- B64D17/40—Packs
- B64D17/52—Opening, e.g. manual
- B64D17/54—Opening, e.g. manual automatic
-
- 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
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
- B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
-
- 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
- B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
-
- 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
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fuses (AREA)
Abstract
The invention provides a locking and unlocking device for an aircraft, which comprises 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, a pre-tightening force exists between the shaft lever and the supporting seat, the driving circuit is switched on and the fusible tension rope is electrified and fused during unlocking, the shaft lever slides on the supporting seat under the action; the unlocking process has no impact, the unlocking time can be accurately controlled, and the unlocking time can be repeatedly utilized.
Description
Technical Field
The invention relates to a non-impact locking and unlocking device, in particular to a device for locking and unlocking an aircraft for umbrella cutting protection and material throwing.
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.
Disclosure of Invention
The invention solves the problem of providing a non-explosive work locking and unlocking device without impact, which can accurately control the unlocking time and can be repeatedly used.
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 locking and unlocking device has the advantages that the pin puller without impact and non-explosive work is adopted, the fusible tensioning rope can be electrified and fused through the design of the structure and the driving circuit, the unlocking time can be accurately controlled, no impact exists in the unlocking process, the pin puller can be recycled, the application range is wide, and the practicability is high.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings 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; 200-a drive circuit.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention 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 200, 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 200, in a locked state, the driving circuit 200 is disconnected, a pre-tightening mechanism is disposed between the shaft rod 103 and the supporting seat 102, and when the driving circuit 200 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.
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 200 is powered on, 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.
The driving circuit 200 provides a fusing current by using a capacitive storage-instantaneous discharge method to reduce the impact on the power source, and the 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(Iimax/Ijmax)/(ti-tj)
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:
Qabsorption of＝cM(T-t)；
Capacitor energy storage formula W ═ CU2/2＝QAbsorption of；
Energy storage capacitor C2QAbsorption 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 (10)
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, and completing the unlocking action.
2. The locking and unlocking device for the aircraft according to claim 1, wherein said positioning copper cylinder is fixed to said insulating base plate by said 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 said 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 the aircraft according to claim 1, wherein the driving circuit provides the fusing current by capacitive energy storage-instant discharge.
9. The locking and unlocking device for aircraft according to claim 1, wherein said drive circuit is in principle equivalent to an RLC series circuit.
10. 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011500473.XA CN112498700A (en) | 2020-12-18 | 2020-12-18 | Locking and unlocking device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011500473.XA CN112498700A (en) | 2020-12-18 | 2020-12-18 | Locking and unlocking device for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112498700A true CN112498700A (en) | 2021-03-16 |
Family
ID=74922226
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011500473.XA Pending CN112498700A (en) | 2020-12-18 | 2020-12-18 | Locking and unlocking device for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112498700A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022213448A1 (en) * | 2021-04-09 | 2022-10-13 | 天津大学 | Air-dropped underwater vehicle |
-
2020
- 2020-12-18 CN CN202011500473.XA patent/CN112498700A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022213448A1 (en) * | 2021-04-09 | 2022-10-13 | 天津大学 | Air-dropped underwater vehicle |
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