CN112693639B - Energy storage type ejection sealing protection device and aircraft launching method - Google Patents
Energy storage type ejection sealing protection device and aircraft launching method Download PDFInfo
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- CN112693639B CN112693639B CN202110014185.1A CN202110014185A CN112693639B CN 112693639 B CN112693639 B CN 112693639B CN 202110014185 A CN202110014185 A CN 202110014185A CN 112693639 B CN112693639 B CN 112693639B
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- energy storage
- protective cover
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
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Abstract
The application discloses energy storage formula is launched sealed protector and aircraft transmission method relates to space flight technical field, and it includes: the launching tube is sleeved outside the aircraft, and the inner wall of the launching tube is also provided with a limiting groove; a shield cover detachably coupled to one side of the launch tube; the locking assemblies are arranged on the inner wall of the protective cover in a centrosymmetric manner and comprise steel balls and locking and unlocking devices, when the locking and unlocking devices are in a locking state, the steel balls are partially embedded into the limiting grooves, and when the locking and unlocking devices are in an unlocking state, the steel balls are separated from the limiting grooves; the elastic energy storage component is arranged between the protective cover and the aircraft; the number of the limiting grooves is the same as that of the locking assemblies. The application aims to solve the problems that in the prior art, a sealing device for the drum-type launching of a small and medium-sized aircraft is complex in structure, heavy in weight and serious in fragment interference.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to an energy storage type ejection sealing protection device and an aircraft launching method.
Background
At present, the cylinder type aircraft is required to have better sealing performance when being stored on the ground, and meets the protection and use of environmental conditions such as rainwater, salt fog, sand dust and the like; when the small aircraft is launched in a ground or air cylinder mode, the small aircraft also needs to have the characteristics of small passive weight, weak interference and the like. The prior art mainly adopts the following techniques: the technology of the sealing cover of the fragile cover adopts the fragile characteristic of certain materials and is assisted with a specific structural design, so that the aim of discharging the cylinder by breaking the fragile cover through airflow emitted by an aircraft or self kinetic energy is fulfilled; the scheme is simple, but the sizes and falling tracks of the fragments are random, so that the aircraft is easily interfered, and the method is often applied to protection of large-tonnage aircraft. The mechanical switch sealing cover technology adopts a specific power unit to realize the closing/opening of the sealing cover; the technology has a complex structure and large mass, needs additional power and control units, and is often applied to the protection of aircrafts with abundant space structures. In summary, the technical solution of the protective cover of the existing barrel-type launching aircraft has no technical advantages for barrel-type launching of a small aircraft, especially for the barrel-type launching operation in the air.
Disclosure of Invention
Aiming at the defects in the prior art, the application aims to provide an energy storage type ejection sealing protection device and an aircraft launching method, so as to solve the problems of complex structure, heavy weight and serious fragment interference of a sealing device during barrel type launching of a small and medium aircraft in the related technology.
In order to achieve the above purposes, the technical scheme is as follows: the launching tube is sleeved outside the aircraft, and the inner wall of the launching tube is also provided with a limiting groove;
a protective cover detachably coupled to one side of the launch barrel;
the locking assemblies are arranged on the inner wall of the protective cover in a centrosymmetric manner and comprise steel balls and locking and unlocking devices, when the locking and unlocking devices are in a locking state, the steel balls are partially embedded into the limiting grooves, and when the locking and unlocking devices are in an unlocking state, the steel balls are separated from the limiting grooves;
the elastic energy storage component is arranged between the protective cover and the aircraft;
the number of the limiting grooves is the same as that of the locking assemblies.
Preferably, the elastic energy storage assembly comprises:
the bottom plate is fixedly connected with the protective cover;
the pressing plate is elastically connected with the bottom plate through an energy storage spring, and the aircraft and one side of the pressing plate, which is far away from the bottom plate, are mutually butted;
the quantity of energy storage springs is a plurality of and is evenly arranged between the bottom plate and the pressing plate.
Preferably, the locking and unlocking assembly includes:
the base is fixedly arranged on the protective cover or the locking component;
the fastening device is arranged in the base and used for pushing the steel balls into the limiting groove;
a locking device disposed within the base to unlock or lock the fastening device.
Preferably, the fastening means comprises:
the limiting pin is arranged in the base in a sliding mode, and one end of the limiting pin is abutted to the steel ball;
an end cap fixedly disposed within the base;
the unlocking spring elastically connects the limiting pin and the end cap;
the steel balls, the limiting pin, the unlocking spring and the end cap edge are arranged in series in the direction vertical to the inner wall of the launching tube.
Preferably, the locking device includes:
the lock tongue and the limit pin are mutually matched and locked, and extend out of the base along the direction far away from the protective cover;
a locking spring elastically connecting the latch bolt and the base to each other;
the lock tongue and the locking spring are arranged in series along the direction parallel to the inner wall of the launching tube.
Preferably, locking device still includes the manual pull rod, and the manual pull rod part sets up in the protective cover, and manual pull rod and the spring bolt are close to the one end fixed connection of protective cover.
Preferably, the energy storage assembly further comprises a guide screw slidably connected to the base plate and the pressure plate.
Preferably, a plurality of support rings are further arranged on the inner wall of the launching tube.
An aircraft launching method, comprising:
the aircraft is arranged in the launch barrel, the aircraft, the launch barrel, the protective cover and the elastic energy storage assembly are coaxial, and the locking and unlocking device is in a locking state at the moment;
when the aircraft is launched, the front end of the aircraft extrudes the elastic energy storage component on the protective cover to compress;
after the elastic energy storage component is compressed to a preset position, the aircraft triggers the locking and unlocking device, so that the steel balls are separated from the limiting groove, the connection between the protective cover and the launching tube is released, the protective cover is popped out forwards under the elastic force of the elastic energy storage component, and the launching tube and the aircraft are separated relatively.
Preferably, before the aircraft is installed in the launch canister, the selected protective cover and the elastic energy storage component need to satisfy the following relation:
wherein the content of the first and second substances,
s is the safe distance between the protective cover and the aircraft after the protective device is separated, and is determined by a launching task;
f is the total elastic force of the elastic energy storage assembly during unlocking;
f is the resistance when the protective device is disengaged;
t is the time for the protective cover and the aircraft to reach the safe distance after the protective device is separated, and is determined by the launching task;
m is the mass of the shield.
The technical scheme who provides this application brings beneficial effect includes:
the application discloses energy storage formula is launched sealed protector owing to through setting up the energy storage subassembly, at the in-process of aircraft acceleration flight, can absorb aircraft kinetic energy gradually, accumulates the energy, releases protective cover and launching tube separation when reaching appointed energy size, releases the aircraft. This application on the one hand does not have broken piece for the relative position of separation back residue and aircraft judges more easily, and is less to the influence of aircraft, and on the other hand also need not complicated structure, the control unit of unloading of connecing and just can break away from the aircraft with the protection casing.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a cross-sectional view of one embodiment of the present application.
FIG. 2 is a top view of the embodiment of FIG. 1 with the aircraft and launch canister removed.
Fig. 3 is a cross-sectional view taken along a-a in fig. 2.
Fig. 4 is a cross-sectional view taken along B-B in fig. 2.
Figure 5 is a front view of the locking assembly of the embodiment of figure 1.
Fig. 6 is a cross-sectional view taken along the line C-C in fig. 5.
Fig. 7 is a cross-sectional view taken along section E-E of fig. 6.
Fig. 8 is a cross-sectional view taken along section D-D of fig. 5.
Reference numerals:
1. a launch canister; 11. a limiting groove; 12. a support ring; 2. a protective cover; 3. a locking assembly; 31. steel balls; 32. a locking and unlocking device; 321. a base; 322. a fastening device; 3221. a spacing pin; 3222. an end cap; 3223. an unlocking spring; 323. a locking device; 3231. a latch bolt; 3232. a locking spring; 3233. a manual pull rod; 4. an elastic energy storage component; 41. a base plate; 42. pressing a plate; 43. an energy storage spring; 44. and (4) guiding the screw.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
As shown in fig. 1, this embodiment includes launch canister 1, protective cover 2, locking Assembly 3 and elastic energy storage Assembly 4, launch canister 1 cover is established outside the aircraft, and the aircraft is central shadow part in fig. 1, and protective cover 2 can dismantle the connection on launch canister 1, and is provided with spacing groove 11 on launch canister 1, is provided with locking Assembly 3 on protective cover 2, and the quantity of locking Assembly 3 has two pairs in this embodiment, along the axis symmetry installation in launch canister 1. The locking component 3 comprises steel balls 31 and locking and unlocking devices 32, the steel balls 31 are partially embedded into the limiting groove 11 when the protective cover 2 and the launching tube 1 are locked, and are separated from the limiting groove 11 when the protective cover 2 needs to be separated from the launching tube 1, and the locking and unlocking devices 32 are used for controlling the embedding and separation of the steel balls 31 and correspondingly locking and unlocking the locking and unlocking devices 32; an elastic energy storage component 4 is arranged between the aircraft and the protective cover 2, the elastic energy storage component 4 can accumulate elastic potential energy through extrusion of the aircraft in the launching process of the aircraft, and the elastic potential energy is released after corresponding conditions are met to bounce the protective cover 2 and the aircraft.
As a more preferable option of this embodiment, as shown in fig. 2 and 3, the elastic energy storage assembly 4 includes a bottom plate 41, a pressing plate 42 and energy storage springs 43, the bottom plate 41 is mounted on the protective cover 2, the embodiment is adhered by glue, the pressing plate 42 and the bottom plate 41 are elastically connected by the energy storage springs 43, the number of the energy storage springs 43 is several, in the embodiment, the number of the energy storage springs 43 is four, and the energy storage springs are uniformly distributed between the bottom plate 41 and the pressing plate 42.
Further, a plurality of guide screws 44 are provided between the base plate 41 and the pressing plate 42 so that the pressing plate 42 is not displaced when pressed against the base plate 41.
Preferably, the locking and unlocking assembly includes a base 321, a fastening device 322 and a locking device 323, the base 321 is fixedly disposed on the shield cover 2 to provide an installation position, the fastening device 322 is disposed in the base 321 to adjust the insertion and extraction of the steel balls 31, and the locking device 323 is used to unlock and lock the fastening device 322.
Further, the fastening device 322 includes a position-limiting pin 3221, an end cap 3222 and an unlocking spring 3223, the steel ball 31, the position-limiting pin 3221, the end cap 3222 and the unlocking spring 3223 are arranged in series along a direction perpendicular to the inner wall of the launching tube 1, so that in the locking state, the position-limiting pin 3221 can push the steel ball 31 into the position-limiting groove 11 and limit the steel ball 31 to be pulled out of the position-limiting groove 11, and in the locking state, the unlocking spring 3223 is in a stretching state, so that after unlocking, the unlocking spring 3223 can pull out the position-limiting pin 3221, so that the steel ball 31 is pulled out of the position-limiting groove 11.
Furthermore, the locking device 323 comprises a locking tongue 3231 and a locking spring 3232, the locking tongue 3231 and the locking spring 3232 are arranged in series along the parallel direction of the inner wall of the launching tube 1, the locking tongue 3231 and the limit pin 3221 are matched with each other, the locking spring 3232 provides a pushing force to fix and press the locking tongue 3231 on the limit pin 3221, so that the limit pin 3221 cannot move, during the launching process, the aircraft presses the elastic energy storage device until the aircraft just touches the locking tongue 3231, and when the aircraft continues to press, the locking tongue 3231 is pressed down together, so that the locking tongue 3231 and the limit pin 3221 are separated, the limit pin 3221 is pulled open by the spring, so that the steel ball 31 is separated, and the protective cover 2 is ejected under the action of the elastic energy storage component 4.
Furthermore, the locking device 323 further comprises a manual pull rod 3233, one end of the manual pull rod 3233 is fixedly connected with one end of the latch bolt 3231 close to the protective cover 2, and the other end of the manual pull rod 3233 extends out of the protective cover 2, so that a person can control locking and unlocking outside the protective cover 2, and the installation and the disassembly are convenient.
As a more preferable option of this embodiment, the inner wall of the launch barrel 1 is further provided with a plurality of support rings 12, one support ring is selected in this embodiment, and the support rings 12 are used to adjust the orientation of the aircraft so that the central axis of the aircraft aligns with the central axis of the launch barrel 1, and simultaneously fill up the gap between the aircraft and the launch barrel 1.
An aircraft launching method using the energy storage type ejection sealing protection device described in the above embodiment includes:
firstly, an aircraft is installed in a launch barrel 1, the thickness and the position of a support ring 12 are adjusted to enable the aircraft and the launch barrel 1 to be coaxial, when the aircraft is installed, a manual pull rod 3233 is pulled first to enable a lock tongue 3231 to be separated from a limiting pin 3221, a protective cover 2 is pushed upwards until a steel ball 31 is embedded into a limiting groove 11 on the inner wall of the launch barrel 1, then the manual pull rod 3233 is loosened, the lock tongue 3231 is pushed out by the aid of elasticity of a locking spring 3232, the limiting pin 3221 is locked and cannot rebound, and the protective cover 2 is fixed;
secondly, when the aircraft is launched, the front end of the aircraft extrudes the elastic energy storage component 4 on the protective cover 2, and an energy storage spring 43 in the elastic energy storage component 4 is extruded to generate elasticity;
step three, after the energy storage spring 43 is compressed to a specific length, the aircraft contacts the part of the lock cylinder extending out of the base 321, after the aircraft is compressed continuously, the lock tongue 3231 is pressed down, so that the lock tongue 3231 is separated from the limit pin 3221, the limit pin 3221 no longer has the limit capacity, the steel ball 31 is separated from the limit groove 11 under the elastic force action of the energy storage spring 43, and the protective cover 2 is separated from the launching tube 1.
Further, before the aircraft is installed in the launch canister 1, the selected protective cover 2 and the elastic energy storage component 4 need to satisfy the following relation:
wherein, the first and the second end of the pipe are connected with each other,
s is the safe distance between the protective cover and the aircraft after the protective device is separated, and is determined by a launching task, and the distance is not less than 5m in the embodiment;
f is the total elastic force of the elastic energy storage component during unlocking, which is 100N in the embodiment;
f is the resistance when the protective device is separated, and the resistance is 10N at the moment;
t is the time for the protective cover and the aircraft to reach the safe distance after the protective device is separated, and is determined by the launching task, and the time is 0.2s in the embodiment;
m is the mass of the shield, 1.5Kg in this example.
The present invention is not limited to the above-described embodiments, and it will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements are also considered to be within the scope of the present invention.
Claims (9)
1. The utility model provides an energy storage formula ejection sealing protector which characterized in that, it includes:
the launching tube (1) is sleeved outside the aircraft, and the inner wall of the launching tube is also provided with a limiting groove (11);
a protective cover (2) detachably attached to one side of the launch barrel;
the locking assemblies (3) are arranged on the inner wall of the protective cover (2) in a central symmetry mode, the locking assemblies (3) comprise steel balls (31) and locking and unlocking devices (32), when the locking and unlocking devices (32) are in a locking state, the steel balls (31) are partially embedded into the limiting grooves (11), and when the locking and unlocking devices (32) are in an unlocking state, the steel balls (31) are separated from the limiting grooves (11);
the elastic energy storage component (4) is arranged between the protective cover (2) and the aircraft;
the number of the limiting grooves (11) is the same as that of the locking assemblies (3);
the elastic energy storage assembly (4) comprises:
the bottom plate (41) is fixedly connected with the protective cover (2);
the pressure plate (42) is elastically connected with the bottom plate (41) through an energy storage spring (43), and the aircraft and one side, far away from the bottom plate (41), of the pressure plate (42) are mutually abutted;
the number of the energy storage springs (43) is a plurality, and the energy storage springs are uniformly arranged between the bottom plate (41) and the pressing plate (42).
2. The energy storing ejection seal guard of claim 1, wherein: the energy storage assembly further comprises a guide screw (44), and the guide screw (44) is slidably connected to the bottom plate (41) and the pressure plate (42).
3. The energy storing ejection seal guard of claim 1, wherein: the lock-unlock device (32) includes:
a base (321) fixedly arranged on the protective cover (2) or the locking component (3);
a fastening device (322) arranged in the base (321) and used for pushing the steel ball (31) into the limiting groove (11);
a locking device (323) disposed within the base (321) to unlock or lock the fastening device (322).
4. The energy storing ejection seal guard of claim 3, wherein: the fastening device (322) comprises:
the limiting pin (3221) is arranged inside the base (321) in a sliding mode, and one end of the limiting pin and the steel ball (31) are mutually abutted;
an end cap (3222) fixedly disposed within the base (321);
the unlocking spring (3223) is used for elastically connecting the limiting pin (3221) and the end cap (3222);
the steel ball (31), the limiting pin (3221), the unlocking spring (3223) and the end cap (3222) are arranged in series in the direction perpendicular to the inner wall of the launching tube (1).
5. The energy storing ejection seal guard of claim 4, wherein: the locking device (323) comprises:
the bolt (3231) is matched and locked with the limit pin (3221) and extends out of the base (321) along the direction far away from the protective cover (2);
a locking spring (3232) elastically connecting the latch tongue (3231) and the base (321) to each other;
the lock tongue (3231) and the locking spring (3232) are arranged in series along the direction parallel to the inner wall of the launching tube (1).
6. The energy storing ejection seal guard of claim 4, wherein: the locking device (323) further comprises a manual pull rod (3233), the manual pull rod (3233) is partially arranged in the protective cover (2), and the manual pull rod (3233) and the lock tongue (3231) are fixedly connected at one end close to the protective cover.
7. The energy storing ejection seal guard of claim 1, wherein: the inner wall of the launch barrel (1) is further provided with a plurality of support rings (12).
8. An aircraft launching method based on the energy-storing ejection sealing protection device of claim 1, characterized by comprising:
the method comprises the following steps that firstly, an aircraft is arranged in a launch barrel (1), the aircraft, the launch barrel (1), a protective cover (2) and an elastic energy storage assembly (4) are coaxial, and at the moment, a locking and unlocking device (32) is in a locking state;
secondly, when the aircraft is launched, the front end of the aircraft extrudes the elastic energy storage component (4) on the protective cover (2) to compress;
step three, after the elastic energy storage assembly (4) is compressed to a preset position, the aircraft triggers the locking and unlocking device (32), so that the steel ball (31) is separated from the limiting groove (11), the connection between the protective cover (2) and the launching tube (1) is released, the protective cover (2) is ejected forwards under the elastic force of the elastic energy storage assembly (4), and the launching tube (1) and the aircraft are separated relatively.
9. An aircraft launching method as defined in claim 8, wherein: before the aircraft is installed in the launching tube (1), the selected protective cover (2) and the elastic energy storage component (4) need to satisfy the following relation:
wherein the content of the first and second substances,
s is the safe distance between the protective cover and the aircraft after the protective device is separated, and is determined by a launching task;
f is the total elastic force of the elastic energy storage component (4) during unlocking;
f is the resistance when the protective device is disengaged;
t is the time for the protective cover and the aircraft to reach the safe distance after the protective device is separated, and is determined by the launching task;
m is the mass of the shield.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110014185.1A CN112693639B (en) | 2021-01-06 | 2021-01-06 | Energy storage type ejection sealing protection device and aircraft launching method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110014185.1A CN112693639B (en) | 2021-01-06 | 2021-01-06 | Energy storage type ejection sealing protection device and aircraft launching method |
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| Publication Number | Publication Date |
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| CN112693639A CN112693639A (en) | 2021-04-23 |
| CN112693639B true CN112693639B (en) | 2022-09-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110014185.1A Active CN112693639B (en) | 2021-01-06 | 2021-01-06 | Energy storage type ejection sealing protection device and aircraft launching method |
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| CN114180106B (en) * | 2021-11-16 | 2023-08-11 | 北京卫星制造厂有限公司 | Ventilating device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2810377B1 (en) * | 2000-06-14 | 2002-12-06 | Lacroix Soc E | BRUSH SWITCHED CONTROL DEVICE, AND PYROTECHNIC DEVICE FOR CUTTING AIRCRAFT CANOPY OR THE LIKE COMPRISING SUCH A CONTROL DEVICE |
| CN105035321B (en) * | 2015-07-08 | 2017-05-24 | 中国电子科技集团公司第二十七研究所 | Miniature cylindrical launched unmanned plane and launcher |
| CN105857646B (en) * | 2016-04-08 | 2017-11-24 | 上海机电工程研究所 | A kind of spherical locking separating mechanism |
| DE102016108606A1 (en) * | 2016-05-10 | 2017-11-16 | ECM Space Technologies GmbH | Eject unit for a satellite |
| CN107458579A (en) * | 2017-08-01 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of unmanned plane device |
| CN110530202B (en) * | 2019-07-31 | 2022-07-12 | 北京北机机电工业有限责任公司 | Automatic cover opening device |
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