CN218022235U - Unmanned aerial vehicle launcher convenient to type of falling V fin - Google Patents
Unmanned aerial vehicle launcher convenient to type of falling V fin Download PDFInfo
- Publication number
- CN218022235U CN218022235U CN202221960524.1U CN202221960524U CN218022235U CN 218022235 U CN218022235 U CN 218022235U CN 202221960524 U CN202221960524 U CN 202221960524U CN 218022235 U CN218022235 U CN 218022235U
- Authority
- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- aircraft
- telescopic link
- inverted
- 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.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model relates to an aircraft firing equipment field discloses a be convenient for type of falling V fin unmanned aerial vehicle emitter, the utility model provides a be convenient for type of falling V fin unmanned aerial vehicle emitter, including transmission telescopic link, base, support telescopic link, tripod, be used for installing the aircraft installation department of aircraft; launch telescopic link one end and articulate on the base, the other end and aircraft installation department fixed connection, support telescopic link one end and tripod fixed connection, the other end is articulated with the one end that the launch telescopic link is close to the aircraft installation department. Through the setting of above-mentioned technical scheme, when erectting the aircraft, the transmission telescopic link forms stable triangle-shaped structure with the support telescopic link, and the tripod forms stable triangle-shaped structure, and the stability of launching cradle can be improved greatly to two triangle-shaped structures, and two telescopic link structures can adjust transmission angle in a flexible way.
Description
Technical Field
The utility model relates to an aircraft firing equipment field specifically relates to a type of being convenient for fin unmanned aerial vehicle emitter of falling V.
Background
The rocket-assisted aircraft is one of a plurality of aircrafts, is an aircraft launched on a launcher in a rocket-assisted mode, and has wide application prospects in multiple fields of aerial photography, patrol, measurement and the like; the launcher is the launching base station of aircraft, in order to guarantee the launch is successful, has higher requirement to the launcher.
The invention with publication number CN 110683068A discloses a launcher for a rocket boosting aircraft, relates to the technical field of aircraft launching equipment, and comprises a bottom plate made of carbon fiber plates, wherein two ends and the middle part of the bottom plate are provided with four guide rods made of carbon fiber hollow tubes, and the guide rods at the two ends of the bottom plate are sleeved with stop blocks for placing aircraft wings.
In the prior art, because the aircraft supporting part is large in size, and the ground supporting is only completed by the tripod, the stability of the aircraft on the ground is poor in the prior art, the aircraft is easy to topple over after the launching angle is adjusted, and certain potential safety hazards are caused.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a type of being convenient for down V fin unmanned aerial vehicle emitter, this utility model can solve the relatively poor problem of stability when placing ground that exists among the prior art.
In order to achieve the purpose, the utility model provides an unmanned aerial vehicle launching device with an inverted V-shaped tail wing, which comprises a launching telescopic rod, a base, a supporting telescopic rod, a tripod and an aircraft mounting part for mounting an aircraft; launch telescopic link one end and articulate on the base, the other end and aircraft installation department fixed connection, support telescopic link one end and tripod fixed connection, the other end is articulated with the one end that the launch telescopic link is close to the aircraft installation department.
Through the setting of above-mentioned technical scheme, when erectting the aircraft, the transmission telescopic link forms stable triangle-shaped structure with the support telescopic link, and the tripod forms stable triangle-shaped structure, and the stability of launching cradle can be improved greatly to two triangle-shaped structures, and two telescopic link structures can adjust transmission angle in a flexible way.
Further, the aircraft installation department includes bottom plate, a plurality of guide bar, bottom plate and transmission telescopic link fixed connection are a plurality of the vertical fixed connection of guide bar is in the bottom plate.
Further, the bottom plate is of a multi-section bent structure, and two depressions for accommodating the inverted V-shaped tail wings are formed in one side of the bottom plate.
Furthermore, a plurality of guide bars distribute two respectively in the both sides and the middle part of bottom plate.
Furthermore, the launching telescopic rod is hinged with the base in a spherical mode.
Furthermore, the supporting telescopic rod is provided with a rotating wheel for controlling the telescopic movement of the supporting telescopic rod.
Furthermore, the launching telescopic rod and the supporting telescopic rod are provided with fastening structures used for limiting expansion and contraction, and the fastening structures comprise limiting bolts or limiting bolts.
Furthermore, the base is provided with at least one fixing hole penetrating through the upper surface and the lower surface of the base.
Further, the fixing hole obliquely penetrates through the base.
Other features and advantages of the present invention will be described in detail in the detailed description which follows.
Drawings
Fig. 1 is a schematic structural diagram of an embodiment of the present invention;
fig. 2 is a right side view of fig. 1.
Description of the reference numerals
Launching the telescopic rod 1; a base 2; supporting the telescopic rod 3; a tripod 4; a base plate 51, a guide bar 52; a recess 53; a rotating wheel 6; and a fixing hole 7.
Detailed Description
The following describes the embodiments of the present invention in detail. It is to be understood that the description of the embodiments herein is for purposes of illustration and explanation only and is not intended to limit the invention.
In the present invention, the use of the terms of orientation such as "upper and lower" in the case where no description is made to the contrary generally means the orientation in the assembled and used state. "inner and outer" refer to the inner and outer contours of the components themselves.
The utility model provides an unmanned aerial vehicle launching device with an inverted V-shaped tail wing, as shown in figures 1-2, comprising a launching telescopic rod 1, a base 2, a supporting telescopic rod 3, a tripod 4 and an aircraft mounting part for mounting an aircraft; launch 1 one end of telescopic link and articulate on base 2, the other end and 5 fixed connection of aircraft installation department, 3 one end of support telescopic link and tripod 4 fixed connection, the other end is articulated with the one end that launch telescopic link 1 is close to the aircraft installation department.
Through the setting of above-mentioned technical scheme, when erectting the aircraft, launching telescopic link 1 and support telescopic link 3 and form stable triangle-shaped structure, tripod 4 forms stable triangle-shaped structure, and the stability of launching cradle can be improved greatly to two triangle-shaped structures, and two telescopic link structures can adjust launch angle in a flexible way.
Specifically, the aircraft installation portion includes bottom plate 51, a plurality of guide bar 52, bottom plate 51 and transmission telescopic link 1 fixed connection, and a plurality of guide bar 52 is vertical fixed connection in bottom plate 51. Further, the bottom plate 51 has a multi-segment bent structure, and two recesses 53 for accommodating inverted V-shaped stabilizers are formed at one side thereof; the depression 53 prevents the rear wing from colliding with the launcher when the inverted v-shaped rear wing aircraft is launched. Further, a plurality of guide rods 52 are respectively distributed on two sides and the middle of the bottom plate 51; as shown in fig. 1, two guide rods 52 are respectively disposed at two sides and a middle portion of the bottom plate 51, and the two guide rods 52 are used for fixing the wing of the aircraft to achieve a fixing effect.
Compare ordinary axle hinge, launch telescopic link 1 and base 2 ball pivot, not only can adjust in the vertical direction, can also adjust launch angle in the horizontal direction, the adjustment range is wider.
In order to conveniently and manually adjust the length of the supporting telescopic rod 3, preferably, a rotating wheel 6 for controlling the telescopic extension of the supporting telescopic rod 3 is arranged on the supporting telescopic rod 3. As an embodiment, the rotating wheel 6 is connected with the telescopic rod 3 through the matching of a rack and a gear, the gear fixedly connected with the rotating wheel 6 is driven by the rotating wheel, and the rack fixedly connected with the movable end of the telescopic rod 3 is driven by the gear to move up and down. As another embodiment, the supporting telescopic rod 3 is an electric telescopic rod, the rotating wheel 3 is an electric control knob, and the electric telescopic rod is controlled to stretch and contract through the electric control knob.
After angular adjustment accomplished, in order to further improve the firm of transmission telescopic link 1, support telescopic link 3, under preferred circumstances, be provided with on transmission telescopic link 1, the support telescopic link 3 and be used for restricting flexible fastening structure, as two kinds of embodiments, fastening structure includes spacing bolt or spacing bolt. Wherein, fastening structure is spacing bolt, and during spacing bolt can insert the hole of telescopic link, this hole is including setting up a hole at the outside stiff end of telescopic link and setting up a plurality of holes at inside expansion end. The limiting bolt penetrates through the fixed end outside the telescopic rod and is screwed with the movable end inside the telescopic rod so as to achieve the fastening effect.
The tripod 4 can be an adjustable tripod capable of adjusting the distance between the legs, and can also be a tripod with a fixed bracket distance.
In order to make the connection with the ground reliable, the base 2 is provided with at least one fixing hole 7 penetrating through the upper surface and the lower surface of the base 2. The fixing hole 7 can penetrate through the rod to be embedded into the ground, and the ground grabbing force of the base 2 and the ground is improved. Further, the fixing hole 7 is obliquely penetrated through the base 2. The obliquely arranged fixing hole 7 can enable the axis of the fixing hole 7 to be vertical to the axial direction of the supporting telescopic rod 3, and therefore the ground gripping force is improved.
The above detailed description describes the preferred embodiments of the present invention, but the present invention is not limited to the details of the above embodiments, and the technical idea of the present invention can be within the scope of the present invention, and can be right to the technical solution of the present invention, and these simple modifications all belong to the protection scope of the present invention.
It should be noted that the various features described in the above embodiments may be combined in any suitable manner without departing from the scope of the invention. In order to avoid unnecessary repetition, the present invention does not separately describe various possible combinations.
In addition, various embodiments of the present invention can be combined arbitrarily, and the disclosed content should be regarded as the present invention as long as it does not violate the idea of the present invention.
Claims (9)
1. An unmanned aerial vehicle launching device with an inverted V-shaped tail wing convenient to launch is characterized by comprising a launching telescopic rod (1), a base (2), a supporting telescopic rod (3), a tripod (4) and an aircraft mounting part for mounting an aircraft; launch telescopic link (1) one end and articulate on base (2), the other end and aircraft installation department (5) fixed connection, support telescopic link (3) one end and tripod (4) fixed connection, the other end is articulated with the one end that launch telescopic link (1) is close to the aircraft installation department.
2. The unmanned aerial vehicle launcher with inverted-V-shaped tail according to claim 1, wherein the aircraft mounting portion comprises a bottom plate (51) and a plurality of guide rods (52), the bottom plate (51) is fixedly connected with the launching telescopic rod (1), and the plurality of guide rods (52) are vertically and fixedly connected to the bottom plate (51).
3. The launch device of unmanned aerial vehicle with inverted V-shaped tail for facilitating launch according to claim 2, wherein said bottom plate (51) is a multi-segment bent structure with two recesses (53) formed on one side thereof for accommodating inverted V-shaped tail.
4. The launching device of unmanned aerial vehicle with inverted-V-shaped tail according to claim 2, characterized in that the plurality of guide rods (52) are respectively distributed on two sides and in the middle of the bottom plate (51).
5. The launching device of unmanned aerial vehicle with inverted V-shaped tail wing convenient to use according to claim 1, characterized in that the launching telescopic rod (1) is hinged with the base (2) in a spherical manner.
6. The unmanned aerial vehicle launcher with inverted V-shaped tail according to claim 1, wherein the supporting telescopic rod (3) is provided with a rotating wheel (6) for controlling the telescopic movement of the supporting telescopic rod (3).
7. The unmanned aerial vehicle launcher with inverted V-shaped tail according to claim 1, wherein the launching telescopic rod (1) and the supporting telescopic rod (3) are provided with fastening structures for limiting telescoping, and the fastening structures comprise limiting bolts or limiting bolts.
8. The unmanned aerial vehicle launcher with inverted V-shaped tail convenient for launching according to claim 1, wherein the base (2) is provided with at least one fixing hole (7) penetrating through the upper and lower surfaces of the base (2).
9. The launch device of unmanned aerial vehicle with inverted V-shaped tail according to claim 8, wherein the fixing hole (7) is obliquely penetrated through the base (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221960524.1U CN218022235U (en) | 2022-07-25 | 2022-07-25 | Unmanned aerial vehicle launcher convenient to type of falling V fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221960524.1U CN218022235U (en) | 2022-07-25 | 2022-07-25 | Unmanned aerial vehicle launcher convenient to type of falling V fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218022235U true CN218022235U (en) | 2022-12-13 |
Family
ID=84342124
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221960524.1U Active CN218022235U (en) | 2022-07-25 | 2022-07-25 | Unmanned aerial vehicle launcher convenient to type of falling V fin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218022235U (en) |
-
2022
- 2022-07-25 CN CN202221960524.1U patent/CN218022235U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20200307826A1 (en) | Damping device, gimbal assembly having same, and unmanned aerial vehicle | |
| CA1106341A (en) | Supporting structure for reflectors, solar cells or solar cell carriers | |
| CN107972894B (en) | A kind of Control System for Reusable Launch Vehicle landing and buffering device | |
| CN105667789A (en) | Universal type elastic potential energy mechanical catapult for single tandem wing unmanned aerial vehicle with rear propeller | |
| CN218022235U (en) | Unmanned aerial vehicle launcher convenient to type of falling V fin | |
| CN106882391B (en) | Spherical triaxial allies oneself with accuse vector motor cabinet that unmanned aerial vehicle used | |
| CN107176310B (en) | Unmanned aerial vehicle launching cradle | |
| CN105366068A (en) | Vehicle-mounted unmanned plane adjustable net-catch recovery apparatus | |
| IL37395A (en) | Tripod mounting for an infantry weapon | |
| US2843020A (en) | Zero-length launcher | |
| CN201032444Y (en) | Liftable frame firework | |
| RU2002126561A (en) | ELECTROMAGNETIC RADIATION DEVICE AND PILON, ANTENNA MOUNT FOR SUCH DEVICE | |
| CN110877750B (en) | Adjustable high-adaptability field launching support for unmanned aerial vehicle | |
| CN101654151B (en) | Supporting mechanism applied unmanned aerial vehicle launching system | |
| CN113386950A (en) | Adjustable skid undercarriage for unmanned helicopter | |
| CN220130366U (en) | Unmanned aerial vehicle emission regulating frame | |
| CN216102844U (en) | Unmanned aerial vehicle transportation and emitter | |
| CN220221142U (en) | Applicable type transmitting frame | |
| CN109094800B (en) | Cross double-rotor unmanned helicopter and protection frame thereof | |
| CN219524288U (en) | Unmanned aerial vehicle with buffering take-off and landing | |
| CN219008150U (en) | Unmanned aerial vehicle for forest fire prevention and extinguishment | |
| CN217520351U (en) | Adjustable firework launching device base | |
| CN114152146B (en) | Embedded gun sighting telescope base convenient to installation | |
| CN221059389U (en) | Portable bird repellent emitter | |
| SE8703584L (en) | gun systems |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |