阅读说明：本技术 一种火箭助推飞行器用发射架 (Launcher for rocket boosting aircraft ) 是由 聂博 沈一军 王荀学 葛雨峰 王静静 刘梦源 方素玲 于 2019-10-30 设计创作，主要内容包括：本发明公开了一种火箭助推飞行器用发射架,涉及飞行器发射设备技术领域,包括碳纤维板材制作的底板,所述底板两端与中间部位共设有四根碳纤维空心管制作的导向杆,其中,底板两端部位的所述导向杆上套接有搁置飞行器机翼的挡块,本发明操作便捷,指向性好；水准管用于观测发射架侧斜情况,可以有效地防止发射架侧斜问题；发射架的底板和导向杆采用碳纤维材质,强度高且耐用；通过松开连接发射架底板与导向杆的螺丝与螺母,可以将发射架拆卸成几个部分,方便携带和运输；点火电线下端延至底板下方,可有效防止挂尾现象。(The invention discloses a launcher for a rocket boosting aircraft, which relates to the technical field of aircraft launching equipment and comprises a bottom plate made of carbon fiber plates, wherein guide rods made of four carbon fiber hollow tubes are arranged at two ends and the middle part of the bottom plate, and stop blocks for placing aircraft wings are sleeved on the guide rods at the two ends of the bottom plate; the level pipe is used for observing the lateral inclination condition of the launching frame, so that the lateral inclination problem of the launching frame can be effectively prevented; the bottom plate and the guide rod of the launching frame are made of carbon fiber materials, so that the launching frame is high in strength and durable; the launching rack can be disassembled into a plurality of parts by loosening the screw and the nut which are used for connecting the bottom plate of the launching rack and the guide rod, so that the launching rack is convenient to carry and transport; the lower end of the ignition wire extends to the lower part of the bottom plate, so that the tail hanging phenomenon can be effectively prevented.)

1. The launcher for the rocket boosting aircraft is characterized by comprising a bottom plate (1) made of carbon fiber plates, wherein guide rods (2) made of four carbon fiber hollow tubes are arranged at two ends and the middle part of the bottom plate (1), a stop block (8) for placing aircraft wings (14) is sleeved on the guide rods (2) at the two ends of the bottom plate (1), a stop rod (9) made of the carbon fiber rods is arranged on the stop block (8), connectors (10) used for connecting ignition leads (15) are arranged on the two guide rods (2) at the middle part of the bottom plate (1), an ignition wire (11) is arranged below the connectors (10), the lower end of the ignition wire (11) extends to the lower part of the bottom plate (1), and the ignition wire (11) is fixed on the guide rods (2) through insulating fireproof adhesive tapes (12); the bottom plate (1) below is equipped with connecting plate (4), connecting plate (4) below installing support (13).

2. A launcher for rocket-assisted spacecraft according to claim 1, wherein: the bottom plate (1) is provided with five circular holes (3) and is connected with the guide rod (2) and the connecting plate (4) through screws (6) and nuts (7).

3. A launcher for rocket-assisted spacecraft according to claim 2, wherein: and a leveling pipe (5) is arranged on the upper surface of the bottom plate (1).

4. A launcher for rocket-assisted spacecraft according to claim 3, wherein: the outer diameter of the guide rod (2) is 12mm, the inner diameter of the guide rod is 10mm, and the length of the guide rod (2) is 800 mm-1200 mm.

5. A launcher for rocket-assisted spacecraft according to claim 4, wherein: the bottom plate (1) is rhombic or rectangular and is 6mm thick.

6. A launcher for rocket-assisted spacecraft according to claim 5, wherein: the stop block (8) is made of carbon fiber plates and is 6mm thick.

7. A launcher for rocket-assisted spacecraft according to claim 6, wherein: the outer diameter of the stop lever (9) is 4mm, the inner diameter of the stop lever is 3mm, and the length of the stop lever (9) is 300 mm-600 mm.

Technical Field

The invention relates to the technical field of aircraft launching equipment, in particular to a launcher for a rocket boosting aircraft.

Background

The rocket boosting aircraft is one of a plurality of aircrafts, is an aircraft launched on a launcher in a rocket boosting mode, and has wide application prospects in the fields of aerial photography, inspection, measurement and the like; the launcher is a launching base station of an aircraft, and has higher requirements on the launcher in order to ensure the success of launching; however, the prior art launcher is generally universal, and has one or more of the following disadvantages:

1. the launcher guide rail is shorter, so that the directivity is poorer;

2. when the launching angle of the launching frame is adjusted, the problem of lateral inclination of the launching frame is easy to occur;

3. the launcher made of plastic materials has insufficient strength and short service life;

4. the launcher adopts an undetachable integral frame body, is not convenient to carry and transport, and is easy to damage;

5. the tail hanging phenomenon of the ignition wire can occur, so that the takeoff route of the aircraft is interfered, and even safety accidents are caused;

accordingly, the art is yet to be improved and improved upon to meet the needs.

Disclosure of Invention

The invention aims to provide a launcher for a rocket-assisted aircraft, which aims to overcome the defects of the problems in the prior art.

A launcher for a rocket boosting aircraft comprises a bottom plate made of carbon fiber plates, wherein guide rods made of four carbon fiber hollow tubes are arranged at two ends and the middle part of the bottom plate, stop blocks for placing aircraft wings are sleeved on the guide rods at the two ends of the bottom plate, stop rods made of carbon fiber rods are arranged on the stop blocks, connectors for connecting ignition wires are arranged on the two guide rods at the middle part of the bottom plate, ignition wires are arranged below the connectors, the lower ends of the ignition wires extend to the lower part of the bottom plate, and the ignition wires are fixed on the guide rods through insulating fireproof adhesive tapes; the bottom plate below is equipped with the connecting plate, connecting plate below installing support.

Preferably, the bottom plate is provided with five circular holes, and the guide rod and the connecting plate are connected through a screw and a nut.

Preferably, a leveling pipe is arranged on the upper surface of the bottom plate.

Preferably, the guide rod has an outer diameter of 12mm and an inner diameter of 10mm, and the guide rod has a length of 800 mm-1200 mm.

Preferably, the bottom plate is in a diamond shape or a rectangular shape, and the thickness of the bottom plate is 6 mm.

Preferably, the stop block is made of carbon fiber plates and has a thickness of 6 mm.

Preferably, the stop lever has an outer diameter of 4mm and an inner diameter of 3mm, and the length of the stop lever is 300 mm-600 mm.

The invention has the advantages that: the invention has convenient operation and good directivity; the level pipe is used for observing the lateral inclination condition of the launching frame, so that the lateral inclination problem of the launching frame can be effectively prevented; the bottom plate and the guide rod of the launching frame are made of carbon fiber materials, so that the launching frame is high in strength and durable; the launching rack can be disassembled into a plurality of parts by loosening the screw and the nut which are used for connecting the bottom plate of the launching rack and the guide rod, so that the launching rack is convenient to carry and transport; the lower end of the ignition wire extends to the lower part of the bottom plate, so that the tail hanging phenomenon can be effectively prevented.

Drawings

FIG. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a schematic structural view of the present invention without a bracket.

Fig. 3 is a schematic structural view of each part in fig. 2.

Fig. 4 is a schematic structural diagram of the bottom plate of the present invention.

The device comprises a base plate, a guide rod, a circular hole, a connecting plate, a leveling pipe, a screw, a nut, a stop block, a stop rod, a connector, an ignition wire, an insulating fireproof adhesive tape, a support, an aircraft wing and an ignition lead, wherein the base plate is 1, the guide rod is 2, the circular hole is 3, the connecting plate is 4, the leveling pipe is 5, the screw is 6, the nut is 7, the stop block is 8, the stop rod is 9, the connector is 10, the ignition.

Detailed Description

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.

As shown in fig. 1 to 4, a launcher for a rocket-assisted aircraft comprises a bottom plate 1 made of carbon fiber plates, wherein two ends and the middle part of the bottom plate 1 are provided with guide rods 2 made of four carbon fiber hollow tubes, wherein the guide rods 2 at the two ends of the bottom plate 1 are sleeved with a stop block 8 for placing an aircraft wing 14, the stop block 8 is provided with a stop rod 9 made of carbon fiber rods, two guide rods 2 at the middle part of the bottom plate 1 are provided with a connector 10 for connecting an ignition lead 15, an ignition wire 11 is arranged below the connector 10, the lower end of the ignition wire 11 extends to the lower part of the bottom plate 1, and the ignition wire 11 is fixed on the guide rods 2 by using an insulating fireproof adhesive tape 12; a connecting plate 4 is arranged below the bottom plate 1, and a support 13 is arranged below the connecting plate 4.

In this embodiment, the base plate 1 is provided with five circular holes 3, and the guide bar 2 and the connection plate 4 are connected by screws 6 and nuts 7.

In this embodiment, the upper surface of the base plate 1 is provided with a level tube 5.

In this embodiment, the guide rod 2 has an outer diameter of 12mm and an inner diameter of 10mm, and the length of the guide rod 2 is 800mm to 1200 mm.

In this embodiment, the bottom plate 1 is in the shape of a diamond or a rectangle and has a thickness of 6 mm.

The dog 8 is made of carbon fiber plates and has the thickness of 6 mm. Said stop 8 can be obtained by cutting from the bottom plate 1.

In this embodiment, the stop lever 9 has an outer diameter of 4mm and an inner diameter of 3mm, and the length of the stop lever 9 is 300mm to 600 mm.

The invention has the advantages that the stop blocks 8 sleeved on the guide rods 2 at the two ends of the bottom plate 1 are used for placing the aircraft wings 14, the operation is convenient and fast, the length of the guide rods 2 is 800 mm-1200 mm, and the stop blocks 8 are provided with the stop rods 9, so that the directivity is good; the leveling tube 5 is used for observing the lateral inclination of the launching frame, so that the lateral inclination problem of the launching frame can be effectively prevented; the bottom plate 1 and the guide rod 2 of the launching frame are made of carbon fiber materials, so that the launching frame is high in strength and durable; the launcher can be disassembled into a plurality of parts by loosening the screw 6 and the nut 7 which connect the launcher bottom plate 1 and the guide rod 2, so that the launcher is convenient to carry and transport; the lower end of the ignition wire 11 extends to the lower part of the bottom plate 1, so that the tail hanging phenomenon can be effectively prevented.

It will be appreciated by those skilled in the art that the invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The embodiments disclosed above are therefore to be considered in all respects as illustrative and not restrictive. All changes which come within the scope of or equivalence to the invention are intended to be embraced therein.