阅读说明：本技术 螺旋式飞箭 (Spiral flying arrow ) 是由 冯桂华 于 2019-10-31 设计创作，主要内容包括：本发明所提出的一种螺旋式飞箭包括螺旋形箭体和操控组件,以及发射组件,该螺旋形箭体包括侧面设置有舱盖的中空螺杆和设置在中空螺杆内的长轴承,以及分别设置在中空螺杆上下顶端且与长轴承连接的箭首舵和箭尾舵；该操控组件包括设置在内轴管内的载人舱和两端封闭且内部安装有发电机组的上管体与下管体,所述载人舱与管体之间设置有设备舱,且内轴管内设置有传感器；该发射组件包括固定安装于地面上且内部设置有驱动组件的支撑台和设置于支撑台顶部的限位筒,以及与限位筒相接触的弹性杆件,所述螺旋式飞箭能够以单发、连发、组发等方式实现飞箭的上升或降落,不但速度快,还具有很好的作业效果,在保障能源自给自足的同时可有效避免安全隐患。(The spiral flying arrow comprises a spiral arrow body, a control assembly and a launching assembly, wherein the spiral arrow body comprises a hollow screw rod, a long bearing, an arrow head rudder and an arrow tail rudder, wherein the side surface of the hollow screw rod is provided with a cabin cover, the long bearing is arranged in the hollow screw rod, and the arrow head rudder and the arrow tail rudder are respectively arranged at the upper top end and the lower top end of the hollow screw rod and are connected with the long bearing; the control assembly comprises a manned cabin arranged in an inner shaft tube, an upper tube body and a lower tube body, wherein the two ends of the upper tube body and the lower tube body are closed, a generator set is arranged in the upper tube body and the lower tube body, an equipment cabin is arranged between the manned cabin and the tube body, and a sensor is arranged in the inner shaft tube; this transmission subassembly includes fixed mounting in subaerial and inside supporting bench that is provided with drive assembly and sets up in the spacing section of thick bamboo at supporting bench top to and the elastic rod spare that contacts with a spacing section of thick bamboo, spiral flying arrow can be with single-shot, running fire, the group send the mode such as realize the rising or the descending of flying arrow, not only fast, still have fine operation effect, can effectively avoid the potential safety hazard when guaranteeing the energy self-sufficiency.)

1. Spiral flying arrow, its characterized in that includes:

spiral arrow body: the spiral arrow body comprises a hollow screw rod, a long bearing, an arrow head rudder and an arrow tail rudder, wherein the side surface of the hollow screw rod is provided with a cabin cover, the long bearing is arranged in the hollow screw rod, the arrow head rudder and the arrow tail rudder are respectively arranged at the upper top end and the lower top end of the hollow screw rod and are connected with the long bearing, an inner shaft tube is nested in the long bearing and is connected with the long bearing through a round bearing, and shaft connectors are respectively arranged at connecting parts of the arrow head rudder and the arrow tail rudder and the long bearing; and

the control assembly is: the control assembly comprises a manned cabin arranged in an inner shaft tube, an upper tube body and a lower tube body, wherein the two ends of the upper tube body and the lower tube body are closed, a generator set is arranged in the upper tube body and the lower tube body, an equipment cabin is arranged between the manned cabin and the upper tube body and between the manned cabin and the lower tube body, and a sensor is arranged in each cabin section of the inner shaft tube; and

the emission component: the launching assembly comprises a supporting table fixedly installed on the ground and internally provided with a driving assembly, a limiting cylinder arranged at the top of the supporting table, and an elastic rod piece in contact with the limiting cylinder.

2. The spiral-type flying arrow according to claim 1, characterized in that: the upper pipe body and the lower pipe body are respectively arranged at the upper end part and the lower end part of the equipment cabin, and a push-pull pipe fitting is arranged between the inner shaft pipe and the long bearing of the upper pipe body and the inner shaft pipe of the lower pipe body.

3. The spiral-type flying arrow according to claim 1, characterized in that: the generator set comprises a generator and a motor, and is arranged at the upper end part of the equipment cabin in the pipe body.

4. The spiral-type flying arrow according to claim 1, characterized in that: the top of the limiting cylinder is provided with a cylinder cover which is in contact with the elastic rod piece, and the middle area of the cylinder cover and the bottom of the limiting cylinder are provided with circular grooves corresponding to the shapes of the arrow head rudder or the arrow tail rudder.

5. The spiral-type flying arrow according to claim 1, characterized in that: the driving assembly comprises a motor connected with the elastic rod piece through rollers on two sides and a sensor arranged between the motor and the elastic rod piece.

6. The spiral flying arrow of claim 5 wherein: the elastic rod pieces are arranged on two sides of the limiting cylinder at intervals, the bottom of each elastic rod piece penetrates through a through hole in the supporting table to be connected with rollers on two sides of the motor, and an arc-shaped piece is arranged at the top of each elastic rod piece.

7. The spiral-type flying arrow according to claim 1, characterized in that: and two sides of the long bearing are respectively provided with a separating frame.

8. The spiral-type flying arrow according to claim 1, characterized in that: the flying arrow landing position is provided with a recovery device, and the recovery device comprises a box body, a spiral body and a limiting frame, wherein the spiral body is arranged in the box body, the bottom of the spiral body is provided with a circular groove, and the limiting frame is arranged at the top of the box body at a certain interval.

9. The spiral-type flying arrow according to claim 8, characterized in that: the spiral bodies and the circular grooves are arranged in an array, and the spiral bodies are matched with the spiral flying arrows in the opposite direction.

Technical Field

The invention relates to a spiral flying arrow.

Background

The liquid hydrogen combustion and three-stage ignition rockets are taken as vehicles by the spacecrafts such as satellites and spacecrafts at present, the performance is very good, but in the face of the development requirement of the future spaceflight, the following short plates exist in the modern rockets, the spacecrafts, the space stations and the like: 1. the whole power system of a two-stage oxidant box, a two-stage combustion agent box, a two-stage active engine, four boosters, a booster engine and the like which are necessary for launching the rocket occupies more than half space of the rocket, not only consumes a large amount of energy and prevents the rocket from being lightened, but also seriously occupies remote sensing, communication, navigation, science and other effective loads; 2. because the rocket and various spacecrafts cannot be self-supplied with energy, the carrying amount of fuel energy is a determining factor for how far the rocket and various spacecrafts can continue the journey, so that the endurance capacity of the rocket and various spacecrafts is determined to be limited; 3. because the orbit and the attitude of the satellite are mainly adjusted by a rocket engine in space, the rocket is exhausted, and the service life of the satellite is only influenced and determined by one or two years to ten years; 4. although the rocket shell is protected by the fairing and protected by the composite structure shared by the sandwich structure and the aluminum alloy honeycomb sandwich structure, the carried satellite, airship and the like are also influenced by aerodynamic force and pneumatic heating, the radiation of particle flow to personnel and equipment in the rocket body and the rocket body is difficult to avoid, and the contradiction which is difficult to reconcile exists between the fairing protection and the good radio wave penetrability maintenance; 5. the rocket only has a launching and carrying function and cannot be directly designed into a multifunctional high-speed aircraft and a multifunctional navigation device; 6. the launching of the rocket has strict requirements on weather conditions, address environments, launching rack facilities and the like, and the cost is high; 6. no matter the spacecraft with various shapes such as a cone-shaped rocket or a triangular and dragonfly-shaped unmanned aerial vehicle is not true high-speed streamline, the spacecraft does not have an optical rotation function, and the spacecraft cannot be true stealth even though special coating is provided; 7. rockets and various spacecrafts can not be recycled generally, so that serious waste is caused; 8. even if individual space equipment can be recovered, the parachute which is supported in the recovery process has great potential safety hazard.

Currently, scientists are developing photonic rockets. The propulsion system is a concave reflector with the diameter of dozens of square kilometers, but the energy consumed in the development process can not be borne, especially, the photon beam energy is extremely large, even though the protective screens are arranged on the positive hydrogen storage tank and the negative hydrogen storage tank, personnel and instrument equipment are difficult to avoid radiation damage, the environmental damage can be caused seriously, and the consequences of burning off space equipment such as a carrying airship and the like can be caused under special conditions, so that how to develop novel aviation equipment according to the development requirement becomes an important subject.

Disclosure of Invention

The invention aims to provide a spiral flying arrow which solves the problems of serious energy consumption, insufficient continuous kinetic energy, slow speed, poor load capacity, certain potential safety hazard and the like by utilizing a rotary ascending and descending mode.

The spiral flying arrow provided by the invention comprises a spiral arrow body, a control assembly and a launching assembly, wherein the spiral arrow body comprises a hollow screw rod, a long bearing, an arrow head rudder and an arrow tail rudder, wherein the side surface of the hollow screw rod is provided with a cabin cover, the long bearing is arranged in the hollow screw rod, the arrow head rudder and the arrow tail rudder are respectively arranged at the upper top end and the lower top end of the hollow screw rod and are connected with the long bearing, an inner shaft tube is nested in the long bearing, two sides of the inner shaft tube are respectively provided with a separating frame, the inner shaft tube is connected with the long bearing through a round bearing, and connecting parts of the arrow head rudder and the arrow tail rudder; the control assembly comprises a manned cabin arranged in an inner shaft tube, an upper tube body and a lower tube body, wherein the two ends of the upper tube body and the lower tube body are sealed, a generator set is arranged in the upper tube body and the lower tube body, an equipment cabin is arranged between the manned cabin and the upper tube body and between the manned cabin and the lower tube body, a sensor is arranged in each cabin section of the inner shaft tube, the upper tube body and the lower tube body are respectively arranged at the upper end part and the lower end part of the equipment cabin, a push-pull type pipe fitting is arranged between the inner shaft tube and a long bearing of the upper tube body and the inner shaft tube of; the launching component comprises a supporting table fixedly arranged on the ground and internally provided with a driving component, a limiting cylinder arranged at the top of the supporting table and an elastic rod piece contacted with the limiting cylinder, wherein the driving component comprises a motor connected with the elastic rod piece through rollers at two sides and a sensor arranged between the motor and the elastic rod piece, the top of the limiting cylinder is provided with a cylinder cover contacted with the elastic rod piece, the middle area of the cylinder cover and the bottom of the limiting cylinder are respectively provided with a circular groove corresponding to the shape of an arrow head rudder or an arrow tail rudder, the elastic rod piece is arranged at two sides of the limiting cylinder at a certain interval, the bottom of the elastic rod piece penetrates through a through hole on the supporting table and is connected with the rollers at two sides of the motor, the top is provided with an arc piece, and the landing position of the flying arrow is also provided with a recovery device which comprises a box body and a spiral body, and the limiting frames are arranged at the top of the box body at intervals, the spiral bodies and the circular grooves are arranged in an array, and the spiral bodies are matched with the spiral flying arrows in the opposite direction.

The spiral flying arrow provided by the invention can meet various modes of carrying flying arrows, satellite flying arrows, spacecraft arrows, double flying arrows of a space station, missiles, anti-pilot flying arrows, torpedo flying arrows, spiral array flying arrows of an aircraft carrier base, unmanned aerial vehicle flying arrows, personal flying arrows and the like and various climatic and environmental requirements, and the flying arrows can be lifted or landed by using the launching assembly and the hollow screw rod as the shell of the flying arrow in a single-shot, continuous-shot, group-shot and other modes to enable the hollow screw rod of the flying arrow to rotate at high speed and generate acceleration, wherein the flying arrow is lifted or landed by upwards or downwards rotating according to the external thread of the hollow screw rod, and through the structure, the self-sufficiency of energy can be fully realized, the self-weight of the arrow body is further lightened, so that the load capacity is effectively enhanced, and in the process of flying arrow landing, the speed can be effectively controlled, the flying arrow can smoothly land in a preset recovery device, and in the process of ascending the flying arrow, the flying arrow can turn along with the relative rotation of the coupling through the arrow head rudder and the arrow tail rudder, so that the flying attitude and direction of the arrow body are effectively controlled, the flying arrow has the characteristics of rapidness, accuracy in position, strong maneuverability and the like, the phenomena of thermal barrier, black barrier and the like are avoided, and the radiation to personnel and equipment in the arrow body is reduced; meanwhile, a manned cabin, an equipment cabin, a sensor and a generator set are arranged in the inner shaft tube, wherein an operator entering the manned cabin can carry out aerial operation, related equipment such as remote sensing equipment, communication equipment, navigation equipment and the like in the equipment cabin can be contacted and responded with equipment on the ground at any time, and a very ideal operation effect can be achieved through the sensor and the generator set; in addition, military and aerospace equipment such as satellites, airships, missiles and the like are loaded on the separation frames on the two sides of the long bearing, so that the flying arrow can be used as military equipment and also can be used as civil equipment.

Drawings

FIG. 1 is a schematic diagram of the overall appearance structure of a spiral flying arrow provided by the invention

FIG. 2 is a schematic sectional view of FIG. 1

FIG. 3 is a schematic cross-sectional view of the long bearing disposed in the hollow screw of FIG. 2

FIG. 4 is a schematic diagram of the overall appearance structure of the launching assembly in the spiral flying arrow

FIG. 5 is a schematic view showing the state of launching the spiral flying arrow in example 1

FIG. 6 is a schematic view showing the state of launching the spiral flying arrow in embodiment 2

FIG. 7 is a schematic view showing the state of launching the spiral flying arrow in embodiment 3

FIG. 8 is a schematic view showing the state of launching the spiral flying arrow in embodiment 4

FIG. 9 is a schematic view of the overall appearance structure of the spiral flying arrow recycling device

Detailed Description