CN110920921B

CN110920921B - Near space aircraft launching system and method

Info

Publication number: CN110920921B
Application number: CN201911045077.XA
Authority: CN
Inventors: 秦玉梅; 闫峰; 刘永奇; 付强; 何泽青; 张泰华; 杨燕初
Original assignee: Academy of Opto Electronics of CAS
Current assignee: Academy of Opto Electronics of CAS
Priority date: 2019-10-30
Filing date: 2019-10-30
Publication date: 2022-08-30
Anticipated expiration: 2039-10-30
Also published as: CN110920921A

Abstract

The invention relates to the field of aircrafts, and discloses a near space aircraft launching system and a method, wherein the near space aircraft launching system comprises the following steps: a throwing frame; the throwing frame is fixedly connected with the floating platform, hanging points are respectively arranged on wingspans on two sides of the aircraft and at the head of the aircraft, the aircraft is connected with the throwing frame through a rope at the hanging points, the length of the rope is set according to the throwing angle of the aircraft, and a cutter is arranged on the rope. According to the near space aircraft launching system and the near space aircraft launching method, the hanging points are arranged at the wingspan and the head parts on the two sides of the aircraft, so that the system can adapt to the shape of the aircraft, and the hanging stability of the aircraft is favorably realized; the aircraft is connected with the throwing frame through ropes at each hanging point, and the specific posture of the aircraft can be controlled and adjusted by adjusting the length of each rope, so that the requirements of the aircraft on different throwing angles can be met; the rope is cut by the cutter to be put in, the design is ingenious, and the rope cutting device is convenient to control.

Description

Near space aircraft launching system and method

Technical Field

The invention relates to the field of aircrafts, in particular to a near space aircraft launching system and a near space aircraft launching method.

Background

The near space is an airspace 20-100 kilometers away from the ground, and has attracted wide attention internationally due to important development and application values. The near space aircraft is an aircraft or a sub-orbital aircraft which can continuously fly in the near space for a long time or a hypersonic cruise aircraft which can fly in the near space, and the aircraft has great development potential in the aspects of communication guarantee, information collection, electronic suppression, early warning, civil use and the like.

At present, an aircraft flying to the adjacent space height independently faces two major problems: firstly, the ascending section needs to pass through an unstable airflow zone, so that the structure of the machine body is easy to damage; secondly, the propulsion power required for the climb segment is large, resulting in a significant increase in the energy train and structural weight, and in turn a significant reduction in payload capacity. Face aerial delivery technique can be fine solve above-mentioned two problems, can not only make unmanned aerial vehicle's design more pointed, improve the efficiency of design point to can also reduce the requirement to ground take off and land condition, supporting guarantee, reduce by a wide margin and close on spacecraft system's design, the use degree of difficulty.

In the process of implementing the air-facing throwing, the aircraft is taken to the height of the adjacent space by the aerostat platform and then is controlled to be thrown, so that the method is a feasible scheme. Especially for an aircraft with a large wingspan, such as a solar unmanned aerial vehicle, due to the large wing area with solar energy, if the solar unmanned aerial vehicle autonomously flies to the adjacent space height, a large energy system is needed, and meanwhile, the phenomenon that the wings are damaged easily occurs when the rigidity of the wings with the large wingspan is limited and the wings pass through an unstable area with large airflow. Therefore, the solar unmanned aerial vehicle is passively brought into the near space environment by the aerostat platform, and separated and thrown in after reaching a certain height. The scheme that the high-altitude balloon is thrown close to the space platform at high altitude is a very feasible scheme, and an irreplaceable effect is provided for the development of the solar unmanned aerial vehicle.

At present, no precedent for implementing air-to-air delivery of an aircraft with a large wingspan exists internationally, and a system for delivering the aircraft in the adjacent space is lacked.

Disclosure of Invention

Technical problem to be solved

The invention aims to provide a near space aircraft launching system and a near space aircraft launching method, which are used for solving or partially solving the problem of the lack of the existing system for launching an aircraft in a near space.

(II) technical scheme

In order to solve the above technical problem, in a first aspect of the present invention, there is provided a delivery system for a near space vehicle, comprising: a throwing frame; the throwing frame is fixedly connected with the floating platform, hanging points are respectively arranged on wingspans on two sides of the aircraft and at the head of the aircraft, the aircraft is connected with the throwing frame through a rope at the hanging points, the length of the rope is set according to the throwing angle of the aircraft, and a cutter is arranged on the rope.

In a second aspect of the present invention, a method for launching a near space vehicle based on the system for launching a near space vehicle is provided, which includes: connecting the aircraft with the throwing frame at a hoisting point through ropes, and adjusting the throwing angle of the aircraft by adjusting the length of each rope; releasing the floating platform to drive the launching system of the near space vehicle to ascend to a launching area; and cutting the rope by using a cutter, and throwing the aircraft.

(III) advantageous effects

According to the near space aircraft launching system and the near space aircraft launching method, the hanging points are arranged at the wingspan and the head parts on the two sides of the aircraft, so that the system can adapt to the shape of the aircraft, and the hanging stability of the aircraft is favorably realized; the aircraft is connected with the throwing frame through ropes at each hanging point, and the specific posture of the aircraft can be controlled and adjusted by adjusting the length of each rope, so that the requirements of the aircraft on different throwing angles can be met, and the applicability and the use flexibility of the throwing system are improved; the cutter is arranged to cut the rope to realize throwing, and the rope throwing device is ingenious in design and convenient to control.

Drawings

FIG. 1 is a general schematic diagram of a delivery system for a near space vehicle according to an embodiment of the invention;

fig. 2 is a schematic structural diagram of a throwing frame in the embodiment of the present invention;

FIG. 3 is a schematic structural view of a cross beam in an embodiment of the present invention;

FIG. 4 is a schematic structural view of a stringer according to an embodiment of the present invention;

fig. 5 is a schematic structural diagram of a front beam in an embodiment of the present invention.

Description of the reference numerals:

1-floating platform pod; 2, putting in a frame; 3, an aircraft;

41-a first rope; 42-a second rope; 21-a cross beam;

22-longitudinal beam; 23-a forward extending beam; 24-a linking unit;

25-a fixed connection element; 26-a hoisting ring; 27-metal part.

Detailed Description

The following detailed description of embodiments of the present invention is provided in connection with the accompanying drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in a specific case to those of ordinary skill in the art.

An embodiment of the present invention provides a delivery system for a near space vehicle, and referring to fig. 1, the delivery system includes: a throwing frame 2; the throwing frame 2 is fixedly connected with the floating platform, hanging points are respectively arranged on wingspans on two sides of the aircraft 3 and at the head of the aircraft, the aircraft 3 is connected with the throwing frame 2 through a rope at the hanging points, the length of the rope is set according to the throwing angle of the aircraft 3, and a cutter is arranged on the rope.

The launch system is primarily intended for the launch of large-span aircraft 3 in the immediate space. The method mainly comprises the steps of utilizing a floating platform to bring the launching frame 2 and the aircraft 3 into an adjacent space environment, and then separating the aircraft 3 from the launching frame 2 for launching. The putting frame 2 can be a frame structure so as to reduce weight and save energy consumption.

The aircraft 3 is hung on the throwing frame 2 through a rope. And a cutter is arranged on the rope and used for cutting off the rope when the launching system reaches a preset launching position so as to launch the aircraft 3. Three positions of the aircraft 3 are provided with hoisting points for connecting ropes to fix the aircraft 3. Hanging points can be respectively arranged on the wingspans at the two sides of the aircraft 3, and the ropes are respectively connected with the wingspans at the two sides of the aircraft 3; while a suspension point is provided at the head of the vehicle 3 and a rope is connected to the head of the vehicle 3.

According to the near space aircraft launching system provided by the embodiment, the hanging points are arranged at the wingspan and the head parts at two sides of the aircraft 3, so that the system can adapt to the shape of the aircraft 3, and the hanging stability of the aircraft 3 is realized; the aircraft 3 is connected with the throwing frame 2 through ropes at each hanging point, and the specific posture of the aircraft 3 can be controlled and adjusted by adjusting the length of each rope, so that the requirement of the aircraft 3 at different throwing angles can be met, and the applicability and the use flexibility of the throwing system are improved; the cutter is arranged to cut the rope to realize throwing, and the rope throwing device is ingenious in design and convenient to control.

On the basis of the above embodiment, further, referring to fig. 2, the launch frame 2 includes a cross beam 21, a longitudinal beam 22, and a forward extending beam 23; the cross beam 21 is arranged along the wingspan direction of the aircraft 3, two ends of the cross beam 21 are respectively and vertically connected with a longitudinal beam 22, and the middle part of the cross beam 21 is vertically connected with a front extension beam 23; the hanging points on the wingspans of the two sides of the aircraft 3 are correspondingly connected with the two longitudinal beams 22, and the hanging point of the head of the aircraft 3 is connected with the front extension beam 23.

The present embodiment explains a specific structure of the dispensing shelf 2. The structure of the launch frame 2 should be such that it is easy to connect it to a suspension point on the aircraft 3 by means of a rope and that it is light. The putting frame 2 provided by the embodiment is mainly a beam structure. The cross-beams 21 may be arranged parallel to the span of the aircraft 3. The cross beam 21 is the main supporting part of the launch frame 2. The stringers 22 are intended to be connected to suspension points on the wingspan of the aircraft 3. The forward beam 23 is intended to be connected to a suspension point of the head of the aircraft 3. Two suspension point positions on the wingspans of the two sides of the aircraft 3 can be connected with the two longitudinal beams 22 in a one-to-one correspondence mode.

The putting frame 2 is designed to be a connected structure between the beam bodies, so that the weight of the putting frame 2 can be reduced as much as possible, and the requirement for hanging the aircraft 3 can be met. Further, the cross beam 21, the longitudinal beam 22 and the forward extending beam 23 can be truss structures, i.e. frame structures, so as to reduce the weight of the drop frame 2.

On the basis of the above-described embodiment, furthermore, the suspension points at each span of the aircraft 3 are connected to the launch frame 2 by means of two first cables 41. Through two first ropes 41 with throw in frame 2 and link to each other, can improve the firm stability of connection, and be convenient for adjust the gesture angle of aircraft 3. The suspension point of the head of the aircraft 3 is connected to the launch frame 2 by a second rope 42.

On the basis of the above embodiment, further, two first ropes 41 are connected to suspension points on the span of the aircraft 3 by means of third ropes; the first end of the first rope 41 connected with the aircraft 3 is provided with a hoisting ring 26; the third rope passes through the lifting rings 26 at the ends of the two first ropes 41 in sequence and then is connected with the aircraft 3, and a cutter is arranged on the third rope.

The two first ropes 41 are connected with the aircraft 3 through the third rope, a cutter can be arranged on the third rope, and the cutter only needs to cut the third rope, so that the aircraft 3 and the throwing frame 2 can be separated and thrown. After the third rope is cut, the third rope is separated from the two first ropes 41 along with the launching of the aircraft 3, so that the connection of the two first ropes 41 is released, the two first ropes 41 are separated from each other and released from the connection, and the phenomenon that the end parts of the third rope are connected together to form a ring shape to hook other settings in the environment can be avoided.

Further, a cutter is also provided on the second cord 42. The cutter may be arranged at the end of the line near the aircraft 3. Furthermore, the connection part of the throwing frame 2 and the rope is also provided with a hanging ring 26, which is convenient for connecting the rope.

In addition to the above embodiment, the second ends of the two first ropes 41 are correspondingly connected to the two ends of the longitudinal beam 22, and the second rope 42 is connected to one end of the front beam 23 away from the cross beam 21. The two first ropes 41 are crossed and arranged at an angle, so that the aircraft 3 can be connected more firmly and stably. Further, the length of the longitudinal beam 22 should be adapted to the distance between the second ends of the two first cords 41. The longitudinal beam 22 is long enough to provide the first rope 41 at both ends, and it is not necessary to provide an excessively long rope to reduce the weight.

In addition to the above embodiment, further, referring to fig. 2, the side member 22 is provided above the end portion of the cross member 21 and the middle portion of the side member 22 is connected to the cross member 21. That is, the longitudinal beams 22 are symmetrically arranged with respect to the cross beam 21, the bottom surface of the middle portion of the longitudinal beam 22 is connected to the top surface of the end portion of the cross beam 21, and the longitudinal beam 22 and the cross beam 21 are not located on the same plane. The longitudinal beam 22 is arranged above the cross beam 21, and the cross beam 21 can firmly and stably support the longitudinal beam 22; compared with the case that the longitudinal beam 22 is connected with the end part of the cross beam 21 and the longitudinal beam 22 and the cross beam 21 are positioned on the same plane, the requirement on the connection firmness of the connection part can be reduced.

The front extension beam 23 and the cross beam 21 are located on the same plane, and one end of the front extension beam 23 is connected with the cross beam 21. I.e. the front beam 23 is located at one side of the cross beam 21. The front beams 23 may be connected at the ends to the sides of the middle portion of the cross beam 21. The length of the front beam 23 is adapted to the position of the second rope 42.

On the basis of the above embodiment, further, referring to fig. 2, the middle portion of the longitudinal beam 22, the two ends of the transverse beam 21, the middle portion of the transverse beam 21 and one end of the front beam 23 are respectively provided with a connecting unit 24, referring to fig. 3, 4 and 5, the connecting unit 24 is provided with a fixed connecting element 25, and the longitudinal beam 22 and the transverse beam 21 and the front beam 23 are fixedly connected at the fixed connecting element 25.

The connecting elements 24 may likewise be truss structures, and with reference to fig. 4, the connecting elements 24 in the middle region of the stringers 22 may be part of the stringers 22, integrally formed with the stringers 22. Referring to fig. 3, the connection units 24 at the ends and in the middle of the beam 21 may also be part of the beam 21. Referring to fig. 5, the connection unit 24 of the end of the front beam 23 may be a part of the front beam 23. The connection unit 24 may be a frame structure having a frame.

Referring to fig. 4, the fixed connecting elements 25 may be provided only on the side of the longitudinal beam 22 where the connecting unit 24 is connected to the lateral beam 21, and referring to fig. 3, the fixed connecting elements 25 may be provided only on the side of the lateral beam 21 where the connecting unit 24 is connected to the longitudinal beam 22, and the fixed connecting elements 25 may be provided on the side of the lateral beam 21 where the connecting unit 24 is connected to the front beam 23. Referring to fig. 5, a fixed connection member 25 is provided at a side of the front beam 23 where the connection unit 24 is connected to the cross beam 21. The connection unit 24 of the longitudinal beam 22 can be detachably fixedly connected to the connection unit 24 of the transverse beam 21 and the connection unit 24 of the front beam 23 at a fixed connection element 25 by means of bolts.

The fixed connection members 25 may be connectors welded to the rims of the connection units 24, and the positions of the fixed connection members 25 on the two connected faces correspond one to one.

On the basis of the above embodiment, further, the head of the aircraft 3 is arranged downward, the center of gravity of the aircraft 3 is located right below the center of gravity of the launch frame 2, and the suspension points on the wingspans on both sides of the aircraft 3 are symmetrically arranged with respect to the aircraft 3. Is favorable for firmly and stably hoisting and connecting the aircraft 3. The longitudinal beams 22 on the two sides of the cross beam 21 can be symmetrically arranged with respect to the cross beam 21, so that the middle part of the cross beam 21 is the gravity center part of the putting-in frame 2, and the aircraft 3 can be stably hung conveniently.

On the basis of the above embodiment, further, the length of the cross beam 21 is adapted to the distance between the suspension points on the wingspans of the two sides of the aircraft 3; the length of the cross beam 21 does not need to be too long, and is adapted to the distance between the hanging points on the wingspans of the two sides of the aircraft 3, so that the aircraft 3 can be hung well. A safe distance is reserved between the launching frame 2 and the tail of the aircraft 3; so as to avoid collision between the tail of the aircraft 3 and the throwing frame 2.

Further, the floating platform may be at least one of a high altitude balloon, a super pressure balloon, and an airship. The cutter can be an initiating explosive device cutter, the initiating explosive device cutter is electrified, and the cutting rope is thrown to the aircraft 3. The rope may be a high horsepower rope. The throwing frame 2 is fixedly connected with a nacelle 1 of the floating platform.

On the basis of the foregoing embodiments, further, this embodiment provides a near space vehicle launching method based on the near space vehicle launching system described in any of the foregoing embodiments, and the launching method includes: connecting the aircraft 3 with the throwing frame 2 at a hoisting point through ropes, and adjusting the throwing angle of the aircraft 3 by adjusting the length of each rope; releasing the floating platform to drive the launching system of the near space aircraft 3 to lift to a launching area; the cutter is used for cutting the rope, and the aircraft 3 is thrown.

On the basis of the embodiment, further, a near space aircraft launching system can be used for launching a solar unmanned aerial vehicle with a large wingspan in a near space. The connection mode of the high-altitude balloon platform throwing frame 2 of the large-wingspan unmanned aerial vehicle, the unmanned aerial vehicle and the high-altitude balloon nacelle 1 is shown in figure 1. The throwing frame 2 and the high-altitude balloon pod 1 are in hard connection by adopting a metal piece 27, the metal piece 27 can be welded and connected on the frame in the middle part of the cross beam 21, and the pod is connected with the cross beam 21 at the position of the metal piece 27 through bolts and the like; the throwing frame 2 is flexibly connected with the large-span unmanned aerial vehicle through a throwing rope. 3 lifting points are arranged on the unmanned aerial vehicle, and the lifting points on two sides adopt a form that two lifting ropes are converged into one rope, namely two first ropes 41 are converged to a third rope; the middle lifting point adopts one lifting point. 5 ropes are adopted to connect the throwing frame 2 and the unmanned aerial vehicle lifting point.

According to unmanned aerial vehicle's the difference of input angle can realize through adjustment rope length, put into 2 designs of frame with unmanned aerial vehicle's focus and put under putting into 2 crossbeams 21 centers. The gravity center of the throwing frame 2 is designed at the gravity center position of the beam 21 of the throwing frame 2. Set up certain distance between unmanned aerial vehicle afterbody and the frame 2 of puting in, avoid unmanned aerial vehicle afterbody and the frame 2 of puting in bump in the high altitude balloon platform is provided and is flown.

The span of the throwing frame 2 along the wingspan direction of the unmanned aerial vehicle is consistent with the hanging point position of the unmanned aerial vehicle in the direction. According to unmanned aerial vehicle self design characteristics, the hoisting point generally sets up in the more solid position of unmanned aerial vehicle structure, for example the hoisting point on the span can be established near unmanned aerial vehicle's screw propulsion. Since the span of the launch frame 2 is large and the weight requirement of the adjacent space vehicle 3 is high, high requirements are put on the design of the launch frame 2. The putting frame 2 is composed of 4 truss girder structures and comprises two side longitudinal girders 22, a middle cross girder 21 and a middle front extension girder 23.

All the beams are in the form of trusses, the longitudinal beams 22 on the two sides span the two ends of the cross beam 21, and the middle front extension beam 23 and the cross beam 21 are in the same plane. The longitudinal beams 22 and the transverse beams 21 are each provided with a connecting unit 24 near the middle, the connecting units 24 can be provided in the form of a cube, and the transverse beams 21 of the connecting units 24 are provided with fixed connecting elements 25. The connection units 24 are provided in the middle and both ends of the cross member 21, and in theory, the respective faces of the connection units 24 may be provided with connections. The connecting elements are welded only to the surfaces of the respective connections.

One end of the middle front beam 23 is provided with a connecting unit 24. The rigidity of the whole structure is greatly improved by adopting a truss form for each beam, and the truss structure is suitable for a large-span putting frame 2 structure through simulation calculation verification. The truss girder structure can be not only provided with a square cross section, but also provided with a triangle or a square trapezoid and the like according to a specific form. In addition, the truss girder can also adopt a form of a gradual section. For example, the side member 22 may have a structure in which the cross section gradually decreases from the middle portion to both ends; the front beam 23 may have a structure in which the cross section gradually decreases from one end connected to the cross beam 21 to the other end.

In addition, a throwing connection point is arranged at a connection position corresponding to the lifting point rope, and a U-shaped ring connecting piece, namely a lifting ring 26, is arranged at each connection point, so that the lifting rope is convenient to replace. The span of the launch frame 2, i.e. the length of the cross beam 21, is about 4-6m, the transverse width, i.e. the length of the longitudinal beam 22, is about 2-4m, and the centre of gravity of the launch frame 2 is designed to be located in the centre of the structure. In addition, the putting frame 2 can be welded by steel materials under the condition that the weight of the high-altitude balloon platform is allowed, and a titanium alloy welding mode is selected for the working condition with higher weight requirement. The weight of the throwing frame 2 can be approximately equal to that of a total unmanned aerial vehicle 1/4 structure for throwing the unmanned aerial vehicles; the throwing frame 2 is reliable in structure and can completely fulfill the task of empty throwing of the high-altitude balloon.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents, improvements, etc. within the spirit and scope of the present invention.

Claims

1. A near space vehicle launch system, comprising: a throwing frame; the throwing frame is fixedly connected with the floating platform, hanging points are respectively arranged on wingspans and heads on two sides of the aircraft, the aircraft is connected with the throwing frame through a rope at the hanging points, the length of the rope is set according to the throwing angle of the aircraft, and a cutter is arranged on the rope;

the putting frame comprises a cross beam, a longitudinal beam and a front extension beam; the cross beam, the longitudinal beam and the front extending beam are all truss structures; the cross beam is arranged along the wingspan direction of the aircraft, the two ends of the cross beam are respectively and vertically connected with the longitudinal beam, and the middle part of the cross beam is vertically connected with the front extension beam; hanging points on wingspans on two sides of the aircraft are correspondingly connected with the two longitudinal beams, and hanging points on the head of the aircraft are connected with the forward extending beam;

and the suspension point on each wingspan of the aircraft is connected with the launching frame through two first ropes, and the suspension point on the head of the aircraft is connected with the launching frame through one second rope.

2. The near space vehicle delivery system of claim 1, wherein the two first cables are connected to suspension points on the span of the aircraft by third cables; a lifting ring is arranged at the first end of the first rope connected with the aircraft; the third rope sequentially penetrates through the lifting rings at the end parts of the two first ropes and then is connected with the aircraft, and the cutter is arranged on the third rope.

3. The close-space vehicle delivery system of claim 1, wherein second ends of the two first ropes are connected to ends of the longitudinal beams, and the second rope is connected to an end of the front beam, which is far away from the cross beam.

4. A launch system for a near space vehicle according to any of claims 1 to 3, characterised in that said longitudinal beam is arranged above the ends of said transverse beam and the middle of said longitudinal beam is connected to said transverse beam; the front extension beam and the cross beam are located on the same plane, and one end of the front extension beam is connected with the cross beam.

5. The launch system for a near space vehicle as defined in claim 4 wherein said longitudinal beam, said cross beam and said nose beam are each provided with a connecting element at a central portion thereof, said connecting elements being provided with a fixed connecting element, said longitudinal beam and said cross beam and said nose beam being fixedly connected at said fixed connecting element.

6. The close-proximity spacecraft launch system of claim 1 wherein the nose of the aircraft is oriented downward, the center of gravity of the aircraft is located directly below the center of gravity of the launch frame, and the suspension points on the two side spans of the aircraft are symmetrically disposed about the aircraft.

7. The close-proximity space vehicle delivery system of claim 1, wherein the beam has a length that is compatible with a distance between suspension points on both side spans of the vehicle; and a safe distance is reserved between the launching frame and the tail of the aircraft.

8. A method for delivering a spacecraft to a near space vehicle based on the system for delivering a spacecraft of any one of claims 1 to 7, comprising:

connecting the aircraft with the throwing frame at a hoisting point through ropes, and adjusting the throwing angle of the aircraft by adjusting the length of each rope;

releasing the floating platform to drive the launching system of the near space aircraft to lift to a launching area;

and cutting the rope by using a cutter, and throwing the aircraft.