阅读说明：本技术 一种用于垂直起降飞行器的发射平台 (Launching platform for vertical take-off and landing aircraft ) 是由 孙志超 王英诚 于 2021-08-17 设计创作，主要内容包括：本申请涉及航空航天领域,尤其涉及一种用于垂直起降飞行器的发射平台,包括：下框架、转动平台和电推杆；下框架的上端中部与转动平台的中部铰接,并且下框架的上端具有向下凹的旋转容纳空间,容纳以铰接点为转动中心转动的转动平台；在转动平台的上表面上固定有多个面板,每个面板的中部开设有吸力孔,吸力孔内设置有吸引固定垂直起降飞行器的吸引装置,并且吸引装置的上表面与面板的上表面齐平或者吸引装置的上表面低于面板的上表面；转动平台的下表面与电推杆的上端铰接,电推杆的下端与下框架的下端铰接,并且电推杆位于旋转容纳空间内,以推动转动平台转动。本申请可以提高操作人员点火时的安全性,提高垂直起降飞行器起飞时的可靠性。(The application relates to the aerospace field, especially relates to a launch platform for VTOL aircraft, includes: the lower frame, the rotating platform and the electric push rod; the middle part of the upper end of the lower frame is hinged with the middle part of the rotating platform, and the upper end of the lower frame is provided with a downward concave rotating accommodating space for accommodating the rotating platform which rotates by taking the hinged point as a rotating center; a plurality of panels are fixed on the upper surface of the rotating platform, a suction hole is formed in the middle of each panel, a suction device for sucking and fixing the vertical take-off and landing aircraft is arranged in each suction hole, and the upper surface of each suction device is flush with the upper surface of the corresponding panel or the upper surface of each suction device is lower than the upper surface of the corresponding panel; the lower surface of the rotating platform is hinged with the upper end of the electric push rod, the lower end of the electric push rod is hinged with the lower end of the lower frame, and the electric push rod is located in the rotating containing space to push the rotating platform to rotate. The application can improve the safety of the operator during ignition and improve the reliability of the vertical take-off and landing aircraft during take-off.)

1. A launch platform for a VTOL aerial vehicle, comprising: the lower frame, the rotating platform and the electric push rod;

the middle part of the upper end of the lower frame is hinged with the middle part of the rotating platform, and the upper end of the lower frame is provided with a downward concave rotating accommodating space for accommodating the rotating platform which rotates by taking the hinged point as a rotating center;

a plurality of panels are fixed on the upper surface of the rotating platform, a suction hole is formed in the middle of each panel, a suction device for sucking and fixing the vertical take-off and landing aircraft is arranged in each suction hole, and the upper surface of each suction device is flush with the upper surface of the corresponding panel or the upper surface of each suction device is lower than the upper surface of the corresponding panel;

the lower surface of the rotating platform is hinged with the upper end of the electric push rod, the lower end of the electric push rod is hinged with the lower end of the lower frame, and the electric push rod is located in the rotating containing space to push the rotating platform to rotate.

2. The launch platform for a VTOL aerial vehicle of claim 1, wherein the lower frame comprises: the top corner of the rectangular top frame and the corresponding top corner of the rectangular bottom frame are connected with vertically extending stand columns.

3. The launch platform for a VTOL aerial vehicle of claim 2, wherein a reinforced short middle frame is connected to the middle of the two long rims of the rectangular top frame, and a plurality of reinforced short middle frames are connected between the two long rims of the rectangular bottom frame.

4. The launch platform for a VTOL aerial vehicle of claim 2 or 3, wherein a caster is provided downwards at each top corner of the rectangular base frame.

5. The launch platform for a VTOL aerial vehicle of claim 4, wherein the rectangular bottom frame is further provided with at least four vertically movable ground feet downwards.

6. The launch platform for a VTOL aerial vehicle of claim 2 or 3, wherein the rotating platform is a rectangular frame with two short reinforced middle frames connected between two long rims and two second long reinforced middle frames connected between two short reinforced middle frames.

7. The launch platform for a VTOL aerial vehicle of claim 6, wherein a panel is fixed between each reinforced short middle frame of the rotating platform and the upper surface of the short side frame adjacent thereto, and a panel is fixed between each reinforced sub-long middle frame of the rotating platform and the upper surface of the long side frame adjacent thereto.

8. The launching platform for a VTOL aerial vehicle of claim 6, wherein two bearings are coaxially fixed in the middle of two opposite side frames of the rectangular top frame; two bearings are coaxially fixed in the middle of two opposite frames of the rotating platform; and each bearing on the rectangular top frame is connected with a corresponding bearing on the rotating platform through a rotating shaft so as to realize that the middle part of the upper end of the lower frame is hinged with the middle part of the rotating platform.

9. The launch platform for a VTOL aerial vehicle of any of claims 1-3, wherein the attraction device is an electromagnet.

10. The launch platform for a VTOL core machine according to any of claims 1-3, wherein the lower end of the electric push rod is hinged to the upper surface of the rectangular bottom frame so that the electric push rod is located in the rotation containing space.

Technical Field

The application relates to the field of aerospace, in particular to a launching platform for a vertical take-off and landing aircraft.

Background

With the continuous development of the aerospace industry, people are continuously exploring the recoverable technology of the vertical aircraft, and the corresponding launching auxiliary equipment of the vertical take-off and landing aircraft is also developed.

At present, a vertical take-off and landing aircraft usually uses a small turbojet engine which requires ignition in a horizontal or 45-degree inclination angle state, so that an operator is required to firstly incline the vertical take-off and landing aircraft, and then the vertical take-off and landing aircraft is vertically placed on a working position after ignition, and therefore, high temperature, high noise and the like exist in the ignition process, and the vertical take-off and landing aircraft is not friendly to the environment of the operator and even has certain danger to the operator.

In addition, the structure of the launching auxiliary equipment of the existing VTOL aircraft is complex, the locking devices mostly adopt locking claws, hooks and the like, and the locking devices such as the locking claws, the hooks and the like cause uneven platform surfaces after unlocking, so that the locking devices are easy to scratch and rub the VTOL aircraft, the takeoff inclination of the VTOL aircraft is caused, and even the takeoff inclination of the VTOL aircraft fails, and the reliability is low.

Therefore, how to improve the safety of the operator in ignition and improve the reliability of the vertical take-off and landing aircraft in takeoff is a technical problem to be solved by those skilled in the art at present.

Disclosure of Invention

The application provides a launching platform for VTOL aircraft to improve operating personnel security when igniting, reliability when improving VTOL aircraft and taking off. In order to solve the technical problem, the application provides the following technical scheme:

a launch platform for a VTOL aerial vehicle, comprising: the lower frame, the rotating platform and the electric push rod; the middle part of the upper end of the lower frame is hinged with the middle part of the rotating platform, and the upper end of the lower frame is provided with a downward concave rotating accommodating space for accommodating the rotating platform which rotates by taking the hinged point as a rotating center; a plurality of panels are fixed on the upper surface of the rotating platform, a suction hole is formed in the middle of each panel, a suction device for sucking and fixing the vertical take-off and landing aircraft is arranged in each suction hole, and the upper surface of each suction device is flush with the upper surface of the corresponding panel or the upper surface of each suction device is lower than the upper surface of the corresponding panel; the lower surface of the rotating platform is hinged with the upper end of the electric push rod, the lower end of the electric push rod is hinged with the lower end of the lower frame, and the electric push rod is located in the rotating containing space to push the rotating platform to rotate.

The launching platform for a vtol aircraft as described above, wherein preferably the lower frame comprises: the top corner of the rectangular top frame and the corresponding top corner of the rectangular bottom frame are connected with vertically extending stand columns.

The launching platform for the VTOL aircraft as described above, wherein preferably, the middle parts of the two long frames of the rectangular top frame are connected with one reinforced short middle frame, and a plurality of reinforced short middle frames are connected between the two long frames of the rectangular bottom frame.

The launching platform for a VTOL aerial vehicle as described above, wherein preferably, a caster is provided downward at each top corner of the rectangular underframe.

The launching platform for the VTOL aerial vehicle as described above, wherein preferably, the rectangular bottom frame is further provided with at least four feet which can move up and down.

The launching platform for the VTOL aircraft as described above, wherein, preferably, the rotating platform is a rectangular frame, two reinforced short middle frames are connected between two long frames of the rotating platform, and two reinforced secondary long middle frames are connected between two reinforced short middle frames.

The launching platform for the VTOL aerial vehicle as described above, wherein preferably, a panel is fixed between each reinforced short middle frame of the rotating platform and the upper surface of the short side frame adjacent to the reinforced short middle frame, and a panel is fixed between each reinforced sub-long middle frame of the rotating platform and the upper surface of the long side frame adjacent to the reinforced sub-long middle frame.

The launching platform for the VTOL aircraft is characterized in that two bearings are coaxially fixed in the middle parts of two opposite side frames of the rectangular top frame; two bearings are coaxially fixed in the middle of two opposite frames of the rotating platform; and each bearing on the rectangular top frame is connected with a corresponding bearing on the rotating platform through a rotating shaft so as to realize that the middle part of the upper end of the lower frame is hinged with the middle part of the rotating platform.

The launch platform for a VTOL aerial vehicle as described above, wherein the attraction means is preferably an electromagnet.

The launching platform for a VTOL core machine as described above, wherein preferably the lower end of the electric push rod is hinged with the upper surface of the rectangular bottom frame so that the electric push rod is located in the rotation receiving space.

Compared with the background technology, the launching platform for the vertical take-off and landing aircraft provided by the invention can improve the ignition safety of operators and avoid scraping the vertical take-off and landing aircraft.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.

FIG. 1 is a diagram of a firing state of a launch platform for a VTOL aircraft provided by an embodiment of the present application;

FIG. 2 is a perspective view of a launch platform for a VTOL aerial vehicle provided by an embodiment of the present application;

FIG. 3 is a front view of a launch platform for a VTOL aerial vehicle provided by an embodiment of the present application.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. In addition, spatial relationship terms such as "upper", "above", "lower", "below", and the like are used for convenience of description to explain a positional relationship between two components. The embodiments described below with reference to the drawings are illustrative only and should not be construed as limiting the invention.

Referring to fig. 1 to 3, the present application provides a launching platform for a vertical take-off and landing aircraft, comprising: a lower frame 110, a rotary platform 120 and an electric push rod 130.

The middle portion of the upper end of the lower frame 110 is hinged to the middle portion of the rotating platform 120, which is the middle position or a position close to the middle position, but not only the middle position, and the upper end of the lower frame 110 has a downward-concave rotation accommodating space, so as to accommodate the rotating platform 120 in any state rotating around the hinge point as a rotation center.

The lower frame 110 is a rectangular parallelepiped frame, preferably a rectangular parallelepiped frame made of an aluminum profile, and may be a rectangular parallelepiped frame made of an aluminum alloy square tube. Specifically, the lower frame 110 includes: rectangular top frame 111 and rectangular underframe 112, the apex angle department of rectangular top frame 111 and the corresponding apex angle department of rectangular underframe 112 are connected with vertical extension's stand 113 to form the underframe 110 that has the frame format, and then guaranteed that underframe 110 has the rotatory accommodation space who holds rotary platform 120 under rotatory to the arbitrary state.

On the basis, in order to ensure the bearing performance of the lower frame 110, a vertically extending upright column 113 is further connected between the long frame of the rectangular top frame 111 and the corresponding long frame of the rectangular bottom frame 112, and a vertically extending upright column 113 is connected between each long frame of the rectangular top frame 111 and the corresponding long frame of the rectangular bottom frame 112; the middle parts of two long frames of the rectangular top frame 111 are connected with a reinforced short middle frame; a plurality of reinforcing short middle frames are connected between the two long side frames of the rectangular bottom frame 112, and preferably two reinforcing short middle frames are connected, on the basis, a plurality of reinforcing long middle frames are connected between the two short side frames of the rectangular bottom frame 112, and preferably two reinforcing long middle frames are connected.

In addition, every apex angle department of rectangle underframe 112 all is provided with truckle 140 downwards to convenient the removal is used for VTOL aircraft's transmission platform, of course can also set up truckle 140 in other positions of rectangle underframe 120, as long as can satisfy the effect that this application implementation will reach. At least four feet 150 are further downwardly disposed on the rectangular bottom frame 112, and preferably two feet 150 are disposed on each long side frame of the rectangular bottom frame 112 in this application, so that when the launching platform for the VTOL aircraft is not moved, the feet 150 can downwardly movably support the whole launching platform for the VTOL aircraft, and lock the position, and when the launching platform for the VTOL aircraft is moved, the feet 150 upwardly move to ensure that the casters 140 land and support the whole launching platform for the VTOL aircraft. Preferably, the ground feet 150 are hand-operated ground feet, that is, the ground feet are in threaded connection with the rectangular bottom frame 112, so that the ground feet 150 can move upwards or downwards relative to the rectangular bottom frame 112 through the hand-operated mode. In addition, a cushion rubber pad is further disposed on the rectangular bottom frame 112 for buffering at the end of the stroke, so as to improve the stability.

The rotary platform 120 is a rectangular frame, preferably a rectangular frame made of aluminum section, and may be a rectangular frame made of aluminum alloy square tubes. Specifically, in order to ensure the bearing capacity of the rotary platform 120 and facilitate the safety of other components, two reinforcing short middle frames are connected between two long frames of the rotary platform 120, and two reinforcing secondary long middle frames are connected between the two reinforcing short middle frames.

A plurality of panels 121 are fixed on the upper surface of the rotary platform 120, and a suction hole is opened in the middle of each panel 121. Preferably, 4 panels 121 are fixed on the upper surface of the rotating platform 120, specifically, one panel 121 is fixed between each reinforced short middle frame of the rotating platform 120 and the upper surface of the short side frame adjacent to the reinforced short middle frame, and one panel 121 is fixed between each reinforced sub-long middle frame of the rotating platform 120 and the upper surface of the long side frame adjacent to the reinforced sub-long middle frame. Preferably, the panel 121 has a through hole penetrating up and down, the upper surface of the rotating platform 120 has a through hole penetrating down, and the bolt passes through the through hole of the panel 121 and the through hole of the rotating platform 120 to be connected with the nut. In order to ensure that the upper surface of the panel 121 is flush, the through hole formed in the panel 121 is a counter bore, so that the head of the bolt is sunk into the counter bore.

An attraction device for attracting and fixing the VTOL aerial vehicle 210 is arranged in the attraction hole of the panel 121, in particular to a support leg for attracting and fixing the VTOL aerial vehicle 210, the upper surface of the attraction device is flush with the upper surface of the panel 121 or the upper surface of the attraction device is lower than the upper surface of the panel 121, so that after the attraction device unlocks the VTOL aerial vehicle 210, the surface of the panel 121 is flat, even the surface of a launching platform for the VTOL aerial vehicle is flat, the scratch between the convex locking device and the VTOL aerial vehicle is avoided, and the take-off effect of the VTOL aerial vehicle 210 is ensured. In addition, the suction device locks the VTOL aerial vehicle 210 only by suction force, so the launching platform for the VTOL aerial vehicle of the embodiment of the application has a simpler structure.

On the basis, the attraction device can be a magnet, and in the application, the attraction device is preferably an electromagnet, and the locking/unlocking of the VTOL aerial vehicle 210 is realized by electrifying/powering off the electromagnet.

In addition, two bearings are coaxially fixed in the middle of two opposite side frames of the rectangular top frame 111; two bearings are coaxially fixed in the middle of two opposite frames of the rotating platform 120; and each bearing on the rectangular top frame 111 is connected with a corresponding bearing on the rotating platform 120 through a rotating shaft, so that the middle part of the upper end of the lower frame 110 is hinged with the middle part of the rotating platform 120. Preferably, the bearing is a bearing with a seat, and the bearing is fixedly connected with the rectangular top frame 111 and the rotating platform 120 through a base of the bearing with the seat.

Specifically, a bearing is fixed to the middle of each long frame of the rectangular top frame 111, and a bearing is fixed to the middle of each long frame of the rotating platform 120. Preferably, a bearing is fixed at a position near one of the short frames in the middle of each long frame of the rectangular top frame 111, so that the bearing is offset from the vertical column between the rectangular top frame 111 and the rectangular bottom frame 112.

In addition, the lower surface of the rotary platform 120 is hinged to the upper end of the electric push rod 130, the lower end of the electric push rod 130 is hinged to the lower end of the lower frame 110, the electric push rod 130 is located in the rotary accommodating space, the rotary platform 120 is pushed to rotate by taking a hinge point as a rotation center through the extension and the shortening of the electric push rod 130, and then the rotary platform is guaranteed to have a 45-degree included angle with a horizontal plane, 0-degree included angle or other included angles, the vertical take-off and landing aircraft which is in a tilting state after ignition is prevented from being adjusted to a horizontal working position, so that the operation of operators in unfriendly environments such as high temperature and high noise is avoided, the safety is improved, and the emission reliability is improved. Specifically, the lower end of the electric push rod 130 is hinged to the upper surface of the rectangular bottom frame 112, so as to ensure that the electric push rod 130 is located in the rotary accommodating space.

On the basis of the above, in the present application, it is preferable to set the hinge point between the lower end of the electric push rod 130 and the rectangular bottom frame 112 to be adjustable, that is: the lower end of the electric push rod 130 may be hinged to a predetermined range of the rectangular bottom frame 112, so as to eliminate installation errors and to make the horizontal position of the rotary platform 120 more accurate.

When the launching platform for the VTOL aerial vehicle provided by the present application is used, the VTOL aerial vehicle is horizontally placed on the rotating platform 120, and the legs of the VTOL aerial vehicle 210 are positioned at the suction holes of the panel 121 of the rotating platform 120, so that the suction device attracts and fixes (the electromagnet is electrified to attract) the VTOL aerial vehicle 210. Then, the rotating platform 120 is automatically turned to an inclined state by the extension of the electric push rod 130, and after the engine of the vertical take-off and landing aircraft 210 is ignited, the rotating platform 120 is automatically restored to a horizontal state by the shortening of the electric push rod 130. Then, the attraction means cancels the attraction force release (electromagnet power-off release) of the VTOL aerial vehicle 210, and the VTOL aerial vehicle 210 can take off freely.

The whole ignition process of the launching platform for the vertical take-off and landing aircraft has high automation degree, is safe and reliable, and greatly improves the operation safety of the vertical take-off and landing aircraft. The lower frame and the rotating platform are built by using aluminum profiles, the structure is simple, and the economical efficiency is good. And the attraction device (electromagnet) is used for locking and releasing the VTOL aircraft, the structure is simple, the effect is good, the problems of complex structural mechanisms, more parts, uneven surfaces and the like of hooks, locking claws and the like are solved, and the situation that the VTOL aircraft is scratched and rubbed with a launching platform during takeoff can be effectively prevented.

It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.