阅读说明：本技术 一种无人机用起落架减震控制系统及方法 (System and method for damping control of landing frame for unmanned aerial vehicle ) 是由 董永武 邓涛 于 2020-05-07 设计创作，主要内容包括：本发明属于无人机配件技术领域,公开了一种无人机用起落架减震控制系统及方法,两个斜撑中部通过转轴转动连接；通孔通过销轴与连接板转动连接,连接板一侧固定设置有内杆,内杆外侧套接有外杆,外杆上侧一体化设置有卡环,外杆下侧通过焊接有第一支架,第一支架两端下部设置有伸缩支腿,伸缩支腿下部设置有第二支架；伸缩支腿设置有外筒,外筒内部滑动连接有内筒,外筒底部和内筒上部均设置有固定块,固定块之间设置有弹簧。本发明通过设置的内杆、外杆和斜撑,能够根据无人机起落架的宽度进行调节,具有更好的适用性；且本发明通过设置的第二支架和伸缩支腿能够起到双重缓冲减震的作用,防止无人机在降落时受到较大的冲击。(The invention belongs to the technical field of unmanned aerial vehicle accessories and discloses a system and a method for controlling shock absorption of a landing frame for an unmanned aerial vehicle, wherein the middle parts of two inclined struts are rotationally connected through a rotating shaft; the through hole is rotatably connected with the connecting plate through a pin shaft, an inner rod is fixedly arranged on one side of the connecting plate, an outer rod is sleeved on the outer side of the inner rod, a snap ring is integrally arranged on the upper side of the outer rod, a first support is welded on the lower side of the outer rod, telescopic support legs are arranged on the lower portions of two ends of the first support, and a second support is arranged on the lower portions of the telescopic support legs; the telescopic support leg is provided with an outer barrel, an inner barrel is connected to the inner portion of the outer barrel in a sliding mode, fixed blocks are arranged at the bottom of the outer barrel and on the upper portion of the inner barrel, and springs are arranged between the fixed blocks. According to the invention, the inner rod, the outer rod and the inclined strut are arranged, so that the adjustment can be carried out according to the width of the landing gear of the unmanned aerial vehicle, and the unmanned aerial vehicle has better applicability; in addition, the second support and the telescopic support legs can play a role in double buffering and shock absorption, so that the unmanned aerial vehicle is prevented from being impacted greatly when being landed.)

1. The landing gear damping control method for the unmanned aerial vehicle is characterized in that the lower limit value of the induction of a six-dimensional sensor and a horizontal sensor is reached when the unmanned aerial vehicle lands; the six-dimensional sensor and the horizontal sensor are used for collecting the angle change and the horizontal inclination angle of the unmanned aerial vehicle; corresponding numerical values are set in the processor through setting different angles and the running strength of the shock absorber when the angle is inclined; collecting the acceleration of the unmanned aerial vehicle through an acceleration sensor, starting an enhanced signal for the normal condition, and starting a weakened signal for the negative condition; the shock absorber receives the signal of the shock absorber, the strength of the shock absorber is improved on the corresponding numerical value by enhancing the signal, and the strength of the shock absorber is reduced on the corresponding numerical value by weakening the signal;

the width of the unmanned aerial vehicle base is adjusted to adjust the angle of the inclined strut, so that the width of the two clamping rings is consistent with that of the unmanned aerial vehicle base, and the undercarriage of the unmanned aerial vehicle is placed in the clamping rings; when the unmanned aerial vehicle lands, the second support and the telescopic support legs play a role in double buffering and shock absorption;

the processor carries out nonlinear transformation on the acquired signals of the six-dimensional sensor and the horizontal sensor and calculates the generalized cyclic autocorrelation function of the acquired signals; extracting a specific cycle frequency section of the generalized cycle autocorrelation function, and finishing useful symbol length estimation of the acquired signal by searching a spectrum peak of the specific cycle frequency section;

the generalized cyclic autocorrelation functionIs defined as:

where upsilon represents the cyclic frequency, m represents the time delay, and N_rIndicates the signal length, "+" indicates the conjugate operation, f [ r (n)]The expression is a nonlinear transformation:

|r(n)|≠0；

wherein, r (n) is a received signal;

extracting a specific cycle frequency section of the generalized cyclic autocorrelation function, and finishing useful symbol length estimation of the acquired signal by searching a spectrum peak of the specific cycle frequency section: estimating useful symbol duration is estimatingIs the maximum estimated value of m For the duration of the useful symbol or symbols,is the useful symbol length N_uM ∈ [2K ]_min,2K_max]，K_minTo the smallest number of subcarriers possible, K_maxIs the maximum number of subcarriers possible, and the useful symbol duration estimate is:

the processor processes the probability density function of the simplified constellation diagram by utilizing the multi-radius subtraction clustering and the self-correcting clustering effectiveness function, and identifies the modulation order of the acquired signal; the method for estimating the probability density function of the constellation diagram by the grid method comprises the following steps: according to the received constellation point r_iHas the coordinates of (r)_iI,r_iQ) Constructing a square grid, the boundaries of which are determined by the maximum absolute values of the horizontal and vertical coordinates, r_I,r_Q＝±max(r_iI,r_iQ) (ii) a Defining mesh density Meshmum as the number of meshes divided in a single direction, dividing a mesh graph of Meshmum and Meshmum in a determined area, wherein the size of each mesh isEquivalent grid to xOy coordinate plane, where (x)_p,y_p) For the center of each grid, the function value isAfter the discrete points are serialized, an estimated probability density function is obtained

2. The method for controlling shock absorption of an undercarriage for an unmanned aerial vehicle according to claim 1, wherein the processor extracts the acquisition symbol of the first path by acquiring multiple paths, and estimates the time domain initial synchronization parameters of the received signal: taking N by using the cyclic prefix characteristic of the time domain symbol in the DVB-T signal_CPA sampling value and N_FFTThen N_CPCarrying out correlation operation on the sampling values to obtain correlation peak values, and obtaining symbol starting sampling values which are initial timing synchronous values and initial estimation of the fractional carrier frequency; according to the initial estimation result of the fractional carrier frequency, carrying out frequency compensation on the sampling signal; according to the initial symbol timing synchronization estimation result, a symbol start sampling value is obtained, and fast Fourier transform is carried out to obtain a corresponding frequency signal; detecting and acquiring a scattered pilot sequence of a frequency domain signal: the scattered pilot frequency sequence of the current symbol is obtained by detecting the correlation between the scattered pilot frequency signal of the received signal and a plurality of different scattered pilot frequency sequences locally generated by a receiver; and detecting and compensating the integral multiple carrier frequency offset estimation of the OFDM symbols in the received signal.

3. The method for controlling shock absorption of an undercarriage for an unmanned aerial vehicle of claim 1 wherein the fractional low order fuzzy function of the processor digitally modulated signal x (t) is represented as:

wherein tau is time delay shift, f is Doppler shift, 0 < a, b < α/2, x^*(t) represents the conjugate of x (t); when x (t) is a real signal, x (t)^＜p＞＝|x(t)|^＜p＞sgn (x (t)); when x (t) is a complex signal, [ x (t)]^＜p＞＝|x(t)|^p-1x^*(t)。

4. A landing gear shock absorption control system for an unmanned aerial vehicle, which operates the landing gear shock absorption control method for an unmanned aerial vehicle according to any one of claims 1 to 3, wherein the landing gear shock absorption control system for an unmanned aerial vehicle comprises: the device comprises a damping module, an induction module and a regulation and control module;

the shock absorption module comprises a shock absorber and an electromagnetic induction switch which are connected in sequence; the sensing module comprises a six-dimensional sensor, an acceleration sensor and a horizontal sensor; the induction module is connected with the regulation module; the regulation and control module comprises a signal transmission line and a processor; the processor is connected with the acceleration sensor through a signal transmission line and is connected with the electromagnetic induction switch through another signal transmission line; the six-dimensional sensor and the horizontal sensor are both provided with a lower induction limit value and an upper induction limit value; the acceleration sensor is connected with a signal enhancing channel and a signal weakening channel, the shock absorber comprises an outer box, a piston rod is arranged in the outer box, and a damper assembly and a shock pad are arranged on the piston rod in the outer box; one end of the telescopic supporting leg is provided with an adjuster; the regulator is connected with the electromagnetic induction switch.

5. The landing gear shock absorption control system for unmanned aerial vehicle of claim 4, wherein the shock absorption module is provided with:

bracing;

the middle parts of the two inclined struts are rotatably connected through a rotating shaft, and through holes are formed in the two ends of each inclined strut; the through-hole rotates with the connecting plate through the round pin axle to be connected, the fixed interior pole that is provided with in connecting plate one side, the outer pole has been cup jointed in the interior pole outside, the integration of outer pole upside is provided with the snap ring, the outer pole downside is through welding first support, first support both ends lower part is provided with flexible landing leg, flexible landing leg lower part is provided with the second support.

6. The shock absorption control system for the landing gear of the unmanned aerial vehicle as claimed in claim 5, wherein the connecting plate is fixed inside one end of the inner rod, and is provided with an upper connecting plate and a lower connecting plate, a through hole is formed in the middle of the two connecting plates, and the two connecting plates are rotatably connected with the inclined strut through a pin shaft.

7. The landing gear shock absorption control system for unmanned aerial vehicle as claimed in claim 5, wherein the telescopic leg is provided with an outer cylinder, an inner cylinder is slidably connected inside the outer cylinder, fixing blocks are provided on the bottom of the outer cylinder and the upper part of the inner cylinder, and a spring is provided between the fixing blocks.

8. The shock absorption control system for the landing gear of the unmanned aerial vehicle as claimed in claim 5, wherein the second support is made of rubber, and the bottom of the second support is provided with anti-skid lines.

9. The shock absorption control system for the landing gear of the unmanned aerial vehicle as claimed in claim 5, wherein the snap ring is cylindrical, and an opening is formed at an upper portion of the snap ring.

10. The landing gear shock absorption control system for unmanned aerial vehicle of claim 5, wherein the first support and the second support are arranged in parallel, and the telescopic leg is perpendicular to the first support and the second support.

Technical Field

The invention belongs to the technical field of unmanned aerial vehicle accessories, and particularly relates to a shock absorption control system and method for a landing frame of an unmanned aerial vehicle.

Background

Currently, the unmanned aerial vehicle is an unmanned aerial vehicle mainly controlled by radio remote control or self programs. The successful development and the application of the method reveal a curtain of non-contact warfare which takes a remote attack type intelligent weapon and an information weapon as the main parts. Compared with manned unmanned aerial vehicles, the unmanned aerial vehicle has the advantages of small volume, low manufacturing cost, convenient use and the like, and is favored by people. The undercarriage is the important component of unmanned aerial vehicle, and it mainly is taking off the in-process at unmanned aerial vehicle and plays the supporting role to unmanned aerial vehicle, can play certain cushioning effect when unmanned aerial vehicle descends. The existing unmanned aerial vehicle undercarriage can support the unmanned aerial vehicle body to complete takeoff or landing. However, the existing landing gear of the unmanned aerial vehicle is weak in structural strength and impact-resistant, and in the landing process of the unmanned aerial vehicle, under the influence of the inertia of a machine body, the landing gear bears large impact force, so that the loosening of internal parts is easily caused, and the normal work of the unmanned aerial vehicle is further influenced; and current undercarriage width is fixed, can only adapt to the unmanned aerial vehicle of specific width, and the suitability is relatively poor.

Through the above analysis, the problems and defects of the prior art are as follows:

(1) the existing landing gear of the unmanned aerial vehicle is weak in structural strength and impact-intolerant, and the landing gear bears large impact force under the effect of inertia of a machine body when the unmanned aerial vehicle lands, so that the loosening of internal parts is easily caused, and the normal work of the unmanned aerial vehicle is influenced.

(2) The existing undercarriage is fixed in width, can only adapt to the unmanned aerial vehicle with a specific width, and is poor in applicability.

Disclosure of Invention

Aiming at the problems in the prior art, the invention provides a system and a method for controlling shock absorption of a landing frame for an unmanned aerial vehicle.

The invention is realized in such a way that the landing gear damping control method for the unmanned aerial vehicle is used, and the landing gear damping control method for the unmanned aerial vehicle is used for ensuring that the lower limit value of the induction of a six-dimensional sensor and a horizontal inductor is reached when the unmanned aerial vehicle lands; the six-dimensional sensor and the horizontal sensor are used for collecting the angle change and the horizontal inclination angle of the unmanned aerial vehicle; corresponding numerical values are set in the processor through setting different angles and the running strength of the shock absorber when the angle is inclined; collecting the acceleration of the unmanned aerial vehicle through an acceleration sensor, starting an enhanced signal for the normal condition, and starting a weakened signal for the negative condition; the shock absorber receives the signal of the shock absorber, the strength of the shock absorber is improved on the corresponding numerical value by enhancing the signal, and the strength of the shock absorber is reduced on the corresponding numerical value by weakening the signal;

the width of the unmanned aerial vehicle base is adjusted to adjust the angle of the inclined strut, so that the width of the two clamping rings is consistent with that of the unmanned aerial vehicle base, and the undercarriage of the unmanned aerial vehicle is placed in the clamping rings; when the unmanned aerial vehicle lands, the second support and the telescopic support legs play a role in double buffering and shock absorption;

the processor carries out nonlinear transformation on the acquired signals of the six-dimensional sensor and the horizontal sensor and calculates the generalized cyclic autocorrelation function of the acquired signals; extracting a specific cycle frequency section of the generalized cycle autocorrelation function, and finishing useful symbol length estimation of the acquired signal by searching a spectrum peak of the specific cycle frequency section;

the generalized cyclic autocorrelation functionIs defined as:

where upsilon represents the cyclic frequency, m represents the time delay, and N_rIndicates the signal length, "+" indicates the conjugate operation, f [ r (n)]The expression is a nonlinear transformation:

wherein, r (n) is a received signal;

extracting a specific cycle frequency section of the generalized cyclic autocorrelation function, and finishing useful symbol length estimation of the acquired signal by searching a spectrum peak of the specific cycle frequency section: estimating useful symbol duration is estimatingIs the maximum estimated value of mFor holding useful symbolsThe duration of the time period is longer,is the useful symbol length N_uM ∈ [2K ]_min,2K_max]，K_minTo the smallest number of subcarriers possible, K_maxIs the maximum number of subcarriers possible, and the useful symbol duration estimate is:

the processor processes the probability density function of the simplified constellation diagram by utilizing the multi-radius subtraction clustering and the self-correcting clustering effectiveness function, and identifies the modulation order of the acquired signal; the method for estimating the probability density function of the constellation diagram by the grid method comprises the following steps: according to the received constellation point r_iHas the coordinates of (r)_iI,r_iQ) Constructing a square grid, the boundaries of which are determined by the maximum absolute values of the horizontal and vertical coordinates, r_I,r_Q＝±max(r_iI,r_iQ) (ii) a Defining mesh density Meshmum as the number of meshes divided in a single direction, dividing a mesh graph of Meshmum and Meshmum in a determined area, wherein the size of each mesh isEquivalent grid to xOy coordinate plane, where (x)_p,y_p) For the center of each grid, the function value isAfter the discrete points are serialized, an estimated probability density function is obtained

Further, the processor extracts the acquired symbol arriving from the first path by acquiring the multipath, and estimates the time domain initial synchronization parameter of the received signal: taking N by using the cyclic prefix characteristic of the time domain symbol in the DVB-T signal_CPA sampling value and N_FFTThen N_CPCarrying out correlation operation on the sampling values to obtain correlation peak values, and obtaining symbol starting sampling values which are initial timing synchronous values and initial estimation of the fractional carrier frequency; according to the initial estimation result of the fractional carrier frequency, carrying out frequency compensation on the sampling signal; according to the initial symbol timing synchronization estimation result, a symbol start sampling value is obtained, and fast Fourier transform is carried out to obtain a corresponding frequency signal; detecting and acquiring a scattered pilot sequence of a frequency domain signal: the scattered pilot frequency sequence of the current symbol is obtained by detecting the correlation between the scattered pilot frequency signal of the received signal and a plurality of different scattered pilot frequency sequences locally generated by a receiver; and detecting and compensating the integral multiple carrier frequency offset estimation of the OFDM symbols in the received signal.

Further, the fractional low-order fuzzy function of the processor digital modulation signal x (t) is expressed as:

wherein tau is time delay shift, f is Doppler shift, 0 < a, b < α/2, x^*(t) represents the conjugate of x (t); when x (t) is a real signal, x (t)^＜p＞＝|x(t)|^＜p＞sgn (x (t)); when x (t) is a complex signal, [ x (t)]^＜p＞＝|x(t)|^p-1x^*(t)。

Another object of the present invention is to provide a landing gear damping control system for an unmanned aerial vehicle, which operates the landing gear damping control method for an unmanned aerial vehicle, the landing gear damping control system for an unmanned aerial vehicle including: the device comprises a damping module, an induction module and a regulation and control module;

the shock absorption module comprises a shock absorber and an electromagnetic induction switch which are connected in sequence; the sensing module comprises a six-dimensional sensor, an acceleration sensor and a horizontal sensor; the induction module is connected with the regulation module; the regulation and control module comprises a signal transmission line and a processor; the processor is connected with the acceleration sensor through a signal transmission line and is connected with the electromagnetic induction switch through another signal transmission line; the six-dimensional sensor and the horizontal sensor are both provided with a lower induction limit value and an upper induction limit value; the acceleration sensor is connected with a signal enhancing channel and a signal weakening channel, the shock absorber comprises an outer box, a piston rod is arranged in the outer box, and a damper assembly and a shock pad are arranged on the piston rod in the outer box; one end of the telescopic supporting leg is provided with an adjuster; the regulator is connected with the electromagnetic induction switch.

Further, the shock-absorbing module is provided with:

bracing;

the middle parts of the two inclined struts are rotatably connected through a rotating shaft, and through holes are formed in the two ends of each inclined strut; the through-hole rotates with the connecting plate through the round pin axle to be connected, the fixed interior pole that is provided with in connecting plate one side, the outer pole has been cup jointed in the interior pole outside, the integration of outer pole upside is provided with the snap ring, the outer pole downside is through welding first support, first support both ends lower part is provided with flexible landing leg, flexible landing leg lower part is provided with the second support.

Furthermore, the connecting plates are fixed on the inner side of one end of the inner rod and are provided with an upper connecting plate and a lower connecting plate, through holes are formed in the middle of the two connecting plates, and the two connecting plates are rotatably connected with the inclined strut through pin shafts.

Further, flexible landing leg is provided with the urceolus, and the inside sliding connection of urceolus has the inner tube, urceolus bottom and inner tube upper portion all are provided with the fixed block, be provided with the spring between the fixed block.

Further, the second support is made of rubber, and anti-skidding lines are arranged at the bottom of the second support.

Further, the snap ring is cylindrical, and an opening is formed in the upper portion of the snap ring.

Furthermore, the first support and the second support are arranged in parallel, and the telescopic supporting legs are perpendicular to the first support and the second support.

By combining all the technical schemes, the invention has the advantages and positive effects that: according to the invention, the inner rod, the outer rod and the inclined strut are arranged, so that the adjustment can be carried out according to the width of the landing gear of the unmanned aerial vehicle, and the unmanned aerial vehicle has better applicability; in addition, the second support and the telescopic support legs can play a role in double buffering and shock absorption, so that the unmanned aerial vehicle is prevented from being impacted greatly when being landed. The inclined strut is rotatably connected with the inclined strut through the connecting plate, and is fixed through the pin shaft, so that the structure is stable. According to the invention, the springs arranged in the telescopic legs can play a role in buffering and damping, so that the unmanned aerial vehicle is prevented from being impacted greatly when being landed. The second support is made of rubber, so that the buffering and damping effects of the damping device are further improved. The invention can be fixedly connected with the landing gear of the unmanned aerial vehicle by arranging the snap ring in Europe.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained from the drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a landing gear damping control system for an unmanned aerial vehicle according to an embodiment of the present invention;

FIG. 2 is a schematic structural diagram of another side of a shock absorption control system for a landing gear of an unmanned aerial vehicle, according to an embodiment of the invention;

FIG. 3 is a schematic structural diagram of a connecting plate according to an embodiment of the present invention;

FIG. 4 is a schematic structural diagram of a telescopic leg provided in an embodiment of the present invention;

in the figure: 1. a snap ring; 2. a pin shaft; 3. bracing; 4. an outer rod; 5. a rotating shaft; 6. an inner rod; 7. a first bracket; 8. a telescopic leg; 9. a second bracket; 10. a connecting plate; 11. an inner barrel; 12. a spring; 13. a fixed block; 14. an outer cylinder.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Aiming at the problems in the prior art, the invention provides a shock absorption control system of a landing frame for an unmanned aerial vehicle, and the invention is described in detail with reference to the attached drawings.

As shown in fig. 1 to 4, the present invention provides a shock absorption control system for a landing gear of an unmanned aerial vehicle, including: the device comprises a clamping ring 1, a pin shaft 2, an inclined support 3, an outer rod 4, a rotating shaft 5, an inner rod 6, a first support 7, a telescopic supporting leg 8, a second support 9, a connecting plate 10, an inner barrel 11, a spring 12, a fixing block 13 and an outer barrel 14.

The middle parts of the two inclined struts 3 are rotationally connected through a rotating shaft 5, and through holes are formed in the two ends of each inclined strut 3; the through-hole rotates through round pin axle 2 and connecting plate 10 to be connected, and pole 6 in the fixed being provided with in connecting plate 10 one side, and outer pole 4 has been cup jointed in the interior pole 6 outside, and the integration of 4 upsides of outer pole is provided with snap ring 1, and 4 downside of outer pole are through welding first support 7, and 7 both ends lower parts of first support are provided with flexible landing leg 8, and 8 lower parts of flexible landing leg are provided with second support 9.

According to the invention, the inner rod 6, the outer rod 4 and the inclined strut 3 are arranged, so that the adjustment can be carried out according to the width of the landing gear of the unmanned aerial vehicle, and the unmanned aerial vehicle has better applicability; in addition, the double-buffering and shock-absorbing functions can be achieved through the second support 9 and the telescopic supporting legs 8, so that the unmanned aerial vehicle is prevented from being impacted greatly when being landed.

Preferably, the connecting plates 10 are fixed on the inner side of one end of the inner rod 6 and are provided with an upper connecting plate and a lower connecting plate, through holes are formed in the middle parts of the two connecting plates 10, and the two connecting plates 10 are rotatably connected with the inclined strut 3 through pin shafts 2.

The invention realizes the rotary connection with the inclined strut 3 through the connecting plate 10, and the structure is stable because the inclined strut is fixed through the pin shaft 2.

Preferably, the telescopic leg 8 is provided with an outer cylinder 14, the inner cylinder 11 is connected inside the outer cylinder 14 in a sliding manner, fixing blocks 13 are arranged at the bottom of the outer cylinder 14 and the upper part of the inner cylinder 11, and a spring 12 is arranged between the fixing blocks 13.

According to the invention, the springs 12 arranged in the telescopic legs can play a role in buffering and damping, so that the unmanned aerial vehicle is prevented from being impacted greatly when being landed.

Preferably, the second bracket 9 is made of rubber, and the bottom of the second bracket is provided with anti-skid lines.

The second bracket 9 of the present invention is made of rubber, and preferably, the buffering and shock absorbing effects of the present invention are increased.

Preferably, the snap ring 1 is cylindrical and has an opening at the upper portion.

The invention can be fixedly connected with the landing gear of the unmanned aerial vehicle by arranging the snap ring 1 in Europe.

Preferably, the first support 7 and the second support 9 are arranged in parallel, and the telescopic legs 8 are perpendicular to the first support 7 and the second support 9.

The invention provides a shock absorption control system of a landing frame for an unmanned aerial vehicle, which comprises: the device comprises a damping module, a sensing module and a regulating module.

The shock absorption module comprises a shock absorber and an electromagnetic induction switch which are connected in sequence; the shock absorber includes: the device comprises a clamping ring 1, a pin shaft 2, an inclined support 3, an outer rod 4, a rotating shaft 5, an inner rod 6, a first support 7, a telescopic supporting leg 8, a second support 9, a connecting plate 10, an inner barrel 11, a spring 12, a fixing block 13 and an outer barrel 14. The sensing module comprises a six-dimensional sensor, an acceleration sensor and a horizontal sensor; the induction module is connected with the regulation module; the regulation and control module comprises a signal transmission line and a processor; the processor is connected with the acceleration sensor through a signal transmission line and is connected with the electromagnetic induction switch through another signal transmission line; the six-dimensional sensor and the horizontal sensor are both provided with a lower induction limit value and an upper induction limit value; the acceleration sensor is connected with a signal enhancing channel and a signal weakening channel, the shock absorber comprises an outer box, a piston rod is arranged in the outer box, and a damper assembly and a shock pad are arranged on the piston rod in the outer box; one end of the telescopic supporting leg 8 is provided with an adjuster; the regulator is connected with the electromagnetic induction switch. When the unmanned aerial vehicle lands, the lower induction limit values of the six-dimensional sensor and the horizontal sensor are reached; the six-dimensional sensor and the horizontal sensor are used for collecting the angle change and the horizontal inclination angle of the unmanned aerial vehicle; corresponding numerical values are set in the processor through setting different angles and the running strength of the shock absorber when the angle is inclined; collecting the acceleration of the unmanned aerial vehicle through an acceleration sensor, starting an enhanced signal for the normal condition, and starting a weakened signal for the negative condition; the damper receives the signal from the damper, the boost signal increases the strength of the damper by a corresponding amount, and the buck signal decreases the strength of the damper by a corresponding amount.

The processor carries out nonlinear transformation on the acquired signals of the six-dimensional sensor and the horizontal sensor and calculates the generalized cyclic autocorrelation function of the acquired signals; extracting a specific cycle frequency section of the generalized cycle autocorrelation function, and finishing useful symbol length estimation of the acquired signal by searching a spectrum peak of the specific cycle frequency section;

the generalized cyclic autocorrelation functionIs defined as:

where upsilon represents the cyclic frequency, m represents the time delay, and N_rIndicates the signal length, "+" indicates the conjugate operation, f [ r (n)]The expression is a nonlinear transformation:

wherein, r (n) is a received signal;

extracting a specific cycle frequency section of the generalized cyclic autocorrelation function, and finishing useful symbol length estimation of the acquired signal by searching a spectrum peak of the specific cycle frequency section: estimating useful symbol duration is estimatingIs the maximum estimated value of mFor the duration of the useful symbol or symbols,is the useful symbol length N_uM ∈ [2K ]_min,2K_max]，K_minTo the smallest number of subcarriers possible, K_maxIs the maximum number of possible sub-carriers, havingEstimated with the symbol duration as:

the processor processes the probability density function of the simplified constellation diagram by utilizing the multi-radius subtraction clustering and the self-correcting clustering effectiveness function, and identifies the modulation order of the acquired signal; the method for estimating the probability density function of the constellation diagram by the grid method comprises the following steps: according to the received constellation point r_iHas the coordinates of (r)_iI,r_iQ) Constructing a square grid, the boundaries of which are determined by the maximum absolute values of the horizontal and vertical coordinates, r_I,r_Q＝±max(r_iI,r_iQ) (ii) a Defining mesh density Meshmum as the number of meshes divided in a single direction, dividing a mesh graph of Meshmum and Meshmum in a determined area, wherein the size of each mesh isEquivalent grid to xOy coordinate plane, where (x)_p,y_p) For the center of each grid, the function value isAfter the discrete points are serialized, an estimated probability density function is obtained

Further, the processor extracts the acquired symbol arriving from the first path by acquiring the multipath, and estimates the time domain initial synchronization parameter of the received signal: taking N by using the cyclic prefix characteristic of the time domain symbol in the DVB-T signal_CPA sampling value and N_FFTThen N_CPCarrying out correlation operation on the sampling values to obtain correlation peak values, and obtaining symbol starting sampling values which are initial timing synchronous values and initial estimation of the fractional carrier frequency; according to the initial estimation result of the fractional carrier frequency, carrying out frequency compensation on the sampling signal; according to the initial symbol timing synchronization estimation result, obtaining a symbol start sampling value, and performing fast Fourier transform to obtainTo a corresponding frequency signal; detecting and acquiring a scattered pilot sequence of a frequency domain signal: the scattered pilot frequency sequence of the current symbol is obtained by detecting the correlation between the scattered pilot frequency signal of the received signal and a plurality of different scattered pilot frequency sequences locally generated by a receiver; and detecting and compensating the integral multiple carrier frequency offset estimation of the OFDM symbols in the received signal.

Further, the fractional low-order fuzzy function of the processor digital modulation signal x (t) is expressed as:

wherein tau is time delay shift, f is Doppler shift, 0 < a, b < α/2, x^*(t) represents the conjugate of x (t); when x (t) is a real signal, x (t)^＜p＞＝|x(t)|^＜p＞sgn (x (t)); when x (t) is a complex signal, [ x (t)]^＜p＞＝|x(t)|^p-1x^*(t)。

The working principle of the invention is as follows: adjusting the angle of the inclined strut 3 according to the width of the unmanned aerial vehicle base to enable the width of the two clamping rings 1 to be consistent with the width of the unmanned aerial vehicle base, and placing the landing gear of the unmanned aerial vehicle in the clamping rings 1; when unmanned aerial vehicle descends, second support 9 and flexible landing leg 8 can play the absorbing effect of double buffering.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention, and the scope of the present invention is not limited thereto, and any modification, equivalent replacement, and improvement made by those skilled in the art within the technical scope of the present invention disclosed herein, which is within the spirit and principle of the present invention, should be covered by the present invention.